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 NUMBERPhysical Sciences Inc 20 New England Business Ctr Andover, MA 01810-1077 SPONSORING / MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONSOR/MONITOR'S ACRONYM(S)*Air Force Research Laboratory AFRL/VSEA Space Vehicles 3550 Aberdeen Ave SE SPONSOR/MONITOR'S REPORTKirtland AFB, NM 87117-5776 NUMBER(S) DISTRIBUTION / AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTESPresented at 41 st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 10-13 Jul 05, Tucson, Arizona. Government Purpose Rights ABSTRACTThis paper discusses results of a program to develop an innovative solar thermal propulsion system for application to orbit change and mobility for small spacecraft. In this system, solar radiation is collected by the concentrator which transfers the concentrated solar radiation to the optical waveguide cable consisting of low-loss optical fibers. The optical waveguide cable transmits the high intensity solar radiation to the thermal receiver for efficient, high performance thrust generation. Through the course of the preceding program, we have demonstrated the base for the system hardware. This paper discusses results of the program to develop and evaluate an engineering model of the solar thermal propulsion system based on the OW technology. This paper discusses results of a program to develop an innovative solar thermal propulsion system for application to orbit change and mobility for small spacecraft. In this system, solar radiation is collected by the concentrator which transfers the concentrated solar radiation to the optical waveguide cable consisting of low-loss optical fibers. The optical waveguide cable transmits the high intensity solar radiation to the thermal receiver for efficient, high performance thrust generation. Through the course of the preceding program, we have demonstrated the base for the system hardware. This paper discusses results of the program to develop and evaluate an engineering model of the solar thermal propulsion system based on the OW technology. SUBJECT TERMS
AeroAstro's patented RF Probe 1 is a system designed to address the needs of spacecraft developers and operators interested in measuring and analyzing near-field RF emissions emanating from a nearby spacecraft of interest. The RF Probe consists of an intelligent spectrum analyzer with digital signal processing capabilities combined with a calibrated, wide-bandwidth antenna and RF front end that covers the 50 kHz to 18 GHz spectrum. It is capable of acquiring signal level and signal vector information, classifying signals, assessing the quality of a satellite's transponders, and characterizing near-field electromagnetic emissions. The RF Probe is intended for either incorporation as part of a suite of spacecraft sensors, or as a stand-alone sensor on spacecraft or other platforms such as Unmanned Aerial Vehicles (UAVs). The RF Probe was initially conceived as a tool to detect and aid in diagnosis of malfunctions in a spacecraft of interest. However, the utility of the RF Probe goes far beyond this initial concept, spanning a wide range of military applications. Most importantly, the RF Probe can provide space situational awareness for critical on-orbit assets by detecting externally induced RF fields, aiding in protection against potentially devastating attacks.
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