| In the process of the design of the space optical remote sensor, the design of the secondary mirror andits supporting structure is one of the indispensable parts. At the same time, in the process of vehicle launching, the vibration input vector increase from the satellite to remote sensor end step by step,dynamic mechanics environment of the secondary mirror and support structure is worse. In order to decrease the cost of the launch of space optical remote sensor, at the same time meet the requirements of structural design under complicated environment, designers need to optimize the reflector and its components design.First of all, under the design status of mirror, introduce mirror and support design of the basic principle,and analysis several different forms of reflector support way.Introduce the finite element analysis method and the reflection mirror evaluation method.Secondly, according to the related theory, design the lightweightsecondary mirror model, calculate the scope of the basic size by theory, and finally, and switch mirror parameterized model size by UG software.Then introduce the design method of experiment(DOE) research, describe the relevant principles of optimization design, in ANSYS software, optimize the secondary mirror parametric model design, to realize the secondary mirror model parameter optimization, get the optimization model, and optimize the model of dynamics and statics analysis.Finally, design and assemble the rest of the secondary support.Get a dynamics and statics analysis of the secondary mirror and support structure, results show that the secondary mirror and support structure design meet the design requirements completely. |
PDF Full Text Request