Study on the Tuning Method of Shock Test Condition for Spacecraft Instruments

抄録

Satellites are exposed to various shock environments during launch. Large shock responses can be generated on rocket separation or deployment of solar arrays and antennas when the strain energy of retained parts is released. Therefore, a test to verify the shock resistance of spacecraft components is necessary. Specially designed separation mechanisms or explosive devices are used to facilitate separation but such methods are expensive to test. To reduce this cost, alternative methods (such as the falling weight shock method) are used but the shock excitation source and structural propagation paths of the test apparatus are different from the operational configurations. This poses problems in making adjustments to match the specified Shock Response Spectrum (SRS) and often causes over- and under-testing, decreasing confidence in the test. This paper reports the results of our study to improve the accuracy of the SRSs of satellite components in shock testing. In the mechanical impact method implemented by the drop weight shock test, the SRS is usually adjusted by changing the material at the impact point, but this method is often inadequate. Rather than changing the hardness of the impact point we modified the SRS adjustment by altering the structure in the path of shock propagation.