Wide-temperature-range high-rigidity statically-determinate pressing system
A high-rigidity, wide-temperature-range technology, applied in the field of spacecraft, can solve the problems of system detection task loss, mechanism function failure, thermal stress damage, etc., and achieve the effect of strong adaptability, reliable function, and elimination of thermal stress
Pending Publication Date: 2021-12-07
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology
The low temperature of my country's first Mars exploration mission is -130°C, while the environment of the lunar south pole exploration mission can be as low as -200°C, while the high temperature can still reach 80°C. The compaction poses a serious threat, and even causes thermal stress damage, which leads to the failure of the mechanism function to be successfully realized, and causes irreparable losses to the detection task of the entire system
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[0029] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the technical field of the present invention; the terms used in the specification herein are only for the purpose of describing specific embodiments, and are not intended to To limit the invention, for example, the terms "length", "width", "upper", "lower", "left", "right", "front", "rear", "vertical", "horizontal", "top ", "bottom", "inner", "outer" and other indicated orientations or positions are based on the orientations or positions shown in the drawings, which are only for convenience of description and cannot be understood as limitations on the technical solution.
[0030] The terms "include" and "have" in the specification and claims of the present invention and the description of the above drawings, as well as any variations thereof, are intended to cover a non-exclusive inclusion; The terms "first", "second", etc. are used t...
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The invention relates to the technical field of spacecrafts, and discloses a wide-temperature-range high-rigidity statically-determinate pressing system which is used for pressing a pressed mechanism on a spacecraft body. The system comprises a fixed pressing device and at least two floating pressing devices located on the two sides of the fixed pressing device. Each floating pressing device is used for limiting two translational degrees of freedom and three rotational degrees of freedom of the pressed mechanism and adjusting the stretching of the pressed mechanism in the thermal deformation direction; the fixed pressing device is used for limiting all six degrees of freedom; the floating pressing device comprises a sliding groove support, a fixedly-connected flange and a first pressing assembly, the fixed pressing device comprises a fixedly-connected support and a second pressing assembly arranged on the fixedly-connected support, and the fixedly-connected flange and the fixedly-connected support are installed on a pressed mechanism; and the first pressing assembly and the second pressing assembly are installed on the spacecraft body. The system has the characteristics of high rigidity and high fundamental frequency, and has a strong adaptability to high and low temperature environments.
Description
technical field [0001] The invention relates to the technical field of spacecraft, and more specifically relates to a statically determinate pressing system with wide temperature range and high rigidity. Background technique [0002] During the process of launch to orbit, the spacecraft mechanism is limited by the size of the rocket's carrying envelope. It is generally adopted to fold and compress first, and then expand and release after entering orbit. In order to ensure that the mechanism is reliably pressed to withstand the harsh vibration conditions of the rocket launch section, it is necessary to install the mechanism product on the spacecraft structural plate, and connect the mechanism to the structural plate through a compression device. In addition, the compression state of the mechanism needs to have sufficient compression stiffness to avoid the coupling of the fundamental frequency of the mechanism compression state with the whole device, which will lead to excessi...
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Login to View More IPC IPC(8): B64G1/64
CPCB64G1/64Y02T90/00
Inventor 刘卫鄢青青刘学满剑锋齐跃姜生元马超
Owner BEIJING INST OF SPACECRAFT SYST ENG