The determination method of spacecraft sine control envelope based on the force of shaker

Abstract

This paper describes the method of determining reasonable test levels for product of spacecraft with big size, low mass and high test levels when the force of the shaker facilities is limited. The major step is to compute the test envelope from both Newton’s law and Ampere’s force aspects, the minimum of which is defined as the final safety control envelope for flight spacecraft hardware. By using this method, the shaker facilities can provide maximum force for spacecraft experiencing effective assessment and the interruptions can be avoid during the process of test operation.