The High Performance Hal! System (HPHS) program supports the development and llight qualilication of a 45 k\?' electric propulsion system that includes the SPT-140 Hall thruster. The Air Force Research Laboratory (AFlU) and International Space Technology, Inc. (ISTI) arc co-funding the HPHS program which is being conducted by a team led by Atlantic Research Corporation @RC). The team includes ISTI, Experimental Design Bureau Fake1 (Fakel), and Space Systems/Loral (S/SL). The Research Institute of Applied hlechamcs and Electrodynamics (RIAME) also provided support for this project. The SPf-l-l0 is being designed developed, manufactured, and tested by Fake1 in Kaliningrad, Russia, where extensive performance testing and advanced development have been performed. In addition to the testing in Russia, a suite of experiments on the development model and the qualification model thrusters, sponsored by the US Go\.emment, has occurred during 1999 and is scheduled to occur in 2000. These experiments include thruster performance, plume characterization, electromagnetic compatibility, and life characterization, This paper presents the stahis of government testing of the SPT-1-l-O in the United States. ,.

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The Small Probes for Orbital Return of Experiments (SPORE) flight system will provide low-cost on-orbit operation, Earth return and recovery for small payloads. The SPORE flight system design includes a service module for orbital operations and de-orbit capability, and an entry vehicle to perform entry, descent and landing. The SPORE system architecture is scalable, allowing payload sizes ranging from the CubeSat standard one-unit (1U) configuration 2U and 4U configurations. Experiments including biological science, materials science, and thermal protection system flight demonstrations are targeted applications for SPORE. The flight system can be launched as either a primary or secondary payload into low-Earth orbit or geosynchronous transfer orbit. It can also be deployed from the International Space Station. This paper describes the driving requirements for the SPORE system architecture. Conceptual designs for the service module and entry vehicle are provided, and launch vehicle and ISS interfaces are discussed. Future work leading to SPORE commercialization is described. NomenclatureEDL = entry, descent and landing EELV = Evolved, Expendable Launch Vehicle ESPA = EELV secondary payload adapter GTO = geosynchronous transfer orbit I sp = specific impulse ISS = International Space Station LEO = low-Earth orbit RCS = reaction control system RF = radio frequency SPORE = Small Probes for Orbital Return of Experiments