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摘要
This paper presents an innovative work on the optimum design of microvibration isolation for the multiple-flywheel system of spacecraft. A theoretical model is first developed to describe the coupled system, which consists of an multiple-flywheel system and a multi-axis isolator. The rotating wheels in multiple-flywheel system, which introduce gyroscopic effects, are modeled as rigid rotors supported by resilient isolation struts mounted on a fixed spacecraft. Next, the optimization problem of multiple-flywheel system isolation is formulated by a constrained nonlinear multi-objective function. The objective function is used to minimize the transmitted disturbances to the spacecraft and simultaneously obtain the most favorable modal characteristics for the integrated system of multiple-flywheel system and an isolator under the constraints of spacecraft application. The mass properties of multiple-flywheel system, stiffness coefficients and mounting configuration of isolation struts, which play important roles in the dynamic characteristics and isolation performance of isolators, are chosen as the design variables. A hybrid algorithm combining both genetic algorithms and sequential quadratic programming methods has been adopted to calculate optimum solutions. An analytical frequency sensitivity model is derived based on the proposed theoretical dynamic model. Finally, numerical examples based on an multiple-flywheel system with a typical topology configuration are examined to demonstrate the effects of optimum design and validate the analytical sensitivity of the model.
- 出版日期2016-5
- 单位中国人民解放军国防科学技术大学
