23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-R9

MOTOR CASE FOR ROCKET TRAJECTORY CORRECTION SYSTEM

S. Boguslavsky (1), A. Cherevatsky (2) , H Dayan (2), M.Shabtai (1), F.Olevsky (1)
(1) Israel Military Industries, Israel; (2) Shafir Production Systems, Israel

Keywords: filament winding, glass/epoxy, pressure test, design to cost

This presentation describes the development of the composite, filament wound glass/epoxy motor case for the Guidance Rocket Motor (GRM).The “design to cost” approach (DTC) for the GRM, including the segmented mandrel and integrated fitting/skirt assembly engineering concepts have been chosen. The influence of the DTC on the general design of the case, its geometry, mechanical properties, and failure mode during pressure test are emphasized. The GRM, as developed, was successfully tested and found to meet the required specifications. The principal stages of low cost manufacturing procedure, implemented at IMI’s facilities, are briefly described.

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