HTV "Stork"Six Unit (HTV6)
[Mission press kit]
2016 Year Eleven Month twenty four Day
National Research and Development Japan Aerospace Exploration Agency
1-1 (Blank Page) "Stork"Six Unit is ISS Support the foundation of the operation, to expand the use of space Carry such equipment, is a mission to demonstrate the future of space technology ISS Operation period of 2024 First flight from being extended to a year. ISS To transport the goods to support the foundation of the operation.
ISS Battery, which is one of the foundation of the operation, because it is an essential instrument in order to secure the power supply that needs to be replaced due to aging, Japanese-made lithium-ion battery (cell) Equipped with the (Detailbattery is at 5.2 a Seetime section) Six Platform (about including mounting structure 1.9 Tons) carries. ISS Among the life-support system for making the air astronauts breathe in, an apparatus for removing carbon (Shidora)There is no spare replacement parts (carbon dioxide adsorbent) of) dioxide (CDRA Was for, it carries. (Detail is 5.1.1 See section)
"Stork"Five Following the Unit, astronaut of drinking water (600 Liter: water intake at the Tanegashima) and carries the fresh food. (Detail is 5.1.2 See section)
And transportation and equipment for expanding the use of space.
Because of the universe expanded use, ever once in CubeSAT In size 6U An ultra-small satellite that could only release 12UIt carries a release mechanism that was capacity doubled so that it can be released. And in response to the capacity,Seven Machine (13U) Of (Detail is 5.1.3 See section) carry along with the ultra-small satellite. ※ CubeSAT(CubeSat) is,TenCm cube is the base and the satellite.1U = 10 Cm x 10Cm x 10 Cm so,2U,3U The length of each to be Twenty Cm,Thirty It will be cm.
In addition, only in Asia ISS Simple exposure experimental apparatus in the "hope" outboard as plan participating countries (ExHAMThe use opportunities) as part of the international cooperation(Detail is 5.1.3 with (5)See Turkey section) carries the material sample.
To transport the equipment to win the future of space technology.
The sophistication and the size of the spacecraft requires a highly efficient cooling system. This time, by using the boiling- two-phase flow loop, a knowledge of the heat transfer coefficient system of heat rejector, which is one of the critical equipment Acquired,JAXAIt shows the spacecraft design criteria proposed. (TPF: Two Phase Flow) It carries. (Detail is 5.1.3 (3)See section) For the "Boiling, two-phase flow experimental apparatus" "Cosmic radiation realistic to be able to measure a more accurate cosmic radiation in real time Time monitoring (PS-TEPC: Position Sensitive Tissue Equivalent Proportional device " Chamber)It carries. (Detail is 5.1.3 (4)See section)
ISS It finished the mission in, in the future to take the opportunity to re-entry Make the technology demonstrated that lead.
For long-term sustainability of space development and utilization is, efficient debris (space junk) measures must be taken. Still there is no track on the record in order to implement the debris removal of the low cost and early, take (kite)to hold. (Detailon an electricalis 6.1 See Elementalsection) technology demonstration of conductive tether for obtaining propulsion force by"KITE" Improve the performance of future spacecraft/Technology demonstration of the thin-film solar cell film array sheet (Sphinx)to hold. (Detail is 6.2 See section) which leads to weight reduction"SFINKS" "Stork" Unit 6 Press Kit
Revision history
TAFE date Revision page Reason for Revision
First edition 2016.11.24 - - "Stork" Unit 6 Press Kit table of contents
1. Introduction ...... 1-1
2. "Stork" Overview ...... 2-1
3. "Stork"Six Unit mission of launch / flight plan summary ...... 3-1
Four. "Stork"Six Unit operation schedule ...... 4-1
Five. "Stork"Six Goods that Unit carries ...... 5-1
5.1 Logistics Carrier pressurized section mounted products (ship goods) ...... 5-2
5.1.1 System-related goods ...... 5-5
5.1.2 Drinking water, food and household goods-related goods ...... 5-6
5.1.3 Experiment-related goods ...... 5-7
5.2 ULC part mounted products (outboard goods) ...... 5-15
6. Accumulation of technology by utilizing the "stork" ...... 6-1
6.1 Conductive tether demonstration experiment (KITE) ...... 6-1
6.2 "Stork"Six Thin-film solar cell film for Unit equipped with the universe Array sheet module (SFINKS) ...... 6-4
(I) "Stork" Unit 6 Press Kit
1. Introduction
Not just carry, lead to the future "stork"
The International Space (StationInternational Space Station: ISS) In astronauts Regularly goods (food but in order to work, water, oxygen,ISS The equipment and samples, etc.) of the experiments carried out in the you need to deliver from the earth. ISS Participating countries,ISS Based on a common operational expenses to the International Space Station cooperation agreement We share. Japan that was developed as a means of transport of the goods required for the operation and use of goods and "hope" corresponding to the sharing obligation is "stork". Current,Have a resupply capability the day the United States and Russia of Three Country is only,The importance ※ European unmanned supply ship (ATV) Is 2015 Year Two He retired a month. of the "stork" has increased.
2009 "Stork" of the year(HTV)01 machine (technology demonstrator) or later, so far Five Machine of Successful launch and operation, futureNineLaunch and operation is planned up to the Unit.
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2. "Stork" Overview
HTV "stork" (H-II Transfer Vehicle: HTV) Is,ISS Supply to As a means of transportation to carry the goods, Japan is in the unmanned resupply ship that was developed, is this time Six The launch of the machine eyesIt will be. It should be noted that,TwoIt is used nickname of "stork" from the Unit. Configuration and specification of the "stork", for more information Appendix One Please refer to.
Logistics Carrier pressurized(Pressurized section part) (Equipped with a ship for replenishing supplies. Crew There can work get inside. ) Exposed Pallet (Outboard experimental apparatus Equipped with, etc.)
ULC part (Equipped with the Exposed Pallet)
And electrical module (Equipped with the navigation and electronic equipment)
- Propulsion module (Equipped with a propellant, Ya orbit change Generating a thrust for attitude change)
Figure 2-1 The configuration of the "stork" (Photo Six Unit) (JAXA)
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(1) The world's largest supply capacity
~ There is a work that can not be only to - "stork"
It is a feature of the "stork"Transport capacity of large-scale,(maximum mass goods Six Ton: for cargo loaded Including the mass of theThe shelf alive, structure)ISS It contributes to the maintenance and expansion of the use and operation.
ISS Large to be used in large-scale and standard rack plurality of "hope" outboard platform Experimental apparatus Ya ISS Of the use battery can be transported at the same time is only the "stork".
Figure 2-2 (left) International Standard Payload[About Rack(ISPR) height 2m, About the width and depth 1m](NASA)
(right) Hope Exposed(JAXA)
(2) ISS Technology to support the foundation of operational
~ Unsung hero ~
2009 Year of technology demonstration unit (first unit) or later,ISSIt has achieved a smooth goods supply without interfering with the work plan. (Mission achievement rate Hundred percent) From international partners by the height of proof to become stable operation of the technical capabilities of our country It has won a further confidence.
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(3) Establish a new international standard in Japan unique technology
- Track record supporting "reliable technology is trusted in the world" -
"Stork" is ISS As close-coupling method to, the high safety robot arm A docking system that usesThe first time in the worldIt was realized. This docking system,Also used in spacecraft of the United States private sectorIt is,ISS In It has been established as a standard. "Stork" is ISS Communication system (in the vicinity of communication to continue to safely close to the system,Proximity Communication System: PROX) Is,US Cygnus Also use supply shipdoing. For this reason,JAXAIt isNASAIt is the operational support of Cygnus in response to the request.
In addition to this communication equipment was also adopted in the "stork", trajectory change for the engine, domestic technology such as a battery overseas spacecraft,ISS It has been adopted as a replacement, the "stork" Also contributed to the development of the domestic space industry combined with multiple machine manufacturing.
Cygnus supply ship Operational support of the United States spacecraft
ISS Communication equipment for access (Adopted in Cygnus)
Orbital change for engine (Export as for satellite, etc.)
Battery (A battery of "stork"NASA But adopted for the ISS exchange)
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(Four) Improvement of user services
Supply ability - to continue to ~ evolution
Supply capacity of the ship for the supply goods (about Twenty% Improvement)
• The efficiency of the goods mounting method, can be
mounted supplies※ to the pressurized part of the "stork" Transportation back(CTB: Cargo Transfer Bag; appendix 2-8 reference)Number, 01 machine (208 From pieces) Six Unit (248 Until the pieces) Forty Pieces (about Twenty%) Has been increased.
※ OneCTB Of the standard: 502mm x 425mm x 248mm
table 2-1 Actual comparison of the "stork" and the ship can be mounted amount of US supply ship (including Express Mail Service)
Unit As ship supplies Among them, the express delivery service It can be mounted CTB In terms of theCapable total number of accommodating CTB Converted number
First aircraft 208 Four
Two Unit 230 Thirty
3, 4 Unit 230 80
Five Unit 242 92
Six Unit 248 92
Supply ship Dragon (USA) 108 Ten Cygnus (US) 226 twenty two
Figure 2-3"Stork"Six Transport goods to be mounted on the pressurized part of the Unit
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Supply capacity of Funegaiyo supply goods (about 60%Improvement)
• "Stork"Six In Unit ISS Battery attached to the outside of the ※ You launch. This batteryAll at once Six TableIt increased the supply capacity of Funegaiyo goods in order to launch. (Traditional 1.2 From ton 1.9 Enhanced tons) ※ ISSIt is mounted on the 48 A nickel-hydrogen battery of high capacity made in Japan of the platform Battery using lithium ion battery (cell) twenty four It plans to replace the platform. (Detail is 5.2 See section)
Figure 2-4 (left)ISS Iodine battery One Exposed Pallet platform mounted state
(right)ISS Iodine battery Six Exposed Pallet platform mounted state
Launch 80 by the time※ Goods loading service to the (usually about Four Months ago)
• To suit your needs, just before the launch (80 Time ago) to maintain quality Experimental samples and fresh food of the required biological systems (life sciences),ISS Equipment of Failure crowded loading supplies such as replacement parts needed urgently by,ISS After arrival, the first to retrieve express support services most (late access:Late Access) To support. • The amount and size of the correspondence is possible luggage of express delivery service is the largest in the world of the supply ship. ※ Usually equipped with: launch about Four Loading in months ago Express Mail Service: Launch Ten Days ago ~80 Until the time before
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reference Express-enabled services (late access:Late Access)
In the "loading time is tight supplies" "fresh state late access ISS To It is necessary to goods "" hastily launch that need to be transported ISS Launch and of supplies " Ten Days ago ~80 It is a service that can be mounted by time before. Because it is housed in the "stork" is already fairing of the rocket at this point, In order to perform the loading due to late access opens the access door of the fairing, Open the hatch (door) of the "stork", make the loading of goods. For loading at the end, the volume that can be installed, but you are not limited to, the experiment of the ISS is to diversify In, "stork" since the first unit, has expanded its support of the late access ※ 1 .
It should be noted that, (the amount can be mounted in the Express Mail Service) capability of the late access of "stork" is, Such as the United States of the Dragon and Cygnus Largest of the ISS supply shipIt boasts.
※ 1 "Devised to increase the late access amount"
"Stork"Four Unit and later, to a variety of ideas, we have to increase the mounting amount of late access.
It can be mounted goods transport※ TwobagExpansion of the allowable volume
Conventional double CTB bag(about Fifty×43×50cm)About from Two Times the volume M02 bag (about Ninety×51×54cm)The can now be mounted.
Expansion of the allowable mass of mountable bag The can be mounted mass to bag Five From Unit 70kg(Until then Twenty Kg) to was pulling up.
Expansion of can be mounted volume (space in the "stork") "Stork"Five A mountable volume in the late access from Unit 92CTB Substantially ※ Three(Four Unit or so 80CTB It was increased to the equivalent).
Corresponding to the special shape / size Products with "Stork"Six Carbon dioxide removal device of special shape / size is Unit (CDRABy devising the mounting method replacement parts) Two It was realized to be incorporated in the platform.
※ 2: Appendix 3-8 you about the various sizes of goods transport for the bags that are used to transport to the ISS Please see. ※ 3: the 1CTB minute as (502mm × 425mm × 248mm), in terms of the volume in the CTB number. Mounted server performance Tsu is different from the clock number.
Figure 2-3 double CTB (JAXA) Figure 2-4 M02 bag (JAXA)
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H-IIB rocket Fairing
For late access kit "Stork" Pressurized section
Figure 2-5 Large rocket Assembly Building (VAB) Of the inLate access schematic diagram (JAXA)
Figure 2-6 (1/2) Work landscape at the time of late access(Four Unit) (JAXA)
Figure 2-6 (2/2) Work landscape at the time of late access(Four Unit) (JAXA)
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(Five) Contribution to strengthening industrial competitiveness
To continue the "stork" ISS To resupply to the, about the country, including the small and medium-sized enterprises not only in space industry 350 The company has led to the development and human resources of the inheritance of those manufacturing (6)technology Contribution by. to the development of space development and utilization
"Stork"Six The Unit,ISS In addition to the supply of goods to the "KITE"When"SFINKSCalled " Two One of the on-orbit verification test (for more information SixChapter performs a reference please), and make the technology demonstration test for the future. "Stork" has also helped to provide a verification test opportunity in such a universe.
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3. "Stork"Six Unit mission of launch / flight plan summary
The following are "stork"Six Unit is a summary of the launch / flight plan of the mission. According to that timeAll Nippon timeIt has become. It should be noted that,For schedule of the mission event ISS And so on by changing operating conditions of possibilityPlease note that there is.
table 3-1 "Stork"Six Overview of the Unit of the launch / flight plan
2016 Year Eleven Month One Day now Item plan
Flight name HTV "stork"Six Unit (HTV6)
2016 Year Twelve Month Nine Day twenty two Time 26 Minute time※One (Japan time) Launch date (planned) ※One Determined by the trajectory of the latest of the International Space Station.
2016 Year Twelve Month Ten Day toTwelve Month 31 Day Preliminary period launch For the launch date and time during the preliminary period, the operation of the International Space Station Determined by the international adjustment of.
Location launch Tanegashima Space Center Large rocket launch site No. Two Launch Complex (LP2)
ISS Gripping of the robotic arm 2016 Year Twelve Month 13 Day(Twenty ISS Binding Around time)ISS Binding to 2016 Year Twelve Month 14 Day(Two of (plans) Around time) (Note: with the binding completion of the power and communication lines will be "binding completed")
ISS 2017 Year One During the month※Two Separation ※Two Depending on the situation of the mission might be changed. from the (plans) ISS After withdrawal about Nine Day after ISS Re-entry date (planned) After the withdrawal,Seven Daily interest rate KITE We will implement the demonstration pilot. ※Two Depending on the situation of the mission might be changed.
Turned Altitude: about 200 × 300km(Elliptical Orbital altitude orbit) ISS About: rendezvous advanced with 400km
Orbital inclination 51.6 Degree
For the latest information and the information of the in-flight related to Unit 6 mission "stork", the following JAXAIt can be found at the website. http://iss.jaxa.jp/htv/mission/htv-6/ ("Stork" Unit 6 of information)
http://fanfun.jaxa.jp/countdown/htv6 (mainly H-IIBInformation of the rocket center)
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Four."Stork"Six Unit operation schedule
table 4-1 "Stork"Six Unit operation schedule
Flight date "Stork" related major work Launch / orbit insertion, operation after the orbit by an automatic sequence of "stork" (Start-up of the sub-system, three-axis attitude control establishment, abnormal inspection of the aircraft, tracking data relay satellite(Tracking and One Japan eyes Data Relay Satellite: TDRS)Establish communication with, communication connection with the Tsukuba "stork" Mission Control Room), orbit control start for rendezvous One~Four JapanISS eyes Rendezvous with Final approach ISS Grip on the robot arm ISS Binding of(Mooring)
Four Japan eyes - Common berthing mechanism of Harmony module lower side that "hope" is bound (CBM) Binding to - Outfitting of the coupling portion (wiring, cable installation, etc.) - Mooring power system start-up, switching of the Transportcommunication and installation path (radio of the outboard experimental platformwaves →ofWired), drawer etc. / "hope" of exposure palette from the ULC part Entry into Logistics Carrier pressurized section
- CBMRemoval of the control device - Hatch Open - Inter-module ventilation ventilation (Inter-Module Ventilation: IMV)Start-up
From the "stork" ISS Hakobidashi of ship supplies to It was transported by Exposed Pallet ISS The battery was moved by the robot arm, conducted a spacewalk Exchange
Discard ISS Recovering the exposure palette equipped with a battery to supply the carrier ULC
Loading of transfer operations / ship scrap supplies
Preparing the separation of "stork" CBM Mounting of the control ISS Separation device, inter-module ventilation ventilation (IMVStop), hatch closure, Switching of the communication path (wired→Radio The day beforewaves) Of "stork" ISS Withdrawal from - Stop of mooring power system - Removal of the wiring and cable joints - ISS Gripping the "stork" in the robot arm - Common Berthing Mechanism (CBMBolt released) - ISS Move the "stork" to the release position in the robot arm - Guiding and navigation and control (Guidance Navigation Control: GNCStart-up of), ISS Separation Date
Thruster injection preparation - ISS Release the grip of the robot arm of the,ISSWithdrawal injection from orbit
From the separation KITE Conducted a demonstration test Seven Daily interest rate
Re-entry Deorbit control, re-entry
note Schedule ISS Please note that will be changed depending on the situation of the operation.
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[Reference] major event
Six In Unit mission, flight Four The day first ISSIt is scheduled to be bound to. Supply during the quarantine period Do the transport of goods, and the transfer of the supply goods is completed,ISS Loading the battery, which finished the non-supplies and role of,ISSAfter separation from,SevenDays overKITEAfter the demonstration test, it is scheduled to re-entry into the atmosphere.
Bond
ISS Of the robot arm Near the communicationGripped area by Entry / goods transport arrival
Trajectory control Tracking data relay satellite(TDRS)
TDRS With Exposed Pallet fetch / store Communication established
Three-axis attitude control established
ISS Un- supplies loading of Separation of the "stork" about 200km x 300km Introduction of the elliptical orbit
No. Two Stage engine combustion stop
No. Two Start stage engine combustion
ISS Separation preparation
No. One Dan first Two Stage separation No. One Stage engine combustion stop
ISS Separation
KITE demonstration test (6 Unit-specific) Fairing separation
Companies andTKSC Out SRB-A Separation
Tanegashima Space Center (TNSCArrival in) Re-entry
VAB Move to: SFA2 Carried into: H-IIB Mounted on the rocketInstallation of each No. Two Launch Complex (LP2) module inspection / Move to:Launch goods / "stork" of all filling aircraft binding / propellant Figure 4-1 "Stork" Mission major event (JAXA)
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Five."Stork"Six Goods that Unit carries
Six In total, including the ship, the outboard goods in Unitabout 5.9 Ton(Ship goods about 3.9 Tons, outboard Supplies about 1.9 Ton: the including the mass of the shelf structure for cargo installed) ISS Carry on.
(1) Ship goods
Six The Unit, about the Logistics Carrier pressurized section 7/8 of NASA Supplies and about 1/8 of JAXA The goods It carries.
table 5-1 "Stork"Six The main ship goods to be transported in the Unit
organ Classification Goods example
NASA system supplies Orbit on the replacement unit of the carbon dioxide removal system (CDRA) Drinking water 30 water bag for drinking water (600 liters) Food and household goodsFresh food, clothing, etc. household goods, space food JAXA System supplies Hope conservation supplies, etc. Experiments related equipmentSmall satellite release mechanism (JSSOD) and boiling, two-phase flow experimental apparatus ultra-small satellite 7 groups (TPF) space radiation real-time monitoring device (PS-TEPC) ExHAM sample
Figure 5-1 During normal equipped with the completion of the (late access before) "stork"Five State of the Unit ship (JAXA)
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(2) Outboard goods
This time ISS Japanese-made lithium-ion batteries needed to power maintenance in the (cell) Equipped with lithium-ion batterySixTable (NASAOf goods) and transport.
Li-ion Battery ×Six
Exposed Pallet
Figure 5-2 6 Equipped with the image on the exposure palette at the time of the launch of Unit (JAXA)
5.1 Logistics Carrier pressurized section mounted products (ship goods)
"Stork"(HTV) 6 Ship goods, the total of which carry in Unit Eight Be pedestal mounted HTV Supply rack (HTV Resupply Rack: HRR) To housed and transported (as a whole Eight Among the places one rack mounting space, all HRR Transport the goods to use in). food,NASA And "hope" of conservation products and spare parts, astronaut life supplies, ultra-compact satellite(CubeSat)Various sizes transport bag of accommodating the like(Cargo Transfer Bag: CTB)But, this HRRIt will be housed in. To maximize can be mounted volume in the "stork" To take advantage of these CTB It is HRR In a way that also projecting to the front, strapped It is carried is.
HRR (Fig. 5.1-2) (Fig. 5.1-2) (Fig. 5.1-2) (Fig. 5.1-2) (Fig. 5.1-2)
(Fig. 5.1-2) (Fig. 5.1-2) (Fig. 5.1-2)
HRR (Fig. 5.1-3)
Figure 5.1-1 Six Rack mounted status of the Unit Logistics Carrier pressurized section (JAXA)
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HTV Supply rack (HRRMounted on)
Food, daily necessities, such as Lab Supplies Packed transport bag (CTB) HTV Supply rack (HRR)
Figure 5.1-2 Six Example of mounting Unit ship goods (JAXA)
Figure 5.1-3 Five It was newly established from Unit HRR Mounting structure of (JAXA)
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Figure 5.1-4 HTV Supply rack (HRRGoods transport for the bags to be mounted on)(JAXA) (CTB)
Figure 5.1-5 Rack-mountable have been transporting supplies for the bag to the front(JAXA) (CTBExamples of) (2 Unit)
Figure 5.1-6 Goods transport bag (CTB) (JAXA)(Photo Single(standard)size(left)Half and(1/2)size(right)) *CTB To accommodate goods of various sizes in a plurality of sizes exist. (appendix 3-8 See because it introduces the figure of each size to the page)
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5.1.1 System-related goods
Carbon dioxide removal device (CDRAOrbit on the replacement unit of)
ISSTo transport the supplies necessary in common to the operation and maintenance of the system. "Stork"Six Unit In, stable transport performance of "stork" is evaluated,NASA By request from ISS Carbon dioxide removal system is a very important device for maintaining the life of the astronauts to stay in(CDRA: Carbon Dioxide Removal Assembly; Shidora)Of carbon dioxide adsorbent is a replacement part (CDRA bed)Two And equipped with a platform.
CDRA It is,ISS In US-made equipment for adsorbing carbon dioxide of an inner,CDRA Bed It is the adsorption of carbon dioxide using a zeolite.CDRA Bed Two One might, because it can play by heating with a heater,Two Continuous by repeating playback and adsorption alternately in the stand It has been driving.ISS Including the reserve system within Two Of the table CDRA There have been installed.
Figure 5.1.1-1 For repair CDRA State which was drawn from the air playback rack (The lower box-shaped part of the CDRA See bed, the photo of the following) http://spaceflight.nasa.gov/gallery/images/station/crew-16/html/iss016e020614.html
Figure 5.1.1-2 CDRA Astronaut Wakata with a bed http://jda.jaxa.jp/result.php?lang=j&id=8bf593ac5440b11f2e0b9aff33637fc9
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5.1.2 Drinking water, food and household goods-related goods
"Stork"Six In Unit Five Unit to continue, food products such as fresh food, water for drinking water bag Thirty Number (a total of 600 Liter) and transport, and the like.
Figure 5.1.2-1 "Stork"Five Fresh food carried in the Unit
Water filling device Through the water filling device, Water bag packing Filled with water of Tanegashima
Recycling as a beverage in orbit Le while using
In the "stork", to the ISS
Rack water bag is mounted The water bag rack Equipped with state of the pressurizedThe part mounted on the pressurized part Mounted on
Figure 5.1.2-2 "Stork"Five Also it carried Japan of water in the Unit
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5.1.3 Experiment-related goods
NASA And goods to be used for the use experiment, is going to continue in the "hope" JAXA of It transports the experimental equipment and experimental samples related to the use of the experiment.
(1) Ultra-small satellite release mechanism (J-SSOD)
Enhancement - of ultra-small satellite release function to respond to - a new demand
"Stork"Six In the Unit in order to increase the frequency of release opportunities of ultra-small satellite, traditional 6U of Two Hit double 12U To develop a mechanism to release an ultra-small satellite, and then transport.
Figure 5.1.3-1 (Left) of this to the ultra-small satellite 6U Correspondence(3UxTwo Release mechanism of the group) (Right) in total, which was double the release number and the volume of ultra-small satellite 12U Correspondence(3UxFour Group)Release of Image of out mechanism
[The point here! ]
● demand respond to circle ultra type satellite of J-SSOD
(1) Four Heavy protection (Four Launch in the heavy-duty packaging) is friendly to the user!
Spaceborne case containing an ultra-small satellites,ISS As ship cargo towards CTB (Cargo Transfer Bag) To be called, in order to be launched in a bag stuffed with cushioning material, mechanical environment conditions of random vibration and the like at the time of the rocket launch will be relaxed. (It is just as gentle as placed on the bed of a car.) Test required in satellite development is reduced, the development period shorter alive like consumer electronics It will lead to contraction.
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(2) Several times of launch opportunities year, can be set flexible release time!
Of ultra-small satellite ISS Transport to the,JAXA But not only the "stork" developed, countries We are developing ISS Transport means towards available, you can choose a launch opportunity.
And it is also free time release. In the previous track record,ISS From being transported to, or number It has been released in less than a month. You can respond to time use you want.
(3) Enhancement of the release capacity to meet the demand
2019 Year (FY Thirty Year) current ability to up to (6U)of Eight Some at double 48U The ability to release We will step-by-step functional improvement of ultra-small satellite release mechanism so as Fuyaseru.
r 48U corresponding e b 18U corresponding m 12U corresponding u n
e s a e l e
r 50kg correspondence
e t i l l 6U correspondence e J-SSOD # 5/6 t
a J-SSOD # M1 By combining S J-SSOD # 3 The number of various mounting machines J-SSOD # 4 J-SSOD Flexibly J-SSOD #
6 3 2 4 5 7 Implementation year 1 1 1 1 1 1 0 0 0 0 0 0 2 2 2 2 2 2
Figure 5.1.3-2 Step-by-step release capacity expansion plans of the ultra-small satellite release mechanism
[Reference] ultra-small satellite release mechanism (J-SSOD)about
Ultra-small satellite release mechanism (J-SSOD) Is market expansion in recent ※yearsCorresponding of ultra-small to satellite use And made efforts to expand the stepwise release capability in order to.
※ Expansion of the ultra-small satellite market
2013 From around, ultra-small satellite (CubeSaUse of t) has been expanded,2012 Year Thirty Machine/About a year.2013 The year Ninety Machine than,2014 The year 135 Machine/It has become a year. (2015 Than a year Institute of Aerospace Industries Association of material). In addition, ultra-small satellite (CubeSat) Is,3U From the commercial use of a large number federated constellation size, university of human resource development, such as the use in developing countries that do not have a launch means, it is becoming more diverse.
-JAXA of J-SSOD Introduction page http://iss.jaxa.jp/kiboexp/equipment/ef/jssod/
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(2) Ultra-small satellite(CubeSat)
- Contribute to the development and industrial development of space development and utilization -
• ISSRelease of the ultra-small satellite from is the only system in the world that can "hope" That's why realization combines the air lock and the robot arm. • So far, in addition to Japan, the United States, Vietnam, Peru, Lithuania, such as Brazil Ultra-small satellite total 147 (2016 Year Ten 31,)There have been released from the "hope". Machine • Ultra-small satellite to be released from the "hope" is a few times a year ISS With the transport opportunity to, also because it can be flexibly set the timing of the release, high convenience for the user Expectations from the world of users is growing.
• Through the ultra-small satellite Feng TamaTsu of highly convenient in this high frequency, "hope", to further promote the use by private companies and universities and other educational institutions, will contribute to the development and industrial development of our country space• "Stork" developmentSix The Unit, andJAXA utilization. Ultra-compact to the release from the ultra-small satellite release mechanism satellite Seven Opportunity of ISS And transported to.
[Six Carry in the Unit, ultra-small satellite release mechanism (J-SSOD) Ultra-small satellite to be released from the]
[Satellite name] Aoba [size:2U]
organ Kyushu Institute of Technology
Mission PPT(Pulsed Plasma Thruster) Demonstration and performance evaluation
[Satellite name] UbatubaSat [size:2U]
organ BrazilUbatubaCityTancredop rimary school (Brazil National Space Research Institute(INPE)There support) Mission PPT(Pulsed Plasma Thruster) Demonstration and performance evaluation
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[Satellite name] EGG [size:3U]
organ University of Tokyo
Mission •Deployment demonstration of the torus-shaped inflatable structure•Iridium satellite communication andGPSPosition of Specific system•Orbital experiment decay demonstrated by the air resistance of the inflatable structure [Satellite name] ITF-2 [size:1U]
organ University of Tsukuba
Mission •Of the network using the satellite data Construction •Demonstration of the ultra-small antenna •Demonstration of the new microcomputer
[Satellite name] STARS-C [2U]
organ Shizuoka University
Mission •Technology demonstration of the tether extension system by satellite
[Satellite name] FREEDOM [1U]
organ (stock)Nakashimadatekkosho
Mission •Of membrane deployment type orbit equipment Space Demonstration
[Satellite name] WASEDA-SAT3 [1U]
organ Waseda University
Mission •LCDOn-orbit demonstration of active thermal control mechanism by Demonstration of • de Orbit system • power generation demonstrated by the thin film photovoltaic solar cells
5-10 "Stork" Unit 6 Press Kit
(3) Boiling, two-layer flow experimental apparatus(TPF)
Along with the sophistication and the size of the spacecraft, it has a more efficient cooling system is required. In order to do as compared with the conventional It issingle-phase that's most floweffective (fluid to introduceonly liquid)Five a boiling More thantwo-phase double of flowthe withheat (boiling transport fluid capability bubbles are mixed) It is considered.
TPF In the experiment using, in boiling, two-phase flow loop by Fluorinert, in microgravity Even when the temperature Oite 57℃ and 47℃ to verify that it works between, the radiator area compared with the single-phase system 49 It will demonstrate for percent aim to reduce the size of. And, with the aim of spacecraft applications, The heat transfer coefficient of the heat rejector to be unpredictable and most critical in earth, ± the lower limit of the flow rate free from the influence of gravityTen% Of determined by the accuracy, of JAXA spacecraft design criteria proposed We aim to presentation.
[The point here! ]
the design criteria for the _ to universe machine ●
This experiment achievement, Tokura only in observation of sophisticated heat transfer coefficient and the bubble behavior in microgravity Is not, you can expect academic achievements give the knowledge to the mechanism elucidation of the liquid supply to the bubble withdrawal and heated surface to dominateAnd, the a provisionlarge boiling of design phenomenon. criteria, satellite, spacecraft, such as the space station a wide range of waste heat cis Due to significant reduction and compactness of the tem design period,2030 To the innovative spacecraft around Deployment can be expected. Furthermore, in the exhaust heat system for the spacecraft, than such as a single-phase flow Much to obtain a design criteria of boiling two-phase fluid system performance can be highly compact, built a technical advantage by the optimal design, you can ensure Japan's superiority.
Figure 5.1.3-6 Boiling two-layer fluid loop equipment(TPF)Image of http://www.mext.go.jp/component/b_menu/shingi/toushin/__icsFiles/afieldfile/2016/10/06/1377906_4.pdf
5-11 "Stork" Unit 6 Press Kit
[Mechanism of the device]
The test fluid, and allowed to flow into the loop at a set flow rate by the pump. Desired in the preheater To warm up to the temperature was raised, it is heated in a test section boiling, and observe the situation in the camera. Then, heat is removed in a condenser, to return to the single-phase flow (ie, liquid).
Figure 5.1.3-7 Outline of the operation of the boiling two-layer fluid loop equipment
Boiling, two-layer flow experimental apparatus(TPF)It is, multi-purpose experiment rack of "hope"(MSPR)Work of volume(WV)Experiment is done by installing within.
Figure 5.1.3-8 MSPR Of the ground model WV (Work Volume)In part TPF Photo that was installed http://www.mext.go.jp/component/b_menu/shingi/toushin/__icsFiles/afieldfile/2016/10/06/1377906_4.pdf
5-12 "Stork" Unit 6 Press Kit
(Four) Real-time monitoring device of cosmic radiation(PS-TEPC)
For stay of people in space, which is limited by the radiation exposure dose, cosmic radiation There is a need to accurately grasp the. In the future of ultra- long-term stay,ISS Also there is assumed activities in the beyond, the immediate decision such as an emergency evacuationTherefore, by towards the solar the flare establishment is becoming of important. an accurate dosimetry capable measurement technology in real time, ISS- In the hope,PS-TEPC (Position Sensitive Tissue Equivalent Proportional Chamber)Make the technology demonstration that was used. If measurement is realized specifications, it will be the most high-precision real-time dosimeter in the world.
This time, the maximum Six The on-orbit demonstration data acquisition of the month,NASA Similar measurement instrumentation with the Location (NASA TEPC) Analysis performed to improve evaluation of the accuracy of using the exposure dose calculation analysis model of comparative measurement and astronaut with. [The point here! ] (The latest real-time measurement to reduce the error) Improve the accuracy of radiation dose calculation analysis model, astronaut from the point of view of radiation effects You can make of the universe stay conditions more clearly.PS- TEPC Through the results of the experiment the radiation exposure dose calculation error of the astronaut, from the current 1/5 We aim to extent.
Low-LET detector (0.2 ~ 600keV / μm)
Control part
High LET detector (400 ~ 1000keV / μm)
Figure 5.1.3-5 (Left) to the ship of "hope" PS-TEPC Installation image of (right)PS-TEPC Body
(Five) Turkish Republic of material exposure experiment for the sample (ExHAM With outboard of using Material long-term exposure experiments)
This year Nine Month,JAXA And the Republic of Turkey Transport Maritime Ministry of Communications (MTMACEntered into between) ※ Simple exposure attached to the outboard of the "hope" as part of the "hope" use cooperation agreement Experimental device(ExHAM) To implement the long-term material exposure experiment using.
※ Simple exposure experimental apparatus attached to the outboard of the "desired" (ExHAM) And long-term material exposure experiments using Cooperation agreement of "hope" available on the ultra-small satellite release.
5-13 "Stork" Unit 6 Press Kit
Figure 5.1.3-3 (Left) Simple exposure experimental apparatus the Turkey of the material sample (ExHAMState attached to) (Right) Turkey was prepared "stork"Six Material sample to be launched in the Unit
(6) Next-generation high-definition camera (HDTV-EF2)system Breaking transmission of natural disasters, in addition to the fixed-point observation, aiming to take advantage of in such as private use,FourNext-generation high- definition camera (HDTV-EF2) To transport the system. The camera system has a camera platform biaxial for Youcontrolling can move the in camerathe direction sight, of ground the purpose of the camera by the operation from above. Also,Two Equipped with the kind of high-definition cameras (consumer products), the night of observation and optical Twenty Double looks like zoom can be.
1920×1080 Pixel (full HD Real-time transmission)[Camera 1, camera 2] 3840×2160 Pixel (4K Animation SD Card recording)[camera 2] Number of pixels 4240×2832 Pixel (1200 Megapixel still image SD Card recording) [camera 2]
Expansi Optics Twenty Fold zoom, ground resolution 15m It can on be taken with a degree (medium resolution).[Camera 1] shooting and resolutiosensitivity Night observable (ISO sensitivity 102400 nominal max)[Camera 2] n
Figure 5.1.3-3 4K The location of the outboard camera
5-14 "Stork" Unit 6 Press Kit
5.2 ULC part mounted products (outboard goods)
"Stork"Six In the Unit, the exposure palette of ULC part ISS New use Battery (adopted Japanese-made lithium-ion battery cell)SixPlatform will be installed. Of this amount Equipped with a battery at a time/Transportation is available supply machine is essentially say that only "stork" You.
Figure 5.2-1 Six Mounted image to the Unit of the Exposed Pallet (JAXA)
Figure 5.2-2 Six Unit of the forward and return path of the mounting form of the Exposed Pallet (JAXA) http://www.mext.go.jp/b_menu/shingi/gijyutu/gijyutu2/060/shiryo/__icsFiles/afieldfile/2016/07/08/1374186_2.pdf
5-15 "Stork" Unit 6 Press Kit
The new battery,ISS It is in currently used 48 Place the pedestal of the nickel-metal hydride battery It intended to replace, "stork"Six From Unit Nine Up Unit Four Using the machine Six Stand by a total of twenty fourPlatform will be transported. Because the new battery that capacity has been strengthened, existing battery Two The capacity of the platform worth One You can pay at the table.
Existing nickel-metal hydride battery In this spacewalkTwelveRemove the platform, was launchedSixTable of battery And replace it with.
It should be noted, has been removed Twelve Among the table, "stork"Six Unit is Nine Equipped with a table (remaining Three The platform ISS The remaining state), such as to finally atmosphere equipped with a other used materials And re-entry.
Lithium-ion cells LSE 134 Set to the battery of lithium-ion cells Battery capacity 134A (GS Yuasa Write (Aerojet Rocketdyne Shrine) Corp.) (Tanegashima Space Center)
The battery to the exposure palette of "stork" Six Installation of the platform
Figure 5.2-3 Flow of up to battery mounting (JAXA) http://jda.jaxa.jp/result.php?lang=j&id=11bee7cab0be2a74e920eaca91e9344b
5-16 "Stork" Unit 6 Press Kit
reference ISS About the battery
ISSAbout theNinetyThe Earth in minutesOneAlthough we are week, of which approximately35For minutes to enter the shadow of the Earth, During this period of power is not from the solar panels, it will be drawn from the battery.
Current,ISS Of the truss structure to support, such as solar panels in the United States side Four In places Total 48 Table of nickel-metal hydride battery (One Places per TwelveTable) are used. (The Russian side will have its own power system) "Stork"Six From Unit Nine Sum up Unit Four In the machine, mass and volume both these battery About to Three Times of the lithium ion battery cells made in Japan that achieves a high energy density(1 cell Capacity per ※ In exchange it should be given to,ISS of 134Ah,mass 3.53kg)Equipped with a battery the You can halve the number of the battery is at the heart of the operation.
※ The weight of each of the lithium ion battery is about 430 lb(195kg), Of the adapter plate weight 65 lb(29kg)So, nickel-metal hydride battery ORU 365 lb (165.5kg) 2 The weight of the platform worth(330kg)About Compared with 106kg It will be lighter.
ISS Battery exchange of so far 2009 Year Seven Month of the space shuttle mission STS-127 (2J / A)In had been used from the oldest P6 Of truss Six Individual,2010 Year Five moon'sSTS-132 (ULF-4)But P6 The rest of the truss Six Pieces have been replaced, but the lithium ion Replacement of the battery will be the first time.
Life of the lithium-ion batteryTenBecause it is a year,ISSThis until the end of the operation Mom use is expected to continue.
Figure 5.2-4 Perform this exchange S4 Position of the truss of the battery (NASA) http://spaceflight.nasa.gov/gallery/images/station/crew-28/html/s134e010590.html
5-17 "Stork" Unit 6 Press Kit
Figure 5.2-5 spaceIt is mounted on the shuttle P4 On the truss Six Table of battery(NASA KSC) (other ORU Another power system of the device, the back side is also similar arrangement) http://mediaarchive.ksc.nasa.gov/#/Detail/864
Figure 5.2-6 Procedure of replacement battery in orbit (JAXA)
5-18 "Stork" Unit 6 Press Kit
ISS Replacement of the battery spacewalk is to be Four But it had been estimated to need time, This time ISS Of the robot arm(SSRMS / SPDM)By carrying out the exchange of the battery using, the number of times required for the spacewalk about half Two It is scheduled to be reduced to time. Adapter plate that can not be implemented in the work by the robot※ Installation arm and ISS In that It is mom left Three Number of nickel-metal hydride (Ni-H2) Such as the relocation of the battery to the spacewalk crew Drunk is scheduled to be carried out. ※ Adapter plate is, so far of nickel-metal hydride batteryTwo Connect the standOne The platform of the battery Lithium-ion battery that newly replaced this time the things that you are using on One So that it could be used even at the table It is an adapter for that. It should be noted that,ISS Will remain is that in Three Number of nickel-metal hydride battery is electrically disconnected It will be in the state.
P6 truss before being relocated to the port (Z1 fixed on a truss) This item is also the battery is visible.
Battery
Figure 5.2-7 Crew to perform a spacewalk in the vicinity of the battery replacement location(STS-115 Mission) http://spaceflight.nasa.gov/gallery/images/shuttle/sts-115/html/s115e05704.html
5-19 "Stork" Unit 6 Press Kit
Figure 5.2-8 STS-127 State of the battery replacement work by extravehicular activity that has been performed at the time of the mission (NASA) https://spaceflightsystems.grc.nasa.gov/sopo/ihho/iss-technology-demonstration/sustaining-engineering-of-eps-hardware/s127e008452/
5-20 "Stork" Unit 6 Press Kit
6. Accumulation of technology by utilizing the "stork"
"Stork" is Four And later Unit,ISS Not only transport supplies to the future of our country spacecraft It has also been utilized in a small demonstration experiment for the accumulation of technology to help you develop.Six Large following of scale than ever in the Unit Two One of you do the experiment. 6.1 conductive tether demonstration experiment (KITE) KITE (Kounotori Integrated Tether Experiment)It is, space junk(Space Deb Re)Conductive tether is an element technology relates to the removal(Electrodynamic Tether:EDT)Performance in the test to demonstrate in the space of,ISS After the withdrawal from,700m To stretch the tether (wire) to the length of, electronic collection, and make the electron emission, etc. due to the electric field emission electron source.
NASA According to the study of, is performed with the debris mitigation measures for future spacecraft, year Five If we remove the large debris by aircraft, it is expected to be maintained without deteriorating the debris environment on the track any more.JAXA In order to achieve this debris removal at a low cost and early, propellant is not required EDTI believe it is promising. For this reason, the "stork"Six Unit bare (uncoated) and the extension of the tether 10mA Perform on-orbit demonstration that to get the characteristics of the class of the current drive (effective compact and lightweight to debris removal EDT Of elemental technology and space demonstration of the tether vibrationThis experiment, control by "stork"the thrusterSix Unit will is be ISS the After world's the withdrawal first). from,ISS Orbit below the 20km Than Above away Seven It is scheduled to be carried out over a period of the day about.After the demonstration experiment (Tether and Endomasu you disconnect is expected to re-entry within 3-6 months)And, "This cut the tether by cutting mechanism Of taking "will re-enter the atmosphere.Mission equipment of mass 60kg (Endomasu: 20kg, "Stork" body side: 40kg)is. (reference URL: https://www.youtube.com/watch?v=AIBXnRz5-7g )
Figure 6.1-1 KITE Equipment configuration of http://www.ard.jaxa.jp/research/kite/kite-details.html
6-1 "Stork" Unit 6 Press Kit
reference EDT Tether commentary page: http://www.ard.jaxa.jp/research/debris/deb-edt.html
Endomasu release mechanism
FEC-M LP-POM
camera
Figure 6.1-2 KITE Equipment location of (JAXA) http://jda.jaxa.jp/result.php?lang=j&id=550e6f43ea79ee45b1540abfe3d67145 FEC (Field Emission Cathode): Field-emission electron source LP-POM (Large probe Plasma current monitor and POtential Monitor module): Electrostatic
Probe function charge potential monitor
Figure 6.1-3 KITE Tether release image view of the(JAXA) http://jda.jaxa.jp/result.php?lang=j&id=0a2a0dbe0defbd4c8edc314718c21e08
6-2 "Stork" Unit 6 Press Kit
Figure 6.1-4 KITE Operation sequence Overview http://www.ard.jaxa.jp/research/kite/kite-details.html
Figure 6.1-5 EDT Debris removal image of a practical level using the (JAXA)
6-3 "Stork" Unit 6 Press Kit
6.2 "Stork" Unit 6 equipped with space for a thin film solar cell film array sheet module (SFINKS)
Solar cell FIlm array sheet for Next generation on KOUNOTORI Six
JAXA Thin-film solar cell array sheet but that was jointly developed with Sharp, currently practicable In the universe for a solar cell, which was realized in the world of conversion efficiency and lightness, it is expected to adopt for future spacecraft. In this orbit verification test, the current array sheet(Isc),Voltage(Voc)By measure, and impact the environment at the time of launch, it will demonstrate how to withstand harsh environments such as cosmic radiation and ultraviolet light. In addition, an array of the thin-film solar cell array sheet has a solar cell for each string Because it is supplied in shape, it is possible to panel into a simple in comparison with the conventional aluminum honeycomb panel. Comparing the manufacturing process of the case of introducing an aluminum honeycomb panel and the solar cell array sheet of the prior method and is expected to shorten the process from weeks level to several days level.
Figure 6.2-1 Film array sheet appearance (JAXA) (Photo Five Straight ×Three And average sheet Six Straight ×Three Connect the average sheet (modular) sheets:SFINKS In the array Sheet Six Connect the sheets, Five Straight ×Three The weight of the average sheet) is about 30g, Conversion efficiency is about 32% http://jda.jaxa.jp/result.php?lang=j&id=c573b8f8d51c3f7429e00e61cea2665d
6-4 "Stork" Unit 6 Press Kit
Figure 6.2-2 SFINKS Installation situation of (JAXA) (Note: the left side of the device KITE of FEC-M, Before launch SFINKS It will remove the ground cover of) http://jda.jaxa.jp/result.php?lang=j&id=550e6f43ea79ee45b1540abfe3d67145
KASPER ATOTIE-mini
Four Unit Five Unit
Figure 6.2-3 reference:Four Unit ATOTIE-mini When Five Unit KASPER Photos of the mounting (JAXA) ATOTIE-mini(Advanced Technology On-orbit Test Instrument for space Environment - mini) KASPER(Kounotori Advanced Space Environment Research equipment module)
("Stork"Six Charge potential monitor to be mounted on a Unit LP-POM It is,KITE It is part of the experiment,ATOTIE-miniWhen KASPER With equipment that was developed based on the design of, is also the successor experiment of charge potential measurement.)
6-5 "Stork" Unit 6 Press Kit (appendix)
Appendix Table of Contents appendix One The configuration of the "stork" ...... appendix 1-1 appendix Two "Stork" (HTVOperation Overview of) ...... appendix 2-1 appendix Three "Stork" /ISS Related Acronyms...... appendix 3-1
(I) "Stork" press kit (appendix)
appendix One The configuration of the "stork"
"Stork" is, "Logistics Carrier pressurized part", "ULC replenishment carrier", "Exposed Pallet", "electrical module", It consists of "propulsion module". Goods is, as "Logistics Carrier pressurized part", carry the exposure palette equipped with such an outboard experimental apparatus of "ULC replenishment carrier" Two One of the cargo and then mounted in a compartment. Near a communication system for performing bidirectional communication when the "stork" approaches the ISS (Proximity Communication System: PROX) And antenna, such as a reflector (laser radar reflector) is,ISS Of "hope" it has been installed in the Japanese Experiment Module.
Common berthing mechanism (CBM)
Figure A1-1 Overall structure of the "stork" (JAXA)
appendix 1-1 "Stork" press kit (appendix)
table A1-1 Main specifications of the "stork" operational machine
item specification
full length about 10.0m
diameter about 4.4m
Aircraft excluding supplies about 10.5 Ton Mass of
Gross mass maximum 16.5 Ton
fuel MMH(Monomethyl hydrazine)
Propellant
Oxidant MON-3(Nitric oxide addition dinitrogen tetroxide)
total Up to about 6.0 Ton
Pressurized section: ship goods up to about 4.5 Ton (ISS Crew of food, clothing, drinking water, experiment rack, the ship, such as Lab Supplies Supply capacity In equipped with supplies to use, etc.)
ULC: outboard goods up to about 1.5 Tons →Six Unit from 1.9 Strengthening to ton (Outboard experimental apparatus Ya ISS Installing a replacement devices that are used in the outboard)
Scrap On- Up to about Six Ton board capabi lity Altitude:350km~460km Target trajectory Orbital inclination angle: about 51.6 Degree
Rendezvous flight period: Mission Normal Five Daily interest rate period ISS Stay: the longest 45 Daily interest rate Orbit on the emergency waiting period: the longest Seven Daily interest rate
appendix 1-2 "Stork" press kit (appendix)
table A1-2 "Stork" mission performance One Unit Two Unit Three Unit Four Unit Five Unit Technology Demonstration machine
Launch Date 2009 Year Nine Month Eleven Day 2011 Year One Month twenty two Day 2012 Year Seven Month twenty one Day 2013 Year Eight Month Four Day 2015 Year Eight Month 19 Day
Re-entry date 2009 Year Eleven Month Two Day 2011 Year Three Month Thirty Day 2012 Year Nine Month 14 Day 2013 Year Nine Month Seven Day 2015 Year Nine Month Thirty Day
ISS Replenishment amount to
Of the ship goods 3.6 Ton about Four Ton about 3.5 Ton* 2 about 3.9 Ton about 4.5 Ton
Of Outboard goods 0.9 Ton about 1.3 Ton about 1.1 Ton about 1.5 Ton about 1.0 Ton
total 4.5 Ton* 1 about 5.3 Ton about 4.6 Ton* 2 about 5.4 Ton about 5.5 Ton
about 53 Daily interestabout rate 67 Daily interest56 rate Daily interest rate34 Daily interest rate Mission period 42 Daily interest rate (plan 37 Day) (plan 37 Day) (plan 49 Day) (plan 35 Daily interest rate)
Rendezvous flight Five Daily interest rate* 3 Seven Daily interest rate Six Daily interest rateSix Daily interest rateFive Daily interest rate period (plan Seven Daily interest rate) Sixty Daily interest rate*Four 43 Daily interest rate (HTV2 Later ISS The length of stay( Design request design 48 Daily interest rate26 Daily interest rate35 Daily interest rate Thirty Daily interestrequest rate )45 DayTo between)
Withdra wal - Re- Three Daily interest Tworate Daily interest rateTwo Daily interest rateTwo Daily interest rateOne Daily interest rate entry period
Two Unit or later, technology demonstration unit(1 Unit)Due to the improvement in operating machine, it has different materials of supply capacity.
* 1) technology demonstration machine, because it was equipped with an additional to the four minute primary battery propellant such as compared with the operational machine, cargo weight is now 4.5 tons. * 2) with respect to the replenishment amount is,Since mass is also bulky even with a small cargo, it can not be a simple comparison only mass. Unit 3 looks like transport volume of the ship goods is small, but* 3) washas fullbeen to reduced the volumetric. launch in the postponement relationship two days in bad weather. * 4) With the launch postponement of the STS-133, due to the overlap STS-133 and the mission period, has been extended a quarantine period on the basis of coordination with NASA.
appendix 1-3 "Stork" press kit (appendix)
A1.1 Logistics Carrier pressurized section (PLC)
Logistics Carrier pressurized section,ISS Replenishing supplies for the ship (experiment rack, goods transport bag (CTB), Drinking water, apparel Etc.) and then mounted. The interior One They kept at atmospheric pressure, in the internal temperature of solo flight,ISSBoth are controlled in the binding. AlsoISS After the bond with the fans ISS Do the ventilation in between. In front Logistics Carrier pressurized section,ISS Common binding mechanism as the coupling portion with the (Common Berthing Mechanism: CBM) And hatch have been installed. ISS In bonds,ISS Crew this hatch (1.3m × 1.3m) Boarded the inside from, do the unloading. Supplies After Hakobidashi the will,ISS In and equipped with, such as non-supplies that were used.
Passive side common berthing mechanism (Passive CBM)
Figure A1.1-1 Appearance of Logistics Carrier pressurized section (Six Unit)(JAXA)
Figure A1.1-2 The inside of the Logistics Carrier pressurized section that was taken in orbit (left: One Unit(JAXA),right: 2 Unit(NASA))
appendix 1-4 "Stork" press kit (appendix)
The inside of the Logistics Carrier pressurized section, hatch side first One Lac Bay (Bay # 1), The back side of the first Two Lac Bay (Bay # 2Called) Are we. Each compartment, the rack Four Can be mounted by the platform, total EightYou can install the platform of the rack. Rack to be mounted on the "stork" is,ISS It is the same size as that of the rack, about height 2m, Width and depth 1m is.
Figure A1.1-3 "Stork"Five Unit inside of the rack placement (JAXA) (Taken from the hatch side: late access ago)
The first of the hatch side One The Lac Bay,ISS International standard payload rack (ISPR) Or a fixed type of cargo storage rack (HRR) It can be equipped with.ISPR It is removable, "stork" is ISS No. One Lac Bay After arriving in ISS Is transferred to the ship, it will be installed. (Bay # 1) The vacant Lac Bay, it is no longer needed in orbit ISPR You can discard equipped with a.
No.TwoLac Bay is a fixed type of cargo storage rack (HRR) No. Two Lac Bay Only.HRRIt isISSIt does not transfer to the inside.HRRGoods transport bag mounted on the (CTB) Is taken out in the unit ISS (Bay # 2) After being transferred to the ship,ISS In and equipped with a goods and waste that has become spent.
HRR(HTV Resupply Rack):HTV Supply rack
appendix 1-5 "Stork" press kit (appendix)
A1.2 ULC part (ULC)
ULC part, on the side 2.9 × 2.5m Large There are openings, outboard laboratory equipment and replacement equipment in its Etc.ISSYou will install an exposure palette for transport to. Has a large opening in the side, because the large load is concentrated portion at the time of the launch can be, the difficulty of the structural design is higher. The outer wall of the ULC part, "stork" isISSUpon binding toISS"Stork" in the robot arm The grip portion for gripping the Grad pull fixture (FRGF) It has been equipped with.
Gras pull Fixture:ISS When bond,ISSFringes of the robot arm grip this partIt is.
ULC
Figure A1.2-1 ULC part (One Unit)(Left before exposure pallet mounted) (JAXA)
ISS After coupling, the outboard experimental device or the like has been carried by mounting the Exposed Pallet ISS In order to transfer to the side,ISS Hollow The exposure palette bot arm withdrawal from ULC part,ISS Or outboard experimental platform of the side ( "hope",ISS Mobil-based systems (Mobile Base System: MBS)) In and temporarily placed. When the transfer of the outboard laboratory equipment and exposure equipment that has been mounted on the exposure palette is completed, the exposure palette, supply calibration It will be returned to the rear ULC.
Figure A1.2-2 Loading work of the Exposed Pallet (Six Unit)(JAXA)
appendix 1-6 (JAXA)
ULC part of the mechanism
● Launch restraint separation mechanism (Tie-down Separation Mechanism: TSM) Logistics Carrier to the non-pressurized portion, launch restraint separation mechanism Four Pieces have been installed. Launch restraint separation mechanism is, 曝 In mechanism for restraining / separating the dew palette, to securely fix the exposure palette at the time of the launch of the "stork".ISS At the time of withdrawal / re-attachment of the exposure pallet by the robot arm will operate this● Harness mechanism. separation mechanism (Harness Separation Mechanism: HSM)
Harness separation mechanism is installed in the vicinity of the opening of the ULC, when pulling out the exposure palette, non pressurizedDepartment and is a mechanism to separate the power and data communication lines between the exposure palette.
● Guide rail / wheel ISS
When the return exposure pallet by the robot arm to ULC part, to minimize the resistance, in the correct positionIn the mechanism for adjusting, the guide rail is in the non-pressurized portion side, the exposure palette side is equippedGuide rails, with in wheelsthe opening (roller) of it the is. ULC port, starboard, on the lower side Three It is equipped to place. Roller,It is equipped to port, starboard and a lower exposure palette.
Figure A1.2-3 (Up)The inside of the ULC part(1 Unit), (under)Exposed Pallet of roller(2 Unit) 曝 reference 曝
"Stork" press kit (appendix) appendix 1-7 Unit)
A1.3 Exposed Pallet (EP) Exposure palette, Ya outboard experimental apparatusISS Palette for carrying equipped with a ship foreign currency products, such as outboard exchange equipment.The cargo ISS During the transfer, the exposure palette, is taken out from the ULC part,ISSIt will be temporarily temporarily placed on the side. After transferring the cargo is stored again in the ULC part, to end the operation to enter the atmosphere along with the "stork". Exposed Pallet is about maximum payload 1.9 Tons to be mounted (Six Payload is the strengthening) from Unit. From exposure palette, launch ISS Period of up to mooring, subject to the power supply from the ULC part. OutboardWhile it is bound to the experimental platform, etc. ISS You will receive the power supply from the side. The size of the exposure palette,(Longitudinal)about 2.8m×(side)about 4.1m,(height)about 2.3m, Weight about 0.6 It is a ton.
Figure A1.3-1 (1/2) Exposed Pallet (3 For Unit EP-MP) (JAXA)
)
Figure A1.3-1 (2/2) Exposed Pallet (Five For Unit EP) (JAXA) (Five Unit, the fixed for the recovery and disposal of the exposure payload of "hope"As a mechanism HEFU It was first equipped
"Stork" press kit (appendix) appendix 1-8 HREP
The exposure palette has the following types, and used according to the mission.
"Hope" outboard experimental platform mooring only type (I Type) (1, 2, 5 Unit ) This type is temporarily placed overboard experimental platform (OneThis is a UnitIUse the type outboard experimental apparatus Two Equipped with a table,Two In Unit I Set up a US-made attachment mechanism to the type spareIt partswas equipped of the United with a Statesplatform) of .exposure equipment Two
FRGF Cargo mounting machineOrganization (HCAM)
SMILES
Equipment exchange mechanism(PIU)
Connector separatorOrganization (HCSM)
Figure A1.3-2 "Hope" outboard experimental platform mooring only type(I Type ) (Figure One Unit configuration) (JAXA) Multipurpose Exposed Pallet type (EP-MPType) (3, 4, 6 to 9Unit is used here ) Multipurpose Exposed Pallet(Exposed Pallet - Multi-Purpose: EP-MP)Type has become a specification that can transport a combination of a variety of outboard equipment and outboard laboratory equipment, outboard experimental platform(JEM Exposed Facility: JEF)Type to be temporarily placed in(3 First used in the Unit)When,ISS Mobil-based systems (Mobile Base System: MBS) There is a type to be temporarily placed. Type to be temporarily placed overboard experimental platform is outboard experimental apparatusOneNumber andISSIt is possible to transport a combination of common outboard equipment. Type to be temporarily placed in Mobile-based system ISS It will be used to only transport common outboard equipment.Six Battery starting from Unit ORUIn the transportSixMounted platform(Time feedback Nine Table)I can.
Figure A1.3-3 Multipurpose Exposed Pallet type(EP-MP) (left: TypeThree Unit, right:Four Unit ) (JAXA)
"Stork" press kit (appendix) appendix 1-9 Mechanism of the Exposed Pallet The exposure pallet, cargo attachment mechanism, connector separation mechanism, removable type Gras pull fixture ( Flight Releasable Grapple Fixture: FRGF), Power and video Gras pull fixture (Power & Video Grapple Fixture: PVGF), Such as a camera is equipped with. These mechanisms safely outboard laboratory equipment and Funegaiyo exchange equipment transported ISS It plays a role in order to transfer to the side.
● Simple payload side device exchange mechanism (HTV Payload Interface Unit: HPIU)
Simple payload side device exchange mechanism, it was mounting the exposure palette in the "hope" outboard experimental platformIt is because of the mechanism.
Figure A1.3-4 Simple payload side device exchange mechanism (HPIU) (JAXA) ● Cargo mounting mechanism (HTV Cargo Attachment Mechanism: HCAM)
Cargo attachment mechanism is a mechanism for fixing the outboard experimental apparatus to exposure pallet, secure the four corners of the outboard experimental apparatus It is.
● Connector separation mechanism (HTV Connector Separation Mechanism: HCSM)
Connector separation mechanism, in order to separate the connector supplying the heater power overboard experimental apparatus and Funegaiyo exchange equipment It is the mechanism.
● Gras pull fixture (FRGF/PVGF) Gras pull fixture,ISS Of the robot arm(SSRMS)
Bunch for gripping in and "hope" robot armIn the equity section,ISS In a mechanism that is normally used. Power and video Gras pull fixture (PVGF) Is,SSRMS Through the order to exchange the power and video dataIt has an interface.
● HTVBar single camera system (HTV Berthing Camera System: HBCS) SSRMS
The camera to support the positioning work of when to return to the ULC exposure palette by manipulating the, equipped at the tip of the exposure palette. In addition, the tower of the target (target) in positioning the camera to supply the carrier ULC It has been mounting.
Figure A1.3-5 HTV Bar single camera system (HBCS) (JAXA)
"Stork" press kit (appendix) appendix 1-10 A1.4 Electrical module (AM)
Electrical module, guidance control, communication, equipped with electronic devices such as power systems, autonomously finger or from the ground,Make the navigation control of the "stork" in accordance with the decree. In addition, it makes the power supply to the "stork" each part. Electrical module is about the diameter 4.4m, About height 1.2m In the module, the mass is about 1,700kg. Table the subsystem Overview A1.4-1To shows.
Figure A1.4-1 Electrical module (appearance of from the side)(1 Unit ) (JAXA)
Figure A1.4-2 Internal electrical module (2 Unit ) (JAXA) Electrical module, the commands from the ground,NASA Of Tracking and Data Relay Satellite (TDRS ) And the International Space stearylNear the communication system mounted on the tions(PROX) Received via the, and sends it to each of the devices of the "stork". Also,TDRS as well as PROX Through, and then send the data of the "stork" on the ground.
"Stork" press kit (appendix) appendix 1-11 table A1.4-1 Overview of the sub-system of the electrical module - After the orbit of "stork", Kou using the position and orientation sensor of the guidance and control systemSystem for to get the legal information, at a - mainly,commandGPS from the ground, to carry out the solo flight Navigation and guidance controlof the "stork". system Antenna, rendezvous sensors, earth sensors, guidance and control computerData, consists of abort control unit. - Just before to be gripped by the robot arm,ISSThe relative position of the76cm Within,Per second the relative speed7mmControl within.ISSAnd "stork" each about per second7,800mIn has been flying, that the relative speed0.0001%Control up to. - Communication system sub-system of the "stork" is,NASA Tracking and data relay satellite(TDRSSatellite communication apparatus for communicating via a)(Inter-Orbit Link System: IOS)When,ISSIn the vicinityISSNear the communication apparatus Communication systemfor communicating with(Proximity Link System: PLS)It consists of. In any of the communicationSUse the band.
- PLSabout,ISSNeighborhood about200kmIn establishing a communication,ISSDirectly under10m TreesUse until it reaches the Yapucha point.
- Data processing sub-system includes a command receiver, telemetry transmission function.- Data-processing system Thermal control of the electrical module propulsion module, Logistics Carrier pressurized part of the environmentControl, fault detection and notification, etc. of "stork" various places, the data processing and control of the other sub-system support. - BatteryOneNext battery (Primary Battery: P-BAT)SixIndividual(6In UnitSeven From individualOneReduce the number)When,TwoNext battery (Secondary Battery: S-BAT)OneMounting number. - Power controller electric power generated by the solar cell panel at the time of sunshine ( Power Control Unit:PCUIs supplied to control), the surplus powerTwoNext battery (S-BAT) In storage.
- At the time of the shade during the solo flight,TwoNext battery (S-BAT Power system ) Power is accumulated in andOneNext battery (P-BATSupplied to each of the system of power). - ISSIn the bindingISSIf the power supply from is interrupted,One The following battery(P-BATSupplied to each of the system of power). - Of "stork"ISSIn bonds,ISSThe electric power supplied from the(120V)The DC / DCA predetermined voltage in the converter(50V)Conversion / stabilization to supply to each equipment in the "stork" in. Solar cell - The "stork" Unit 6 of the outer wall, a total of48Equipped with sheets of solar panels (Four Unit55Sheet,FiveIn UnitSixSingle reduction to49Sheet,SixUnit 48Sheet). - The outer wall of the Logistics Carrier pressurized part:TwentySheet - The outer wall of the ULC:twenty threeImages →FiveIn UnitFourSingle reduction to19Sheet,SixUnit isOne Sheets increasePalmTwentySheet - The outer wall of the electrical module:EightSheet - The outer wall of the propulsion module:0Sheets (Note)
Note) Delete one in Unit 3. Cut one in order to mount the surface potential sensor at Unit 4 Removal. In addition two deleted in Unit 5, abolishedSheets, in Unit four 6 Unit[1, 2 4, Unit two six, Unit Unit 5, 3 05 sheets Unit 6]
"Stork" press kit (appendix) appendix 1-12 (JAXA)
A1.5 Propulsion module (PM) Propulsion module,Four The propellant tank of spherical group, usually Two And equipped with a ton of propellant. Propellant, MonomechiLe hydrazine (MMH) And nitrogen monoxide addition dinitrogen tetroxide (MON3) Use the. From the propellant tank,Four Based on the main engine of (Two Group× 2 System) and 28 Attitude control thruster of the group (14 Group× 2 system)In it is supplied propellant, according to which signal sent from the electric module, and generates a thrust for orbit changes and attitude control. Three Unit later, I switched the main engine and the attitude control thruster on domestic products(But Four Unit is stock activeUsing the conventional product for use).
Figure A1.5-1 Propulsion Figure A1.5-2 Propellant tank module (Multilayer insulation cover mounting ago) (JAXA)
Figure A1.5-3 Photographed propulsion module in orbit (One Unit) (JAXA) (Look at the bottom photo Four Nozzle of the group is the main engine)
"Stork" press kit (appendix) appendix 1-13 table A1.5-1 Thruster configuration of the "stork"
specification
Main engine Attitude control thruster (RCS Thruster
Two Group × 2 System (redundant configuration)14 Group × 2 System (redundant configuration) ) quantity Total Four Group Total 28 Group *
IHI Aerospace IHI Aerospace HBT-5 500N (Newton)Class 120N(Newton)Class (3, 5 And later Unit ※ (3, 5 And later Unit ※ ) ) Thrust /One Group (Reference: imports (Reference: imports ) Aerojet Shrine ) Aerojet Shrine R-4D 500 N (Newton R-1E 120 N (Newton ) (1, 2, 4 Unit ) (1, 2, 4 Unit ) ) * all 28 Of the group,Twelve Based on the installation to supply the carrier pressurized outer wall ※ Four Unit imported goods(What was left as spares)use.
(JAXA) Main engine
Figure A1.5-4 Position of the main engine and the attitude control thruster
"Stork" press kit (appendix) appendix 1-14 A1.6 Near the communication system ()PROX
"Stork" near the communication system (Proximity Communication System: PROX) Is, "stork" is ISS WhenFor communication, a wireless communication device which is opposed to the "stork",ISS It has been installed on the side. PROX Communications, data processing,GPS Each equipment, command panel for the crew (Hardware Command Panel: HCP), Communication antenna,GPS Is composed of an antenna, it is disposed on the robot arm workstations in "cupola" HCP Onboard equipment other than a "hope" between the ship laboratory of satellite communication system (Inter-orbit Communication System: ICS) It has been mounted in thePROX rack. Communication antenna is installed on the outer wall side of the "desired" inboard laboratory,PROX GPS antenna Two GroupIt is attached to the zenith of the "hope" ELM-PS.
(JAXA) It is installed on the ceiling of the "desired" inboard laboratoryICS/PROX On the right half of the rack (the portion indicated by a red frame) PROX Communications equipment has been installed. [Reference] US Orbital Sciences Company, Cygnus the company is in development(Cygnus)For use in transport aircraft, purchase a "stork" in the vicinity communication equipment of equivalent from Mitsubishi Electric Corporation (Nine Machine content: about Sixty Billion yen (6,600 Ten thousand US dollars)) it has been. Japan's space technology(ISS Achievement in)There is the first case that led to exports and industrialization of overseas.
Figure A1.6-1 PROX Communication equipment (JAXA) PROX Communication antenna,ISS "This close to the vicinityIt will be used to direct radio communication with Unotori ".
"Hope" inboard laboratory
Earth direction
Figure A1.6-2 PROX Communication antenna
"Stork" press kit (appendix) appendix 1-15 )
● Crew for the command panel (HCP) ●ABORT(Forced evacuation) Abort, emergency evacuation ●FRGF SEP (Forced separation from the arm) SSRMS Of when trouble grasping is no longer open, the "stork" FRGF Forcibly separated by separating the
●RETREAT(One o'clock recession) 30m Or 100m Retreat to a point
●HOLD(Relative position holding)
●FREE DRIFT(Control stop)
For the "stork" grip, "saidTo the take "off the control of Figure A1.6-3 Crew for the command panel (HCP) (JAXA)
Crew for the command panel (Hardware Control Panel: HCP ) Is,Such as sending an approaching stop command to the "stork" at the time of abnormality, the urgent command,ISS Crew is the control panel that can be performed in the push button.HCP During the, near the operation of the "stork",ISS It has attached to the robot arm of the workstation.
ISS Photograph shown to the right Space X Company's CCP (Crew Command Panel)is. That the experience of the "stork" is also utilized in the US commercial spacecraft you can see also from here.PROX In the Cygnus resupply ship to use, in the same Figure A1.6-4 Space X Company of manner as the "stork" HCP It will be used. the crew for the command panel for the Dragon (CCP
A1.7 Reflector (laser radar reflector)
Position of the reflector
Yui "stork"To case CBM It was taken from the earth direction side
(JAXA) Reflector (laser radar reflector) is, of "hope"This laser reflector disposed at the bottom. "Stork" is ISS Rendezvous sensors of the "stork" when approaching from below (Earth direction) (Rendezvous Sensor: RVS) And reflects the laser beam irradiated from.
Figure A1.7-1 Reflector for that is installed in "hope", "stork"
"Stork" press kit (appendix) appendix 1-16 749mm x 425mm x 502mm "Stork" Unit 6 Press Kit (appendix)
A1.8 曝 reference 曝 ISS Comparison of supply machine
"Stork"HTV Cygnus Dragon ATV (Japan) (usa) (usa) (Europe)
Supply machine
2008~2015 Operation period 2009 Year - 2013 Year - 2012 Year - Year recessionRole
ISS Supply performance to Five Time success/Five Time Five Time success/ 6 Time Eight Time success/ 9 Time Five Time success/Five Time
5.3 Ton / * 1 Gross weight 16.5 Ton 8.7 Ton Twenty Ton After enhancement 6 (~ 7.5)Ton
Supply about 2-3 Ton ISS To about Two Ton / * 1 Six Ton * 2Seven Ton Materials supply capacity After enhancement 2.4 (to 3.5)Ton Recovery about 1.5 Ton * 2
Experiment rack (ISPR) M01 Bag* 3 Triple size CTB*FourTransport allowed to the extent Ship goods transport Etc., multipleLarge goods transport FriendlyTo the extent thatTransportation Allowed [Hatch size] [1.3mx 1.3m] [0.9mx 0.9m] [1.3mx 1.3m]
○ ISS Outboard battery and, large ○ Outboard goods transport × 500-600kg) × goods transport (Normal Allowed, such as "hope" outboard ISS Track experimental changes ISS Fuel apparatus × × × ○ supply to * 1) 4 Enhancing the installed capacity after Unit(In parentheses Atlas V During launch),* 2)Supply capacity in inclusive outboard goods,* 3) M01 bag: 749mm x 897mm x 508mm *Four)Triple size CTB(Cargo Transfer Bag):
appendix 1-17 "Stork" press kit (appendix)
2-1 appendix Two "Stork" (HTVOperation Overview of) An overview of the operation that is commonly performed in the "stork" mission is shown below.
FD1(Flight Day 1)Operation of Mission overview - Launch / orbit -
Automatic start of operation after the orbit by an automatic sequence ( "stork" sub-system, three-axis attitude control MakeStanding, abnormal inspection of aircraft, communication connection with the "stork" Mission Control Room) - Rendezvous trajectory control
● Launch / orbit "Stork" is,H-IIB Is mounted on the rocket will be launched from the Tanegashima Space Center.ISS For the orbital plane is launched in accordance with the time zone that passes through the sky of Tanegashima, launch opportunities One On the day One
It will be times. H-IIB Launch and aircraft movement of rocket (2 Unit) (JAXA)
About from launch Two Total after minute Four Solid rocket booster group(SRB-A)But TwoAre separated one group, it will then be fairing separation. No. One After stopping the combustion of the stage engine, the first OneStage will be separated. After that first Two Stage engine is started, it advanced the "stork" 200km × 300km, Orbital inclination angle 51.7Turn into a predetermined elliptical orbit of time. No.Two About the stage engine launch 14 It stopped after minute, about from launch Fifteen To separate the "stork" after a minute.
Fairing separation (JAXA) The One Stage separation (JAXA)
Operation after orbit When separated from the "stork" rocket, automatically start the sub-system, to stabilize the attitude of the aircraft, and inspect the presence or absence of the airframe of the anomaly. after that NASA Tracking Data Relay Satellite (TDRS) To establish a communication with, Tsukuba Space Center (Tsukuba Space Center: TKSC) To initiate communication with the "stork" Mission Control Room in.
No. Two Stage separation)(JAXA
appendix "Stork" press kit (appendix)
2-2 RendezvousOperation Mission overview - Rendezvous trajectory control
Rendezvous trajectory control about Four While gradually increasing the altitude over the day ISS Close to.
ISS Was close to the "stork"Four Unit(NASA ) http://jda.jaxa.jp/result.php?lang=j&id=82bcc47ac89d327a3e1fbcec885452d4
appendix (AI)"Stork" press kit (appendix)
2-3 The vicinity of operation Mission overview - The vicinity of operation - ISSThe final approach to the - ISSGripping of the robotic arm - Harmony (No.TwoCommon berthing mechanism of the coupling portion) lower (CBMBinding to) - Outfitting of the coupling portion (wiring, cable installation, etc.) - Mooring power system start-up, switching of the communication path (radio waves→Wired), etc.
The vicinity of operation ISS Upon reaching the vicinity of the communication area (near the communication area) that can directly communicate with, "stork" is,ISS Proximity communication system mounted on (Proximity Communication System: PROX) And communication to establish a of,GPSStart the relative navigation. after that,GPS Trajectory control using the relative navigation(Maneuver)To implement the,ISS About the rear 5km Of approaching the starting point (Approach Initiation: AI) To you will reach. From the first unit Four Until the Unit is AI At the point ISS But it had carried out the relative stop for,Five For operational efficiency from the Unit AI Directly through the point ISSIt has been changed to the operation to be put into close orbit to. It should be noted that, in an emergency as usual AI It is also possible to switch the operation to carry out the relative stop at the point.
(ISS Also "stork" is also about per second7.8km We are flying at a rate of, but the speed difference of each other 0 Be adjusted so as to, it is ready to relatively stop was).
Approaching the starting point (JAXA) AI To reach the point Ninety From the minute before, the United States Houston ISS Mission Control Center (MCC-H) And the integrated operation of the "stork" Mission Control Room will start. "Stork" is,AI To reach the point Ninety From minute ago ISS In order to execute the operation of up to join the end to the crew of the activity time to, in the rendezvous phase, maximum twenty four Make the time adjustment of the time.
ISSThe final approach to (see figure on the next page) AI Before reaching the point ISS To obtain access permission from the Mission Control Center, "stork" is AI Continuously after the point reached AI It will conduct the orbit control (maneuver). "Stork" is,GPS In relative navigation ISS Lower (R Bar on) about 500m(RI Move up to a point), the rendezvous is from thereSensor (Rendezvous Sensor: RVSThe laser light irradiated from) from below while confirming the position by reflecting the "desired" inboard the installed reflector below the laboratory (laser radar reflector) ISSClose to. Rendezvous approach speed in the sensor navigation is One Minutes to One~10m It is the degree. ISS Below the 250m(Hold point) and 30mOf (parking points) Two Automatically performs a stop at the point, finally,ISS Below the 10mAnd relative stop in the vicinity. During this final approach, in an emergency,ISS Crew command panel for the crew (HTV Hardware Command Panel: HCP), The retention of relative position(HOLD), A temporary retreat(RETREAT), Forced evacuation(ABORT)By sending a command, such as you can control the "stork". It should be noted that "stork" is,ISS Lower part 250m At the point, the posture in the yaw direction (lateral direction) 180Change the direction of the main engine and degree rotation. In this attitude changed with the collision avoidance operation, in the event of an emergency, safe the "stork" ISS It shall be performed in order to lay the front.
appendix Photo: NASA"Stork" press kit (appendix)
2-4 "Stork" Grip and bonding operation of
-X ISS Lower part 10m:
-Z ISS The same orbit and, GPS relative navigation Bar Thing box Backward about Parking pointISS Flight direction Relative stop at an inner + Z
ISS Lower part 30m: Withdrawal operation: ISS Away to the frontDe maneuver ISS Lower part 250m: Approaching the starting point (AI point)
Yaw in the hold pointIn the direction of 180 Degree rotation ISS RGPS + X
navigationR Bar close
ISS Lower part 500m: "Kibo" Rendezvous sensor navigationThe final approach begins at
(JAXA) ISS Gripping of the robotic arm "Stork" Mission Control Room, the "stork" is ISS Below the 10m In the vicinity ISSIf you confirm that you have relatively stop to, to stop the thruster of the "stork" (free drift state). Then, length 17.6m of ISS Of the robot arm (SSRMS) In Gras pull fixture of the "stork" (FRGF) To grip the.
Gripping of the "stork"(Four Unit ) (NASA / JAXA) FRGF (NASA) Harmony (No.TwoBinding to the coupling portion) ISS Is gripped by the robot arm "stork" is "Harmony" (No. Two Earth side of the common berthing mechanism of the coupling portion)(Common Berthing Mechanism: CBM) To are combined.
5km
harmony
"Kibo"
appendix "Stork" press kit (appendix)
2-5 "Stork"Grip and bonding operation of(Continuation)
Robot arm console of the cupola to be used when gripping the "stork"(Four Unit before arrival of on-orbit training ) (NASA Offer )
ISS Bound to "stork"Three Unit (NASA Offer ) https://www.flickr.com/photos/nasa2explore/9397024654/
appendix "Stork" press kit (appendix)
2-6 "Stork"(HTV)Entry operation Mission overview - Entry into Logistics Carrier pressurized section - CBMRemoval of the control device - Hatch Open - Inter-module ventilation ventilation (Inter-Module Ventilation: IMV)Start-up
- ISSOf fire extinguisher, such as portable oxygen mask Relocation to the "stork" ship
Entry into Logistics Carrier pressurized section As preparation before entering a room,ISS Crew outfitting of the coupling portion (removal of the insulation cover, a common coupling mechanism (CBMRemoval of the control device of), installation of power and communication wiring and air piping) will implement the.ISS During the bind to,ISS Power in the "stork" is supplied from. after that,ISSEqualization of Logistics Carrier pressurized part by the crew, alsoHTVThe lighting of the interior lighting is performed by the operation control room of the command, the hatch is opened. Crew CBM Check the internal from the hatch the center of the window, make sure that there are no abnormalities, such as scattering of suspended solids.
When the hatch is opened, "Harmony" in circulation fan unit (No. Two Inter-module ventilation ventilation of the coupling portion) (Inter-Module Ventilation: IMV) And the pressurized part of the air circulation in the interior is done. after that,ISS Crew (for the sake of safety first, the mask and goggles fitted) enter the Logistics Carrier pressurized portion is, to get the air sample to confirm that there is no abnormality, performs fire extinguisher, the installation of portable oxygen mask you.
State when I opened the hatch of the Logistics Carrier pressurized section(Five Unit ) (JAXA) http://jda.jaxa.jp/result.php?lang=j&id=e1189d1c788266aaf58ffda0130f58ce
appendix (JAXA / NASA)"Stork" press kit (appendix)
2-7 "Stork" entry - "stork" operations before separation Mission overview - From the "stork"ISSCarrying the work of supplies to - Scrap loading work of loading after the end of the "stork"
From the "stork"ISSCarrying the work of supplies to It was conveyed by mounting to supply the carrier pressurized portion goods transport bag (Cargo Transfer Bag: CTBA), etc. ISS We do the work for carrying within.
Food, daily necessities, such as Lab SuppliesIt was packing Astronaut Hoshide to open the hatch CTB (JAXA / NASA) http://jda.jaxa.jp/result.php?lang=j&id=b94148cb773e1bebf30b1f5488a96cb7
left:FourPhoto at the time of entry Unit (NASA),right:Three Unit at the time of entering state, Astronaut Hoshide is the mask and gogglesCheck the internal wearing (NASA / JAXA) http://jda.jaxa.jp/result.php?lang=j&id=d6c39cefb92f51a95b2823f2bed5c622 http://jda.jaxa.jp/result.php?lang=j&id=cfb32325857e9b4e076699ee4c6afaee
Scrap loading work of loading after the end of the "stork" →See "" unnecessary products of the loading operation of the stork. ' " Waste products, supplies ISS End all carry to, instead of doing from now empty, will continue to appropriately implemented even during loading.
appendix 248 × 425 × 235mm"Stork" press kit (appendix)
2-8
(1 CTB)
(502 × 425 × 248mm) Half-size )Single size Double size ) Triple size (Full-size CTB (1/2 CTB Substantially ) CTB CTB (2 CTB Substantially CTB (3 CTB Substantially M02 bag M01 bag (4 CTB Substantially) (6 CTB Substantially
) Standard-sized CTB
502 × 425 × 502mm 749 × 425 × 502mm )
Figure A2-1 曝 reference 曝 ISS Goods transport for the bags that are used to transport to the (CTBVarious sizes) (NASA / JAXA)
appendix The material obtained by adding iodine traces have been filled in the water bag."Stork" Unit 6 Press Kit (appendix)
[Transport of drinking water] Transport of drinking water by the "stork" is Two It was first performed in the Unit.Six In Unit FourMake the time eyes of transport. Water bag(Contingency Water Container-Iodine: CWC- I:capacity Twenty liter)It is,Two Unit Four bag(80 liter),Four Unit twenty four bag(480 liter)Further increased from 5, 6In Unit Thirty bag(600 liter)It carries the. This astronaut Three person's Four The amount by which meet the month.
Water NASA Those that meet the drinking water standards purified from the tap water of Tanegashima, as a bactericidal component
appendix 2-9 Two"Stork" Unit 6 Press Kit (appendix)
) Filling of water into the water bag
×
Figure A2-2 Water bag filled with drinking water(CWC-I)Packing material and(Bottom right:Five) Unit, the(JAXA) rest Six Unit (Bag purple label is attached is in the water bag at the bottom left of the photograph, around is the packing material
appendix 2-10 (JAXA) "Stork" Unit 6 Press Kit (appendix)
Figure A2-3 Of drinking water equipped with image
appendix 2-11 SSRMS"Stork" Unit 6 Press Kit (appendix)
Moving operation of the Exposed Pallet Mission overview - Temporary placement of the drawer / ISS truss of exposure palette from the ULC part
Temporary placement of the drawer / ISS truss of exposure palette from the ULC part Exposed Pallet which has been stored in the ULC portion is,ISS Of the robot arm(SSRMS)In drawn, it will be temporarily placed in the exchange location near the truss of the battery.
ISS In the robot arm, photo taking out the exposure palette from ULC part(3 Unit
SPDM
) (NASA) SPDMHow to transport the outboard goods of the United States using the "Dexter" (HTV2 In the transportation FHRC Movement of )
appendix 2-12 "Stork" press kit (appendix)
2-13 SPDMRobotics operations and "Dexter" Mission overview - Relocation of the equipment that carried and mounted in the exposure palette of "stork" to the installation site
And mounted on the exposure palette of "stork"JAXAInstallation of laboratory equipment (or exposure of the "hope"NASAIf the transport experiment device) of,JEMRMSUsing must be installed in a "hope" outboard platform.
NASAIf that carried the experimental apparatus and system spare parts, such as batteries, special purpose robot arm made of Canada(Special Purpose Dexterous Manipulator: SPDM)The "Dexter"SSRMSUse in a state of being gripped by the tip and transported and installed in the storage location on the truss.
At this timeJEMRMSOperations andSPDMOperation is carried out in the operation from the ground (JEMRMSPiloted from the ground to move the experimental apparatusThreeUnit introduction from the time of mission). On the ground,NASA,Canada(ISSControl of the robot arm)Such international operation is performed while control center of Japan performs the adjustment.
Perform this exchange S4 Position of the truss of the battery (NASA)
appendix "Stork" press kit (appendix)
2-14 Recovery operation of the Exposed Pallet Mission overview - Storage of exposure palette to ULC part
Storage of exposure palette to ULC part Of the outboard goods from the Exposed Pallet ISS
When the transfer operations to the side is completed, equipped with the now empty (or disposal equipmentIt was) exposure palette to ULC part ISS Of the robot arm(Space Station Remote Manipulator System: SSRMS)Use the returned.
Outboard platform tip is temporarily placed in, exposure pallet finishing the installation of waste (Five Unit) (JAXA)
Exposed Pallet to be housed in the ULC part (Three Unit) (NASA) https://www.flickr.com/photos/nasa2explore/9397290408/
appendix "Stork" press kit (appendix)
2-15 Scrap of loading operation of the "stork" Mission overview - ISSLoading from to the "stork" of scrap
ISSLoading from to the "stork" of scrap The goods that have carried and mounted in the Logistics Carrier pressurized section ISS After Hakobidashi to the side,ISS Goods that are no longer needed at the innerLoading in the "stork" for disposal in the "stork" a.
It should be noted that the item to be discarded,ISS It will be finalized in a few weeks before departure. In the loading, the center of gravityIt is necessary to take into account the requirements of the position, the item to be installed,NASA / JAXA There is a need to be adjusted between.
How the scrap was loaded (2 Unit ) (JAXA / NASA) http://iss.jaxa.jp/library/photo/iss027e008111.php
appendix CPA "Stork" press kit (appendix)
2-16 ISS Of separating the day before operation Mission overview - Separate preparation of the "stork" (lighting, fire extinguisher, recovery, such as portable oxygen mask,CBM Mounting of the control device,Stop of inter-module ventilation ventilation, switching of the communication path (Wired→Radio waves)) - Hatch closure of the "stork"
Preparing the separation of "stork" Prior to the separation of the "stork", such as the lighting of the "stork" ISS
In those that can be reused will be recovered removed.In order to ensure the safety ISS Fire extinguisher that had been temporarily installed in the pressurized part "stork" in the binding (Portable Fire Extinguisher: PFEA), portable oxygen mask (Portable Breathing Apparatus: PBA)Also ISSBack to within. Finally, closing the hatch, perform the removal of the wiring and cable joints, inter-module ventilation ventilation (IMV) To stop. "Stork" by the command from the "stork" Mission Control Room will be carried out, such as switching to internal power supply.
(Photo NASA Offer) Left: fire extinguisher (PFE)
(NASA) Right: portable oxygen mask (PBA)
CBMControl device of (Controller Panel Assemblies: CPAMounting of)
CBM It was used to bond Sixteen Control device for a book of bolt motor drive Four Install the group.
(NASA) Four One square box that there is
appendix "Stork" press kit (appendix)
2-17 ISS Operation of the separation date Mission overview - Stop of mooring power system - Removal of the wiring and cable joints - Separation of the "stork"
Of "stork"ISSSeparation from the "Stork" is, in the next step ISS Separate from. OneISSGripping the "stork" in the robot arm TwoCommon Berthing Mechanism (CBMCancellation of) (TwoAfter the pressure was reduced by vacuuming the air between the sheets of the hatch,CBMTo the control deviceSixteenIt sends a command to loosen the bolts(Usually crew laptopPCSent from)And,CBMTo release the fixed) ThreeISSMove the "stork" to the release position in the robot arm FourGuiding and navigation and control system (Guidance Navigation Control: GNCStart-up of) FivePropulsion thrusters injection preparation (switching from the injection stop of thruster, the injection is possible state) Six ISSRelease the grip of the robot arm of the,ISSWithdrawal injection from orbit
Four Unit(left),Five Unit(right)Release of
(NASA) http://jda.jaxa.jp/result.php?lang=j&id=ee76aa85ec9eeaf2fde1b183e2bbee8f http://jda.jaxa.jp/result.php?lang=j&id=68130cdcd2d8d1adfa57f777bcfb41f4
appendix "Stork" press kit (appendix)
2-18 Re-entry operation Mission overview
- Orbit control - Re- entry
Re-entry Carried out orbit injection for decelerating, and then re-enter the atmosphere.
ISS It was taken from Four How the Unit is to re-entry (NASA) http://jda.jaxa.jp/result.php?lang=j&id=8101e1fa719d8ad941c4a82ba987d124
appendix "Stork" press kit (appendix)
2-19 ISS It was removed from the "stork" is Two Do the times of the orbit change, input will to orbit preparation orbitIt is. Then, adjust the timing of the track change aimed at re- entry in the deorbit preparation orbit, when the last of the orbit change, will be the re-entry into the atmosphere combustion waste. Splashdown planned area of "stork" is in the South Pacific, where the meal and the Automated Transfer Vehicle(ATV)Other that was also used at the time to control fall, are also used in the disposal of the Russian Progress supply ship, is also less sea navigation of When you discard these spacecraft, NOTAM advance(NOTAM) vessels in the area away from the island where people are living (exclusiveConduct of of the other notification, countries outsideMarine &the Aerospace economicOpportunity zone). to leave so as not to approach has become to international rules.
Figure 2.5.4-2 Splashdown plan area and HTV Of orbit (red line)
(HTV1)
Figure A2-4 Plan area that re-entry, and disposal of the "stork" (Space Activities Commission
) [Reference] HTV "stork"Three Unit (HTV3 Information on safety measures in accordance with the re-entry of)March on twenty four Year Four Month Four Japan Space Activities Commission Safety Subcommittee
http://www.mext.go.jp/b_menu/shingi/uchuu/reports/1321150.htm
appendix "Stork" press kit (appendix)
2-20 Mission Control in the "stork"
"Stork" is H-IIB When separated from the rocket, automatically start the sub-system, machineThe posture of the body to stabilize. after that NASA Of Tracking and Data Relay Satellite (TDRS) And communication to establish a of,NASATsukuba Space Center via Center (Tsukuba Space Center: TKSCTo start the communication with the "stork" Mission Control Room, which is installed on the space station operation building within).
Operation and control of the subsequent "stork" is done by the "stork" Mission Control Room."Stork" Mission Control Room monitors the data in the flight of the "stork", by sending a command from the ground and orbital adjustment of the "stork", and"Stork" controls is ISSof the Rear sub-system 5km To reach class. the Ninety From the minute before,NASA Johnson Space SeOf centers ISS Mission control center (MCC-H) And the integrated operation of the "stork" Mission Control Room will start.
Figure A2-5 Mission Control Overview of the "stork" (JAXA)
appendix "Stork" Unit 6 Press Kit (appendix)
(JAXA)The International Space Station(ISS)Crew
Tsukuba Space Center "stork" operation (mission) control room NASA ISS Mission Control Center (Houston) Figure A2-6 "Stork"(HTV)At the time of operation NASA Coordinated operation image of the (at the time of the holding operation)
appendix 2-21 "Stork" Unit 6 Press Kit (appendix)
Figure A2-7 "Stork" Mission Control Room (left), structure and role of the "stork" Mission Control team (right) (JAXA)
appendix 2-22 "Stork" Unit 6 Press Kit (appendix)
appendix Three "Stork" /ISS Related Acronyms
Abbreviation English name Sum name ACU Abort Control Unit Abort control unit (HTV) AI Approach Initiation Approaching the starting point (HTV) AM Avionics Module Electrical module (HTV) AMS Alpha Magnetic Spectrometer Alpha magnetic spectrometer AQH Aquatic Habitat (JAXA)Aquatic organisms experimental apparatus ATOTIE-mini Advanced Technology On-orbit Test Instrument for space Environment - mini HTV4
Surface potential sensorATV equipped with in Automated Transfer Vehicle (ESA)Automated Transfer Vehicle BCS Berthing Camera System Camera System for mooring (HTV) BDCU Battery Discharge Control Unit Battery discharge controller (HTV) CALET Calorimetric Electron Telescope (JAXA)High- energy electrons and CAM Collisiongamma-ray Avoidance observation Maneuver Collision avoidance maneuver equipment CAPCOM Capsule Communicator Kyapukomu (NASA) CATS Cloud-Aerosol Transport System (NASA Of the outboard experimental apparatus ) CBEF Cell Biology Experiment Facility Cell culture apparatus CBM Common Berthing Mechanism Common berthing mechanism CCE Chamber for Combustion Experiment (JAXA)Combustion experiment chamber CDRA Carbon Dioxide Removal Assembly (NASA)Carbon dioxide removal device CFU Colony Forming Unit Colony forming unit CG Computer Graphics Computer graphics CG Center of Gravity Center of gravity CM Co-elliptic Maneuver Co-orbital maneuver (HTV) COTS Commercial Orbital Transportation Services Commercial Orbital Transportation Services COTS Commercial off - the - shelf Consumer products CPA Controller Panel Assemblies (CBM)Control panel CRS Commercial Resupply Services Commercial supply services CTB Cargo Transfer Bag Goods transport bag CTC Cargo Transport Container Exposure cargo shipping container CWC-I Contingency Water Container-Iodine Water bag(Iodized type ) CZ Communication Zone Communication region (HTV) DH Data Handling Data processing DMS Data Management System Data management system DOM Deorbit Maneuver Orbit maneuver (HTV) DSM Descending Maneuver Advanced lowering maneuver (HTV) ECLSS Environmental Control and Life Support SystemEnvironmental control and life support system EDT Electrodynamic Tether Conductive tether EF Exposed Facility "Hope" outboard experimental platform EFU Exposed Facility Unit Outboard experimental platform side device EHR End-massexchange mechanismHold and Release mechanism (KITE)Endomasu holding and release mechanism ELC EXPRESS Logistics Carrier (NASA)Express Logistics Carrier
appendix 3-1 "Stork" Unit 6 Press Kit (appendix)
Abbreviation English name Sum name ELF Electrostatic Levitation Furnace Electrostatic levitation furnace EMC Electro-Magnetic Compatibility Electromagnetic compatibility EP Exposed Pallet Exposed Pallet (HTV) EPC Exposed Pallet Controller Exposed Pallet control device (HTV) EP-MP Exposed Pallet - Multi-Purpose Multipurpose Exposed Pallet EPS Electrical Power System Power system ESA Earth Sensor Assembly Earth sensor (HTV) ESP-2 External Stowage Platform-2 Outboard storage platform Two(ISS) ExHAM Mechanism Exposed Experiment Hadrail Attachment General-purpose space experiment for the hand rail mountingmechanism FD Flight Day Flight date FD Flight Director Flight director FDS Fire Detection and Suppression Fire detection and fire fighting FEC Field Emission Cathode (KITE)Field-emission electron source FHRC Flex Hose Rotary Coupler (NASA)Flex Hose Rotary Coupler FOR Flight Operations Review Flight operation Committee FRAM Flight Releasable Attach Mechanism (NASA of)Attachment mechanism FROST Freezer-Refrigerator of Stirling Cycle JEM Mounting portable refrigeratedInventory FRR Flight Readiness Review Flight Committee FRGF Flight Releasable Grapple Fixture Gras pull Fixture FWD Forward Traveling direction side, front GCC Guidance Control Computer Guidance control computer (HTV) GF Grapple Fixture Gras pull Fixture GHF Gradient Heating Furnace Temperature gradient furnace GHF-MP GHF-Material Processing Unit GHF Furnace body part GMT Greenwich Mean Time Greenwich mean time(World Time ) GNC Guidance Navigation Control Guiding and navigation and control GPS Global Positioning System GPS antenna GPSR GPS Receiver GPS Receiving machine GSE Ground Support Equipment Ground support equipment GTO Geostationary Transfer Orbit Geostationary transfer orbit HAM Height Adjusting Maneuver Altitude adjustment maneuver (HTV) HBCS HTV Berthing Camera System HTV Berthing Camera System HC Hand Controller Hand controller (HTV) HCAM HTV Cargo Attachment Mechanism Cargo mounting mechanism (HTV) HCE Heater Control Electronics Heater control device (HTV) HCSM HTV Connector Separation Mechanism Connector separation mechanism (HTV) HCP Hardware Command Panel Crew for the command panel (HTV) HDEV High Definition Earth Viewing (NASA)High-definition Earth imaging device HDM Holddown Mechanism Orbit on the capture mechanism (HTV)
appendix 3-2 "Stork" Unit 6 Press Kit (appendix)
Abbreviation English name Sum name HDTV-EF High Definition TV Camera- ExposedFacility Consumer high-definition camera (MCE) HEFU HTVsystem Exposed for outboard Facility Unitexperimental JEM-EFU Cargoplatform gripping mechanism HGA High(HTV GainExposed Antenna Pallet) High-gain antenna HGAS HTV GPS Antenna Subsystem HTV Antenna subsystem HPIU HTV Payload Interface Unit Simple payload side device exchange mechanism HRR HTV Resupply Rack HTV Supply rack HREP (HICO) & Remote Atmospheric Hyperspectral Imager for the Coastal Ocean & Ionospheric Detection System (RAIDS) Experimental Payload (NASA)Hyperspectral image for the coastal waters of the apparatus and HSM atmosphereHarness Separation / ionosphere Mechanism Harness separation mechanism HTV H-IIremote Transfer detection Vehicle system HTV "stork" experimental apparatus HTV OCS HTV Operations Control System HTV Mission Control system i-Ball - Re-entry data collection device ICE Box ISS Cryogenic Experiment Storage Box JEM Transport for cold storage box ICS Inter-orbit Communication System "Hope" satellite communication system IMMT ISS Mission Management Team ISS Mission Management IMV Inter-Module Ventilation Inter-module ventilation ventilation IOS Inter-Orbit Link System Inter-Orbit Communication System I / O InputInter-satellite / Output Input and output communication device IOCU Input / Output Controller Unit Input and output control unit (HTV) (Alternatively)Satellite ICS Inter-orbitcommunication Communications system System Satellite communication system (JEM) ISPR International Standard Payload Rack International standard payload rack ISS International Space Station The International Space Station ITCS Internal Thermal Control System Internal heat control system (ISS) JAXA Japan Aerospace Exploration Agency Japan Aerospace Exploration Agency JEF JEM Exposed Facility "Hope" outboard experimental platform JEM Japanese Experiment Module Japanese Experiment Module "Kibo" JEMRMS JEM Remote Manipulator System "Hope" robot arm JPM JEM Pressurized Module "Hope" inboard laboratory JSC Johnson Space Center NASA Johnson Space Center J-SSOD JEM Small Satellite Orbital Deployer Small satellite release mechanism JST Japanese Standard Time Japan Standard Time KASPER Research equipment (HTV5) Space environment observation apparatus KOUNOTORI Advanced Space Environment KITE Kounotori Integrated Tether Experiment (HTV6) Conductive tether demonstration experiment KOS Keep Out Sphere Entry prohibited area (ISS Radius from 200m ) KOZ Keep Out Zone No entry zone LED Light Emitting Diode Light-emitting diode LGA Low Gain Antenna Low-gain antenna LP1 Launch Pad1 Large rocket launch site first One Launch Complex(Tanegashima ) LP2 Launch Pad2 Large rocket launch site first Two Launch Complex(Tanegashima )
appendix 3-3 "Stork" Unit 6 Press Kit (appendix)
Abbreviation English name Sum name LP-POM Large Plasma current probe and Potential Monitor (KITE)Electrostatic probe LRR Laserfunction Rader with Reflector a charge potential monitor Reflector (laser radar reflector)(HTV) MAXI Monitor of All-sky X-ray Image Monitor of All-sky X-ray equipment MBS Mobil Base System Mobil-based systems (ISS) MBSU Main Bus Switching Unit ISS Power system switching device MBU Main Bus Unit The main bus unit MCC Mission Control Center Mission Control Center (JSC) MCC-H MCC-Houston Mission Control Center HyusutoDown MCE Multi-mission Consolidated Equipment (JAXA)Port Sharing experimental apparatus MCU Mission control computer MET Mission Elapsed Time Mission elapsed time MGA Medium Gain Antenna Mid-gain antenna MHU Mouse Habitat Unit Small animal breeding device MLI Multi-Layer Insulation Multilayer insulation material MMH Monomethylhydrazine Monomethyl hydrazine (fuel) MON3 Mixed oxides of nitrogen contains 3% nitric oxideNitric oxide MPEP Multi-purposeaddition dinitrogen Experiment Platform Parent arm tip-mounted tetroxide (Oxidant) Experimental platform MSPR Multi-purpose Small Payload Rack (JAXA)Multi-purpose experiment rack MT Mobile Transporter Mobile transporter (dolly) MUSES Multi-User System for Earth Sensing nadir - nadir NASA National Aeronautics and Space Administration National Aeronautics and Space Administration NET No Earlier Than Later ~ NREP NanoRacks External Platform US nano-Lux's outboard Pratt followerOver-time OBS On-Board Software On-board software ORU Orbital Replacement Unit On-orbit replaceable unit OSE Orbital Support Equipment On-orbit support device PADLES in Space (JAXA) Passive Dosimeter for Lifescience Experiments Passive integrated type cosmic radiation doseTotal PAS Payload Attach System Payload mounting system P-ANT PROX Antenna Antenna for neighborhood communication system(HTV) P-BAT Primary Battery One Next battery (HTV) PBA Portable Breathing Apparatus Portable exchange respiratory PCBM Passive CBM Passive side common berthing mechanism PCS Portable Computer System Laptop computer PCU Plasma Contactor Unit Plasma contactor unit (ISS) PDB Power Distribution Box Distribution box
appendix 3-4 "Stork" Unit 6 Press Kit (appendix)
Abbreviation English name Sum name PFE Portable Fire Extinguisher (ISS Inside)Fire extinguisher PEV Pressure Equalization Valve Equalizing valve PIM Position Inspection Mechanism Position detection mechanism PIU Payload Interface Unit Equipment exchange mechanism PLC Pressurized Logistics Carrier Logistics Carrier pressurized section (HTV) PLS Proximity Link System Near the communication device (HTV) PM Phase Adjusting Maneuver Phase adjustment trajectory control (Maneuver) PM Pressurized Module Inboard laboratory of "hope" PM Propulsion Module Propulsion module (HTV) PMM Permanent Multipurpose Module Permanent multi-purpose module POA Payload and Orbital Replacement Unit Accommodation POCC Payload Operations/ orbit on the Control Center Payload Operations Center replacement unit POIC Payload Operations Integration Center Payload Operations Integration Center gripping device Port - The port side PROX Proximity Communication System Near the communication system (HTV) Psi Pounds per square inch Pressure unit PSL Permanent Solid-state Lighting LED illumination (HTV) PSRR Pressurized Stowage Resupply Rack "Hope" ELM-PS-mounted storage LaClick PS-TEPC Proportional Chamber Position Sensitive Tissue Equivalent Real-time monitoring of the cosmic radiationapparatus PVGF Power & Video Grapple Fixture Power and video Gras pull Fixture R-Bar - Aruba RCS Reaction Control System Attitude control system REBR Reentry Breakup Recorder Re-entry data collection device( RiceAerospace Shrine ) RGPS Relative Global Positioning System GPS Relative navigation RPCM Remote Power Controller Module Remote power control module RSP Resupply Stowage Platform (NASA) Supplies storage platformArm RVFS Rendezvous Flight Software HTV Rendezvous equipped with software RVS Rendezvous Sensor Rendezvous sensors (HTV) SAFER Simplified Aid for Self- rescue propulsion system during SARJ Solarspacewalk Array Rotary Joint Solar cell paddle rotation mechanism (ISS) S-BAT Secondary Battery Two The following battery (HTV) SCAM Sample Cartridge Automatic Exchange Mechanism (GHF)Sample automatic exchange mechanism
Testbed (NASA)Satellite communication laboratory equipment SCAN Testbed Space Communications and Navigation SDR Software Defined Radios Software-defined radio SEA Small Experiment Area (MSPR)Small-scale experiment area
appendix 3-5 "Stork" Unit 6 Press Kit (appendix)
Abbreviation English name Sum name SEDA-AP Space Environment Data Acquisition equipment-Attached Payload Space Environment Measurement Mission equipment
SFA Small Fine Arm Child architect of the robot arm of the "hope"Arm SFA2 Second Spacecraft and Fairing Assembly Building No. Two
Satellite fairing assemblySFINKS building (Tanegashima) Solar cell FIlm array sheet for Next generation on KOUNOTORI Six "Stork"Six Thin-film solar cell film array sheet module for Unit SIGI Space Integrated GPS / INS (Inertial Navigation System) For space equipped with the universe GPS / INS (GPS/Inertial navigation system ) SMILES Superconducting Submillimeter-Wave Limb-Emission Sounder Superconducting Submillimeter-Wave Limb-Emission Sounder
SPDM Special Purpose Dexterous Manipulator Special purpose robot arm "Dexter" SRB Solid Rocket Booster Solid rocket booster SRCA System on / off Remote Control Assembly Or Switch Remote Control Assembly (ISS Inside)Light switch
SSCC Space Station Control Center Space Station Control Center SSIPC Space Station Integration and Promotion Center Space Station Integration and Promotion Center (TKSC) SSM Shockless Separation Mechanism Low-impact separation mechanism (HTV) SSRMS Space Station Remote Manipulator System ISS Of the robot arm STBD starboard starboard STP-H Space Test Program-Houston (The United States of outboard experimental apparatus ) TCM Tether Cutting Mechanism (KITE)Tether cutting mechanism TDRS Tracking and Data Relay Satellite Tracking and data relay satellite (NASA) TRRJ Thermal Radiator Rotary Joint Heat dissipation radiator rotating mechanism TSM Tie-down Separation Mechanism Launch restraint separation mechanism TKSC Tsukuba Space Center Tsukuba Space Center TNSC Tanegashima Space Center Tanegashima Space Center TPF Two Phase Flow Boiling two-layer fluid loop equipment ULC Unpressurized Logistics Carrier ULC part ULF Utilization and Logistics Flight (shuttle)Use supply flight UPA Urine Processor Assembly Urine processor UTA Utility Transfer Assembly ISS Power system communication equipment VAB Vehicle Assembly Building Large rocket Assembly Building(Tanegashima ) VDC Volt Direct Current Power unit WB Work Bench (MSPR)Workbench WORF Window Observational Research Facility Observation research facilities to use the window WPA Water Processor Assembly Water treatment equipment WV Work Volume (MSPR)Work volume ZOE Zone of Exclusion Invisible area zenith - zenith
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