The use of transient tests in the dynamic qualification of spacecraft structures is outined. The technique uses a combination of spacecraft dynamic mass identification tests and open loop transient tests based on an impedance coupling and an equivalent force formulation. A closed loop transient vibration test theoretical formulation is presented as well as a prototype implementation. A comparison of the two techniques, transient tests and sine vibration tests, is given. Accuracy, monitoring, and control are given special attention. The closed loop driving procedure gives better results than the open loop driving method.
Transient Tests for Spacecraft Structures
1989
5 pages
Report
No indication
English
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