ISS Orbit and Ground Track Applicability for Earth Observation, Astrophysics and Heliophysics
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Correlation of the SAGE III on ISS Thermal Models in Thermal Desktop
47th International Conference on Environmental Systems ICES-2017-171 16-20 July 2017, Charleston, South Carolina Correlation of the SAGE III on ISS Thermal Models in Thermal Desktop Ruth M. Amundsen1, Warren T. Davis2, and Kaitlin A. K. Liles3 NASA Langley Research Center, Hampton, VA, 23681 and Shawn C. McLeod4 Analytical Mechanics Associates, Inc., Hampton, VA, 23666 The Stratospheric Aerosol and Gas Experiment III (SAGE III) instrument is the fifth in a series of instruments developed for monitoring aerosols and gaseous constituents in the stratosphere and troposphere. SAGE III was launched on February 19, 2017 and mounted to the International Space Station (ISS) to begin its three-year mission. A detailed thermal model of the SAGE III payload, which consists of multiple subsystems, has been developed in Thermal Desktop (TD). Correlation of the thermal model is important since the payload will be expected to survive a three-year mission on ISS under varying thermal environments. Three major thermal vacuum (TVAC) tests were completed during the development of the SAGE III Instrument Payload (IP); two subsystem-level tests and a payload-level test. Additionally, a characterization TVAC test was performed in order to verify performance of a system of heater plates that was designed to allow the IP to achieve the required temperatures during payload-level testing; model correlation was performed for this test configuration as well as those including the SAGE III flight hardware. This document presents the methods that were used to correlate the SAGE III models to TVAC at the subsystem and IP level, including the approach for modeling the parts of the payload in the thermal chamber, generating pre-test predictions, and making adjustments to the model to align predictions with temperatures observed during testing. -
Orbital Lifetime Predictions
Orbital LIFETIME PREDICTIONS An ASSESSMENT OF model-based BALLISTIC COEFfiCIENT ESTIMATIONS AND ADJUSTMENT FOR TEMPORAL DRAG co- EFfiCIENT VARIATIONS M.R. HaneVEER MSc Thesis Aerospace Engineering Orbital lifetime predictions An assessment of model-based ballistic coecient estimations and adjustment for temporal drag coecient variations by M.R. Haneveer to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Thursday June 1, 2017 at 14:00 PM. Student number: 4077334 Project duration: September 1, 2016 – June 1, 2017 Thesis committee: Dr. ir. E. N. Doornbos, TU Delft, supervisor Dr. ir. E. J. O. Schrama, TU Delft ir. K. J. Cowan MBA TU Delft An electronic version of this thesis is available at http://repository.tudelft.nl/. Summary Objects in Low Earth Orbit (LEO) experience low levels of drag due to the interaction with the outer layers of Earth’s atmosphere. The atmospheric drag reduces the velocity of the object, resulting in a gradual decrease in altitude. With each decayed kilometer the object enters denser portions of the atmosphere accelerating the orbit decay until eventually the object cannot sustain a stable orbit anymore and either crashes onto Earth’s surface or burns up in its atmosphere. The capability of predicting the time an object stays in orbit, whether that object is space junk or a satellite, allows for an estimate of its orbital lifetime - an estimate satellite op- erators work with to schedule science missions and commercial services, as well as use to prove compliance with international agreements stating no passively controlled object is to orbit in LEO longer than 25 years. -
Mission Design for the Lunar Reconnaissance Orbiter
AAS 07-057 Mission Design for the Lunar Reconnaissance Orbiter Mark Beckman Goddard Space Flight Center, Code 595 29th ANNUAL AAS GUIDANCE AND CONTROL CONFERENCE February 4-8, 2006 Sponsored by Breckenridge, Colorado Rocky Mountain Section AAS Publications Office, P.O. Box 28130 - San Diego, California 92198 AAS-07-057 MISSION DESIGN FOR THE LUNAR RECONNAISSANCE ORBITER † Mark Beckman The Lunar Reconnaissance Orbiter (LRO) will be the first mission under NASA’s Vision for Space Exploration. LRO will fly in a low 50 km mean altitude lunar polar orbit. LRO will utilize a direct minimum energy lunar transfer and have a launch window of three days every two weeks. The launch window is defined by lunar orbit beta angle at times of extreme lighting conditions. This paper will define the LRO launch window and the science and engineering constraints that drive it. After lunar orbit insertion, LRO will be placed into a commissioning orbit for up to 60 days. This commissioning orbit will be a low altitude quasi-frozen orbit that minimizes stationkeeping costs during commissioning phase. LRO will use a repeating stationkeeping cycle with a pair of maneuvers every lunar sidereal period. The stationkeeping algorithm will bound LRO altitude, maintain ground station contact during maneuvers, and equally distribute periselene between northern and southern hemispheres. Orbit determination for LRO will be at the 50 m level with updated lunar gravity models. This paper will address the quasi-frozen orbit design, stationkeeping algorithms and low lunar orbit determination. INTRODUCTION The Lunar Reconnaissance Orbiter (LRO) is the first of the Lunar Precursor Robotic Program’s (LPRP) missions to the moon. -
Mission Overview
CRS Orb-1 Mission Mission Overview Overview Under the Commercial Resupply Services (CRS) contract with NASA, Orbital will provide approximately 20 metric tons of cargo to the International Space Station over the course of eight missions. Orb-1 is the first of those missions. The Orb-1 mission builds on the successful Commercial Orbital Transportation Services (COTS) demonstration mission conducted from September 18 to October 23, 2013. The Orb-1 flight will carry substantially more cargo (1465 kg vs. 700 kg) than the COTS mission, including several time-sensitive payloads and Cygnus’ first powered payload, the Commercial Generic Bioprocessing Apparatus (CGBA) from Bioserve. Mission Overview, Cont. Antares® The configuration of the Antares launch vehicle for the Orb-1 Mission is much the same as the two previous Antares flights with a CASTOR 30B second stage motor instead of the CASTOR 30 used previously. The first stage includes a core that contains the tanks for the liquid oxygen and kerosene, the first stage avionics, and two AJ26 rocket engines. The second stage consists of the CASTOR® 30B solid rocket motor, an avionics section containing the flight computer and guidance/ navigation/control functions, an interstage that connects the solid rocket motor to the first stage, the Cygnus spacecraft, and a fairing that encloses and protects the Cygnus spacecraft during ascent. Continued on Next Page Mission Overview, Cont. Cygnus™ The Cygnus spacecraft is composed of two elements, the Service Module (SM) and the Pressurized Cargo Module (PCM). The SM provides the propulsion, power, guidance, navigation and control, and other “housekeeping” services for the duration of the mission. -
Cubesat-Services.Pdf
Space• Space Station Station Cubesat CubesatDeployment Services Deployment Services NanoRacks Cubesat Deployer (NRCSD) • 51.6 degree inclination, 385-400 KM • Orbit lifetime 8-12 months • Deployment typically 1-3 months after berthing • Soft stowage internal ride several times per year Photo credit: NASA NRCSD • Each NRCSD can deploy up to 6U of CubeSats • 8 NRCSD’s per airlock cycle, for a total of 48U deployment capability • ~2 Air Lock cycles per mission Photo Credit: NanoRacks LLC Photo credit: NASA 2. Launched by ISS visiting vehicle 3. NRCSDs installed by ISS Crew 5. Grapple by JRMS 4. JEM Air Lock depress & slide 6. NRCSDs positioned by JRMS table extension 1. NRCSDs transported in CTBs 7. Deploy 8. JRMS return NRCSD-MPEP stack to slide table; 9. ISS Crew un-install first 8 NRCSDs; repeat Slide table retracts and pressurizes JEM air lock install/deploy for second set of NRCSDs NanoRacks Cubesat Mission (NR-CM 3 ) • Orbital Sciences CRS-1 (Launched Jan. 9, 2014) • Planet Labs Flock1A, 28 Doves • Lithuanian Space Assoc., LitSat-1 • Vilnius University & NPO IEP, LituanicaSat-1 • Nanosatisfi, ArduSat-2 • Southern Stars, SkyCube • University of Peru, UAPSat-1 Photo credit: NASA Mission Highlights Most CubeSats launched Two countries attain in a single mission space-faring status World’s largest remote Kickstarter funding sensing constellation • NR-CM3 • Orbital Science CRS-1, Launch Jan 9, 2014 • Air Lock Cycle 1, Feb 11-15, 2014 Dove CubeSats • Deployers 1-8 (all Planet Labs Doves) Photo credit: NASA • NR-CM3 • Orbital Science CRS-1, -
10Th International Limb Workshop – Scientific Program Greifswald, June 3 – 7, 2019
10th International Limb Workshop – Scientific program Greifswald, June 3 – 7, 2019 Monday, June 3, 18:00: Icebreaker and Reception Restaurant Campo Alegre (Lange Reihe 1) Session 1: Tuesday, June 4, 08:30 – 10:30 (Chair: Christian von Savigny) Welcome 08:30 – 08:35 Welcome by local organizers (Christian von Savigny) 08:35 – 08:45 Welcome address by representative of the City of Greifswald (Jeanette von Busse) 08:45 – 08:55 Welcome address by University administration (Pro-rector Prof. Katharina Riedel) 08:55 – 09:05 Welcome address by Dr. Christian Suhm (Academic coordinator of Alfried Krupp Institute of Advanced Study) 09:05 – 09:15 Logistics (Christian von Savigny) New missions and mission concepts 09:15 – 09:45 Didier Fussen Forthcoming limb observations with ALTIUS (invited talk) 09:45 – 10:00 Nick Lloyd The Canadian Atmospheric Tomography System (CATS) – The Next Generation OSIRIS Instrument 10:00 – 10:15 Marilee Roell Stratospheric Aerosol and Gas Experiment (SAGE) III installed on the International Space Station (ISS): Mission overview and Science Data Product Validation 10:15 – 10:30 Matthew DeLand MASTAR: Limb Scattering Measurements of Stratospheric Aerosols 10:30 – 11:00 Coffee break 10th International Limb Workshop, June 4 – 7, 2019 Greifswald Session 2: Tuesday, June 4, 11:00 – 13:00 (Chair: Adam Bourassa) New missions and mission concepts 11:00 – 11:25 Christoph R. Englert MIGHTI (Michelson Interferometer for Global High-resolution Thermospheric Imaging): The Wind and Temperature Instrument Onboard the NASA Ionospheric Connection (ICON) Mission (invited talk) 11:25 – 11:50 Donal Murtagh MATS - a micro satellite for studies of Mesospheric Airglow /aerosol by Tomography and Spectroscopy (invited talk) 11:50 – 12:15 Kristell Pérot SIW: a New Satellite Mission to Explore Middle Atmospheric Wind Structure and Composition (invited talk) 12:15 – 12:30 John Burrows A new Concept SLIPSTREAM/SCIA-L2 12:30 – 12:45 William E. -
IAC-17-#### Page 1 of 6 IAC-17-### Crowdfunding for Space Missions
68th International Astronautical Congress (IAC), Adelaide, Australia, 25-29 September 2017. Copyright ©2017 by the International Astronautical Federation (IAF). All rights reserved. IAC-17-### Crowdfunding For Space Missions Graham Johnsona a Inmarsat Global Ltd. [email protected] Abstract Crowdfunding (via websites such as kickstarter.com) has become an increasingly popular method for funding projects and start-up companies for a wide range of terrestrial products and services. A small, but not insignificant number of space projects have also used this method of fundraising, and there is potentially much greater scope for this type of funding. This paper presents an analysis of crowd-funding campaigns that have been used to fund space- related projects, and in particular, spaceflight missions. It assesses the relative success of these campaigns and proposes some insights as to what makes a successful space crowdfunding campaign. Keywords: Crowdfunding, Space, Mission Acronyms/Abbreviations have attempted to use crowdfunding as either their CAT Cubesat Ambipolar Thruster principle source of funding, or as a stepping stone to ISS International Space Station further progress their project. Kickstarter appears to be LEO Low Earth Orbit the most popular platform for space mission funding, although there have also been a small number of space projects on IndieGoGo, Rockethub and Gofundme. 1. Introduction In this paper a summary of space mission ‘Crowdfunding’ is a process by which the creator of crowdfunding campaigns is presented, an assessment is a product or service can appeal directly to the public for made of the typical level of funding which individuals cash funding. It is important to note that the contribute, and the potential for scale-up to future space contributors, or ‘funders’, are not actually investing in projects is discussed. -
In This Issue
Vol. 39 No.3, December 2013 Editor: Jos Heyman FBIS In this issue: Satellite Update 3 Cancelled Projects: SLOMAR 4 News Artemis 2 Baikonour 3 Chang'e-3 6 Cygnus-2 3 Dnepr 1 9 Dreamchaser 6 DX-1 11 EDRS-C 2 FUEGO 6 GSat-15 3 GSat-16 3 Hylas 2 Made in Russia 7 Minotaur 1 7 O3b 6 OASIS 4 Phoenix 7 Planck 3 SkySat-1 and -2 2 Tiangong-4 11 Vega 7 VEX 3 OASIS Node-1 (courtesy Space Times) TIROS SPACE INFORMATION SkySat-1 and -2 86 Barnevelder Bend, Southern River WA 6110, Australia Tel + 61 8 9398 1322 (e-mail: [email protected]) The Tiros Space Information (TSI) - News Bulletin is published to promote the scientific exploration and commercial application of space through the dissemination of current news and historical facts. In doing so, Tiros Space Information continues the traditions of the Western Australian Branch of the Astronautical Society of Australia (1973-1975) and the Astronautical Society of Western Australia (ASWA) (1975-2006). The News Bulletin can be received worldwide by e-mail subscription only. Subscriptions can be requested by sending an e-mail address to [email protected]. Tiros Space Information reserves the right to refuse any subscription request without the need to provide a reason. All opinions expressed are those of the authors and do not necessarily reflect the opinions of the Editor or Tiros Space Information. All material contained in this publication may be reproduced provided due acknowledgment is made. Calling card... In a recent article that I drafted for the on-line Sat Magazine, I predicted that by the end of this calendar year a total of 192 satellites were to have been launched, the highest ever for a single year since spaceflight began in 1957. -
A Methodology for Cubesat Mission Selection Luis Zea, Victor Ayerdi, Sergio Argueta, and Antonio Muñoz Universidad Del Valle De Guatemala, Guatemala City, Guatemala
Zea, L. et al. (2016): JoSS, Vol. 5, No. 3, pp. 483–511 (Peer-reviewed article available at www.jossonline.com) www.DeepakPublishing.com www. JoSSonline.com A Methodology for CubeSat Mission Selection Luis Zea, Victor Ayerdi, Sergio Argueta, and Antonio Muñoz Universidad del Valle de Guatemala, Guatemala City, Guatemala Abstract Over 400 CubeSats have been launched during the first 13 years of existence of this 10 cm cube-per unit standard. The CubeSat’s flexibility to use commercial-off-the-shelf (COTS) parts and its standardization of in- terfaces have reduced the cost of developing and operating space systems. This is evident by satellite design projects where at least 95 universities and 18 developing countries have been involved. Although most of these initial projects had the sole mission of demonstrating that a space system could be developed and operated in- house, several others had scientific missions on their own. The selection of said mission is not a trivial process, however, as the cost and benefits of different options need to be carefully assessed. To conduct this analysis in a systematic and scholarly fashion, a methodology based on maximizing the benefits while considering program- matic risk and technical feasibility was developed for the current study. Several potential mission categories, which include remote sensing and space-based research, were analyzed for their technical requirements and fea- sibility to be implemented on CubeSats. The methodology helps compare potential missions based on their rele- vance, risk, required resources, and benefits. The use of this flexible methodology—as well as its inputs and outputs—is demonstrated through a case study. -
Mission Concept for a Satellite Mission to Test Special Relativity
Mission Concept for a Satellite Mission to Test Special Relativity VOLKAN ANADOL Space Engineering, masters level 2016 Luleå University of Technology Department of Computer Science, Electrical and Space Engineering LULEÅ UNIVERSITY of TECHNOLOGY Master Thesis SpaceMaster Mission Concept for a Satellite Mission to Test Special Relativity Supervisors: Author : Dr. Thilo Schuldt Volkan Anadol Dr. Norman Gürlebeck Examiner : Assoc. Prof. Thomas Kuhn September 29, 2016 Abstract In 1905 Albert Einstein developed the theory of Special Relativity. This theory describes the relation between space and time and revolutionized the understanding of the universe. While the concept is generally accepted new experimental setups are constantly being developed to challenge the theory, but so far no contradictions have been found. One of the postulates Einsteins theory of Relativity is based on states that the speed of light in vac- uum is the highest possible velocity. Furthermore, it is demanded that the speed of light is indepen- dent of any chosen frame of reference. If an experiment would find a contradiction of these demands, the theory as such would have to be revised. To challenge the constancy of the speed of light the so- called Kennedy Thorndike experiment has been developed. A possible setup to conduct a Kennedy Thorndike experiment consists of comparing two independent clocks. Likewise experiments have been executed in laboratory environments. Within the scope of this work, the orbital requirements for the first space-based Kennedy Thorndike experiment called BOOST will be investigated. BOOST consists of an iodine clock, which serves as a time reference, and an optical cavity, which serves as a length reference. -
Orbit Design Marcelo Suárez
Orbit Design Marcelo Suárez 6th Science Meeting; Seattle, WA, USA 19-21 July 2010 Orbit Design Requirements The following Science Requirements provided drivers for Orbit Design: ¾ Global Coverage: the entire extent (100%) of the ice-free ocean surface to at least ±80° latitude should be observed. ¾ Swath shall be at least 300 km with gaps between the footprints within a swath not exceeding 50 km on average. ¾ Temporal Coverage: In order to provide monthly accurate salinity measurements, grid point should be visited at least 8 times per month (counting both ascending and descending passes) ¾ Radiometer Geometry: Zenith angle of the Sun on the footprint should be greater than 90° (in shadow) to the extent possible. ¾ Instruments should operate in the 600 +100/-50 km altitude range. ¾ Orbit shall have a repeat pattern of less than or equal to 9 days maintained within ± 20 km Orbit Design - Suárez 2of 12 6th Science Meeting; Seattle, WA, USA 19-21 July 2010 Orbit Design The Aquarius/SAC-D Mission Orbit is defined by the following parameters and tolerances: • Mean Semi-major axis: 7028.871 km +/- 1.5 km • Mean Eccentricity: 0.0012 +/− 0.0001 • Mean Inclination: 98.0126 deg + / - 0.001 degrees • Mean Local Mean Time of Ascending Node: 18:00 0 /+5 min • Mean Argument of perigee: 90 deg +/- 5 deg Remarks : Equatorial altitude: 657 km +/- 1.5 km Ground-track Repeat: 7 days Ground-track Separation at Equator: 389 km Ground-track kept within +/- 20 km of nominal along equator Sun-Synchronous Orbit Orbit Design - Suárez 3of 12 6th Science Meeting; Seattle, WA, USA 19-21 July 2010 Leap-frog sampling pattern 389 Km 2724 Km 4 Day 0-7 5 1 2 6 Day 0-7 3 4of 12 19-21 July 2010 Orbit Design - Suárez Seattle, WA, USA 6th Science Meeting; Eclipses Because of the changing position of the Sun with respect to the orbital plane there are yearly Eclipse seasons which take place between May and August at southern latitudes. -
NASA Earth Science Division Overview
NASA Earth Science Division Overview: Michael H. Freilich October, 2017 OUTLINE • ESD overview and Non-Flight summary • Budget Status • Flight Program including Venture Class • Innovation including Small-Sat Constellation • Satellite Needs Working Group results 2 3 NASA’s Earth Science Division Research Flight Applied Sciences Technology 4 NASA Earth Science Division Elements Flight (incl. Data Systems) Research & Analysis Develops, launches, and operates Supports integrative research that NASA’s fleet of Earth-observing advances knowledge of the Earth as a satellites, instruments, and aircraft. system, and capabilities to conduct Manages data systems to make data research. Six focus areas plus field and information products freely and campaigns, modeling, and scientific openly available. computing. Technology Applied Sciences Tests and demonstrates scientific Develops, tests, and supports technologies for future satellite and innovative and uses of Earth airborne missions: observations and scientific Instruments, Information Systems, knowledge by private and public Components, InSpace Validation sectors to inform their planning, (cubesats). decisions, and actions. 5 Earth Science Research Focus Areas Carbon cycle and Ecosystems Climate Variability and Change Atmospheric Composition Global Water and Energy Cycle Earth Surface and Interior Weather >2,100 current awards (valued at $384M) to Centers, other agencies, private entities, universities, etc. >1,100 ($144M) of these are grants/coop. agreements issued through HQ Grants Office 6 HLS: Harmonized Landsat/Sentinel-2 Products https://hls.gsfc.nasa.gov Laramie County, WY May 4, 2016 August 8 August 17 September 1 October 20 3km 0.1 NDVI 0.9 Seasonal High temporal Sentinel-2 phenology: density of obs. + Landsat-8 allows Alfalfa Natural individual Grassland mowing (blue line) events to NDVI Irrigated be detected Alfalfa Grassland within alfalfa (red line) mowing fields.