NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Aerospace Laser Ignition/Ablation Variable High Precision ThrusterA laser ignition/ablation propulsion system that captures the advantages of both liquid and solid propulsion. A reel system is used to move a propellant tape containing a plurality of propellant material targets through an ignition chamber. When a propellant target is in the ignition chamber, a laser beam from a laser positioned above the ignition chamber strikes the propellant target, igniting the propellant material and resulting in a thrust impulse. The propellant tape is advanced, carrying another propellant target into the ignition chamber. The propellant tape and ignition chamber are designed to ensure that each ignition event is isolated from the remaining propellant targets. Thrust and specific impulse may by precisely controlled by varying the synchronized propellant tape/laser speed. The laser ignition/ablation propulsion system may be scaled for use in small and large applications.
Document ID
20150009340
Acquisition Source
Headquarters
Document Type
Other - Patent
Authors
Campbell, Jonathan W.
Edwards, David L.
Campbell, Jason J.
Date Acquired
June 2, 2015
Publication Date
May 5, 2015
Subject Category
Spacecraft Propulsion And Power
Lasers And Masers
Report/Patent Number
Patent Application Number: US-Patent-Appl-SN-12/862,510
Patent Number: US-Patent-9,021,782
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Patent
US-Patent-9,021,782
Patent Application
US-Patent-Appl-SN-12/862,510
No Preview Available