Comparative in-flight thrust measurements of the SERT II ion thruster
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Comparative in-flight thrust measurements of the SERT II ion thruster by William C. Nieberding

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Published by National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.] in Washington .
Written in English

Subjects:

  • Rocket engines -- Thrust -- Measurement.

Book details:

Edition Notes

Statementby William C. Nieberding, Daniel J. Lesco, and Frank D. Berkopec.
SeriesNASA technical note, NASA TN, D-6008
ContributionsLesco, Daniel J., joint author., Berkopec, Frank D., joint author.
Classifications
LC ClassificationsTL521 .A3525 no. 6008
The Physical Object
Paginationiii, 22 p.
Number of Pages22
ID Numbers
Open LibraryOL5276043M
LC Control Number71609822

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ECR ion thruster generates a V, A xenon ion beam that produces mN of thrust at an Isp of s and a total efficiency of 36%. The most recent launch of a new ion thruster was by the Japan Aerospace Exploration Agency (JAXA), who launched four 20mN-class Kaufman ionFile Size: KB. Thrust measurements are essential to qualify thrusters for space missions, especially for new technologies. In the framework of the Gaia mission, the 13 newly developed cold gas micronewton. NASA report on the SERT II spacecraft and mission. "In-Flight Operation of the Dawn Ion Propulsion System through Orbit Capture at Vesta," AIAA Paper , [5] Hofer, R. R. and Randolph, T. M., "Mass and Cost Model for Selecting Thruster Size in Electric Propulsion Systems," AIAA Paper , July

In Hall effect thrusters (HETs), ions are accelerated to generate thrust. There are some magnetized effects on ion motion, including the swirl torque, [8] but HETs are designed such that ions. test are: (I)to demonstrate reliable thruster operation over a typical mission profile requiring hr thrusting in cycles, (2) to make ''• in-flight measurements of thruster/spacecraft interactions pertaining to flight applications, and (3) to demonstrate compatibility during simul-taneous operation of two thrusters. The flight. The University of Tokyo and the Next generation Space system Technology Research Association (NESTRA) in Japan successfully completed initial operations of a miniature ion thruster propulsion system on board 50 kg nano-satellite “Hodoyoshi-4” on Octo ; the world’s first operation of an ion thruster on a satellite smaller than 50 kg. Electrothermal thrusters differ from both electromagnetic and electrostatic propulsion systems due to their operational design; electromagnetic and electrostatic systems propel charged ions through the use of electric and magnetic fields, while electrothermal systems heat the propellant, and rely upon thermal dynamics to propel the system (Jordan, ).

Thrust is the amount of push a rocket engine provides to the rocket. Propulsion works when matter (something you can touch--like a gas or a liquid) is pushed out the back of a spacecraft. The amount of thrust or push in a spacecraft is related to how much matter is leaving the engine and at what speed the matter is leaving, minus resistance. Measurements of the manoeuvre margin end the derivatives rn$ (ma + ma) zw were obtained. The resulta are compared with those obtained from one of the same model8 in a transonic wind tunnel and from a related M-wing model in flight. They are al80 corrected for a8roeLaatlc effects.   Theory of Aerospace Propulsion provides excellent coverage of aerospace propulsion systems, including propellers, nuclear rockets, and space propulsion. The book's in-depth, quantitative treatment of the components of jet propulsion engines provides the tools for evaluation and component matching for optimal system Edition: 1. Kerslake, W. R., “SERT II Thrusters-Still Ticking After Eleven Years,” AIAA paper 81–, AIAA/ SAE/ASME 17th Joint Propulsion Conference, Google Scholar