Apollo Earth Landing Simulation Columbus Div., North American Aviation, Incorporated

Format:

Conference/Event

Author/Creator:

Blackburn, Charles L., 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:

To alleviate Earth landing loads on the Apollo command module, a configuration was considered consisting of two bodies; namely, the command module and heat shield. The command module and heat shield are connected by an arrangement of active (oleo) and passive (crushable core) struts. The equations of motion describing the response of the vehicle for impact landings are developed for simulation on an operational analog computer. Structural and inertial properties of the vehicle are represented by normal modes of vibration in conjunction with the conventional longitudinal dynamic-stability degress of freedom. Simulation techniques and problems are discussed

Notes:

Vendor supplied data

Publisher Number:

640207

Access Restriction:

Restricted for use by site license