The invention provides a test system for thermally induced dynamic response characteristics of a large space structure. The test system comprises a vacuum container, a controller, a heat sink subsystem, a test piece bracket, an infrared radiation subsystem, a transient heat flow simulation device, a laser displacement measurement subsystem and a strain measurement subsystem; the vacuum container is used for providing a space pressure environment; the heat sink subsystem is used for simulating a space cold black environment; the infrared radiation subsystem is used for simulating an external heat flow received by a test piece in orbit; the transient heat flow simulation device is used for simulating the heat flow irradiation change rate when the space structure enters and exits the earth shadow; the laser displacement measurement subsystem is used for acquiring a change curve of the vibration displacement of the test piece in different directions along with time and transmitting the change curve to the controller; and the strain measurement subsystem is used for measuring the tensile strain and the shear strain of the test piece. The test system is used for the ground test of the thermally-induced dynamic response characteristics of the large space structure, and is simple in structure and high in reliability.
本申请提供一种用于大型空间结构热致动态响应特性的试验系统,包括真空容器、控制器及热沉子系统、试验件支架、红外辐射子系统、瞬态热流模拟装置、激光位移测量子系统以及应变测量子系统;真空容器,用于提供太空压力环境;热沉子系统,用于模拟太空冷黑环境;红外辐射子系统,用于模拟试验件在轨所收到的外热流;瞬态热流模拟装置,用于模拟空间结构进出地影时所受到的热流照射变化速率;激光位移测量子系统,用于获取试验件在不同方向上的振动位移随时间的变化曲线,并传送至控制器;应变测量子系统,用于测量试验件的拉应变和剪切应变。本发明用于大型空间结构热致动态响应特性的地面试验,结构简单、可靠性高。
Test system for thermally induced dynamic response characteristics of large space structure
一种用于大型空间结构热致动态响应特性的试验系统
12.02.2021
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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