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Electric Propulsion Demonstration Module ( EPDM ) Flight Hall Thruster System
| Content Provider | Semantic Scholar |
|---|---|
| Author | Lynn, Peter R. Osbom, Michael F. Arseni, C. John Sankovic |
| Copyright Year | 1998 |
| Abstract | The Naval Research Laboratory (NRL) has completed the United States’ fint flight Hall thruster propulsion system. The mission objective of the Electric Propulsion Demonsaation Module (EPDM) program is to assemble and fight demonstrate an electric propulsion system, based on maturing technology, that evaluate8 system capability and operational utility. The 600 W xenon Hall thruster system will be used on a low earth orbiting spacecraft to provide orbit raising as well as stationkeeping for a life of 3 years. The EPDM system consists of 4 subassemblies; the xenon fiow system (XP!J). the power processor (PPU), the auxiliary interface unit (AIU), and the engine assembly. The modular nature of the design allows for ease and flexibility of integration onto the spacecraft. The technology being etiuated is a electrostatic propulsion device. specifically a Thruster with Anode Layer CTAL). The EPDM program is being run by the Naval Center for Space Technology (NCST) at NRL. The Ballistic Missile Defense Office (BMDO) in conjunction with the National Aeronautics and Space Administration (NASA) Lewis Research Center has sponsored the development of the TAL thruster, power processor, and flow system technology being used by EPDM. NASA Lewis is also assisting in the qualification and testing of the EPDM hardware. The TAL thruster is a Russian Hall thruster technology developed by the Central Scientific Research Institite of Machine Building (TsNIIMash) in Korolev, Russia. The power processor is developed by Primex Aerospace Co. The EPDM program is a cooperative D&/NASA effort with expertise. fiscal sponsorship, and national space test beds from across the govemrnent used to successfully implement the program. The EPDM system will fly in 1998. providing the first use of Hall thruster electric propulsion technology in the United States. INTRODUCTION During the 1990 s the Department of Defense (DoD), specifically the Ballistic Missile Defense Office (BMDO) and it’s predecessor the Strategic Defense Initiative Office (SDIO) identified and evaluated advanced propulsion technologies in the former Soviet Union. The BMDO’s Russian Hall Thruster Technology (RHE’IT) program centered around developing western power processors to operate the hall thrusters as well as extensive thruster testing to understand spacecraft interaction issues, lifetime capability, power handling, and stability.’ These investments were also the “seedcorn” for the EPDM program. With several power processing units (PPU) in development and qualification in the US, the time was ripe to bring a complete system together for a flight demonstration and validation of the technologies. In September of 1995 NRL, was tasked to develop a flight hall thruster system and deliver it for integration on the host spacecraft by March of 1997. The EPDM system is now integrated onto the host vehicle and preparing to launch in early 1998. MISSION DEXXIPTION The EPDM mission consists of two parts, an orbit transfer phase, and a stationkeeping phase. The host spacecraft will be launched into a low earth orbit (LEO) and remove initial orbit errors via an on-board conventional chemical propulsion system. After initial orbital errors are removed, the EPDM system will perfom several days of orbit raising. Once at the final orbit, EPDM will provide 3 years of on-orbit precision stationkeeping. |
| File Format | PDF HTM / HTML |
| Alternate Webpage(s) | http://erps.spacegrant.org/uploads/images/images/iepc_articledownload_1988-2007/1997index/7100.pdf |
| Language | English |
| Access Restriction | Open |
| Content Type | Text |
| Resource Type | Article |
