Publication Date:
2019-07-13
Description:
The coupled equations of motion of a system composed of a launch vehicle and multiple payloads are derived. In the process, it is shown how superfluous interface degrees of freedom on the booster side can be accommodated in the formulation. The discrete system equations are directly integrated, avoiding the solution of an expensive system eigenvalue problem. A modified Newmark-Chan-Beta numerical integration scheme is used to obtain the response. The unique form of the equations of motion allow for a quick and accurate solution both for the response and the internal loads. Although completely general, the presented technique is most effective when the number of interface degrees of freedom is relatively small compared to the overall number of degrees of freedom of the system. The technique is applied to the case of the S.T.S.-S.T.-OMS Kit system. Finally, an evaluation of the presented method is included.
Keywords:
LAUNCH VEHICLES AND SPACE VEHICLES
Type:
AIAA PAPER 82-0632
,
In: Structures, Structural Dynamics and Materials Conference; May 10, 1982 - May 12, 1982; New Orleans, LA
Format:
text
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