NASA's Space Launch System: Opportunities for Small Satellites To
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NASA’s Space Launch System: Deep-Space Delivery for Smallsats Dr. Kimberly F. Robinson1 and George Norris2 NASA Marshall Space Flight Center, Huntsville, AL, 35812 ABSTRACT Designed for human exploration missions into deep space, NASA’s Space Launch System (SLS) represents a new spaceflight infrastructure asset, enabling a wide variety of unique utilization opportunities. While primarily focused on launching the large systems needed for crewed spaceflight beyond Earth orbit, SLS also offers a game-changing capability for the deployment of small satellites to deep-space destinations, beginning with its first flight. Currently, SLS is making rapid progress toward readiness for its first launch in two years, using the initial configuration of the vehicle, which is capable of delivering 70 metric tons (t) to Low Earth Orbit (LEO). On its first flight test of the Orion spacecraft around the moon, accompanying Orion on SLS will be small-satellite secondary payloads, which will deploy in cislunar space. The deployment berths are sized for “6U” CubeSats, and on EM-1 the spacecraft will be deployed into cislunar space following Orion separate from the SLS Interim Cryogenic Propulsion Stage. Payloads in 6U class will be limited to 14 kg maximum mass. Secondary payloads on EM-1 will be launched in the Orion Stage Adapter (OSA). Payload dispensers will be mounted on specially designed brackets, each attached to the interior wall of the OSA. For the EM-1 mission, a total of fourteen brackets will be installed, allowing for thirteen payload locations. The final location will be used for mounting an avionics unit, which will include a battery and sequencer for executing the mission deployment sequence. -
New Moon Explorer Mission Concept
New Moon Explorer Mission Concept Les JOHNSONa,*, John CARRa,Jared Jared DERVANa, Alexander FEWa, Andy HEATONa, Benjamin Malphrusd, Leslie MCNUTTa, Joe NUTHb, Dana Tursec, and Aaron Zuchermand aNASA MSFC, Huntsville, AL USA bNASA GSFC, Huntsville, AL USA cRoccor, Longmont, CO USA dMorehead State University, Morehead, KY USA Abstract New Moon Explorer (NME) is a smallsat reconnaissance mission concept to explore Earth’s ‘New Moon’, the recently discovered Earth orbital companion asteroid 469219 Kamoʻoalewa (formerly 2016HO3), using solar sail propulsion. NME would determine Kamoʻoalewa’s spin rate, pole position, shape, structure, mass, density, chemical composition, temperature, thermal inertia, regolith characteristics, and spectral type using onboard instrumentation. If flown, NME would demonstrate multiple enabling technologies, including solar sail propulsion, large-area thin film power generation, and small spacecraft technology tailored for interplanetary space missions. Leveraging the solar sail technology and mission expertise developed by NASA for the Near Earth Asteroid (NEA) Scout mission, affordably learning more about our newest near neighbor is now a possibility. The mission is not yet planned for flight. Keywords: Kamoʻoalewa, solar sail, moon, Apollo asteroid 1. Introduction The emerging capabilities of extremely small spacecraft, coupled with solar sail propulsion, offers an opportunity for low-cost reconnaissance of the recently- discovered asteroid 469219 Kamoʻoalewa (formerly 2016HO3). While Kamoʻoalewa is not strictly a new moon, it is, for all practical purposes, an orbital companion of the Earth as the planet circles the sun. Kamoʻoalewa’s orbit relative to the Earth can be seen in Figure 1. Using the technologies developed for the NASA Fig. 1 The orbit of Earth’s companion, Kamoʻoalewa Near Earth Asteroid (NEA) Scout mission, a 6U as both it and the Earth orbit the Sun. -
The Cubesat Mission to Study Solar Particles (Cusp) Walt Downing IEEE Life Senior Member Aerospace and Electronic Systems Society President (2020-2021)
The CubeSat Mission to Study Solar Particles (CuSP) Walt Downing IEEE Life Senior Member Aerospace and Electronic Systems Society President (2020-2021) Acknowledgements – National Aeronautics and Space Administration (NASA) and CuSP Principal Investigator, Dr. Mihir Desai, Southwest Research Institute (SwRI) Feature Articles in SYSTEMS Magazine Three-part special series on Artemis I CubeSats - April 2019 (CuSP, IceCube, ArgoMoon, EQUULEUS/OMOTENASHI, & DSN) ▸ - September 2019 (CisLunar Explorers, OMOTENASHI & Iris Transponder) - March 2020 (BioSentinnel, Near-Earth Asteroid Scout, EQUULEUS, Lunar Flashlight, Lunar Polar Hydrogen Mapper, & Δ-Differential One-Way Range) Available in the AESS Resource Center https://resourcecenter.aess.ieee.org/ ▸Free for AESS members ▸ What are CubeSats? A class of small research spacecraft Built to standard dimensions (Units or “U”) ▸ - 1U = 10 cm x 10 cm x 11 cm (Roughly “cube-shaped”) ▸ - Modular: 1U, 2U, 3U, 6U or 12U in size - Weigh less than 1.33 kg per U NASA's CubeSats are dispensed from a deployer such as a Poly-Picosatellite Orbital Deployer (P-POD) ▸NASA’s CubeSat Launch initiative (CSLI) provides opportunities for small satellite payloads to fly on rockets ▸planned for upcoming launches. These CubeSats are flown as secondary payloads on previously planned missions. https://www.nasa.gov/directorates/heo/home/CubeSats_initiative What is CuSP? NASA Science Mission Directorate sponsored Heliospheric Science Mission selected in June 2015 to be launched on Artemis I. ▸ https://www.nasa.gov/feature/goddard/2016/heliophys ics-cubesat-to-launch-on-nasa-s-sls Support space weather research by determining proton radiation levels during solar energetic particle events and identifying suprathermal properties that could help ▸ predict geomagnetic storms. -
Lunar Flashlight & NEA Scout
National Aeronautics and Space Administration Lunar Flashlight & NEA Scout A NanoSat Architecture for Deep Space Exploration Payam Banazadeh (JPL/Caltech) Andreas Frick (JPL/Caltech) EM-1 Secondary Payload Selection • 19 NASA center-led concepts were evaluated and 3 were down-selected for further refinement by AES toward a Mission Concept Review (MCR) planned for August 2014 • Primary selection criteria: - Relevance to Space Exploration Strategic Knowledge Gaps (SKGs) - Life cycle cost - Synergistic use of previously demonstrated technologies - Optimal use of available civil servant workforce Payload Strategic Knowledge Gaps Mission Concept NASA Centers Addressed BioSentinel Human health/performance in high- Study radiation-induced DNA ARC/JSC radiation space environments damage of live organisms in cis- • Fundamental effects on biological systems lunar space; correlate with of ionizing radiation in space environments measurements on ISS and Earth Lunar Flashlight Lunar resource potential Locate ice deposits in the Moon’s JPL/MSFC/MHS • Quantity and distribution of water and other permanently shadowed craters volatiles in lunar cold traps Near Earth Asteroid (NEA) NEA Characterization Slow flyby/rendezvous and Scout • NEA size, rotation state (rate/pole position) characterize one NEA in a way MSFC/JPL How to work on and interact with NEA that is relevant to human surface exploration • NEA surface mechanical properties 2 EM-1: Near Earth Asteroid (NEA) Scout concept WHY NEA Scout? – Characterize a NEA with an imager to address key Strategic -
Solar Sail Propulsion for Deep Space Exploration
Solar Sail Propulsion for Deep Space Exploration Les Johnson NASA George C. Marshall Space Flight Center NASA Image We tend to think of space as being big and empty… NASA Image Space Is NOT Empty. We can use the environments of space to our advantage NASA Image Solar Sails Derive Propulsion By Reflecting Photons Solar sails use photon “pressure” or force on thin, lightweight, reflective sheets to produce thrust. 4 NASA Image Real Solar Sails Are Not “Ideal” Billowed Quadrant Diffuse Reflection 4 Thrust Vector Components 4 Solar Sail Trajectory Control Solar Radiation Pressure allows inward or outward Spiral Original orbit Sail Force Force Sail Shrinking orbit Expanding orbit Solar Sails Experience VERY Small Forces NASA Image 8 Solar Sail Missions Flown Image courtesy of Univ. Surrey NASA Image Image courtesy of JAXA Image courtesy of The Planetary Society NanoSail-D (2010) IKAROS (2010) LightSail-1 & 2 CanX-7 (2016) InflateSail (2017) NASA JAXA (2015/2019) Canada EU/Univ. of Surrey The Planetary Society Earth Orbit Interplanetary Earth Orbit Earth Orbit Deployment Only Full Flight Earth Orbit Deployment Only Deployment Only Deployment / Flight 3U CubeSat 315 kg Smallsat 3U CubeSat 3U CubeSat 10 m2 196 m2 3U CubeSat <10 m2 10 m2 32 m2 9 Planned Solar Sail Missions NASA Image NASA Image NASA Image Near Earth Asteroid Scout Advanced Composite Solar Solar Cruiser (2025) NASA (2021) NASA Sail System (TBD) NASA Interplanetary Interplanetary Earth Orbit Full Flight Full Flight Full Flight 100 kg spacecraft 6U CubeSat 12U CubeSat 1653 m2 86 -
Space Launch System (Sls) Motors
Propulsion Products Catalog SPACE LAUNCH SYSTEM (SLS) MOTORS For NASA’s Space Launch System (SLS), Northrop Grumman manufactures the five-segment SLS heavy- lift boosters, the booster separation motors (BSM), and the Launch Abort System’s (LAS) launch abort motor and attitude control motor. The SLS five-segment booster is the largest solid rocket motor ever built for flight. The SLS booster shares some design heritage with flight-proven four-segment space shuttle reusable solid rocket motors (RSRM), but generates 20 percent greater average thrust and 24 percent greater total impulse. While space shuttle RSRM production has ended, sustained booster production for SLS helps provide cost savings and access to reliable material sources. Designed to push the spent RSRMs safely away from the space shuttle, Northrop Grumman BSMs were rigorously qualified for human space flight and successfully used on the last fifteen space shuttle missions. These same motors are a critical part of NASA’s SLS. Four BSMs are installed in the forward frustum of each five-segment booster and four are installed in the aft skirt, for a total of 16 BSMs per launch. The launch abort motor is an integral part of NASA’s LAS. The LAS is designed to safely pull the Orion crew module away from the SLS launch vehicle in the event of an emergency on the launch pad or during ascent. Northrop Grumman is on contract to Lockheed Martin to build the abort motor and attitude control motor—Lockheed is the prime contractor for building the Orion Multi-Purpose Crew Vehicle designed for use on NASA’s SLS. -
Lunar Programs
LUNAR PROGRAMS NASA is leading a sustainable return to the Moon Aerospace is partnered with NASA to with commercial and international partners to return humans to the Moon in every expand human presence in space and gather phase and journey, including the: new knowledge and opportunities. In 2017, Space › Planning and supporting the Policy Directive-1 called for a renewed emphasis on first lifecycle review of the commercial and international partnerships, return Gateway Initiative of humans to the Moon for long-term exploration and utilization followed by human missions to Mars. › Design, systems engineering and Aerospace is partnered with NASA in this endeavor integration, and operational concepts and is involved in every phase and journey. of the EVA system Artist’s conception of a gateway habitat. Image credit: NASA Humans must return to the moon for long-term › Ground testing of the NEXTStep deep exploration and utilization of deep space, but lunar space habitat module prototypes exploration is more than a stepping stone to Mars missions. The phased plan includes › Design and test of the Orion sending missions to the moon and cislunar space for exploration and study, and the capsule avionics construction of the Deep Space Gateway, a space station intended to orbit the moon. Aerospace provides support to these missions in areas such as systems engineering and integration, program management, and various subsystem expertise. Current Lunar Programs GATEWAY INITIATIVE NASA’s Gateway is conceived to be an exploration and science outpost in orbit around the moon that will enable human crewed missions to both cislunar space and the moon’s surface, meet scientific discovery and exploration objectives, and demonstrate and prove enabling technologies through commercial and international partnerships. -
Paper Session IA-Shuttle-C Heavy-Lift Vehicle of the 90'S
The Space Congress® Proceedings 1989 (26th) Space - The New Generation Apr 25th, 2:00 PM Paper Session I-A - Shuttle-C Heavy-Lift Vehicle of the 90's Robert G. Eudy Manager, Shuttle-C Task Team, Marshall Space Flight Center Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Eudy, Robert G., "Paper Session I-A - Shuttle-C Heavy-Lift Vehicle of the 90's" (1989). The Space Congress® Proceedings. 5. https://commons.erau.edu/space-congress-proceedings/proceedings-1989-26th/april-25-1989/5 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. SHUTTLE-C HEAVY-LIFT VEHICLE OF THE 90 ' S Mr. Robert G. Eudy, Manager Shuttle-C Task Team Marshall Space Flight Center ABSTRACT United States current and planned space activities identify the need for increased payload capacity and unmanned flight to complement the existing Shuttle. To meet this challenge the National Aeronautics and Space Administration is defining an unmanned cargo version of the Shuttle that can give the nation early heavy-lift capability. Called Shuttle-C, this unmanned vehicle is a natural, low-cost evolution of the current Space Shuttle that can be flying 100,000 to 170,000 pound payloads by late 1994. At the core of Shuttle-C design philosophy is the principle of evolvement from the United State's Space Transportation System. -
View / Download
www.arianespace.com www.starsem.com www.avio Arianespace’s eighth launch of 2021 with the fifth Soyuz of the year will place its satellite passengers into low Earth orbit. The launcher will be carrying a total payload of approximately 5 518 kg. The launch will be performed from Baikonur, in Kazakhstan. MISSION DESCRIPTION 2 ONEWEB SATELLITES 3 Liftoff is planned on at exactly: SOYUZ LAUNCHER 4 06:23 p.m. Washington, D.C. time, 10:23 p.m. Universal time (UTC), LAUNCH CAMPAIGN 4 00:23 a.m. Paris time, FLIGHT SEQUENCES 5 01:23 a.m. Moscow time, 03:23 a.m. Baikonur Cosmodrome. STAKEHOLDERS OF A LAUNCH 6 The nominal duration of the mission (from liftoff to separation of the satellites) is: 3 hours and 45 minutes. Satellites: OneWeb satellite #255 to #288 Customer: OneWeb • Altitude at separation: 450 km Cyrielle BOUJU • Inclination: 84.7degrees [email protected] +33 (0)6 32 65 97 48 RUAG Space AB (Linköping, Sweden) is the prime contractor in charge of development and production of the dispenser system used on Flight ST34. It will carry the satellites during their flight to low Earth orbit and then release them into space. The dedicated dispenser is designed to Flight ST34, the 29th commercial mission from the Baikonur Cosmodrome in Kazakhstan performed by accommodate up to 36 spacecraft per launch, allowing Arianespace and its Starsem affiliate, will put 34 of OneWeb’s satellites bringing the total fleet to 288 satellites Arianespace to timely deliver the lion’s share of the initial into a near-polar orbit at an altitude of 450 kilometers. -
Lunar Life Sciences Payload Assessment
Lunar Surface Science Workshop 2020 (LPI Contrib. No. 2241) 5077.pdf LUNAR LIFE SCIENCES PAYLOAD ASSESSMENT. S. C. Sun1, F. Karouia2, M. P. Lera3, M. P. Parra1, H. E. Ray4, A. J. Ricco1, S. M. Spremo1. 1NASA Ames Research Center, 2Blue Marble Space Institute of Science, 3KBR, 4ASRC Federal Space and Defense, Inc. Introduction: The Moon provides a unique site to ISS, including systems that integrate into EXPRESS study living organisms. The fractional gravity and (EXpedite the PRocessing of ExperimentS for Space) unique radiation environment have similarities to Mars Racks or are external space exposure research facilities. and will help us understand how life will respond to These same systems can be the basis for future payload conditions on the red planet. Martian and lunar envi- systems for experiments to be performed beyond Low ronments can be simulated on the ground but not to high Earth Orbit. Such facilities would need to be adapted to fidelity. Altered gravity and increased radiation are dif- be compatible with the new research platforms and ficult to replicate simultaneously, which makes study- function in the harsher radiation environment found out- ing their combined effect difficult. The International side the magnetosphere. If Gateway and a lunar based- Space Station, and previously, the Space Shuttle, pro- lab could provide EXPRESS-compatible interfaces, lev- vided a microgravity environment, and could simulate eraging hardware developed for ISS would be more fea- fractional-g only via an onboard centrifuge. Because sible. the ISS and Space Shuttle orbits were within the Earth’s Gaps in Capabilities: Many of the payload systems magnetosphere, experiments on those platforms have that have been developed require human tending. -
Developing Technologies for Biological Experiments in Deep Space
Developing technologies for biological experiments in deep space Sergio R. Santa Maria Elizabeth Hawkins Ada Kanapskyte NASA Ames Research Center [email protected] NASA’s life science programs STS-1 (1981) STS-135 (2011) 1973 – 1974 1981 - 2011 2000 – 2006 – Space Shuttle International Skylab Bio CubeSats Program Space Station Microgravity effects - Nausea / vomit - Disorientation & sleep loss - Body fluid redistribution - Muscle & bone loss - Cardiovascular deconditioning - Increase pathogenicity in microbes Interplanetary space radiation What type of radiation are we going to encounter beyond low Earth orbit (LEO)? Galactic Cosmic Rays (GCRs): - Interplanetary, continuous, modulated by the 11-year solar cycle - High-energy protons and highly charged, energetic heavy particles (Fe-56, C-12) - Not effectively shielded; can break up into lighter, more penetrating pieces Challenges: biology effects poorly understood (but most hazardous) Interplanetary space radiation Solar Particle Events (SPEs) - Interplanetary, sporadic, transient (several min to days) - High proton fluxes (low and medium energy) - Largest doses occur during maximum solar activity Challenges: unpredictable; large doses in a short time Space radiation effects Space radiation is the # 1 risk to astronaut health on extended space exploration missions beyond the Earth’s magnetosphere • Immune system suppression, learning and memory impairment have been observed in animal models exposed to mission-relevant doses (Kennedy et al. 2011; Britten et al. 2012) • Low doses of space radiation are causative of an increased incidence and early appearance of cataracts in astronauts (Cuccinota et al. 2001) • Cardiovascular disease mortality rate among Apollo lunar astronauts is 4-5-fold higher than in non-flight and LEO astronauts (Delp et al. -
Atlas V Cutaway Poster
ATLAS V Since 2002, Atlas V rockets have delivered vital national security, science and exploration, and commercial missions for customers across the globe including the U.S. Air Force, the National Reconnaissance Oice and NASA. 225 ft The spacecraft is encapsulated in either a 5-m (17.8-ft) or a 4-m (13.8-ft) diameter payload fairing (PLF). The 4-m-diameter PLF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction with vertical split-line longerons. The Atlas V 400 series oers three payload fairing options: the large (LPF, shown at left), the extended (EPF) and the extra extended (XPF). The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur upper stage and the spacecraft, which separates using a debris-free pyrotechnic actuating 200 ft system. Payload clearance and vehicle structural stability are enhanced by the all-aluminum forward load reactor (FLR), which centers the PLF around the Centaur upper stage and shares payload shear loading. The Atlas V 500 series oers 1 three payload fairing options: the short (shown at left), medium 18 and long. 1 1 The Centaur upper stage is 3.1 m (10 ft) in diameter and 12.7 m (41.6 ft) long. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle. It uses a single RL10 engine producing 99.2 kN (22,300 lbf) of thrust.