Rocket Engine Thrust Vector Control Operation Through Secondary Injection Aerospace Div., Vickers Incorporated

Format:

Conference/Event

Author/Creator:

Billet, A. B., author.

Conference Name:

SAE World Congress & Exhibition (1964-01-01 : Detroit, Michigan, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1964

Summary:

As the size of rocket engines increase and due to specialized thrust vector control problems, additional emphasis is being given on thrust vector control by other than conventional means. One of the more promising means of thrust vector control is through secondary injection of either liquid or gas into the engine exhaust nozzle.Freon has been found to be one of the more successfully used liquid injectants. In the case of hot gas these might be obtained from either direct engine bleed or from a secondary solid propellant control source. Due to the 6000 F temperatures in this section of the engine, specialized design features are required

Notes:

Vendor supplied data

Publisher Number:

640204

Access Restriction:

Restricted for use by site license