Document 44-3
The Council for Science and
Technology Research Planning
and Evaluation Subcommittee space development and utilization Group
( The 44 Times) H30.11.29
H3 The development status of the rocket
Heisei 30 (2018) Year 11 Moon 29 Japan
Aerospace Exploration Agency
Director Yasuhiro Funo H3 Project team Tadashi Okada Today's your report
• The 40 Times space development and utilization Group ( 2018 Year 1 Moon twenty four In the day), " H3 About migrating "to the detailed design results and fabrication and testing phase of the rocket comprehensive system, I was pleased to report.
• This time, we will explain the progress status of the subsequent development.
1. Progress of production and test phase
2. Implementation of the development test
3. The development status of the ground facilities
Four. Considerations for future development
Five. Future plans
1 1. Progress of production and test phase
• To complete the detailed design in the last year the overall system level, compatible with the conclusion to the mission requirements.
• Sun-synchronous orbit (altitude 500km ) To launch capability: Four Ton or more ( H3-30S )
• MHI Standard launch price, which is calculated by the gluteal 【note 1 ] : about 50 Billion yen ( H3-30S )
【note 1 ] Airframe price of production is in a stable steady-state operation phase and under certain conditions
• The satellite forecast, the mass of the geostationary orbit satellites 2.5 ~ 6.5t In has been widely distributed, H3 It can cope with rocket launch capacity range (The 40 Times space development and utilization Group ( 2018 Year 1 Moon twenty four Sun) article 40-2-1 More excerpt)
• Then, multiplied by the appropriate feedback to the design from the development test, Maintain a design with the latest state .
• on the other hand, International launch market The demand by such all-electric satellite and small constellation satellite Diversification By is willing to have a flexible and quick response H3 Improve competitiveness, not loosened the rocket ' But
essential.
• H3-32 Highly competitive in the form H3-22 Integration in the form (next page)
• 2 Introduction into the plurality orbit by multiple ignition stages engine, such as a plurality satellite adapter Development of Under consideration
• testing machine For, from the long ones of such procurement period Already embarked on some production . 2 H3-22 Form and H3-32 Form integration of
• Geostationary transfer orbit ( GTO Launch capability to) ton
H3-32 Launch Satellite mass ( ) capability of
(By such means as
an adjustment to the input orbit ) H3-22 In 6 2017 Maximum launch H3-22 Launch possible cover)
capability of Five Company B 2015, ΔV = 1500m / s It tends to peak of tons has slowed. ( 6
※ 22 and 32 It is the ability Four fairing size GTO capability to) Tons 3
L in the case of Company B , 3
The expected 2015 Each mass-band satellite demand forecast (research
launch capability Company data, B 2 Company A Of year firm: 2017 ※
H3-30S H3-22L H3-32L H3-24L Machine number
H3-22 Form of launch capability is higher than expected, H3-32 Form of demand can be covered by adjustment of input trajectories ( next page ), And thereby for
advantages production plan is simplified is large, H3-22 It is integrated into the form.
[Note] aircraft identification name H3-abc a : LE-9 Radix ( 2, 3 ) b : SRB-3 The number of ( 0, 2, 4 ) c : Fairing size ( S, L ) 3 Response by adjustment of the closing trajectory Example
• I turned on the track in the past geostationary satellite missions ( GTO ) Is accelerated amount of satellite side necessary staticization ( ΔV
)But 1500m / s 【note 1 ] Be become orbit was the world's de facto standard.
• In recent years, even in the case of large satellite that could not launch in the above-mentioned track, without changing the form of a
rocket, The introduction orbit customers and the flexibility to adjust 【note 2 ] Tendency to, increase hitting a large satellite performs the burden of the speed increasing amount of satellite side But worldwide progress.
【note 1 It was converted to the launch from the equator
7000 Adjust the altitude and orbital inclination, Required to quiescence ΔV The 6500 1500m / s More satellite side is 6000 borne. kg) 5500 So far the world
5000 standard of
4500 Recently, in response to satellite mass, the form of rocket without changing turned
4000 orbit (satellite side ΔV ) Adjusted trend to launch and progress of the Satellite mass during launch ( 3500 Falcon 9 3000
2500 1400 1500 1600 1700 1800 1900 2000 2100 2200 2300
Satellite side needed to quiescence ΔV (m / s) Four Development Plan
• 2020 Testing machine to the year 1 The launch schedule Unit. testing machine 2 After evaluation launch Unit, the development will be completed.
• The total development costs; about 1,900 Billion yen 2012 2013 2014 2015 2016 2017 2018 2019 2020 2021 2022 △ PQR ▲ ▲ Milestone △ MDR △ SDR △ PDR △ CDR testing machinetesting machine 1 Unit 2 Unit
Conceptual Study Conceptual design Basic design detailed design Maintenance design
System design and test Electrical systems test 【note 1 ] ▽ the ground comprehensive test
BFT CFT
Actual production 1 Actual production Actual production 2
Engine propulsion system development
LE-X Technology Demonstration design elements test and design Production Actual type-certification type test 1 Stage / 2 Stage engine
Flight for manufacturing and AT test
Test equipment repair Facility design Equipment work MDR : Mission definition examination SDR : System definition review PDR : Basic design review
CDR : Critical Design Review Structural system / electrical system development Element test and design Production Certification test PQR : Development completed examination AT : Acceptance testing
BFT : Thick-walled tank stage combustion test (combination
test of simulated tank and the engine) Solid booster development Element test, design and sub-size test Actual large combustion test Production CFT : Actual tanks stage combustion test (combination actual exam flight considerable tank and engine)
Ground equipment development Conception, research and basic Detailed design Production and site work and coordination test
【note 1 ] BFT for LE-9 It reflects the readiness of the engine, BFT Review of the implementation period Five 2. Implementation of the development test
• The following tests were carried out. ① first 1 Stage engine ( LE-9 Actual engine # to verify the functionality and performance of) 2 Combustion
test: completion ( P7 )
② first 1 Stage thick-walled tank stage combustion test ( BFT )for LE-9 Engine combustion test ( 2 formula)
• Each 150 Conducted a combustion test of the order of seconds, complete the confirmation of the functions and performance
• The 1 Stage BFT Complete the installation of the test equipment ③ SRB-3 Actual large combustion
test (for the Engineering Test "actual type motor"): Completed ( P8 )
④ electrical systems test: Ongoing
• Also, it is preparing towards the following test. ⑤ first 1 Stage thick-walled
tank stage combustion test ( BFT ) ( P10 )
⑥ second 2 Stage engine ( LE-5B-3 ) Certified engine # 2 Combustion test (for the final certification) [ 11 Moon Ten Start from the day]
⑦ LE-9 Actual engine # 1-2 Combustion test
• Actual engine # 1 To renovate, verification plans the following towards the certified type design
• Design reflects by the data obtained in the tests so far
3D An example of the molding • Aimed at the drastic cost reduction 3D modeling process Wide range of applications of process ( LE-9 Injector elements) 6 ① LE-9 Actual engine # 2 The results of the combustion test
• 2 Expression of the actual type engine (# 1 , # 2 ) A prototype, carried out combustion test.
• So far, Target thrust ( 150 Ton) , The actual flight and the equivalent of burning time (about 270 Sec.) The achievement.
• The total burn time, 19 Kai about 1,640 Sec. # 2 In the engine, Demonstration request time of certification type engine (Flight 2 Double + combustion test and the like of the time: 8 Kai 1,078 Achieved in seconds) as a system.
• While continuing to get a variety of data in the combustion test, Reflected in the final design plans.
300 Cumulative Actual engine # 2 1,800
seconds at the time of the test in seconds 1,600 250 1,400
200 1,200
1,000 150
During the test in seconds (s) Actual engine # 1 When the cumulative second (s) 100 800
600 50 400
0 0 200 1 3 5 7 9 11 13 15 17 19
Number of tests In the combustion LE-9 engine 7 ③ SRB-3 The results of actual large ground firing test
• the purpose
• SRB-3 Actual large ground firing test of, Total 3 Times plan It is (actual motor: 1 Times, certification type motor 2 Times. Epsilon rocket first 1 Also serves as a development stage. Both carried out at the Tanegashima Space Center).
• In this test, For the Engineering Test "actual type motor." Using, Acquired the characteristics and performance data of the ignition and combustion, etc. And, contribute to the design. In the combustion SRB-3
• result
• Planned Achieve the test purpose did. Basic performance are as follows.
item Predicted value result
Maximum thrust 2,106kN 2,137kN
Maximum combustion pressure 10.8MPa 10.7MPa
All combustion time 110.6s 110.1s
• Based on the evaluation results of the test data, Considering reflect matters to the design of the certification type motor .
Actual type motor 8 [Reference] solid rocket booster ( SRB-3 ) basic specifications
Forward Breath item SRB-A ( H-IIA ) SRB-3 ( H3 ) ( 2 Book) Solid propellant Composite propellant Composite propellant
Vacuum thrust about 180ton f about 220tonf
Performance ( Isp ) 283.6s 283.6s that's all
Solid propellant amount 65.9ton about 66.8ton Thrust strut Forward separation thruster ( 2 Book) ( 1 Book) full length 15.2m 14.6m
diameter φ 2.5m φ 2.5m
Combustion time 116s about 105s
Nozzle driving system electric actuator None (nozzle fixed) The thrust pin ( 1 Book) Thrust strut separation Separation system Separation thruster system motor system Separation
motor ( 2 Pieces)
Behind Breath ( 2 Behind the separation thruster • Major development items Book) ( 2 Book) • Simplification of the bonding and separation system (reduction of bond points and pyrotechnics)
• Motor case other, low cost / weight of the respective components
• H3 Establishment of effective promotion characteristics in common epsilon SRB-A ( H-IIA ) SRB-3 ( H3 )
9 ⑤ first 1 Stage thick-walled tank stage combustion test ( BFT ) Readiness
• the purpose
• Such as the curvature and the mounting height of the propellant tank bottom And the thick-walled tank which simulates the actual LE-9 engine( 2 Thick oxygen tank Group and 3 Combining group), a combustion test By performing, The 1 Stage liquid acquires the function and performance data as propulsion system, oxygen tank
contributes to the design.
• Preliminary conditions The 1 Stage liquid Thick hydrogen tank hydrogen tank • By Mitsubishi Heavy Industries Tashiro test site, complete the installation of the renovation and the thick tank engine of the test equipment. In carrying out the installation work of the other components. Engine part
• LE-9 engine( 2 Expression) is, through the combustion test in Tanegashima, attached complete. LE-9 engine
• As soon as the preparation is complete, Scheduled to begin from the test this year .
Rearview
It is attached to the combustion Combustion test stand test stand LE-9 engine Mitsubishi Heavy Industries, Ltd. provides Ten 3. The development status of the ground facilities
• Facilities-based combination study to be performed prior to the ground comprehensive test ( 2019 Toward the year ~), in developing each of the facilities.
Takezaki Launch Control Building
Moving the launch pad of the production situation (factory) Yoshinobu district (next page) • The installation in the regulated area outside to allow the personnel movement in regulations, minimizing operational scale
• After the production of the factory, it plans to migrate to the set standing in Tanegashima • Mobile launch pad: 2018 Year 11 Mon - Production situation of the transport vehicle (factory) Takezaki district • Transport vehicles: 2019 Year 1 Mon -
11 [Reference] Cum point system facilities and equipment
Red frame: new steel blue Launch Control Building Maintenance Assembly Building frame: renovation / diversion • Established in Takezaki district • Existing VAB2 Renovate
Mobile launcher ( ML) • newly made Mobile launcher truck • newly made
VAB1 : Pause Storage and supply system equipment ( LH 2 ) Storage and supply system equipment ( LOX ) • Existing diversion • Existing diversion
Hydrogen gas treatment plants Storage and supply system equipment (gas system) • Existing diversion • HGS Existing diversion
Wastewater treatment facility • Capacity expansion Multi-purpose lightning tower • Existing diversion
The 2 Firing point ( LP2 ) • Existing LP2 Renovate
Support machine building air conditioning equipment Cooling water supply facilities LP1 : Pause • Enhancing some air-conditioning capacity • ML From LP2 Relocation part in 12 Four. Considerations for future development
• Preparation for certification test specimen and tester
• In order to suppress the hand return by the design change, Fine-grained gate management Introduced (each part of the production start judgment).
• Testing machine launch schedule
• It is shown in the Space Basic Plan H-IIA Launch work When H3 Ground integration test / tester launch work And Challenges associated with the parallel implementation (Manufacturing, propellant, human resources) embodying the, The overall plan for the corresponding The stand draft
schedule.
13 [Reference] noted in the development in the efforts to continue point
The 36 Times Space Industry, Science & Technology Infrastructure Committee documents 1-2 More reused
• Project goals and the overall plan
• Corresponding to the ongoing research and analysis of the international launch market trends
• All Electrical satellite Due to the trends Changes in the satellite mass distribution
• Become necessary in the future Corresponding to a variety of orbit Ya Equipped with multiple satellite For the Development of Considered as such
• testing machine 1 Unit and 2 Determination of the Unit of the fuselage form
• Flight demonstration content in accordance with the fuselage form When Corresponding to each mission Integrity, etc. of both sides of
• Implementation of the safety review process towards a significant time-to-launch from order
• In earnest Market Entry For Business Environment Improvement
• Key issues such as
• Variety Development progress management of the sub-system components over, feedback and risk management
• Engine combustion test , Electrical system test In such Reliable design verification And if necessary Rapid design change
• Timely and appropriate reflection of the system based on the obtained performance data
• Thorough risk management associated with these
• Further ensure the development schedule margin
• At the time of firing point standing of the rocket fuselage before the propellant filling, it occurs under certain conditions Aircraft swing To cope with 14 Five. Future plans
• 2018 Year: in the production and test phase, implementation plans the following future
(1) Subsystem creates design and drawings include components such as toward production of specimens for Engineering Test (continued)
(2) Design and manufacture of ground equipment
(3) Of the specimen for engineering test preparation and test ① LE-5B-3 Certified type engine
combustion test [ 11 Moon Ten Start from day] ② LE-9 Actual engine combustion test ③ 1 Stage
thick-walled tank stage combustion test ④ electrical systems test ⑤ 2 Stage actual type tank
stage combustion test preparation, etc.
• 2019 Year: continue the implementation timetable in production and test phase, the following
(1) Subsystem based on the results of the technical tests, the maintenance of design including components like
(2) Manufacture and testing of ground equipment
(3) Manufacture and testing of the testing machine
(Four) Of the specimen for engineering test preparation and test ① LE-9 Certified
type engine combustion test ② 1 Stage thick-walled tank stage
combustion test (continued) ③ 2 Stage actual type tank stage
combustion test ④ SRB-3 Actual large combustion test (continued)
etc 15 The 28 Times space development and utilization Group ( 2016 Year 6 Moon 14 Sun)
H3 System Overview of rocket article 28-3-1 More excerpt (partially modified depending on the development progress)
• full length: about 63m • Core rocket diameter: about 5.2m • Solid rocket booster diameter: about 2.5m • Service to customers
• Mounting environmental conditions: More than the world standard • Duration of the order-to-launch: More than the world standard
fairing
Improved 2 Stage engine ( LE-5B-3 ) Thrust 14 Ton X 1 Basis
mechanism large satellite
Improved solid rocket booster ( SRB-3 ) Average thrust 220 Ton X 0,2,4 Book
Simple decoupling
New style 1 Stage engine ( LE-9 ) Thrust 150
Ton X 2 Groups / 3 Based on switching
【note 1 ] 500km Circular orbit [Note 2 ] Steady-state 202 204 Sun-synchronous orbit 【note 1 ] Four Or more tons Geostationary transfer orbit operational phase and constant About aim 50 Billion yen 【n It aims to more than 6.5ton (cover Aircraft price of under conditions ote 2 ] It aims to the majority of satellite demand in H-IIA H-IIB ( H2A About half) of a single launch) 16