マルマンクランプバンド分離衝撃試験データに基づく衛星構体内の衝撃減衰のモデル化

抄録

Marman clamp band separation mechanism is often used to separate a satellite from a launch vehicle. During the separation, the Marman clamp band releases its clamped force and to expose the satellite to a harsh environment of high-magnitude acceleration with high-frequency in a short period of time, which is named by shock environment in spacecraft developments. Estimation of the shock environment is necessary to specify the equipment design condition which is used to design the equipment’s capability to endure shock environment. Empirical methods based on past development shock test data, due to their convenience and simplicity, are often used to estimate the shock environment. However, the accuracy of empirical methods derived by the past shock test data may be affected by the different structural characteristic of the satellite which was not involved in the methods. There are two typical empirical methods, named by conventional empirical methods in this paper, which are widely used in space development. However, there are no discussions and comments regarding the uncertainty of the estimation and this unknown uncertainty will lead to over conservation safety margin assigned when applying the estimated results to specify the design condition of equipment. To answer the questions as mentioned about the conventional empirical methods, first, we investigate the applicability of conventional empirical methods by two different structural characteristics of JAXA satellites, and second, we propose the improved empirical methods for the two different types of structural characteristics based on shock test data during Marman clamp band separation test. Furthermore, a margin used to envelope the uncertainty of individual test data is statistically derived and its applicability is demonstrated from the test data.