High Power Electric Propulsion

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.{{Cite web |last=Foster |first=John |last2=Haag |first2=Tom |last3=Patterson |first3=Michael |last4=Williams |first4=George J. |last5=Sovey |first5=James S. |last6=Carpenter |first6=Christian |last7=Kamhawi |first7=Hani |last8=Malone |first8=Shane |last9=Elliot |first9=Fred |date=September 1, 2004 |title=The High Power Electric Propulsion (HiPEP) Ion Thruster |url=https://ntrs.nasa.gov/api/citations/20040139476/downloads/20040139476.pdf |access-date=February 6, 2024 |website=nasa.gov}}

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. 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 reaction mass giving a specific impulse of 9620 s.[https://ntrs.nasa.gov/search.jsp?R=20040139476] Page 8 of the September 2004 HiPEP report NASA/TM—2004-213194 Downrated to 24.4 kW, the HiPEP used 5.6 mg/s of reaction mass giving a specific impulse of 8270 s and 460 mN of thrust.

Phase 1 of HiPEP development concluded in early 2003.[https://web.archive.org/web/20040110143547/http://www.grc.nasa.gov:80/WWW/ion/present/hipep.htm HiPEP Project Jan 2004] 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.{{Cite web |last= |first= |date=2019-04-06 |title=Gridded Ion Thrusters |url=https://beyondnerva.com/electric-propulsion/gridded-ion-thrusters/ |access-date=2024-02-07 |website=Beyond NERVA |language=en-US}} Before cancellation, HiPEP completed a 2000 hour wear test.{{Cite web |last=Herman |first=Daniel A. |date=2010 |title=Status of the NASA’s Evolutionary Xenon Thruster (NEXT) Long-Duration Test After 30,352 Hours of Operation |url=https://ntrs.nasa.gov/api/citations/20110000522/downloads/20110000522.pdf}}{{Cite web |last=Williams |first=George J. |last2=Hickam |first2=Tyler A. |last3=Haag |first3=Thomas W. |last4=Foster |first4=John E. |last5=Patterson |first5=Michael J. |date=2005 |title=Preliminary Wear Analysis Following a 2000 h Wear Test of the HiPEP Ion Thruster |url=http://electricrocket.org/IEPC/260.pdf |access-date=February 6, 2024}}

{{expand section|date=November 2021}}

• Exploration of Jupiter
• List of spacecraft with electric propulsion
• Solar electric propulsion

{{reflist}}

• [https://web.archive.org/web/20021227094444/http://www.grc.nasa.gov/WWW/ion/present/hipep.htm NASA GRC Media Packet on HiPEP].
• {{cite web | url=https://ntrs.nasa.gov/search.jsp?R=20040139476 |title= The High Power Electric Propulsion (HiPEP) Ion Thruster NASA/TM—2004-213194 AIAA–2004–3812}}

{{spacecraft propulsion}}

Category:Ion engines