High Power Electric Propulsion (HiPEP) is a variation of ion thruster for use in nuclear electric propulsion applications.[1][2][3] It was ground-tested in 2003 by NASA and was intended for use on the Jupiter Icy Moons Orbiter, which was canceled in 2005.
YouTube Encyclopedic
-
1/3Views:4 419 7304 495 9365 187 287
-
How This Fusion Reactor Will Make Electricity by 2024
-
Can Nuclear Propulsion Take Us to Mars?
-
The Next Generation of Ionic Plasma Thrusters (BSI MARK 2)
Transcription
Theory
The HiPEP thruster differs from earlier ion thrusters because the xenon ions are produced using a combination of microwave and magnetic fields. The ionization is achieved through a process called Electron Cyclotron Resonance (ECR). In ECR, the small number of free electrons present in the neutral gas gyrate around the static magnetic field lines. The injected microwaves' frequency is set to match this gyrofrequency and a resonance is established. Energy is transferred from the right-hand polarized portion of the microwave to the electrons. This energy is then transferred to the bulk gas/plasma via the rare - yet important - collisions between electrons and neutrals. During these collisions, electrons can be knocked free from the neutrals, forming ion-electron pairs. The process is a highly efficient means of creating a plasma in low density gases. Previously the electrons required were provided by a hollow cathode.[4]
Specifications
The thruster itself is in the 20-50 kW class, with a specific impulse of 6,000-9,000 seconds, and a propellant throughput capability exceeding 100 kg/kW.[2] The goal of the project, as of June 2003, was to achieve a technology readiness level of 4-5 within 2 years.
The pre-prototype HiPEP produced 670 millinewton (mN) of thrust at a power level of 39.3 kW using 7.0 mg/s of fuel giving a specific impulse of 9620 s.[2][5] Downrated to 24.4 kW, the HiPEP used 5.6 mg/s of fuel giving a specific impulse of 8270 s and 460 mN of thrust.
Project and development history
Phase 1 of HiPEP development concluded in early 2003.[6] Conceptual Design of the thruster was completed, and individual component testing concluded. A full-scale laboratory thruster was constructed for Phase 2 of the HiPEP's development. However, with cancellation of the Jupiter Icy Moon Orbiter mission in 2005, HiPEP's development also came to a halt.[7] Before cancellation, HiPEP completed a 2000 hour wear test.[8][9]
See also
References
- ^ The Glenn Research Center. NASA.
- ^ a b c HIGH POWER ELECTRIC PROPULSION PROGRAM (HiPEP). Glenn Research Center - NASA. 22 December 2008.
- ^ "The High Power Electric Propulsion (HiPEP) Ion Thruster NASA/TM—2004-213194 AIAA–2004–3812"..
- ^ Foster, John; Haag, Tom; Patterson, Michael; Williams, George J.; Sovey, James S.; Carpenter, Christian; Kamhawi, Hani; Malone, Shane; Elliot, Fred (September 1, 2004). "The High Power Electric Propulsion (HiPEP) Ion Thruster" (PDF). nasa.gov. Retrieved February 6, 2024.
- ^ [1] Page 8 of the September 2004 HiPEP report NASA/TM—2004-213194
- ^ HiPEP Project Jan 2004
- ^ "Gridded Ion Thrusters". Beyond NERVA. 2019-04-06. Retrieved 2024-02-07.
- ^ Herman, Daniel A. (2010). "Status of the NASA's Evolutionary Xenon Thruster (NEXT) Long-Duration Test After 30,352 Hours of Operation" (PDF).
- ^ Williams, George J.; Hickam, Tyler A.; Haag, Thomas W.; Foster, John E.; Patterson, Michael J. (2005). "Preliminary Wear Analysis Following a 2000 h Wear Test of the HiPEP Ion Thruster" (PDF). Retrieved February 6, 2024.
External links
- NASA GRC Media Packet on HiPEP.
- "The High Power Electric Propulsion (HiPEP) Ion Thruster NASA/TM—2004-213194 AIAA–2004–3812".
| Concepts | |||||||||
|---|---|---|---|---|---|---|---|---|---|
| Physical propulsion | |||||||||
| Chemical propulsion |
| ||||||||
| Electrical propulsion |
| ||||||||
| Nuclear propulsion |
| ||||||||
| External power | |||||||||
| Related concepts | |||||||||
This page was last edited on 10 April 2024, at 11:31