NASA GRC is developing a 4.5 kW-class Hall propulsion system. This system includes a long life high performance Hall Effect Thruster (HET), a highly efficient variable input and output voltage power processing unit (PPU), and a xenon feed system (xFS). Several mission studies performed by NASA GRC's Collaborative Modeling for Parametric Assessment of Space Systems (COMPASS) team have identified a 4.5 kW-Class Hall propulsion system with dual model capability (high thrust-to-power and high specific impulse) as enabling for some Discovery and New Frontier class design reference missions (DRMs) and enhancing to others. In addition recent on-orbit data for SOA 4.5 kW-class Hall propulsion systems has shown in-space performance degradation due to inherent thruster design flaws. Additional testing of a HiVHAc thruster is proposed. The new design incorporates the latest advances in thruster technology including a centrally mounted cathode and a magnetic field topology that results in high thruster performance, long thruster life. The design is also invariant to facility background pressure conditions, resulting in ground test performance which is very similar to on-orbit performance. These unique design feature incorporated in the HiVHAc thruster eliminate critical flaws that SOA flight Hall thrusters have exhibited. To transfer the HiVHAc technology to the commercial market, NASA GRC needs to demonstrate that the thruster design has the lifetime capability and structural design maturity to meet NASA and commercial mission requirements. This investment in the HiVHAC thruster wear and environmental tests will demonstrate a HiVHAc thruster design that is ready for qualification. In addition, the HiVHAc thruster design will be fully compatible with the prototype model PPU development that NASA GRC is performing with Colorado Power Electronics, resulting in a new domestic EP subsystem. The goal is to advance the maturity of a 4.5 kW-class dual mode (high thrust-to-power and high specific impulse) Hall Effect Thruster (HET), with a centrally mounted cathode, via analysis and test.
More »Details of the HiVHAc technology value relative to SOA were provided in previous sections. The HiVHAc thruster key innovations are its stable on orbit and efficient dual mode operating capability. NASA mission analysis has shown that the original 3.9 kW HiVHAc thruster (designated EDU) provided great mission benefits when compared to SOA Hall thrusters (xR-5 and SPT-140). The increased power level of the HiVHAc thruster (4.5 kW) further improves on the thruster performance and makes it a more viable efficient option to SOA because it will generate higher thrust levels than SOA at a given power, will operate at high specific impulse during station keeping maneuvers (lower fuel consumption resulting in higher payload capability), and is inherently more stable due to its cathode position and magnetic circuit topology. This higher-performance low-cost HiVHAc thruster system is also applicable to New Frontier-class NASA missions. The commercial applications include orbit raising and station keeping functions on commercial GEO spacecraft. NASA GRC enhancements to the HiVHAc system did not only address the thruster design but also tackled the PPU operating input and output voltage. NASA GRC, in collaboration with our partners, are maturing the PPU design for compatibility with several spacecraft power systems.
More »Organizations Performing Work | Role | Type | Location |
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Glenn Research Center (GRC) | Lead Organization | NASA Center | Cleveland, Ohio |
Lockheed Martin Inc. | Supporting Organization | Industry | Palo Alto, California |
Moog, Inc (MOOG) | Supporting Organization | Industry | East Aurora, New York |