The Air Force Research Laboratory, Space Vehicles Directorate (AFRL/RV) has developed the Demonstration and Science Experiments (DSX) mission to research technologies needed to significantly advance Department of Defense (DoD) capabilities to operate spacecraft in the harsh radiation environment of Medium-Earth Orbits (MEO). The ability to operate effectively in the MEO environment significantly increases the DoD's capability to field space systems that provide persistent global space surveillance and reconnaissance, high-speed satellite-based communication, lower-cost GPS navigation, and protection from space weather and environmental effects on a responsive satellite platform. The three DSX physics-based research/experiment areas are:1. Wave Particle Interaction Experiment (WPIx): Researching the physics of Very-Low-Frequency (VLF) electromagnetic wave transmissions through the ionosphere and in the magnetosphere and characterizing the feasibility of natural and man-made VLF waves to reduce and precipitate space radiation;2. Space Weather Experiment (SWx): Characterizing, mapping, and modeling the space radiation environment in MEO, an orbital regime attractive for future DoD, Civil, and Commercial missions; and 3. Space Environmental Effects (SFx): Researching and characterizing the MEO space weather effects on spacecraft electronics and materials.Collectively, thirteen individual payloads are combined together from these three research areas and integrated onto a single platform (DSX) which provides a low-cost opportunity for AFRL due to their common requirements. All three experiments require a 3-axis stabilized spacecraft bus (but no propulsion), a suite of radiation sensors, and extended duration in a low inclination, elliptical, MEO orbit. DSX will be launch-ready in summer 2010 for a likely launch comanifest with an operational DoD satellite on an Evolved Expendable Launch Vehicle (EELV).Keywords: Wave Particle Interaction, electromagnetic wave transmissions, space radiation, characterization of MEO MISSION OBJECTIVESThe top-level objectives for the DSX space flight experiment are to investigate the electromagnetic wave-particle (electron, proton, ion) interaction in the MEO region of space between the Van Allen radiation belts, also known as the 'slot' region; to collect space weather data in the slot region; and to collect data on the degradation of microelectronics, thermal, optical, and mechanical structures, surfaces, and coatings in the slot region. DSX is planned for an objective mission life of one year 1 due to the amount of data expected to be collected and required to meet program objectives, and due to normal operating procedures at the Space and Missile Systems Center (SMC) Research, Development, Test, and Evaluation (RDT&E) Support Complex (RSC) at Kirtland Air Force Base (KAFB) for flying experimental satellite missions.The overall primary objective of DSX is to resolve critical feasibility issues of injecting VLF waves into the magnetosphere to determine how efficiently, how effe...
Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) AND ADDRESS(ES) PERFORMING ORGANIZATION REPORT NUMBERComposite Technology Development, Inc 2600 Campus Drive Suite D Lafayette, CO 80026 SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S) *Air Force Research LaboratorySpace Vehicles 3550 Aberdeen Ave SE SPONSOR/MONITOR'S REPORTKirtland AFB, NM 87117-5776 NUMBER(S) AFRL-VS-PS-TP-2006-1025 DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. (Clearance #VS06-0130) SUPPLEMENTARY NOTESPublished in the 47 th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference Proceedings, 1 -4 May 2006, Newport, RI Government Purpose Rights ABSTRACTFuture small spacecraft will have a need for lightweight, highly reliable, and cost-effective mechanisms for the deployment of radiators, solar arrays, and other devices. To meet this need, Composite Technology Development, Inc. has developed TEMBO® Elastic Memory Composite (EMC) materials, which accommodate very high folding strains without damage, while providing very high deployed stiffness-and strength-to-weight ratios. Over the past few years, CTD has developed and performed extensive ground testing on a TEMBO® EMC deployment hinge for radiators, solar arrays and other deployable spacecraft components. The present paper will discuss the details of two flight experiments to validate the TEMBO® EMC hinge design on-orbit. In particular, the paper will discuss: 1) detailed design of the flight hardware for both experiments; 2) ground-verification and acceptance testing of the flight hardware; and 3) status of the flight missions. Future small spacecraft will have a need for lightweight, highly reliable, and costeffective mechanisms for the deployment of radiators, solar arrays, and other devices. To meet this need, Composite Technology Development, Inc. has developed TEMBO ® Elastic Memory Composite (EMC) materials, which accommodate very high folding strains without damage, while providing very high deployed stiffness-and strength-to-weight ratios. Over the past few years, CTD has developed and performed extensive ground testing on a TEMBO ® EMC deployment hinge for radiators, solar arrays and other deployable spacecraft components. The present paper will discuss the details of two flight experiments to validate the TEMBO ® EMC hinge design on-orbit. In particular, the paper will discuss: 1) detailed design of the flight hardware for both experiments; 2) ground-verificati...
Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing this collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)AFRL/VSSV Air Force Research Laboratory* Space Vehicles Directorate Advanced solar arrays capable of generating greater than 50 kW of total power, at power densities greater than 250 W/kg, are required for many future Air Force missions. The largest heritage systems are limited to less than 20 kW of total power, at roughly 80 W/kg. To meet the requirements of future Air Force missions, the Rollout And Passively Deployed ARray (RAPDAR™) has been developed. This innovative, patent-pending design takes full advantage of the latest advances in thin-film photovoltaic and TEMBO® Elastic Memory Composite (EMC) deployment technologies. A key feature of the design is the use of solar energy to passively actuate the TEMBO® EMC members and deploy the array. The present paper addresses the development and validation of detailed designs for the RAPDAR™ (patent applied for) structural system. Specific focus is placed on comparing the performance projections of RAPDAR™ with other thin-film array systems, and the development and validation of the EMC longerons, which are the primary structural members for the RAPDAR™ system controlling packaging and deployment, and providing primary stiffness and strength to the deployed system. The present paper addresses the development and validation of detailed designs for the RAPDAR™ (patent applied for) structural system. Specific focus is placed on comparing the performance projections of RAPDAR™ with other thin-film array systems, and the development and validation of the EMC longerons, which are the primary structural members for the RAPDAR™ system controlling packaging and deployment, and providing primary stiffness and strength to the deployed system. SUBJECT TERMS
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