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Allowable Design Loads for Marman Clamp Systems

by Robert DiTolla, General Dynamics Space Systems, San Diego, United States,
Michael Ernst, General Dynamics Space Systems, San Diego, United States,



Document Type: Proceeding Paper

Part of: Engineering, Construction, and Operations in Space IV

Abstract:

Marman clamp separation systems have many aerospace applications. One of their most important applications is in the attachment of spacecraft to expendable launch vehicles. Because their structural capability loss under multiple load cycles has never been quantified, methodologies for determining marman clamp allowable design loads have been conservative. Using recent structural test results and nonlinear, axisymmetric finite element analysis, a method has been developed which accurately predicts the marman clamp ultimate structural capability from which its allowable design load can be readily determined.

Subject Headings: Finite element method | Load factors | Structural analysis | Equipment and machinery | Structural design | Aircraft and spacecraft | Load tests

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