Cubesat-Based Science Missions for Geospace and Atmospheric Research
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Mission to Jupiter
This book attempts to convey the creativity, Project A History of the Galileo Jupiter: To Mission The Galileo mission to Jupiter explored leadership, and vision that were necessary for the an exciting new frontier, had a major impact mission’s success. It is a book about dedicated people on planetary science, and provided invaluable and their scientific and engineering achievements. lessons for the design of spacecraft. This The Galileo mission faced many significant problems. mission amassed so many scientific firsts and Some of the most brilliant accomplishments and key discoveries that it can truly be called one of “work-arounds” of the Galileo staff occurred the most impressive feats of exploration of the precisely when these challenges arose. Throughout 20th century. In the words of John Casani, the the mission, engineers and scientists found ways to original project manager of the mission, “Galileo keep the spacecraft operational from a distance of was a way of demonstrating . just what U.S. nearly half a billion miles, enabling one of the most technology was capable of doing.” An engineer impressive voyages of scientific discovery. on the Galileo team expressed more personal * * * * * sentiments when she said, “I had never been a Michael Meltzer is an environmental part of something with such great scope . To scientist who has been writing about science know that the whole world was watching and and technology for nearly 30 years. His books hoping with us that this would work. We were and articles have investigated topics that include doing something for all mankind.” designing solar houses, preventing pollution in When Galileo lifted off from Kennedy electroplating shops, catching salmon with sonar and Space Center on 18 October 1989, it began an radar, and developing a sensor for examining Space interplanetary voyage that took it to Venus, to Michael Meltzer Michael Shuttle engines. -
Global Ionosphere-Thermosphere-Mesosphere (ITM) Mapping Across Temporal and Spatial Scales a White Paper for the NRC Decadal
Global Ionosphere-Thermosphere-Mesosphere (ITM) Mapping Across Temporal and Spatial Scales A White Paper for the NRC Decadal Survey of Solar and Space Physics Andrew Stephan, Scott Budzien, Ken Dymond, and Damien Chua NRL Space Science Division Overview In order to fulfill the pressing need for accurate near-Earth space weather forecasts, it is essential that future measurements include both temporal and spatial aspects of the evolution of the ionosphere and thermosphere. A combination of high altitude global images and low Earth orbit altitude profiles from simple, in-the-medium sensors is an optimal scenario for creating continuous, routine space weather maps for both scientific and operational interests. The method presented here adapts the vast knowledge gained using ultraviolet airglow into a suggestion for a next-generation, near-Earth space weather mapping network. Why the Ionosphere, Thermosphere, and Mesosphere? The ionosphere-thermosphere-mesosphere (ITM) region of the terrestrial atmosphere is a complex and dynamic environment influenced by solar radiation, energy transfer, winds, waves, tides, electric and magnetic fields, and plasma processes. Recent measurements showing how coupling to other regions also influences dynamics in the ITM [e.g. Immel et al., 2006; Luhr, et al, 2007; Hagan et al., 2007] has exposed the need for a full, three- dimensional characterization of this region. Yet the true level of complexity in the ITM system remains undiscovered primarily because the fundamental components of this region are undersampled on the temporal and spatial scales that are necessary to expose these details. The solar and space physics research community has been driven over the past decade toward answering scientific questions that have a high level of practical application and relevance. -
A Comparison Study on Thermal Control Techniques for a Nanosatellite Carrying Infrared Science Instrument
ICES-2020-15 A comparison study on thermal control techniques for a nanosatellite carrying infrared science instrument Shanmugasundaram Selvadurai1, Amal Chandran2, Sunil C Joshi3 and Teo Hang Tong Edwin 4 Nanyang Technological University, Singapore, 639798 David Valentini5 Thales Alenia Space, Cannes, 06150, France Friedhelm Olschewski6 University of Wuppertal, 42119 Wuppertal, Germany Based on current technological advancements and forecasts, nanosatellites will be used for both scientific and defense applications leveraging advantages on both development cost and development lifecycle. As nanosatellites become more capable, there is an increase in demand for high power applications which makes the missions complex from implementing a proper thermal control system (TCS) to dissipate the huge waste heat generated. One of the applications for nanosatellites is advanced infrared imaging for both scientific and military applications. ARCADE (Atmospheric coupling and Dynamics Explorer), a 27U satellite is being developed by Satellite Research Centre (SaRC) at Nanyang Technological University (NTU) for scientific objectives. The main payload AtmoLITE needs a detector cool down at -30°C and to meet this requirement, an appropriate classical TCS is chosen and described in this paper. Nanosatellites carrying infrared, cryogenic or other scientific instruments that need active cooling, should be equipped with a proper TCS within the highly constrained available volume. Another objective of this study is to compare the existing TCS for nanosatellites and adopt a suitable and efficient TCS for a scientific nanosatellite mission carrying a generic science instrument that needs an active cooling of up to 95K. TCS using Heat pipes (HP), single-phase mechanically pumped fluid loop (SMPFL), and two-phase mechanically pumped fluid loop systems (2ΦMPFL) have been extensively used only by larger satellites. -
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 .................................................................................................................................. -
Space) Barriers for 50 Years: the Past, Present, and Future of the Dod Space Test Program
SSC17-X-02 Breaking (Space) Barriers for 50 Years: The Past, Present, and Future of the DoD Space Test Program Barbara Manganis Braun, Sam Myers Sims, James McLeroy The Aerospace Corporation 2155 Louisiana Blvd NE, Suite 5000, Albuquerque, NM 87110-5425; 505-846-8413 [email protected] Colonel Ben Brining USAF SMC/ADS 3548 Aberdeen Ave SE, Kirtland AFB NM 87117-5776; 505-846-8812 [email protected] ABSTRACT 2017 marks the 50th anniversary of the Department of Defense Space Test Program’s (STP) first launch. STP’s predecessor, the Space Experiments Support Program (SESP), launched its first mission in June of 1967; it used a Thor Burner II to launch an Army and a Navy satellite carrying geodesy and aurora experiments. The SESP was renamed to the Space Test Program in July 1971, and has flown over 568 experiments on over 251 missions to date. Today the STP is managed under the Air Force’s Space and Missile Systems Center (SMC) Advanced Systems and Development Directorate (SMC/AD), and continues to provide access to space for DoD-sponsored research and development missions. It relies heavily on small satellites, small launch vehicles, and innovative approaches to space access to perform its mission. INTRODUCTION Today STP continues to provide access to space for DoD-sponsored research and development missions, Since space first became a viable theater of operations relying heavily on small satellites, small launch for the Department of Defense (DoD), space technologies have developed at a rapid rate. Yet while vehicles, and innovative approaches to space access. -
Aurorae and Airglow Results of the Research on the International
VARIATIONS IN THE Ha EMISSION AND HYDROGEN DISTRIBUTION IN THE UPPER ATMOSPHERE AND THE GEOCORONA L. M. Fishkova and N. M. Martsvaladze ABSTRACT: The variations in intensity of the hydrogen emission showed a maximum during the minimum of solar activity in 1962-1963. The distribution of hydrogen content at altitudes from 400 to 1300 km was calculated. It in creased during the period of the minimum in the solar cycle. No concentration of H, emis sion around the ecliptic was detected. During the International Quiet Solar Year, spectral observa tions of the intensity of H, emission 6563 a in the airglow spec trum were conducted in Abastumani [l, 21. Continuous observations from f ,hyleighs "w 1953 to 1964 provided for finding the annual variations in H, intensity related to the cycle of solar activ ity (Fig. 1). With a decrease in solar activity, the H, intensity increased and reached a maximum in 1962-1963 while, from 1964, it again began to decrease. Such a variation in the H, intensity can be explained by the variations in Fig. 1. Variations in the the amount of hydrogen during the Average Annual Intensities solar cycle. With a decrease in of H, Emission During the the solar activity, the temperature Cycle of Solar Activity. of the thermopause decreases , which then leads to an increase in the concentration of atomic hydrogen in the exosphere and the geocorona. For example, theoretical calculations [SI show that a change in temperature of the themopause from - 2000 to - 1000° K during the transition from maximum to minimum solar activity can bring about an increase in the hydrogen concentration at altitudes of 500-3000 km, almost by one order of magnitude. -
FASTSAT a Mini-Satellite Mission…..A Way Ahead”
Proposed Abstract: Under the combined Category and Title: “FASTSAT a Mini-Satellite Mission…..A Way Ahead” Authors: Mark E. Boudreaux, Joseph Casas, Timothy A. Smith The Fast Affordable Science and Technology Spacecraft (FASTSAT) is a mini-satellite weighing less than 150 kg. FASTSAT was developed as government-industry collaborative research and development flight project targeting rapid access to space to provide an alternative, low cost platform for a variety of scientific, research, and technology payloads. The initial spacecraft was designed to carry six instruments and launch as a secondary “rideshare” payload. This design approach greatly reduced overall mission costs while maximizing the on-board payload accommodations. FASTSAT was designed from the ground up to meet a challenging short schedule using modular components with a flexible, configurable layout to enable a broad range of payloads at a lower cost and shorter timeline than scaling down a more complex spacecraft. The integrated spacecraft along with its payloads were readied for launch 15 months from authority to proceed. As an ESPA-class spacecraft, FASTSAT is compatible with many different launch vehicles, including Minotaur I, Minotaur IV, Delta IV, Atlas V, Pegasus, Falcon 1/1e, and Falcon 9. These vehicles offer an array of options for launch sites and provide for a variety of rideshare possibilities. FASTSAT a Mini Satellite Mission …..A Way Ahead 15th Annual Space & Missile Defense Conference Session Track 1.2 : Operations for Small, Tactical Satellites Mark Boudreaux/NASA -
A Tenuous, Collisional Atmosphere on Callisto
A tenuous, collisional atmosphere on Callisto Shane R. Carberry Mogana;b;c;∗, Orenthal J. Tuckerd, Robert E. Johnsone;f , Audrey Vorburgerg, Andre Gallig, Benoit Marchandh, Angelo Tafunii, Sunil Kumarc, Iskender Sahina, Katepalli R. Sreenivasana;b;f aTandon School of Engineering, New York University, New York, USA; bCenter for Space Sci- ence, New York University Abu Dhabi, Abu Dhabi, UAE; cDivision of Engineering, New York University Abu Dhabi, Abu Dhabi, UAE; dNASA Goddard Space Flight Center, Maryland, USA; eUniversity of Virginia, Virginia, USA; f Physics Department, New York University, New York, USA; gPhysikalisches Institut, University of Bern, Bern, Switzerland; hHigh Per- formance and Research Computing Center, New York University Abu Dhabi, UAE; iSchool of Applied Engineering and Technology, New Jersey Institute of Technology, New Jersey, USA Abstract A simulation tool which utilizes parallel processing is developed to describe molecu- lar kinetics in 2D, single- and multi-component atmospheres on Callisto. This expands on our previous study on the role of collisions in 1D atmospheres on Callisto composed of radiolytic products (Carberry Mogan et al., 2020) by implementing a temperature gradient from noon to midnight across Callisto's surface and introducing sublimated water vapor. We compare single-species, ballistic and collisional O2,H2 and H2O at- mospheres, as well as an O2+H2O atmosphere to 3-species atmospheres which contain H2 in varying amounts. Because the H2O vapor pressure is extremely sensitive to the surface temperatures, the density drops several orders of magnitude with increasing distance from the subsolar point, and the flow transitions from collisional to ballistic accordingly. In an O2+H2O atmosphere the local temperatures are determined by H2O near the subsolar point and transition with increasing distance from the subsolar point to being determined by O2. -
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 -
Highlights in Space 2010
International Astronautical Federation Committee on Space Research International Institute of Space Law 94 bis, Avenue de Suffren c/o CNES 94 bis, Avenue de Suffren UNITED NATIONS 75015 Paris, France 2 place Maurice Quentin 75015 Paris, France Tel: +33 1 45 67 42 60 Fax: +33 1 42 73 21 20 Tel. + 33 1 44 76 75 10 E-mail: : [email protected] E-mail: [email protected] Fax. + 33 1 44 76 74 37 URL: www.iislweb.com OFFICE FOR OUTER SPACE AFFAIRS URL: www.iafastro.com E-mail: [email protected] URL : http://cosparhq.cnes.fr Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law The United Nations Office for Outer Space Affairs is responsible for promoting international cooperation in the peaceful uses of outer space and assisting developing countries in using space science and technology. United Nations Office for Outer Space Affairs P. O. Box 500, 1400 Vienna, Austria Tel: (+43-1) 26060-4950 Fax: (+43-1) 26060-5830 E-mail: [email protected] URL: www.unoosa.org United Nations publication Printed in Austria USD 15 Sales No. E.11.I.3 ISBN 978-92-1-101236-1 ST/SPACE/57 *1180239* V.11-80239—January 2011—775 UNITED NATIONS OFFICE FOR OUTER SPACE AFFAIRS UNITED NATIONS OFFICE AT VIENNA Highlights in Space 2010 Prepared in cooperation with the International Astronautical Federation, the Committee on Space Research and the International Institute of Space Law Progress in space science, technology and applications, international cooperation and space law UNITED NATIONS New York, 2011 UniTEd NationS PUblication Sales no. -
Temporal Variability of Atomic Hydrogen from the Mesopause To
PUBLICATIONS Journal of Geophysical Research: Space Physics RESEARCH ARTICLE Temporal Variability of Atomic Hydrogen From 10.1002/2017JA024998 the Mesopause to the Upper Thermosphere Key Points: Liying Qian1 , Alan G. Burns1 , Stan S. Solomon1 , Anne K. Smith2 , Joseph M. McInerney1 , • In the mesopause, hydrogen density is 3 1,2 1 3 1,2 higher in summer than in winter, and Linda A. Hunt , Daniel R. Marsh , Hanli Liu ,MartinG.Mlynczak , and Francis M. Vitt higher at solar minimum than at 1 2 solar maximum High Altitude Observatory, National Center for Atmospheric Research, Boulder, CO, USA, Atmospheric Chemistry 3 • MSIS exhibits reverse seasonal Observations and Modeling Laboratory, National Center for Atmospheric Research, Boulder, CO, USA, NASA Langley variation than WACCM and SABER Research Center, Hampton, VA, USA do in the mesopause region • In the upper thermosphere, H is higher at solar minimum than solar Abstract We investigate atomic hydrogen (H) variability from the mesopause to the upper thermosphere, maximum, higher in winter than summer, and also higher at night on time scales of solar cycle, seasonal, and diurnal, using measurements made by the Sounding of the than day Atmosphere using Broadband Emission Radiometry (SABER) instrument on the Thermosphere Ionosphere Mesosphere Energetics Dynamics satellite, and simulations by the National Center for Atmospheric Research Whole Atmosphere Community Climate Model-eXtended (WACCM-X). In the mesopause region (85 to Correspondence to: 95 km), the seasonal and solar cycle variations of H simulated by WACCM-X are consistent with those from L. Qian, SABER observations: H density is higher in summer than in winter, and slightly higher at solar minimum than [email protected] at solar maximum. -
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