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根据航天器附件展开运动功能要求,对联动展开机构进行了尺度综合,确立了一组独立的设计参数,推导了满足收拢和展开状态下基板位置要求的联动展开机构数学模型,并建立了参数化的机构展开动力学仿真模型,以对附件展开运动功能及动力学特性进行分析和验证,从而实现了机构的参数化设计与分析.在此基础上,以展开全程所需的最大驱动力矩最小化为目标,以满足收拢状态整体结构尺寸包络为约束条件,建立了联动展开机构优化模型,根据该优化问题的非线性特征以及设计空间的不连续性,采用模拟退火算法进行优化求解,最终得到了机构的最优尺寸,从而达到了降低展开驱动力矩、改善机构动力学性能的目的.
According to the requirements of the spacecraft attachment to expand the motion function, the scale of the linkage expansion mechanism was established, a set of independent design parameters were established, the mathematical model of the linkage expansion mechanism to meet the requirements of the substrate position in the collapsed and expanded state was deduced, Of the institutions to start the kinetic simulation model to analyze and verify the kinematic and kinetic characteristics of the attachment, so as to realize the parameterized design and analysis of the mechanism.On the basis of this, the maximum driving torque required to start the whole process is minimized As an objective, the optimization model of linkage expansion mechanism is established based on the constraint of the overall structure size envelope in the folded state. According to the nonlinear characteristics of the optimization problem and the discontinuity of the design space, the simulated annealing algorithm is used to optimize the solution. Finally, The best size of the mechanism, so as to achieve the purpose of reducing the driving torque and improving the dynamic performance of the mechanism.