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Past Conference Papers:
Responsive Missions - Technology Demonstration
| Paper Number RS1-2003-2002: Improving Space-Asset Responsiveness Using the Shuttle Expendable Rocket for Payload Augmentation | |
| Randall Carlson (AFRL), Arnold Nowinski (AFRL), Jesse Jones (AFRL), Julia Rothman (AFRL), Steven Buckley (NGST) | |
| View/Download:Presentation | Paper | |
| Abstract: The Air Force has a growing mission need for highly-responsive, reliable and orbitflexible micro-satellites. To respond to this need, the Air Force Research Laboratory Space Vehicles Directorate (AFRL/VS), in collaboration with the Missile Defense Agency (MDA) and Space Test Program (STP), is developing the SHuttle Expendable Rocket for Payload Augmentation— SHERPA. The SHERPA system will be a reliable, low-cost asset that will provide orbit flexibility and multi-mission capability from the Shuttle Hitchhiker Experimental Launch System (SHELS) and other launch platforms. Technologies that will be developed under SHERPA include hybrid chemical propulsion, Hall Effect electric propulsion, modular bus architecture, separation systems, miniature star tracker technologies, and guidance, navigation and control systems. Modularity is used to enhance the responsiveness and multimission capability of the SHERPA system. SHERPA is designed with capability for multi orbit changes, station keeping, and de-orbiting at the completion of a mission. The system is being developed toward a proposed flight demonstration in the 2005 timeframe. | |
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| Paper Number RS1-2003-9004: Demonstrating Low Cost Access to Space for Small Satellites: Space Test Program-1 Mission | |
| Tim Sumrall (Kirtland Air Force Base) | |
| View/Download:Presentation | Paper | |
| Abstract: The DoD Space Test Program (STP) is charged with providing spaceflight to Research and Development (R&D) payloads from the Space Experiments Review Board (SERB) priority list. STP is dedicated to timely, cost-effective spaceflight opportunities. Often these opportunities result in innovative missions that maximize the amount of SERB payloads manifested per launch vehicle. In this spirit, STP has designed a multi-manifest mission that will deliver up to seven separate spacecraft to different earth orbits. This mission is called the Space Test Program–1 (STP-1). STP-1 is the most aggressive United States Department of Defense (DoD) multi-satellite R&D mission ever attempted. This complex mission is a collaboration between the Air Force Space Command (AFSPC), the Air Force Research Laboratory (AFRL), and the Defense Advanced Research Projects Agency (DARPA). Other participants include the Naval Research Laboratory (NRL), the Naval Postgraduate School (NPS), United States Naval Academy (USNA) and the United States Air Force Academy (USAFA). This paper will briefly review the STP-1 mission payloads. The focus of this paper is to discuss the Evolved Expendable Launch Vehicle (EELV) Secondary Payload Adapter (ESPA) and challenges facing the first ESPA mission. STP is managing this mission utilizing a diverse Integrated Product Team (IPT). This IPT is working to overcome several unique challenges in balancing limited manpower resources with the requirement to manage all the separate STP-1 mission components. | |
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| 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) | |
| View/Download:Presentation | Paper | |
| 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 RS2-2004-3002: Modular, Reconfigurable, and Rapid Responsive Space Systems: the Remote Sensing Advanced Technology Microsatellite | |
| Jamie Esper (GSFC), Jim Andary (GSFC), John Oberright (GSFC), Maria So (GSFC), Peter Wegener (AFRL), Alok Das (AFRL), Joe Hauser (NRL) | |
| View/Download:Presentation | Paper | |
| Abstract: Modular, Reconfigurable, and Rapid-response (MR2) space systems represent a paradigm shift in the way space assets of all sizes are designed, manufactured, integrated, tested, and flown. This paper will describe the MR2 paradigm in detail, and will include guidelines for its implementation. The Remote Sensing Advanced Technology microsatellite (RSAT) is a proposed flight system test-bed used for developing and implementing principles and best practices for MR2 spacecraft, and their supporting infrastructure. The initial goal of this test-bed application is to produce a lightweight (~100 kg), production-minded, cost-effective, and scalable remote sensing micro-satellite capable of high performance and broad applicability. Such applications range from future distributed space systems, to sensor-webs, and rapid-response satellite systems. Architectures will be explored that strike a balance between modularity and integration while preserving the MR2 paradigm. Modularity versus integration has always been a point of contention when approaching a design: whereas one-of-a-kind missions may require close integration resulting in performance optimization, multiple and flexible application spacecraft benefit from modularity, resulting in maximum flexibility. The process of building spacecraft rapidly (< 7 days), requires a concerted and methodical look at system integration and test processes and pitfalls. Although the concept of modularity is not new and was first developed in the 1970s by NASA’s Goddard Space Flight Center (Multi-Mission Modular Spacecraft), it was never modernized and was eventually abandoned. Such concepts as the Rapid Spacecraft Development Office (RSDO) became the preferred method for acquiring satellites. Notwithstanding, over the past 30 years technology has advanced considerably, and the time is ripe to reconsider modularity in its own right, as enabler of R2, and as a key element of transformational systems. The MR2 architecture provides a competitive advantage over the old modular approach in its rapid response to market needs that are difficult to predict both from the perspectives of evolving technology, as well as mission and application requirements. | |
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| Paper Number RS2-2004-5003: TacSat-1 and a Path to Tactical Space | |
| Jay Raymond (Office of Force Transformation), Greg Glaros (Office of Force Transformation), Joe Hauser (NRL), Mike Hurley (NRL) | |
| View/Download:Presentation | Paper | |
| Abstract: In May of 2003, the Office of the Secretary of Defense’s Office of Force Transformation undertook an initiative to perform Operationally Responsive Space experimentation. One year later the first experiment, TacSat-1, is nearing launch readiness and a second experiment, TacSat-2, is well into the design phase. The Naval Research Lab is the program manager responsible for the implementation of the TacSat-1 experiment. This paper discusses the TacSat-1 experiment, rationale, and status. This paper further discusses a path toward realizing an operational tactical space system. For completeness, much of the 2003 paper’s discussion on the technical, operational, and architectural issues for a tactical space capability is included. | |
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| Paper Number RS2-2004-6004: Department of Defense R&D Responsive Spaceflight | |
| Taylor Locker (SMC), Major Timothy Sumrall (SMC) | |
| View/Download:Presentation | Paper | |
| Abstract: This paper will discuss a new strategy for repeatable launching of Space Research, Development, Test and Evaluation (RDT&E) missions in 12-18 months versus 48 months using mechanisms that are in place today. DoD research and development (R&D) Responsive Space (RRS) is targeting a new way of doing business by creating a standard –service provider relationship. This new standard relationship will be forged through an alliance of government organizations. This alliance of government organizations must commit resources (manning and funding) to meet the timelines established for RRS. This paper will also discuss four RRS scenarios. These are dedicated launch vehicle (LV) (build spacecraft), dedicated LV (spacecraft bought), piggyback on host spacecraft or LV, and secondary satellite deployed form LV. These scenario’s will explore the technical envelope, barriers, considerations, and schedule realities of RRS. | |
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| Paper Number RS3-2005-1006: A TACSAT Update and the ORS/JWS Standard Bus | |
| Jay Raymond (Office of Force Transformation), Greg Glaros (Office of Force Transformation), Patrick Stadter (APL), Cheryl Reed (APL), Eric Finnegan (APL), Michael Hurley (NRL), Charlie Merk (NRL), NRL (NRL), NRL (NRL), NRL (NRL) | |
| View/Download:Presentation | Paper | |
| Abstract: In May of 2003, the Office of the Secretary of Defense’s Office of Force Transformation (OFT) undertook an initiative to perform Operationally Responsive Space (ORS) experimentation. Two years later the first experiment, TacSat-1, is launch ready, TacSat-2 is in the integration and test phase, TacSat-3 is underway, and TacSat-4 is in the planning phase. The TacSat-3 experiment took the important step of creating a joint process for mission selection. Each experiment tests key elements needed for a truly operational system, emerging as the Joint Warfighting Space (JWS) system. A necessary element of this system is a spacecraft bus with accepted standards for interfacing with each segment of this ORS/JWS system. The OFT and Space and Missile systems Command (SMC) have therefore undertaken a four phase initiative to develop and test bus standards and then transition them for acquisition. This effort involves multiple government laboratories, industry, and academia participants. The four phases of this initiative provide steady, tangible steps to spiral warfighting capability and receive operational feedback while moving toward an acquisition. This paper discusses this standard bus initiative with emphasis on Phase 3, which is led by the Naval Research Laboratory (NRL) and Applied Physics Laboratory (APL) team. For context, this paper includes portions of the 2003 and 2004 papers and discusses the status and current challenges of ORS/JWS. | |
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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) | |
| View/Download:Presentation | Paper | |
| 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) | |
| View/Download:Presentation | Paper | |
| 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 RS3-2005-3004: The SSTE-4: DSX Flight Experiemnt: Design of a Low-Cost, R&D Space Mission with Responsive Enabling Technologies | |
| Dan Cohen (Planning Systems), Joseph Wieber (Planning Systems), Jan King (Planning Systems), Shane Kemper (Planning Systems), Shawn Stephens (Planning Systems), Larry Davis (Planning Systems), Gregory Spanjers (AFRL), AFRL (AFRL), AFRL (AFRL), AFRL (AFRL), AFRL (AFRL), AFRL (AFRL) | |
| View/Download:Paper | |
| Abstract: The Air Force Research Laboratory (AFRL) Space Vehicles Directorate is developing the fourth Space Science Technology Experiment (SSTE-4), also known as DSX, to research technologies needed for large space structures and apertures, high-power generation, and survivability in the high radiation environment of a medium earth orbit (MEO). DSX is designed to perform five basic research experiments that coupled together provide DoD with the technological understanding needed to achieve transformational capability in space surveillance, microsats with large aperture and power, active space capability protection from enhanced radiation belts, and radiation-survivability design criteria for satellite systems planned for the highly desirable medium Earth orbit (MEO) regime. The five DSX experiments involve fundamental research on large deployable space structures, on-orbit dynamics identification and adaptive control of large deployable structures, very low frequency (VLF) Wave Particle Interaction (WPI) in the magnetosphere, thin-film photovoltaics (TFPV), and space radiation measurement in the MEO environment. DSX is baselined to launch in 2009 to a 6000-km x 12000-km, mid-inclination MEO orbit for at least one year of mission operations. DSX will serve as a path-finder for future DoD rapid response missions, by developing and demonstrating both technologies and processes that enable low-cost and rapid integration of oneof a-kind R&D satellites and operational systems. DSX addresses the rapid integration problem through the use of an innovative network based infrastructure, the Planning System Incorporated (PSI) Network Data Acquisition System (NDAS), for implementation of Bus and Payload box connectivity, as well as distributed remote sensor payloads on large deployable structures. To address the space access aspect of the rapid-response problem, DSX will utilize an EELV Secondary Payload Adapter (ESPA) capability as a platform for highly-capable small and medium free-flying satellites (or ESPASats) that have plentiful and relatively inexpensive launch opportunities on EELV as secondary payloads. An overview of the DSX spacecraft design will be presented, and its host subsystems, payload designs and experiments will be described. The unique electrical and software interface accommodation of the payload support electronics and Network Data Acquisition System (NDAS) as well as the highly modular mechanical integration approach of a free-flyer dedicated ESPA-sat will be described in the context of their enabling features for both DSX and future responsive DoD missions. | |
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| Paper Number RS3-2005-3005: The Little Probe that Could: Four Months from ATP to Launch | |
| Gerald Murphy (Design_Net Engineering), Ken Center (Design_Net Engineering) | |
| View/Download:Presentation | Paper | |
| Abstract: Responsive Space requires Responsive spacecraft! Last year Design_Net discussed just such a small spacecraft and examined the programmatic lessons that were learned from that development. This was the Floating Potential Probe (FPP). Flight 4A for the ISS was to deploy a new set of high voltage solar arrays which, due to large amount of electron current collected from the LEO plasma, caused the vehicle ground to shift significantly. The potential shift could lead to destructive and dangerous (for EVA) arcing. A set of plasma contactor units (PCUs) were being deployed to provide for emission of electrons collected by the arrays thus bringing the potential closer to zero and mitigating the arcing danger, however no means was in place to verify that the PCUs were working. In late July 2000, the ISS program office at JSC issued an engineering change notice that directed the development of some means to independently assess the performance of the PCU’s, and to have hardware available for launch on STS-97 (ISS Flight 4A) the very mission scheduled to deliver and install the first set of large Station solar arrays on November 30th. Such a schedule allowed only 4.5 months to design, build, test, manifest, complete EVA training, and deliver for launch. NASA Glenn Research Center (GRC), NASA Johnson Space Center (JSC), and Design_Net Engineering (DNet) formed a unique team to try to accomplish the directive. Previous papers (1,2) have discussed in detail the design of the FPP and some of the programmatic lessons that were learned which are applicable to responsive space. In addition to these lessons, a number of engineering and technological innovations are required to support responsiveness. Design_Net has expanded the lessons from the FPP responsive bus to more generic application. In this paper will focus our attention on three key aspects from a technological point of view that support rapid response. We focus on: 1) the systems engineering process and the technologies and tools that are enablers for rapid design/configuration in the early stages of a program; 2) the interaction of configurability with requirements and; 3) the role of standards and Plug and Play (PnP) capability in achieving rapid development and integration. | |
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| Paper Number RS3-2005-6006: A Rocket-Powered Technology Demonstrator for Responsive Access to Space | |
| Daniel P. Raymer (Conceptual Research Corporation), Jess Sponable (AFRL), Timothy Fry (University of Dayton Research Institute), Jeremy Zanzig (Analytical Methods), Jared R. Ethier (Composite Engineering), Mitchell Burnside Clapp (Pionneer Rocketplane) | |
| View/Download:Presentation | Paper | |
| Abstract: A six-company team headed by Conceptual Research Corporation is developing a design concept for a rocket-powered technology demonstrator under funding from USAFWPAFB, with administrative and technical assistance from the University of Dayton Research Institute. This “Micro-X” demonstrator offers affordable and incremental demonstration of responsive space access system concepts and enabling technologies, and will demonstrate high-tempo reusability in an operational environment. To keep the program affordable, the Micro-X demonstrator will have an empty weight of less than 10,000 lbs yet will be capable of reaching space altitudes and hypersonic speeds. | |
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| Paper Number RS4-2006-3006: HexPak Testbed Development | |
| Michael Hicks (Lockheed Martin Advanced Technology Center, Palo Alto, CA), Michael Enoch (Lockheed Martin Advanced Technology Center, Palo Alto, CA), Larry Capots (Lockheed Martin Advanced Technology Center, Palo Alto, CA) | |
| View/Download:Presentation | Paper | |
| Abstract: HexPak is a scalable spacecraft structure with the requisite features that enable responsive space missions. The structure consists of hexagonal equipment/payload bays with embedded harnessing to support multiple mission-specific component layouts. Scalability is supported via embedded network connectivity for plug’n’play avionics and expansion bays. The hexagonal bays are stacked for launch in a self-supporting structure which efficiently packs in the launch fairing, and deploys on orbit to form a large deployed aperture for payload equipment. The large deployed area provides large aperture payloads un-inhibited viewing angle. Since the structure is self-supporting, multiple payloads and multiple manifest are possible with minimal mass impact due to launch support structures. Since each bay is fabricated and tested individually, and easily accessible from all sides, the time/unit mass to manufacture a complete spacecraft is greatly improved over more traditional structures. For missions that require a large number of platforms, the modular structure offers easy interchangeability of HexPak bays which makes it possible to maintain a consistent production flow even during periods of parts shortages. Standard physical interfaces also allow for commonality in tooling, fixturing, testing and ease of satellite integration. The hexagonal geometry is near optimum for taking advantage of available faring envelopes and the folded structure is self-supporting, which minimizes the need for additional structure to support launch. A full-scale mechanical testbed for demonstration of HexPak deployment was built last year and is described, along with the physical integration of a JINI based plug’n’play network onto the structure. Because the structure and C&DH system are physically scalable, their combination provides a clear route for the transfer of the rapid integration advantages of responsive space to more traditional missions. | |
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| Paper Number RS4-2006-4003: Development of the Tactical Satellite 3 for Responsive Space Missions | |
| Thomas M. Davis (AFRL), Capt. Stanley D. Straight (USAF AFRL) | |
| View/Download:Presentation | Paper | |
| Abstract: Numerous Department of Defense studies show implementing a responsive satellite capability provides for significant military utility to augment or surge current space capabilities. The TacSat concept explores the capability/technological maturity of small, low-cost satellites with the most prominent efforts currently being conducted within the Science and Technology (S&T) Program. In addition to providing for ongoing innovation and demonstration in this important technology area, these S&T efforts also help mitigate technology risk and establish a concept of operations (CONOP) for future acquisitions. TacSat efforts underway by the Air Force Research Laboratory (AFRL) and the Naval Research Laboratory (NRL) are focused on demonstrating small (<500kg), operationally responsive, low-cost satellite and launch capabilities to support warfighter. AFRL’s Space Vehicles Directorate is leading the Tactical Satellite 3 (TacSat-3) team and partners include Space and Missiles Center Detachment 12, the Army Space Battle Laboratory, the Air Force Space Warfare Center, the Office of Naval Research, and the DoD Office of Force Transformation. Building on the experiences with TacSats 1 and 2, TacSat-3’s mission was vetted through a formal payload selection process with Air Force Space Command (AFSPC) and Combatant Commands (COCOMs). TacSat-3’s mission was selected for specific capabilities to meet user needs, and to demonstrate those capabilities within cost and schedule constraints. A building block for Operationally Responsive Space, TacSat-3 will experiment with a Hyperspectral Imaging (HSI) capability direct to the tactical warfighter within 10 minutes of a collection opportunity. The TacSat-3 demonstration features a low cost “plug and play” modular bus and low cost militarily significant payloads – a Hyperspectral Imager and a secondary payload demonstrating data exfiltration provided by the Office of Naval Research. TacSat-3 will demonstrate evolutionary steps and traceability towards objective system goals for the capabilities and processes including rapid response to a user defined need for material detection and identification, and battle damage assessment. Additionally, it will demonstrate traceability to enable launch processing at the launch base faster than 7 days. Finally, it will feature a rapid development of the space vehicle and integrated payload and spacecraft bus by using components and processes developed by the Operationally Responsive Space Modular Bus program. Design constraints established for the TacSat-3 program include a total program cost to be less than $50M, to fit on a low cost responsive space booster and a satellite weight of less than 400 kilogram, with a build time for payload and modular bus of less than 18 months. The TacSat-3 CONOPS breaks old paradigms and gives COCOMs first realistic opportunity for responsive, dedicated space capabilities at the operational and tactical level. The TacSat-3 spacecraft will collect and process images and then downlink material ID text and geolocation or downlink full data image using a Common Data Link. An in-theater tactical ground station will have the capability to uplink tasking to spacecraft and will receive full data image. | |
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| Paper Number RS4-2006-4004: Sounding Rocket Technology Demonstration for Small Satellite Launch Vehicle Project | |
| John Tsohas (Purdue University), Lloyd J. Droppers (Purdue University), Stephen D. Heister (Purdue University) | |
| View/Download:Presentation | Paper | |
| Abstract: Purdue University is embarking on a program to demonstrate technologies critical to the development of a small satellite launch vehicle. The first phase of the program involves design, fabrication, testing and flight of a hybrid propulsion sounding rocket from the NASA Wallops flight facility. This paper details the design and test work that has been achieved to date. Propulsion work includes successful hot fire tests of a flight weight, 180 lbf thrust hydrogen peroxide / HTPB hybrid rocket motor at the Purdue rocket test facilities. The tests confirmed the structural integrity of the engine, verified the thermal insulation ablator design, helped determine solid grain regression rate and verified the engine performance characteristics with the internal ballistics simulation code. Detailed design of vehicle plumbing, structure, propulsion, avionics, and recovery subsystems has been completed. The rocket consists of a carbon-fiber composite aero-structure, welded aluminum oxidizer tank, and a fiberglass composite internal structure. A nitrogen blowdown system is used to provide the engine with oxidizer, and the recovery system has dual redundancy. In addition, detailed design has been completed on the ground support equipment used for remote loading and draining operations of liquid hydrogen peroxide to and from the vehicle, while monitoring critical vehicle parameters. Remote disconnect of umbilical cords, engine ignition, launch and aborts are also functions of the ground support equipment. A trajectory analysis and vehicle aerodynamics code was developed to design the vehicle geometry, stability, and mass allocation. Follow-on flights of the technology demonstration vehicle will include the addition of a pressure fed cycle and a thrust vector system with associated guidance and control hardware and software. The second phase of the paper details the conceptual design of a small satellite launch vehicle designed to place 10 lb university or research payloads in low Earth orbit. In order to make use of the already existing rocket test facilities at Purdue and to keep test costs low, the thrust of the first stage engine was constrained to less than 10,000 lbf. To reduce costs associated with structural design, analysis and manufacturing, a three stage launch vehicle with a low propellant mass fraction for each stage (~76%) would be designed. Hybrid propulsion would be used due to its relative simplicity and safety over liquid bi-propellant systems. Hydrogen peroxide would be used as an oxidizer due to the high density Isp and its non-toxic, and non-cryogenic properties. This would lead to a reduction in operations costs and increased safety in propellant handling in comparison with other candidate oxidizers. A small composite solid propellant third stage would provide the final delta-V at the desired orbital altitude. Thus, a three stage launch vehicle with a GLOW of 6,400 lb and 8,700 lbf thrust first stage engine would satisfy the above design requirements. | |
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| Paper Number RS4-2006-5001: SciBox Based Uplink Operations Planning Concepts for Responsive Space | |
| Andy McGovern (Johns Hopkins University Applied Physics Laboratory) | |
| View/Download:Presentation | Paper | |
| Abstract: Time sensitive targeting is of keen interest in the C2 arena. Implementations of this concept also appear in civilian space missions in the form “responsive targeting,” meaning an unexpected event warrants a rapid response. The goal in both C2 and civilian arenas is to quickly produce the desired effect at minimal cost and low risk. Techniques that greatly simplify and streamline the processes of mission planning, command sequence generation and command upload have been developed in the civilian space arena by the Applied Physics Laboratory of Johns Hopkins University. We have developed innovative mission operations techniques and software tools for the CRISM instrument on board the Mars Reconnaissance Orbiter (MRO). CRISM is a gimbaled visible/infrared spectrometer for analyzing the Martian surface and atmosphere. CRISM’s gimbaled platform and MRO’s roll capabilities make responsive targeting and pointing a challenge that we have addressed. We streamline the process of planning, command sequence generation and upload by linking flight software with planning software via a macro library and a visualization tool. Our approach enables the scientist (or the field commander) to directly task the instrument without the need of an operations support center. Part of CRISM’s mission is to target dust storms which form and dissipate rapidly during one season. Our approach, which enables the scientist to command the instrument at a high level and visualize predicted results, is critical for these time sensitive observations. This presentation provides an overview of our approach to responsive targeting in the context of the CRISM mission and how it may be implemented for responsive space systems. | |
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| Paper Number RS4-2006-4005: Responsive Space's Spacecraft Design Tool (SDT) | |
| Robert Strunce (Star Technologies), Fred Eckert (Star Technologies), Craig Eddy (Star Technologies) | |
| View/Download:Presentation | Paper | |
| Abstract: Star Technologies Corporation has developed a “.Net Framwork Simulation Architecture”, “Spacecraft Design Tool” (SDT), which is an open framework for Responsive Space’s rapid design concept spanning mission capture to deployment. SDT has been incorporated in all the test cells at AFRL’s Responsive Space Test Bed. SDT is integrated into the Mission Design phase for spacecraft simulation and analysis as well as providing the spacecraft dynamics/kinematics, earth environment, and sensor/actuator models in the real time hardware-in-the-loop (HITL) test cells. SDT can simulate a sensor/actuator, or interface to its respective hardware emulator or interface to the actual hardware through the Responsive Space’s Plug-n-Play (PnP) electronic environment. SDT provides a true software PnP environment where the User can seamlessly inherit properties from within SDT as well as add his own component or subsystem capabilities such as complex propulsion or electrical power subsystem. SDT has a 3D Visual game engine for display of the earth, sun, moon as well as multiple articulated spacecraft. SDT has been used to model TacSat2, a generic Responsive Space satellite, and TacSat3. SDT provides an environment for rapid prototyping of spacecraft using true software PnP of components and subsystems. In other words, the SDT application recognizes new components such as attitude control sensors and actuators in the same way that your computer recognizes that a new printer has been added. This is accomplished through the latest software technologies of COM and .NET Framework. The .NET Framework provides a higher level of interoperability than COM especially over networks and the internet where COM is a subset of the overall capability. Under the .NET Framework, objects such as a specific Sun Sensor can be written in any language (C#, C++, Fortran, ADA, Basic, Perl) and execute on different computer platforms (PC, PowerPC, Sun) and under different operating systems (Windows, Solaris, Linux). Although SDT is currently aimed at spacecraft, the “.Net Framwork Simulation Architecture” can be applied to any multi-body dynamic system such as launch vehicles, robotics or land rovers. SDT has supported NASA efforts in electro-dynamic tethers as well as tethers employed in future NASA Scientific Missions such as SPECS or TetraStar and is hosted in GSFC’s Formation Flying Test Bed (FFTB). This paper will discuss the implementation and utilization of SDT within the AFRL’s Responsive Space Test Bed. | |
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| Paper Number RS4-2006-7004: Navy Team Responds to Bandwidth Challenges in Support of War Efforts with Innovative Employment of UHF Follow-On (UFO) and LEASAT Satellites | |
| Mike Mattis (Maxim Systems, Inc.), Neil Butler (Maxim Systems, Inc.), Jack Turner (Maxim Systems, Inc.) | |
| View/Download:Presentation | Paper | |
| Abstract: The U.S. Navy’s UFO satellite constellation is the replacement for the Fleet Satellite (FLTSAT) and LEASAT spacecraft and maintains the Navy’s global narrowband communications network. In mid 2002, the operational community expressed the need for increased narrow-band bandwidth in support of Operation Enduring Freedom (OEF). The Naval Networks and Space Operations Command (NNSOC) and the Navy Communications Satellites Program (PMW146) were tasked to investigate methods to increase narrow-band capacity. The 11th UFO spacecraft would not be available until the second quarter of FY04 so the UFO/LEASAT team examined a wide variety of options, including employment of the UFO on-orbit spare satellite (UFO-2). Analysis and testing proved a frequency reuse scheme could allow 12 UFO-2 channels to be turned on to result in a 30% capacity increase in the CENTCOM Area Of Responsibility (AOR). This improved capacity realized by the warfighter in support of OEF saved approximately $1M/month for equivalent commercial services. In Oct 2002, the UFO/LEASAT team, acting as the Acquisition agent for the Joint Staff, inquired about the cost and availability of LEASAT satellites to support emerging bandwidth requirements in the CENTOCM AOR utilizing some of the new frequency reuse techniques developed for UFO-2. Although the LEASAT contract had been terminated once the UFO constellation was deployed; the Program Office coordinated an acquisition scheme with the Royal Australian Navy and negotiated a Memorandum of Agreement with the Australian Ministry of Defense to procure services and share LEASAT-5. To better support users, Strategic Command (STRATCOM) requested LEASAT-5 be moved to the Indian Ocean (IO) to support emerging requirements for Operation Iraqi Freedom (OIF). The UFO/LEASAT team obtained approval for LEASAT-5 reactivation and coordinated use of the Guam TT&C equipment to support the relocation effort. Even after the TT&C facility in Guam was unexpectedly destroyed by a typhoon in December 2002, a new TT&C site in Australia was brought on line, avoiding a three-month delay of the satellite repositioning effort and enabling immediate initiation of the move. Upon receipt of funding and final approval from the Joint Staff, the UFO/LEASAT team had the LEASAT contract modification fully funded and the LEASAT-5 spacecraft moving within 24 hours. In response to this urgent requirement to provide an additional SATCOM asset in the IO, STRATCOM also requested development of a situational awareness tool that could be used by warfighters and communications planners to show LEASAT-5 availability as it was being moved into theater. The team used Satellite Tool Kit (STK) modeling software to produce a simple self extracting flash video tool that could be quickly sent to communications planner and warfighters in country to determine when link closure would occur as the satellite drifted west to its final station. Often time Responsive Space is thought of as responsive launch. In this case the Navy utilized innovative reuse of existing assets and applied new Concepts of Operations (CONOPS) to identify additional assets and support mechanisms to rapidly mobilize additional SATCOM bandwidth to support the Warfighter. | |
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| Paper Number RS6-2008-1005: TREADS – Launching Responsive Space Opportunities | |
| Steve Wichman (Redefine Technologies) | |
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| Abstract: The Testbed for Responsive Experiments and Demonstrations in Space (TREADS) is a technology demonstration and scientific gathering platform specifically designed to allow investigators to easily, and quickly, integrate and launch their instrumentation into a 'full-service' operational environment. The payloads can be: new components increasing their Technology Readiness Levels (TRLs) in order to reduce risks; or tactical instruments that can not wait for multi-million dollar, dedicated missions. Redefine Technologies has developed various configurations of the TREADS platform. Instruments such as board-level electronics (i.e. mass storage units, flight computers and hardware support modules), software (i.e. mission managers, artificial intelligence, or device drivers), or full components (i.e. scientific instruments, momentum wheels, solar panels, mechanisms, or other subsystems) can easily be accommodated on any of the testbed variants. TREADS offers payload capacities from 0.5kg electronic boards, to 2kg hardware stand-alone components, to 15kg free-flying payloads. Power allocations range from 5W to 30W accordingly. TREADS is a recurring, mission of opportunity (i.e. not just one flight) designed to provide affordable access to space for technology demonstration and scientific instrumentation. The adapter ring that mounts TREADS and the instruments to the launch vehicle is already qualified on two launch vehicles: Falcon I and Minotaur I. Other agreements with other launch providers are being worked and acceptance is anticipated within 12 to 24 months. TREADS also is being fitted to the Atlas 5 for a GTO demonstration. TREADS can be launched to almost any orbital position: Low, Medium and High Earth Orbit (LEO, MEO, HEO), as well as to Geo-Transfer Orbit (GTO). All TREADS missions provide the customer with several months, to several years on-orbit. Before launch, TREADS offers a comprehensive, pre-integration test environment. The entire spacecraft can be 'assembled remotely' prior to any hardware actually being shipped to the bus location. This Distributed Wiring Harness (DWH) will be an instrumental tool in determining early compatibility issues and determining optimum mission operational procedures. After launch, TREADS will provide an operational environment for fully testing and using the technology payload. The TREADS mission operations is very flexible and will support the customer in running the experiments on-board the platform and retrieving the data. TREADS can help the Air Force's Responsive Space mission by serving as a testbed platform for various instruments, as an 'incremental build-up capability" for situational awareness, or as an inexpensive demonstration platform that will prove out concepts and technologies quicker and easier than dedicated missions. This paper will investigate the various ways the Air Force can use TREADS to advance their Responsive Space objectives. Example mission profiles will be presented and how they provide tactical and strategic advantages to the joint service community. The freedoms and limitations of the platform will be discussed, as well as the Distributed Wiring Harness approach to simplifying integration and test headaches. | |
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| Paper Number RS6-2008-2004: Rapid Deployment of Proof-of-Concept Missions | |
| Jeffrey S. Cain (COM DEV Ltd.), Franz Newland (COM DEV Ltd.), F. Pranajaya (University of Toronto), R. Zee (University of Toronto) | |
| View/Download:Presentation | Paper | |
| Abstract: COM DEV Ltd. has recently completed two programs that made use of highly responsive space solutions to provide proof-of-concept data for an on¬going project dealing with the reception of Automatic Identification of Ships (AIS) signals from space. The first program, QuickAIS, was designed to fly a simple payload – essentially equivalent to a commercial-grade AIS receiver – with the purpose of determining what signals could be collected using existing, standard technology: a relatively simple question. This mission was based on the Rubin platform, with the payload connected directly to the upper stage of a Dnepr launcher. The launcher had been augmented to provide power and space-ground communications through the Orbcomm network. The mission payload was developed within 60 days, was launched in November 2007 and is currently in operation. The second program, Nanosatellite Tracking of Ships (NTS) was developed to answer a number of precise questions regarding the AIS signal environment from space. This mission, based on the UTIAS CanX2 bus, has been designed, developed and readied for flight in less than 6 months. The two missions varied in complexity and involved rapid development of payloads that met the mission objectives. The QuickAIS program was accomplished using a combination of modifying existing COTS products for flight and the addition of limited new RF components. The payload development for the NTS program was more comprehensive and involved the development of a new design using some of the components developed during QuickAIS and an entirely new digital back-end. The experiences gained by the COM DEV team and its partners while implementing these missions are elaborated upon in this paper. These cover the whole project lifecycle, from mission concept definition through delivery for launch. Both programs showed that it is possible to develop very reactive mission solutions to answer precise questions. This nonethe¬less depends on a number of prerequisites, such as a solid understanding of the mission objectives and a real-time interpretation of how they will be impacted by design decisions taken during the procurement phase. It is also imperative to start from an existing platform and/or payload design that meet the majority of the mission requirements, and have key hardware available at kick-off. The COM DEV team, starting from a hard contractual date for launch delivery, performed a number of innovative design trades, including difficult compromises on system performance whilst still meet¬ing mission objectives. This included accepting higher levels of risk, for example by using processes and parts with no flight heritage, where part alternatives based on supply availability were chosen in order to meet de¬velopment schedules. Testing was also reduced to address elements needed for mission data interpretation, or that could be fixed in the time available. These and other key elements that led to the successful execution of these programs are presented and explored in this paper. | |
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