ION ROCKET ENGINE
Patent
·
OSTI ID:4814410
A thrust generating engine utilizing cesium vapor as the propellant fuel is designed. The cesium is vaporized by heat and is passed through a heated porous tungsten electrode whereby each cesium atom is fonized. Upon emergfng from the tungsten electrode, the ions are accelerated rearwardly from the rocket through an electric field between the tungsten electrode and an adjacent accelerating electrode grid structure. To avoid creating a large negative charge on the space craft as a result of the expulsion of the positive ions, a source of electrons is disposed adjacent the ion stream to neutralize the cesium atoms following acceleration thereof. (AEC)
- Research Organization:
- Originating Research Org. not identified
- NSA Number:
- NSA-16-003978
- Assignee:
- U.S. Atomic Energy Commission
- Patent Number(s):
- US 3014154
- OSTI ID:
- 4814410
- Country of Publication:
- United States
- Language:
- English
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