Response of the Apollo command module, service and lunar module airframe while in a docked configuration in the flight environment was measured in a frequency band encompassing the first two bending modes. Transfer characteristics from thrust-application point to control-system sensor were examined. The frequency and the stability margins of the first two predominant structural resonances were verified by the test. This report describes the flight test that was performed and the postflight data analysis.
Inflight dynamics testing of the Apollo spacecraft
1972-03-01
Report
No indication
English
Inflight Dynamics Testing of the APOLLO Spacecraft
| NTIS | 1972
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| NTRS | 1967
Review of Spinning Spacecraft Dynamics Analyses and Inflight Experience
| British Library Conference Proceedings | 1999