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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 -
Pocketqube Standard Issue 1 7Th of June, 2018
The PocketQube Standard Issue 1 7th of June, 2018 The PocketQube Standard June 7, 2018 Contributors: Organization Name Authors Reviewers TU Delft S. Radu S. Radu TU Delft M.S. Uludag M.S. Uludag TU Delft S. Speretta S. Speretta TU Delft J. Bouwmeester J. Bouwmeester TU Delft - A. Menicucci TU Delft - A. Cervone Alba Orbital A. Dunn A. Dunn Alba Orbital T. Walkinshaw T. Walkinshaw Gauss Srl P.L. Kaled Da Cas P.L. Kaled Da Cas Gauss Srl C. Cappelletti C. Cappelletti Gauss Srl - F. Graziani Important Note(s): The latest version of the PocketQube Standard shall be the official version. 2 The PocketQube Standard June 7, 2018 Contents 1. Introduction ............................................................................................................................................................... 4 1.1 Purpose .............................................................................................................................................................. 4 2. PocketQube Specification ......................................................................................................................................... 4 1.2 General requirements ....................................................................................................................................... 5 2.2 Mechanical Requirements ................................................................................................................................. 5 2.2.1 Exterior dimensions .................................................................................................................................. -
Ground-Based Demonstration of Cubesat Robotic Assembly
Ground-based Demonstration of CubeSat Robotic Assembly CubeSat Development Workshop 2020 Ezinne Uzo-Okoro, Mary Dahl, Emily Kiley, Christian Haughwout, Kerri Cahoy 1 Motivation: In-Space Small Satellite Assembly Why not build in space? GEO MEO LEO The standardization of electromechanical CubeSat components for compatibility with CubeSat robotic assembly is a key gap 2 Goal: On-Demand On-Orbit Assembled CubeSats LEO Mission Key Phases ➢ Ground Phase: Functional electro/mechanical prototype ➢ ISS Phase: Development and launch of ISS flight unit locker, with CubeSat propulsion option ➢ Free-Flyer Phase: Development of agile free-flyer “locker” satellite with robotic arms to assemble and deploy rapid response CubeSats GEO ➢ Constellation Phase: Development of strategic constellation of agile free-flyer “locker” satellites with robotic Internal View of ‘Locker’ Showing Robotic Assembly arms to autonomously assemble and deploy CubeSats IR Sensors VIS Sensors RF Sensors Propulsion Mission Overview Mission Significance • Orbit-agnostic lockers deploy on-demand robot-assembled CubeSats Provides many CubeSat configurations responsive to • ‘Locker’ is mini-fridge-sized spacecraft with propulsion rapidly evolving space needs capability ✓ Flexible: Selectable sensors and propulsion • Holds robotic arms, sensor, and propulsion modules for ✓ Resilient: Dexterous robot arms for CubeSat assembly 1-3U CubeSats without humans-in-the-loop on Earth and on-orbit Build • Improve response: >30 days to ~hours custom-configured CubeSats on Earth or in space saving -
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. -
Spaceflight, Inc. General Payload Users Guide
Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Spaceflight, Inc. General Payload Users Guide 3415 S. 116th St, Suite 123 Tukwila, WA 98168 866.204.1707 spaceflightindustries.com i Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Document Revision History Rev Approval Changes ECN No. Sections / Approved Pages CM Date A 2011‐09‐16 Initial Release Updated electrical interfaces and launch B 2012‐03‐30 environments C 2012‐07‐18 Official release Updated electrical interfaces and launch D 2013‐03‐05 environments, reformatted, and added to sections Updated organization and formatting, E 2014‐04‐15 added content on SHERPA, Mini‐SHERPA and ISS launches, updated RPA CG F 2015‐05‐22 Overall update ii Spaceflight, Inc. SF‐2100‐PUG‐00001 Rev F 2015‐22‐15 Payload Users Guide Table of Contents 1 Introduction ........................................................................................................................... 7 1.1 Document Overview ........................................................................................................................ 7 1.2 Spaceflight Overview ....................................................................................................................... 7 1.3 Hardware Overview ......................................................................................................................... 9 1.4 Mission Management Overview .................................................................................................... 10 2 Secondary -
Space Science Beyond the Cubesat
Deepak, R., Twiggs, R. (2012): JoSS, Vol. 1, No. 1, pp. 3-7 (Feature article available at www.jossonline.com) www.DeepakPublishing.com www.JoSSonline.com Thinking Out of the Box: Space Science Beyond the CubeSat Ravi A. Deepak 1, Robert J. Twiggs 2 1 Taksha University, , 2 Morehead State University Abstract Over a decade ago, Professors Robert (Bob) Twiggs (then of Stanford University) and Jordi Puig-Suari (CalPoly- SLO) effected a major paradigm shift in space research with the development of the 10-cm CubeSat, helping to provide a new level of student accessibility to space science research once thought impossible. Seeking a means to provide students with hands-on satellite development skills during their limited time at university, and inspired by the successful deployment of six 1-kg, pico-satellites from Stanford’s Orbiting Picosatellite Automatic Launcher (OPAL) in 2000, Twiggs and Puig-Suari ultimately developed the 10-cm CubeSat. In 2003, the first successful CubeSat deployment into orbit demonstrated the very achievable possibilities that lay ahead. By 2008, 60 launch missions later, new industries had arisen around the CubeSat, creating new commercial off-the-shelf (COTS) satellite components and parts, and conventional launch resources became overwhelmed. This article recounts this history and related issues that arose, describes solutions to the issues and subsequent developments in the arena of space science (such as further miniaturization of space research tools), and provides a glimpse of Twiggs’ vision of the future of space research. Mavericks of Space Science With the development of the Cubesat over a decade ago, Bob Twiggs, at Stanford University (now faculty at Morehead State University), (Figure 1) and Jordi Puig-Suari, at California Polytechnic State University (CalPoly) (Figure 2), changed the paradigm of space research, helping to bring a new economy to space sci- ence that would provide accessibility once thought im- possible to University students around the globe. -
Cubesat-Based Science Missions for Geospace and Atmospheric Research
National Aeronautics and Space Administration NATIONAL SCIENCE FOUNDATION (NSF) CUBESAT-BASED SCIENCE MISSIONS FOR GEOSPACE AND ATMOSPHERIC RESEARCH annual report October 2013 www.nasa.gov www.nsf.gov LETTERS OF SUPPORT 3 CONTACTS 5 NSF PROGRAM OBJECTIVES 6 GSFC WFF OBJECTIVES 8 2013 AND PRIOR PROJECTS 11 Radio Aurora Explorer (RAX) 12 Project Description 12 Scientific Accomplishments 14 Technology 14 Education 14 Publications 15 Contents Colorado Student Space Weather Experiment (CSSWE) 17 Project Description 17 Scientific Accomplishments 17 Technology 18 Education 18 Publications 19 Data Archive 19 Dynamic Ionosphere CubeSat Experiment (DICE) 20 Project Description 20 Scientific Accomplishments 20 Technology 21 Education 22 Publications 23 Data Archive 24 Firefly and FireStation 26 Project Description 26 Scientific Accomplishments 26 Technology 27 Education 28 Student Profiles 30 Publications 31 Cubesat for Ions, Neutrals, Electrons and MAgnetic fields (CINEMA) 32 Project Description 32 Scientific Accomplishments 32 Technology 33 Education 33 Focused Investigations of Relativistic Electron Burst, Intensity, Range, and Dynamics (FIREBIRD) 34 Project Description 34 Scientific Accomplishments 34 Education 34 2014 PROJECTS 35 Oxygen Photometry of the Atmospheric Limb (OPAL) 36 Project Description 36 Planned Scientific Accomplishments 36 Planned Technology 36 Planned Education 37 (NSF) CUBESAT-BASED SCIENCE MISSIONS FOR GEOSPACE AND ATMOSPHERIC RESEARCH [ 1 QB50/QBUS 38 Project Description 38 Planned Scientific Accomplishments 38 Planned -
Pre-Launch Testing of the Lunar Flashlight (LF) Cubesat GNC System David C
Sternberg, D. C. et al. (2021): JoSS, Vol. 10, No. 1, pp. 959–981 (Peer-reviewed article available at www.jossonline.com) www.adeepakpublishing.com www. JoSSonline.com Pre-Launch Testing of the Lunar Flashlight (LF) CubeSat GNC System David C. Sternberg, Peter C. Lai, Aadil Rizvi, Kevin F. Ortega, Kevin D. Lo, Philippe C. Adell, and John D. Baker Jet Propulsion Laboratory California Institute of Technology Pasadena, CA, US Abstract Lunar Flashlight (LF) is a 6U, 14 kg spacecraft that will measure potential surface water ice deposits in the permanently shadowed region (PSR) of the moon. The mission described in this paper will use IR laser technology to search for volatiles in preparation for future human lunar exploration. A CubeSat’s guidance, navigation and control (GNC) system is crucial for the spacecraft to successfully reach the moon, enter a lunar orbit, and acquire scientific data. The Jet Propulsion Laboratory (JPL) has adopted a commercial-off-the-shelf (COTS) integrated GNC spacecraft system after experience from over twenty CubeSat missions. When hardware is delivered to JPL by the vendor, thorough validation testing is performed to guarantee fundamental functionality before the hard- ware is integrated into the spacecraft. Moreover, while the validation processes for the first few CubeSats relying on similar COTS-integrated GNC systems at JPL were very fluid, LF represents the first attempt JPL has made to apply large-mission, rigorous testing processes to a CubeSat, with the intent of standardizing the testing process for a rapidly growing number of CubeSats at JPL. This paper presents the rigorous testing concept applied to the GNC system, the various tests that have been performed and standardized, and the data acquired during the testing campaign to ensure that the LF GNC system will function as part of the integrated spacecraft once launched. -
Lunar Flashlight
https://ntrs.nasa.gov/search.jsp?R=20160008001 2019-08-29T23:45:10+00:00Z Lunar Flashlight Project Manager(s)/Lead(s) John Baker (PM)/Jet Propulsion Laboratory (818) 354–5004 Barbara Cohen (PI)/ZP13 (256) 961–7901 Amy Walden (Project Lead)/FP30 (256) 961–2358 Sponsoring Program(s) Human Exploration and Operations Mission Directorate Advanced Exploration Systems Figure 1: Artist concept of the Lunar Flashlight mission over the lunar surface. Project Description The Lunar Flashlight is a Jet Propulsion Laboratory project, with NASA Marshall Space Flight Center (MSFC) serving as the principal investigator and pro- viding the solar sail propulsion system. The goal of Lunar Flashlight is to determine the presence and abun- dance of exposed lunar water ice within permanently shadowed regions (PSRs) at the lunar south pole, and to map its concentration at the 1–2 km scale to sup- port future exploration and use. After being ejected in cis-lunar space by the launch vehicle, Lunar Flashlight deploys solar panels and an 85-m2 solar sail and maneu- vers into a low-energy transfer to lunar orbit. The solar sail and attitude control system work to bring the satel- lite into an elliptical polar orbit, spiraling down over a period of 18 months to a perilune of 30–10 km above the south pole for data collection. Lunar Flashlight uses Figure 2: Reflectivity testing of the material that will be used to build the Lunar Flashlight solar sail. its solar sail to shine reflected sunlight onto the lunar surface, measuring surface reflectance with a four-filter point spectrometer. -
L-8: Enabling Human Spaceflight Exploration Systems & Technology
Johnson Space Center Engineering Directorate L-8: Enabling Human Spaceflight Exploration Systems & Technology Development Public Release Notice This document has been reviewed for technical accuracy, business/management sensitivity, and export control compliance. It is Montgomery Goforth suitable for public release without restrictions per NF1676 #37965. November 2016 www.nasa.gov 1 NASA’s Journey to Mars Engineering Priorities 1. Enhance ISS: Enhanced missions and systems reliability per ISS customer needs 2. Accelerate Orion: Safe, successful, affordable, and ahead of schedule 3. Enable commercial crew success 4. Human Spaceflight (HSF) exploration systems development • Technology required to enable exploration beyond LEO • System and subsystem development for beyond LEO HSF exploration JSC Engineering’s Internal Goal for Exploration • Priorities are nice, but they are not enough. • We needed a meaningful goal. • We needed a deadline. • Our Goal: Get within 8 years of launching humans to Mars (L-8) by 2025 • Develop and mature the technologies and systems needed • Develop and mature the personnel needed L-8 Characterizing L-8 JSC Engineering: HSF Exploration Systems Development • L-8 Is Not: • A program to go to Mars • Another Technology Road-Mapping effort • L-8 Is: • A way to translate Agency Technology Roadmaps and Architectures/Scenarios into a meaningful path for JSC Engineering to follow. • A way of focusing Engineering’s efforts and L-8 identifying our dependencies • A way to ensure Engineering personnel are ready to step up