空间飞行器分离仿真试验台的研究

发布时间：2019-02-26 07:50

【摘要】：在探月三期中,绕月飞行的探月飞船的轨道舱和返回舱要实现分离,分离的成功与否关乎飞船能否正常完成探月任务。这就需要在地面上用试验台模拟空间零重力环境下轨道舱和返回舱的分离运动。通过仿真试验能检验分离机构的可靠性和分析舱段分离后的运动规律。本论文所设计的空间飞行器仿真试验台就是用来完成此项仿真任务。经过权衡各种零重力模拟方法的利弊,采用了平面气浮轴承和高精度调心球轴承相结合的方案,对核心部件十字轴和抗弯件的装配体进行了多目标优化设计。设计了试验台的整体结构,并进行校核。对动刚度较差的G舱模拟器进行了模态分析获得了前四阶固有频率和振型,从基频可看出G舱段模拟器的抗振性能满足要求。对结构设计的难点质量惯量模拟机构的设计方案进行了研究。由于质量特性方程未知数多,次数高,且非线性,传统的符号推导直接求解法只能求得部分虚数解。采用分块求解和迭代求解的方法可以快速解得尺寸参数。分析推导了关节测量装置的测量精度。采用固定一个舱段,降低模型自由度的方法,建立了地面5自由度动力学模型和空间6自由度动力学模型。采用四阶/五阶龙格-库塔法求解动力学微分方程,求得数值解并分析了地面环境和空间环境两种状态下分离过程姿态速度变化规律。利用ADAMS软件分别模拟空间环境和地面环境的分离过程,得到的规律和动力学方程求解的规律相符,表明动力学模型的有效性。分析了自由度缺失、摩擦阻力矩和试验台非完全体对分离的影响,结果表明地面分离仿真试验台能够有效模拟空间分离过程。
[Abstract]:In the third phase of lunar exploration, the orbital module and the return module of the lunar spacecraft flying around the moon should be separated, and the success of the separation is related to the normal completion of the lunar exploration mission. It is necessary to simulate the separation motion of the orbital cabin and the return module in the space zero gravity environment with a test rig on the ground. Through the simulation test, the reliability of the separation mechanism can be verified and the movement rule of the separated cabin can be analyzed. The space vehicle simulation test-bed designed in this paper is used to complete this simulation task. After weighing the advantages and disadvantages of all kinds of zero gravity simulation methods, the multi-objective optimization design of the cross shaft and anti-bending assembly of the core component is carried out by using the combination scheme of the plane air bearing and the high precision concentric ball bearing. The whole structure of the test-bed is designed and verified. The first four natural frequencies and mode shapes of G-cabin simulator with poor dynamic stiffness are obtained by modal analysis. It can be seen from the fundamental frequency that the anti-vibration performance of G-cabin simulator meets the requirements. The design scheme of mass inertia simulation mechanism which is difficult in structural design is studied. Because of the unknown number, high degree and nonlinearity of the mass characteristic equation, the traditional symbolic direct solution can only obtain the partial imaginary solution. The size parameters can be quickly solved by block solving and iterative solution. The measurement precision of joint measuring device is analyzed and deduced. The dynamic models of 5 degrees of freedom on the ground and 6 degrees of freedom in space are established by using the method of fixing a segment and reducing the degree of freedom of the model. The fourth-order / fifth-order Runge-Kutta method is used to solve the dynamic differential equation. The numerical solution is obtained and the variation rule of attitude velocity in the separation process is analyzed under the two states of ground environment and space environment. The separation process of space environment and ground environment is simulated by ADAMS software, and the law obtained is consistent with the law of solving dynamic equation, which shows the validity of the dynamic model. The effects of the absence of degrees of freedom, friction resistance torque and non-completion of the test bench on the separation are analyzed. The results show that the ground separation simulation test-bed can effectively simulate the spatial separation process.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V416.8

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