NASA Logo, External Link
Facebook icon, External Link to NASA STI page on Facebook Twitter icon, External Link to NASA STI on Twitter YouTube icon, External Link to NASA STI Channel on YouTube RSS icon, External Link to New NASA STI RSS Feed AddThis share icon
 

Record Details

Record 55 of 1422
Hybrid plume plasma rocket
Availability: Go to Request Form
Author and Affiliation:
Chang, Franklin R. [Inventor](NASA Lyndon B. Johnson Space Center, Houston, TX, United States)
Abstract: A technique for producing thrust by generating a hybrid plume plasma exhaust is disclosed. A plasma flow is generated and introduced into a nozzle which features one or more inlets positioned to direct a flow of neutral gas about the interior of the nozzle. When such a neutral gas flow is combined with the plasma flow within the nozzle, a hybrid plume is constructed including a flow of hot plasma along the center of the nozzle surrounded by a generally annular flow of neutral gas, with an annular transition region between the pure plasma and the neutral gas. The temperature of the outer gas layer is below that of the pure plasma and generally separates the pure plasma from the interior surfaces of the nozzle. The neutral gas flow both insulates the nozzle wall from the high temperatures of the plasma flow and adds to the mass flow rate of the hybrid exhaust. The rate of flow of neutral gas into the interior of the nozzle may be selectively adjusted to control the thrust and specific impulse of the device.
Publication Date: Mar 28, 1989
Document ID:
19890015908
(Acquired Nov 06, 1995)
Accession Number: 89N25279
Subject Category: SPACECRAFT PROPULSION AND POWER
Report/Patent Number: US-PATENT-4,815,279, US-PATENT-APPL-SN-046341, NASA-CASE-MSC-20476-2
Document Type: Patent
Publisher Information: United States
Financial Sponsor: NASA; United States
Organization Source: NASA Johnson Space Center; Houston, TX, United States
Description: 11p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: MAGNETOHYDRODYNAMIC FLOW; PLASMA ENGINES; PLASMA PROPULSION; ROCKET EXHAUST; ROCKET NOZZLES; THRUST VECTOR CONTROL; FLOW VELOCITY; HYBRID PROPULSION; MASS FLOW; NEUTRAL GASES; ROCKET THRUST
› Back to Top
Find Similar Records
NASA Logo, External Link
NASA Official: Gerald Steeman
Site Curator: STI Program
Last Modified: March 08, 2016
Contact Us