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Past Conference Papers:
Responsive Missions - Education
| Paper Number RS2-2004-2002: A Novel Approach to Responsive Space: Lessons Learned by the DoD Space Test Program | |
| Sabrina Herrin (The Aerospace Corporation), Eleni Sims (The Aerospace Corporation) | |
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| Abstract: This paper explores four Department of Defense (DoD) Space Test Program (STP) missions and identifies lessons learned in successfully achieving responsive space flight. Case studies included are NanoSat-2, Kodiak Star, MISSE 5, and SPHERES. In creating a responsive space mission, often the focus is on getting a space vehicle built and a launch vehicle procured as quickly as possible to get from a conceptual design to data from space in the least amount of time. As STP has found, there are effective responsive space techniques that may be better suited to a mission than merely building and buying components faster. The examination of the four case studies leads to several conclusions: 1) be open to a change in plans and to solutions that have never been attempted, 2) networking will create more opportunities, 3) if one wants to do something quickly, commit wholeheartedly and apply enough resources to make the project work, 4) risks and how to mitigate them should be identified in the beginning of a program, 5) prior to “starting from scratch,” investigate the utilization of existing resources and designs, 6) be prepared to take advantage of opportunities when they come along, and 7) making a project scalable, so that objectives can be accomplished piecemeal, will increase the number of manifest options. | |
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| Paper Number RS2-2004-2005: Responsive Space Requires Responsive Manufacturing | |
| Todd Mosher (USU), Brent Stucker (USU) | |
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| Abstract: In order to meet the responsive space needs of the future, improvements need to be made not only to the product of satellites themselves, but also the process by which they are created. While many continue to focus primarily on product innovation, with the exception of large commercial satellite projects like communication satellites, the Boeing 601/702 platform, and the Iridium program, few are successfully addressing how do we change how we build satellites rather than changing the satellites we build. Small satellites especially offer opportunities for process innovation and the application of advanced manufacturing techniques to this process. Within the mechanical and aerospace engineering department at Utah State University, professors in space engineering and advanced manufacturing have teamed to focus on making satellite manufacture more responsive. Through a series of studies for the U.S. government, concepts to realize responsive manufacturing to enable responsive space will be discussed and reported. | |
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| Paper Number RS2-2004-2006: EyasSAT™: Creating a Progressive Space Workforce - Today | |
| Obadiah NG Ritchey (USAFA), David J. Barnhart (USAFA), Jerry J. Sellers (USAFA), Jim W. White (USAFA), John B. Clark (USAFA) | |
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| Abstract: The Department of Astronautics at the United States Air Force Academy has transformed the way spacecraft systems engineering is taught, but more importantly, the way it is experienced by the students. The development is called EyasSAT™—a miniaturized, fully-functional satellite model that is “flown” in the classroom. EyasSAT literally means “baby FalconSAT”, where FalconSAT is the name of the flagship program at USAFA where students work as a team their senior year to design, build, launch, or operate a real satellite performing DoD science. To prepare for this interdisciplinary experience students take the prerequisite course titled “Spacecraft Systems Engineering”. Students in this course work in small teams to build up an EyasSAT unit, subsystem by subsystem, after the design issues are covered in the classroom. This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. The premise is simple: EyasSAT is composed of intelligent, stand-alone hardware modules built with COTS components that are integrated through a flexible data and power bus. Instead of designing and building each subsystem in detail, EyasSAT allows students the opportunity to perform acceptance and verification testing on the hardware as they learn about each subsystem in the classroom. This matches the spirit of the course which is to broadly cover all spacecraft system and subsystem level issues and not to cover one subsystem in great detail. After each subsystem is characterized in the lab, it is stacked up in an integrated fashion, ultimately producing a picosatellite-sized fully-operational system by the end of the semester. Telemetry and data commands are accomplished through any telephony device that supports the terminal standard. EyasSAT also can be easily expanded through additional modules to support teaching or commercial objectives. AIAA 2nd Responsive Space Conference 2004 1 The EyasSAT concept exemplifies the idea of ‘progressive space’: education is the foundation for future space practice. By leveraging a new way of educating space professionals, a new breed of progressive thought is created—one that is open to new ideas, faster project turn-around, and betterversed, total-systems-based, engineering. This paper outlines the objectives and the requirements for the concept, as well as assembly, integration and testing requirements to quantify the system. System characterization is likewise covered. | |
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| Paper Number RS2-2004-5004: Leveraging COTS Hardware for Rapid Design and Development of Small Satellites at the USAF Academy | |
| Cristin Anne Smith (USAFA) | |
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| Abstract: The purpose of the United States Air Force Academy (USAFA) Space Systems Research Program is to give cadets the opportunity to “learn space by doing space” while also providing an orbiting platform for Air Force and Department of Defense (DoD) science experiments as FalconSAT-3 is designed to do. This paper describes small satellite programs at the U.S. Air Force Academy’s Space Systems Research Center. FalconSAT- 2 and FalconSAT-3 are student-built small satellites that provide low-cost access to space for DoD space research & development payloads as well as platforms for student experiments. Rapid, low-cost design is achieved by leveraging Commercial Off-the- Shelf (COTS) hardware to the greatest extent possible. FalconsSAT-2, still searching for an alternate launch opportunity, was the first to demonstrate the use of COTS modules for this use. FalconSAT-3, scheduled to be launched in 2006, recently completed critical design and built upon the successful FalconSAT-2 experience to develop an even more capable spacecraft bus. By using the off-the-shelf equipment, student involvement in satellite and mission design has been accelerated and provided the capability to challenge students This paper is declared a work of the U.S. Government and is not subject to copyright protection in the United States. through more intense participation over the years. Realizing the rapid turnover and extended commitments of students in a senior undergraduate program, there is a delicate balance to be found; one between comprehensive mission and satellite design requirements, and adequate experience in a multi-million dollar, real world space program. The development of the FalconSAT program will first be described in the context of the progress made, followed by a more detailed discussion of the COTS hardware for more efficient development of small student satellites as simple payload platforms for educational and technological purposes. | |
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| Paper Number RS3-2005-3001: Cubesats As Responsive Satellites | |
| Armen Toorian (Cal Poly, San Luis Obispo), Emily Blundell (Cal Poly, San Luis Obispo), Jordi Puig Suari (Cal Poly San Luis Obispo), Robert Twiggs (Stanford) | |
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| Abstract: California Polytechnic State University, in coordination with Stanford University, has developed the CubeSat standard to provide inexpensive and timely access to space for small payloads. These picosatellites, built mostly by universities, are 10 centimeter cubes with a mass of 1 kilogram. Of the 40 or so participating universities and private firms, more than 60% of CubeSat developers reside in the United States. Our goal is to make launching these satellites easy and cost effective by coordinating launches and providing a reliable deployment system. This paper will discuss Cal Poly’s role in the CubeSat program, and the characteristics of the project which create practical, reliable, and costeffective launch opportunities. | |
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| Paper Number RS3-2005-3002: KUTESAT-2, A Student Nanosatellite Mission for Testing Rapid-Response Small Satellite Technologies in Low Earth Orbit | |
| Trevor Sorenson (University of Kansas), Glenn Prescott (University of Kansas), Marco Villa (University of Kansas), Dewayne Brown (National Nuclear Security Administration), John Hicks (National Nuclear Security Administration), Arthur Edwards (AFRL), James Lyke (AFRL), Thomas George (JPL), Sohrab Mobasser (JPL), JPL (JPL), Scott Tyson (Space Microsystems) | |
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| Abstract: The Air Force Research Laboratory (AFRL) is interested in using nanosats to perform space experiments, demonstrate new technology, develop operational systems, and integrate advanced responsive space system technology. One potential operational application of nanosats is using clusters of microsatellites that operate cooperatively to perform the function of a larger, single satellite. Each smaller satellite communicates with the others and shares the processing, communications, and payload or mission functions. This type of a distributed system has several advantages: (1) systemlevel robustness and graceful degradation, and (2) distributed capabilities for surveillance and science measurements built into the system architecture. There are a number of technology advancements needed to operationalize and enable tactical missions. These advancements include modular ‘plug-n-play’ satellite architectures and components; high performance tactical downlinks; adaptable, agile propulsion systems, and lean manufacturing, assembly and test. The Kansas Universities’ Technology Evaluation Satellite (KUTESat) program originated at the University of Kansas (KU) in 2002. The technical objective of the program is the development and operation of miniature satellites that can demonstrate and test technologies and techniques necessary to accomplish various government missions. The first satellite, KUTESat-1 Pathfinder, was designed to perform imaging and measure radiation from orbit. The design and construction of this 1-kg satellite helped KU to develop the capability to produce and operate small research satellites. Pathfinder is due for launch in mid-2005. Nanosats are a rapid and low-cost technology platform for the space testing of a broad range of micro-electro-mechanical systems (MEMS) and nanotechnologies as well as new mission architectures. The KUTESat program offers a low-cost solution to the problem of acquiring “space heritage” for new technologies and concepts. These programs can undertake higher risk missions that would be otherwise avoided by more conservative mission planners. Thus new MEMS and nanotechnologies related to avionics, guidance and control, communications, imaging, maneuvering, and instrumentation are offered a rapid and low-cost approach to space testing that will help realize a rapid response space force. The objective of the current program is to develop and fly a nanosatellite to test components, technologies, and concepts that are of use to the AFRL, the National Nuclear Security Administration (NNSA) and the National Aeronautics and Space Administration (NASA), while providing a valuable contribution to the education of students who will soon be entering the space workforce. KU is leading a team consisting of the NNSA Kansas City Plant, the AFRL, and NASA Jet Propulsion Laboratory (JPL) to design and execute the KUTESat-2 mission using a 16-kg nanosatellite based on the Pathfinder satellite with much commonality in the avionics and ground system. The major technologies to be tested include: a miniature distributed and adaptive S-band transceiver; a miniature maneuvering control system; standardized interface (“plug and play”) electronic modules; various MEMS technologies, including a single-axis MEMS gyroscope; a micro sun sensor; an array of miniature dosimeters; and a miniature imager. New capabilities to be tested include a Tracking and Data Relay Satellite (TDRS) communication demonstration with the Sband transceiver, and demonstration of target inspection capability using a deployed inflated target. The KUTESat-2 will be prepared for a launch in 2007. | |
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| Paper Number RS3-2005-5006: How Not to Design an Avionics System | |
| Jason E. Holt (Brigham Young University) | |
| View/Download:Presentation | Paper | |
| Abstract: In 1995, four Utah Universities launched a hybrid sounding rocket at the Utah Test and Training Range. In December 2003, they successfully launched a much larger successor to that rocket. We describe the design, construction, deconstruction, redesign and reconstruction of the avionics package during the 8 year period between flights, then describe the system which was actually flown. That package used COTS hardware worth less than $1000, was substantially redesigned within weeks of the launch, and was completely destroyed after an entirely successful flight upon an otherwise soft, vertical landing. Although the package met only simple requirements and used no cutting-edge hardware, we feel that the lessons we learned from both technical and social standpoints will be useful to others who wish to rapidly develop avionics systems despite severely limited resources. Furthermore, we describe a new, straightforward design for the core control system which is a result of the lessons we learned, and which we hope will be flexible enough to meet the continuing demands of our project and potentially many other projects as well. | |
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| Paper Number RS6-2008-4003: Responsive Spacecraft Bus Implementation for HEO Missions Designed to Bridge Prototype and Operational Systems | |
| P.A. Stadter (Johns Hopkins University Applied Physics Laboratory), M.T. Marley (Johns Hopkins University Applied Physics Laboratory), C.T. Apland (Johns Hopkins University Applied Physics Laboratory), C.T. Apland (Johns Hopkins University Applied Physics Laboratory), R.E. Lee (Johns Hopkins University Applied Physics Laboratory), B.D. Williams (Johns Hopkins University Applied Physics Laboratory), E.D. Schaefer (Johns Hopkins University Applied Physics Laboratory), P.D. Schwartz (Johns Hopkins University Applied Physics Laboratory), B. Kantsiper (Johns Hopkins University Applied Physics Laboratory), E. J. Finnegan (Johns Hopkins University Applied Physics Laboratory), W. Raynor (Naval Research Laboratory), G.S. Sandhoo (Naval Research Laboratory) | |
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| Abstract: This paper will provide details of the implementation, integration, and test of an Operationally Responsive Space spacecraft bus to be used by the TacSat-4 CommX mission in a highly elliptical orbit (HEO). It will provide details of near-term results of the development, integration and test, and the implementation of standard interfaces to facilitate a bridge between prototype and operational systems. The paper details the means by which the technology and system engineering inform further use for future operational systems, including specifically the work of the Integrated System Engineering Team of industry, laboratory, and government participants. Details of the qualification of the spacecraft up through completion of integration and test will be provided, as will lessons observed that specifically translate into information for future operational satellite builds. This will include a discussion of the driving requirements for the bus to provide operations in the HEO orbital environment and the user applications that can take advantage of such a platform in a timely manner given candidate payloads. Aspects of complementary analyses of how similar operationally responsive space systems can military utility will also be presented. | |
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