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Dual Mode Bpt-4000 Hall Thruster Rev. Date: 4/02/03 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export DUAL MODE BPT-4000 HALL THRUSTER 20.3 cm 5.8 cm (8.0”) (2.3”) 14.9 cm (5.5’) MOUNTING INTERFACE Design Characteristics Performance 2.0 kW 3.0 kW 4.5 kW Propellant . Xenon Thrust (300 Volts). 132 mN 195 mN 290 mN Mass (Thruster & Cathode) . <12.3 kg Thrust(400 Volts) . 117 mN 170 mN 254 mN Envelope . 14 x 25 x 28 cm Specific Impulse (300 V) 1676 sec 1700 sec 1790 sec Input Power . 1000 to 4500 Watt Specific Impulse (400 V) 1858 sec 1920 sec 2020 sec Input Voltage . 200 or 400 Volt Life Capability . >10,000 hr Status (as of Feb. 2006) Total Impulse . >5.5 x 106 N-sec Qualification Complete On/Off Cycles . 6,700 Cycles >6,700 hours Demonstrated, Additional Life Testing Planned Reference >6,300 Cycles Demonstrated, Additional Life Testing AIAA-2005-3682 Planned Date: 6/19/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 fax (425) 882-5747 2 Approved for Public Release and Export Rev. Date: 5/23/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export Rev. Date: 5/23/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export MR-502 & MR-502A IMPEHT POWER CONDITIONING UNIT 27.94 cm (11.0”) 13.97 cm (5.50”) 6.731 cm (2.65”) 1.60 cm (.63”) Power Conditioning Unit P/N 34830 14.605 cm (5.75”) Design Characteristics Demonstrated Performance Mass . 2 kg Limits inrush current to the 30 Amps during Envelope . 27.94 x 9.42 x 14.61 cm augmentation heater warm-up Two identical independent channels that can be Input Voltage . .15-29.9 vdc operated either redundantly or simultaneously Inrush Current . 32 Amp Max When used simultaneously, the IMPEHT pair should be started one after the other Efficiency . >97% Status Interface Flight Proven Enable/Disable Command . Latch Relay Drive On/Off Command . 0V – Off, 14V – On Date: 2/22/05 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 fax (425) 882-5747 5 Approved for Public Release and Export Rev. Date: 5/23/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export Rev. Date: 5/23/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export Rev. Date: 5/23/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export PRS-101 Pulsed Plasma Thruster System Design Characteristics Performance Propellant . Teflon® (Solid Bar) Specific Impulse . Up to 1350 sec Max Thrust Level1 . 1.24 mN @ 100 Watts Thrust to Power Ratio . 12.4 N/Watt Power Level . Demonstrated Capability. .3,000 N-sec/thruster . Up to 100 Watts @ 28 vdc Unregulated Predicted Capability (backed by selective testing) . Compact Solid State Propulsion System . 15,600 N-sec/system (thruster pair) Ultra Low Minimum Impulse Bit for Precision Control Status Enables All-thruster ACS (No Momentum Wheels) Flight Proven Mass (w/o propellant) . 4.74 kg Reference Includes Integral Power Processing Electronics Power Efficiency . >80% AIAA-2003-5016 AIAA -2001-3637 AIAA-2002-3973 AIAA-1999-3376 Rev. Date: 4/14/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export Gridded Ion Engine Technology NEXT 6.9 kWe Ion Thruster and Propellant Management System (with NASA GRC) NEXIS 20 kWe Ion Thruster (with JPL) HiPEP 25 kWe Ion Thruster (with NASA GRC) Low Power Ion Thruster 0.5 kWe Ion Propulsion System (with NASA GRC) NSTAR-class 2.5 kWe Ion Thruster Power Processing Digital Controllers Xenon Propellant Management Systems 10 Approved for Public Release and Export NEXT 6.9 kW Ion Propulsion System Thruster, Propellant Management System, Digital Control Interface Unit High Pressure Assembly Low Pressure Assembly Thruster Assembly Propellant Management System Design Characteristics Performance Propellant …………………………..…………… Xenon Thrust ……………………………………...…………. 235 mN Thruster Mass……...…… ……...………...… <13.3 kg Specific Impulse…………………………...……… >4100 sec Thruster Envelope Dimensions .....… 58 dia. x 44 cm Efficiency @ full power …………………....….………. >70% Active optics area……...………………. 36 cm dia. Propellant Throughput…….... …………...…………. >270 kg Thruster Input Power ………………. 600 to 6900 Watt On/Off Cycles …………………….……….…..>3650 cycles End of Life Xenon Residuals ………..………….. < 1% BOL Propellant Management System Mass High Pressure Assembly ……………….. < 2.2 kg Status Low Pressure Assembly…………………..< 4.1 kg Thruster at Prototype Model Design PMS Volume ………………………..…….< 11,775 c.c. Propellant Mgmt System at Engineering Model Design PMS does not require plenum tanks Digital Control Interface at laboratory design level DCIU interface with Power Processing……….RS-485 Reference AIAA-2005-3885 AIAA-2004-4111 Rev. Date: 6/14/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export Space Electronics Heritage 3/03 C80007-44K Approved for public release and export Rev. Date: 5/03/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 FAX (425) 882-5747 Approved for public release and export 4.5 kW HALL THRUSTER POWER PROCESSOR UNIT 9.93 cm 39.345 cm (3.91”) (15.49”) J1 J3 J2 43.03 cm 1553 (16.94”) 15 14 Design Characteristics Demonstrated Performance Mass . 12.5 kg Closed Loop Control of Xenon Flow Controller and Envelope . 43 x 40 x 11 cm Discharge Current Input Voltage . 70 +/- 2 VDC Holding Valve Drivers Efficiency (Avg) . >92% S-Level, Radiation Hardened Components MIL-STD-1553 Command & Telemetry Interface: Optimized for Manufacturability 30 Telemetry Channels Only Four Circuit Cards Commandable Power Settings: Status Discharge Power . 2.0 - 4.5 kW Qualified Discharge Voltage . 150 - 400 V Reference AIAA-2005-3682 Rev. Date: 5/23/06 11411 139th Place NE • Redmond, WA 98052 (425) 885-5000 fax (425) 882-5747 Approved for public release and export .
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