DOCSLIB.ORG

The CU-E3 Communication Subsystem

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
The CU-E3 Communication Subsystem A Deep Space Radio Communications Link for Cubesats: 3 The CU-E Communication Subsystem John S. Sobtzak, Elie G.Tianang, Varun Joshi, Breana M. Branham, Neeti P. Sonth, Michael DeLuca, Travis Moyer, Kyle Wislinsky, and Dr. Scott E. Palo College of Engineering & Applied Science, University of Colorado at Boulder The Challenge! The CU-E3 Solution Key Notes 3 CU's Earth Escape Explorer (CU-E ) Rx_C-Band_Patch 3 Gain dBi The University of Colorado's - Earth Escape Explorer (CU-E ) Rx_LNA Rx_PCB Rx_UHF is a 6U cubesat being designed and built to compete in Pasternack Astronautical NASA's Cube Quest Challenge - Deep Space Derby. PE15A1010 Rx_Mixer Development NF dB Lithium - 2 CU-E3 will be attempting communication from ≥ 4,000,000 Mini-Circuits Rx_IF_BPF Gain dB SIM-73L+ km, requiring us to “escape” the influence of the “Earth” and Lark Engineering “explore” deep space. Rx_COAX_1 Rx_COAX_2 Rx_COAX_3 Rx_COAX_4 RF = 5210 MHz I IF = 450 MHz R L NASA’s Cube Quest Challenge LO = 4770 MHz o The Cube Quest Challenge has two phases: Rx_VCO_Amp † Analog Devics 1. Ground Tournaments (GT-1 thru GT-4) : C-BAND UPLINK HMC3587 XB1 CDH Rx_UHF - Maximum of $100,000 for any one team. RS422 - Phase completed in June 2017. 5182 MHz 2. The "In-space Prizes": Rx_OCXO Taitien - 365-day competition period. XO-0087_TT a) Lunar Derby Rx_PLL_VCO LF 100 MHz Reflectarray & Horn Antennas Analog Devices • Up to $3 million in prizes. 3 HMC833LP6GE PLL o CU-E utilizes a novel, student-designed, reflectarray • Technical objectives in propulsion & – MHz XB1 CDH Rx_PLL_VCO XB1 antenna and feed horn. communications. SPI CDH/FSW • Planar design → fits 6U cubesat form factor. b) Deep Space Derby • Utilizes standard PCB microstrip technology. • Up to $1.5 million in prizes. ADCS → easy and relatively inexpensive to fabricate. • Focus on deep space communications Tx_Reflect_Array • High gain → 22.3 dB at X-band Tx frequency. using small spacecraft. Gain = 22.3 dBi Tx_Hybrid_1 • Competition starts at 4,000,000 km: Anaren EPS X-BAND DOWNLINK o 3 Tx_COAX_5 1E0018-3 CU-E ’s design includes a second feed horn antenna. i. Best Burst Data Rate - $250,000 RL dB IL dB ii. Largest Aggregate Data - $750,000 EIRP IL dB 8447.6 MHz • Provides back-up communication link in the event iii. Spacecraft Longevity - $250,000 +56.6 dBm Tx_COAX_3 primary reflectarray antenna does not deploy. XB1 CDH Tx_HRCCS_FPGA iv. Farthest Communication - $250,000 +34.5 dBm IL dB Tx_PA_PCB • Lower gain → 12.8 dB, but can still close link. RS422 3 nd Tx_SW † CU-E placed 2 during the Ground Tournament phase, Tx_COAX_6 Tx_PA Dow-Key Microwave Tx_PA_VR IL dB Analog Devices High-Rate CubeSat Communication System earning $80,000, and has been offered a position on the 401T-420832 Linear Technologies HMC7357LP5GE ‡ SLS’s EM-1 mission!!! RL dB LT8610AC Tx_HRCCS_PCB (HRCCS) P1dB dBm IL dB η A HRCCS 3 PAE o CU-E will provide the maiden launch for the HRCCS. CU/NASA/LASP 3 Challenges Faced by CU-E Tx_COAX_2 Bias 8.9 V Voltage • Designed for deep space X-band frequencies. IL dB Controller Regulator • Provides a flexible communications platform. o Size – restricted to 6U dimensions. +35.1 dBm Processor/ FPGA • Limits power generation and heat dissipation. 8.0 V Vgg • Compatible with NASA’s NEN & DSN. • Limits transmitter power. Tx_Feed_Horn LO • Limits use of classic high-gain antennas. Tx_COAX_1 Gain = 12.8 dBi Tx_Hybrid_2 I Downlink Budget Analysis Summary → Limits possible radiated signal strength (EIRP)! R L TX ANTENNA Reflect Feed Reflect Feed Reflect Feed Anaren - o 1E0018-3 Array Horn Array Horn Array Horn Limited time & money! Tx_COAX_7 +35.5 dBm RF = 8447.6 MHz SLANT RANGE km 4,000,000 6,000,000 27,000,000 RL dB Quad • GTs’ schedule very short & tight. IL dB TRANSMITTED EIRP dBm 56.6 47.1 56.6 47.1 56.6 47.1 EIRP IL dB Modulator • Rad-hardened parts too expensive. TOTAL SIGNAL POWER @ OUTPUT OF LNB (S) dBm -82.4 -91.9 -85.9 -95.4 -99.0 -108.5 NOISE POWER DENSITY OF RX @ OUTPUT OF LNB (No) +47.1 dBm dBm/Hz -123.0 -123.0 -123.0 -123.0 -123.0 -123.0 → Could not design everything from scratch. +34.5 dBm Tx_COAX_4 NOISE POWER OF RX (N) dBm -94.3 -103.8 -97.9 -107.4 -111.0 -112.2 → Use COTS components as much as possible. IL dB USEFUL BIT RATE bits/s 608 68 270 30 13 1 → Prototype circuits quickly for P.O.C & testing. ENERGY PER BIT (Eb) W/bit -110.3 -110.2 -110.3 -110.2 -110.1 -108.5 Tx_COAX_8 Received SNR (@ OUTPUT OF LNB) dB 11.9 11.9 11.9 12.0 12.0 3.7 o Distance – extremely long range. IL dB Resulting Eb/No dB 12.7 12.7 12.7 12.8 12.8 14.5 Link Margin dB 6.10 6.12 6.11 6.15 6.22 7.86 → EVERY dB COUNTS!!! ‡Palo, S.E., “High Rate Communications for CubeSats”, Proc. of the IEEE International Microwave Symposium, Phoenix, AZ, 2015. SSC17-P1-07 ‡ Palo, S.E., D. O’Connor, E. DeVito, R. Kohnert, G. Crum and S. Altunc, “Expanding CubeSat Capabilities with a Low Cost Transceiver”, Proc. of the AIAA Small Satellite Conference, Logan, UT, 2014. .
Load more

Recommended publications
  • 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.
    [Show full text]
  • Cornell University
    Advanced CubeSat Technologies for Affordable Deep Space Science and Exploration Missions Ground Tournaments, the Moon, and Beyond Jim Cockrell Cube Quest Challenge Administrator iCubeSat - 30 May 2017 • What is Cube Quest? – Why a Cube Quest? – Rules and Prize Structure • Today’s Status Get your CubeSat to the moon, work the best – GT4 Competitors survive the longest win big prizes! – Emerging Technologies • Next Steps – GT4 winners – In-space Competition 30 May 2017 CubeQuest Challenge - iCubeSat 2 • SmallSats/CubeSats > conventional spacecraft – easier to launch – lower in cost • Unique missions with ensembles – planetary seismographs – array of Mars weather stations – distributed, correlated measurements – redundancy at the system level; robust system of systems – nodes for antenna arrays or telescope arrays – Augments traditional probes 30 May 2017 CubeQuest Challenge - iCubeSat 3 To-date, CubeSats don’t venture beyond LEO: Limitation SoA Deep Space Missions Need Limited comm range Low-gain dipoles or patches high gain directional antennas mainly used needed Limited comm data Low power, amateur band High-power, high frequency, wide rate transmitters mainly used bandwidth transmitters needed Lacking radiation COTS, low-cost parts used; more Radiation shielding, fault detection, tolerance benign environment of LEO fault tolerance Lacking in-space Not demonstrated (except solar High thrust, high ISP needed; propulsion sails); chemical fuel/pressurized chemical, electrical, solar containers prohibited Depend on Earth- Passive magnetorquers
    [Show full text]
  • List of Private Spaceflight Companies - Wikipedia
    6/18/2020 List of private spaceflight companies - Wikipedia List of private spaceflight companies This page is a list of non-governmental (privately owned) entities that currently offer—or are planning to offer—equipment and services geared towards spaceflight, both robotic and human. List of abbreviations used in this article Contents Commercial astronauts LEO: Low Earth orbit GTO: Geostationary transfer Manufacturers of space vehicles orbit Cargo transport vehicles VTOL: Vertical take-off and Crew transport vehicles landing Orbital SSTO: Single-stage-to-orbit Suborbital TSTO: Two-stage-to-orbit Launch vehicle manufacturers SSTSO: Single-stage-to-sub- Landers, rovers and orbiters orbit Research craft and tech demonstrators Propulsion manufacturers Satellite launchers Space-based economy Space manufacturing Space mining Space stations Space settlement Spacecraft component developers and manufacturers Spaceliner companies See also References External links Commercial astronauts Association of Spaceflight Professionals[1][2] — Astronaut training, applied research and development, payload testing and integration, mission planning and operations support (Christopher Altman, Soyeon Yi)[1][3] Manufacturers of space vehicles Cargo transport vehicles Dry Launch Return Company Launch Length Payload Diameter Generated Automated Spacecraft mass mass Payload (kg) payload S name system (m) volume (m3) (m) power (W) docking (kg) (kg) (kg) 10.0 (pressurized), 3,310 plus 14 2,500 Falcon 9 pressurized or (unpressurized), Dragon 6.1 4,200[4] 10,200 capsule
    [Show full text]
  • Space Launch System Program March 1, 2018
    https://ntrs.nasa.gov/search.jsp?R=20180003498 2019-08-31T15:55:45+00:00Z National Aeronautics and Space Administration 5 . 4 . 3 .SPACE . 2 . 1 . LAUNCH SYSTEM CubeSats - To The Moon & Beyond Scott Spearing CubeSat Subject Matter Expert Space Launch System Program March 1, 2018 www.nasa.gov/sls www.nasa.gov/sls SLS BLOCK 1 EXPLORATION MISSION-1 (EM-1) Forward Ring Launch Abort System Secondary Payloads Electrical Panels Cabling Orion Avionics Box (2 places) Interim Cryogenic Propulsion Stage Launch Vehicle Stage Adapter OSA Diaphragm Core Stage Secondary Payload Brackets (13) Boosters Isogrid Barrel Panels Access Cover Aft Ring (2 places) Orion Stage Adapter (OSA) www.nasa.gov/sls 0418 EM-1 OSA SECONDARY PAYLOAD ACCOMMODATIONS Secondary Payload Avionics Box Cabling 6U CubeSat Payload 6U CubeSat Secondary Payload Dispenser Brackets (13) (PSC) Secondary Payload Mounting Bracket LEGEND: SLS Provided PD Provided www.nasa.gov/sls 0418 EM-1 SYSTEM DESCRIPTION AND PURPOSE Expand and fully utilize the SLS capabilities for exploration purposes without causing harm or inconvenience to SLS or its primary payload. • Thirteen (max capability 17) 6U payload locations • 6U volume/mass is the current standard OSA (14 kg payload mass) Diaphragm • Payloads will be “powered off” from turnover through Orion separation and ~Ø156” (13’) payload deployment • Payload Deployment System Avionics Unit; payload deployment will begin with pre-loaded OSA ~21° sequence following Orion separation and ~22° ICPS disposal burn • Payload requirements captured in Interface
    [Show full text]
  • National Center for Atmospheric Research 2018 Annual Report
    2018 NCAR Annual Report National Center for Atmospheric Research 2018 Annual Report 2018 NCAR ANNUAL REPORT TABLE OF CONTENTS 2018 NCAR Annual Report A Message from the Interim NCAR Director New Approach to Geoengineering Simulations is Significant Step Forward North American storm Clusters Could Produce 80 Percent More Rain US Gains in Air Quality are Slowing Down Scientists Fly into the Heart of Smoke Plume The Climate Secrets of Southern Clouds New Model Reveals Origins of the Sun's Seasons NCAR-Based Climate Model Gets a Significant Upgrade The Entire Atmosphere in a Single Model Groundbreaking Data Set Gives Unprecedented Look at Future Weather New Climate Forecasts for Watershed - and the Water Sector NCAR 2018 Metrics & Publications A MESSAGE FROM THE INTERIM NCAR DIRECTOR The National Center for Atmospheric Research (NCAR) is one of the world’s premier scientific institutions. With a strong focus on the atmospheric and related sciences we have an internationally recognized staff and research program dedicated to advancing knowledge, providing community- based resources, and building human capacity. In this Annual Report, and in the accompanying Laboratory Reports, I invite you to learn more about NCAR, see how we are collaborating internally and with the worldwide research community to drive advances in our understanding of fundamental processes in our atmosphere and how the atmosphere interacts with, and is influenced by, other components of the Sun-Earth system. This progress is being driven, in part, by new technologies and their effective utilization at NCAR, including: advanced observing facilities for field studies and the Sun, powerful high-performance computing capabilities, valuable research data sets that describe the state of the Sun- Earth system, and widely used state-of-the-science community models that are providing improved capabilities for predictions of weather (including catastrophic events), air quality, hydrology, climate variability and change, and space weather.
    [Show full text]
  • From Ground Tournaments to Lunar and Deep Space Derby
    NASA’s CubeQuest Challenge – From Ground Tournaments to Lunar and Deep Space Derby Liz Hyde1 Millennium Engineering and Integration, Moffett Field, CA, 94035 and Jim Cockrell2 NASA Ames Research Center, Moffett Field, CA, 94035 The First Flight of NASA’s Space Launch System will feature 13 CubeSats that will launch into cis-lunar space. Three of these CubeSats are winners of the CubeQuest Challenge, part of NASA’s Space Technology Mission Directorate (STMD) Centennial Challenge Program. In order to qualify for launch on EM-1, the winning teams needed to win a series of Ground Tournaments, periodically held since 2015. The final Ground Tournament, GT-4, was held in May 2017, and resulted in the Top 3 selection for the EM-1 launch opportunity. The Challenge now proceeds to the in-space Derbies, where teams must build and test their spacecraft before launch on EM-1. Once in space, they will compete for a variety of Communications and Propulsion-based challenges. This is the first Centennial Challenge to compete in space and is a springboard for future in-space Challenges. In addition, the technologies gained from this challenge will also propel development of deep space CubeSats. Nomenclature ARC = Ames Research Center BCT = Blue Canyon Technologies CDR = Critical Design Review ConOps = Concept of Operations COTS = Commercial Off-The-Shelf CU-E3 = University of Colorado Earth Escape Explorer DSN = Deep Space Network EDU = Engineering Development Unit EM-1 = Exploration Mission 1 GRC = Glenn Research Center GT = Ground Tournament Isp = Specific Impulse LEO = Low-Earth Orbit MCR = Mission Concept Review mN = milinewtons MSFC = Marshall Space Flight Center PDR = Preliminary Design Review RACP = Resilient Affordable CubeSat Processor SAR = System Acceptance Review SDR = Software Defined Radio SLS = Space Launch System SRR = System Requirements Review 1 Mechanical Engineer, MEI, MS 213-6, Moffett Field, CA, AIAA Member.
    [Show full text]
  • Cobham Overview
    Advances in European Processor Technology Cobham Gaisler AB ESCCON 12 March 2019 ESTEC/ESA, Noordwijk, The Netherlands In October 2018, the MASCOT lander touched down on the Ryugu asteroid after hitching a ride with the Japanese Hayabusa 2 probe. MASCOT successfully completed its mission 325 million kilometers away from Earth! Cobham developed the MASCOT onboard computer based on their GR712RC processor. In year 2020, NASA’s Exploration Mission 1 to the Moon will carry 13 CubeSats of which 8 use LEON3FT SPARC processor technology either as IP cores, EEE components, or both, all supplied by Cobham: • CubeSat for Solar Particles (CuSP): GR712RC & LEON3FT IP • Near-Earth Asteroid Scout: GR712RC & LEON3FT IP • Lunar Flashlight: GR712RC & LEON3FT IP • BioSentinel: UT669 & LEON3FT IP • ArgoMoon: GR712RC • Lunar IceCube: LEON3FT IP • Earth Escape Explorer (CU-E3): LEON3FT IP • Lunar Polar Hydrogen Mapper (LunaH-Map): LEON3FT IP GR712RC - Dual-Core LEON3FT Processor An ongoing success story • Why choose GR712RC? • Flight proven technology • Highly integrated system on-chip solution • Low power solution • Simple package for assembly • Several single board computer designs • Selected by several ESA and NASA missions • Forward and backward compatible architecture • GR712RC value add • Radiation-hardened by design • A multi-core solution developed for space • Multiple SpaceWire interfaces with RMAP • Mil-Std-1553, SPI, CAN, I2C, Ethernet • CCSDS Telemetry and Telecommand on-chip • Outstanding floating-point performance - times two • Engage second
    [Show full text]
  • Attitude Control for the Lumio Cubesat in Deep Space
    70th International Astronautical Congress, Washington D.C., United States, 21-25 October 2019. Copyright 2019 by the authors. Published by the IAF, with permission and released to the IAF to publish in all forms. IAC-19,C1,6,4,x50894 ATTITUDE CONTROL FOR THE LUMIO CUBESAT IN DEEP SPACE A.´ Romero-Calvo,1 J. D. Biggs, 1 F. Topputo1 The Lunar Meteoroid Impact Observer(LUMIO) is a 12U CubeSat designed to observe, quantify, and characterize the impact of meteoroids on the lunar surface. The combination of a highly demanding Concept of Operations(ConOps) and the characteristics of the deep-space environment determine the configuration of the spacecraft. This paper presents the preliminary Attitude Determination and Control System(ADCS) design of LUMIO, the reaction wheels desaturation strategy and Moon tracking control laws. The proposed solution is shown to (a) prevent the saturation of the reaction wheels, (b) minimize propellant consumption, (c) minimize the parasitic ∆V , (d) keep the pointing angle below a certain limit, and e) maximize power generation. Although no attempt is made to optimize the control parameters, the most efficient alternative in terms of propellant consumption is identified. The proposed LUMIO design could lay the foundations for a standardized minimum mass and volume ADCS system for CubeSats operating in deep-space. Nomenclature ~ns Unit vector normal to surface A Actual DCM matrix Ω Aperture angle of a regular tetrahedron Hadamard’s product Ad Desired DCM matrix P Solar constant Ae Error DCM matrix R Reaction wheels
    [Show full text]
  • NASA's Space Launch System: Opportunities for Small Satellites To
    SSC18-IX-02 NASA’s Space Launch System: Opportunities for Small Satellites to Deep Space Destinations Dr. Kimberly F. Robinson, Scott F. Spearing, David Hitt NASA’s Space Launch System Program Spacecraft Payload Integration and Evolution Office Mailstop XP50, Marshall Space Flight Center, AL 35812; 256-544-5182 [email protected] ABSTRACT The first flight of NASA’s new exploration-class launch vehicle, the Space Launch System (SLS), will test a myriad of systems designed to enable the next generation of deep space human spaceflight, while also providing the rare opportunity for 13 6U CubeSat-class payloads to be deployed in several locations along the flight path. The first mission of SLS and NASA’s new Orion crew vehicle, Exploration Mission-1 (EM-1), will launch from upgraded facilities at Kennedy Space Center no earlier than fiscal year 2020. The initial Block 1 configuration for EM-1 will be capable of lofting at least 26 metric tons (t) of payload to the moon, with propulsion supplied by twin five- segment solid rocket boosters, four RS-25 engines and an Interim Cryogenic Propulsion Stage (ICPS). SLS will send Orion into a distant retrograde lunar orbit, paving the way for future missions to cislunar space and eventually Mars. The multidisciplinary small satellites for EM-1 derive from NASA research, as well as from international partners, industry and academia. Research subjects for the various smallsats include the moon, sun and an asteroid. Science objectives vary from characterizing the effects of radiation on living organisms (yeast) to landing the smallest spacecraft yet on the moon to supporting space weather research.
    [Show full text]
  • Attitude Determination and Control
    Attitude Determination and Control Dan Hegel Director, Advanced Development [email protected] 1 Dan Hegel - Intro • Director of Advanced Development at Blue Canyon Technologies • Advanced mission concepts and new technology • Business development • Helped start Blue Canyon Technologies as ADCS and simulation lead • Over 30 years’ experience in ADCS • Chief architect of the XACT cubesat attitude control system • Star tracker primary developer • Primary developer of high-fidelity simulation and flight software auto-code system • Prior companies include: Ball Aerospace, Motorola, and Lockheed • Held lead GNC role, or had significant involvement, in over 15 spacecraft programs, including: Hubble Space Telescope, Gravity Probe-B, Iridium, QuikSCAT, SUOMI NPP, and the QuickBird and WorldView imaging spacecraft • Education: • Bachelor’s in Aerospace Engineering from Arizona State University • Master’s in Aeronautics and Astronautics from Stanford University. 2 Agenda • Quick BCT overview • Basic attitude control loop • Sensors • Actuators • Control compensator • Orbit determination and propagation • Momentum Control 3 BCT Overview • Founded in 2008 • Experienced team of space industry veterans • Agile small satellites: • Spacecraft • Cubesats (3U, 6U, 12U) • Microsats to ~200kg • Components • Star Trackers • Reaction Wheels • RF Communication • Staff & Facility: • 100+ people • 45,000 square feet 4 Nano Star Trackers • The Blue Canyon Technologies Nano Star Tracker is a reliable, high performance design, compatible with a variety of SmallSat
    [Show full text]
  • Preparation of Papers for AIAA Journals
    https://ntrs.nasa.gov/search.jsp?R=20180006396 2019-08-31T18:37:39+00:00Z NASA’s Space Launch System: Exceptional Opportunities for Secondary Payloads to Deep Space Dr. Kimberly F. Robinson,1 Andrew A. Schorr2, and David Hitt3. Marshall Space Flight Center, Huntsville, AL, 35812, USA When NASA’s Space Launch System (SLS) launches for the first time from Kennedy Space Center, it will send the Orion crew vehicle farther into space than a human-rated spacecraft has ever traveled. The primary objectives of this first uncrewed mission, Exploration Mission- 1 (EM-1), focus on verifying and validating the new technologies and integrated systems developed for SLS, Orion and Exploration Ground Systems (EGS), which together comprise NASA’s new deep space exploration system. EM-1 also provides the opportunity for 13 6U CubeSat secondary payloads to be deployed in deep space. As progress is being made toward that first launch, planning is also taking place for secondary payload opportunities on future missions. This paper will provide an overview of the status of the SLS Block 1 launch vehicle and an overview of the 6U payloads selected for EM-1. In addition, an overview of the EM-1 mission trajectories and the “bus stops” along the trajectory where the payloads will be deployed will be noted. Challenges and new workflows required in identifying and certifying potential payloads will be discussed. The paper will also discuss opportunities that will be presented by future evolutions of SLS. I. Introduction When NASA’s Space Launch System rocket makes its maiden flight, it will propel an uncrewed Orion spacecraft on a trajectory toward the Moon on a mission that will mark a major step in an exploration program that will include a human-tended deep-space outpost, a return of astronauts to the lunar surface, and ultimately crewed missions to Mars.
    [Show full text]
  • Progress and Challenges with Interplanetary Small Satellite Missions
    Progress and Challenges with Interplanetary Small Satellite Missions ^ NASA Cost and Schedule Symposium 2021 April 28th, 2021 Michael Saing, TeamX Lead Cost Engineer, Deputy Systems Engineer Alex Austin, TeamXc Lead Engineer © 2021 Jet Propulsion Laboratory/California Institute of Technology The research was carried out at the Jet Propulsion Laboratory, California Institute of Technology, under a contract with the National Aeronautics and Space Administration. Disclaimer - The cost information contained in this document is of a budgetary and planning nature and is intended for informational purposes only. It does not constitute a commitment on the part of JPL and/or Caltech. Agenda • Motivation and Objective • History and Background of NASA’s Small Sat Mission • NASA’s Interplanetary Mission • Past, Present and Future • Challenges: – Technology – Implementation – Operations – Costs – Access to Space • Comparisons and findings – Show some funding/cost growth • How NASA can help to address challenges and keep cost from growing, or provide provide sufficient • Summary • References • Caveats • Closing 2 jpl.nasa.gov Motivation and Objective • Informational presentation on small sat interplanetary mission challenges • Understand what’s going on in today’s cost and schedule related to these upcoming missions 3 jpl.nasa.gov NASA Cubesat Small Sat Fleet ~20 Interplanetary missions 4 jpl.nasa.gov What do you mean by “Interplanetary” • Interplanetary means traveling between planets. And focus area for interplanetary is between sun and asteroid belt *Interplanetary Space* Deep Space Interstellar Space and beyond 5 jpl.nasa.gov What is a CubeSat? Small Sat? • CubeSat = nanosatellite in a form of a cube, with each “U” measuring 10cm x 10cm x 10cm and weighs ~1.33kg (weight by ROT) • The “U” cube are stackable • SmallSat mass ranging from 15 kg to ~350 kg (Standard definitions varies depending on who you ask) • Common form factors are: 1U, 3U, 6U’s.
    [Show full text]