Mounting Roof for Earth Remote Sensing Satellite Payloads
A payload, remote sensing satellite technology, applied in artificial satellites, transportation and packaging, space navigation equipment, etc., can solve the problems of the rigidity performance of the satellite roof and the thermal deformation performance that is difficult to meet, and achieve micro-controllable on-orbit thermal deformation. The effect of improving load-bearing performance, support rigidity, and excellent installation accuracy
Active Publication Date: 2021-05-11
SHANGHAI SATELLITE ENG INST
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Problems solved by technology
[0003] Conventional satellite platform roof design adopts conventional honeycomb panel structure, and the installation accuracy of the payload is guaranteed by means of uniform scraping and precise measurement of the shovel blades reserved on the surface of the roof. With the increase of the stage, the rigidity and thermal deformation performance of the satellite roof processed and assembled by the traditional design method have been difficult to meet the requirements of the new payload for the satellite installation roof.
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[0031] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.
[0032] The invention provides a mounting top plate suitable for payloads of earth remote sensing satellites, which can realize stiffness and thermal deformation control at the same time, such as Figure 1-Figure 6 As shown, the top plate includes a lower skin 1, a honeycomb core 2, an upper skin 3, a scraper 4, a thermal insulation gasket 5, and a reinforcement frame 6, and the honeycomb core 2 is arranged on the upper skin 3 Between the lower skin 1, the reinforcing frame 6 is pre-embedded inside the h...
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The invention provides an installation roof suitable for payloads of earth remote sensing satellites, comprising an upper skin, a lower skin, a honeycomb core, a reinforcing frame, a shovel and a heat insulation pad, and the honeycomb core is arranged on the upper Between the skin and the lower skin, the reinforcing frame is pre-buried inside the honeycomb core, the heat insulation gasket is installed between the scraper and the payload mounting foot, and the scraper is connected to the lower skin ; The installation top plate is an integrated support structure. The invention provides a design that can realize stiffness and thermal deformation control at the same time, can carry large-scale high-stable, high-precision, high-resolution payloads, and can control small thermal deformation on the track. It can provide better support stiffness and installation accuracy, and is suitable for The harsh environment requirements for installing roofs on large satellite platform payloads.
Description
technical field [0001] The invention relates to the field of structural design of a large satellite platform, in particular to a mounting top plate suitable for payloads of earth remote sensing satellites. Background technique [0002] At present, politics, economy, and national defense have put forward higher and higher requirements for satellites, making satellites develop in the direction of high stability, high precision, and high resolution. In addition to putting forward higher performance requirements for large satellite payloads In addition, more stringent requirements are put forward for the mechanical environment and precision stability of the large-scale satellite platform structure in orbit. The satellite payload is installed on the roof of the satellite platform structure. The stiffness of the roof and the thermal deformation with the change of space temperature will have an important impact on the functional performance of the payload it carries. Therefore, it...
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IPC IPC(8): B64G1/10B64G1/66
CPCB64G1/10B64G1/66
Inventor 周静孔祥森陶炯鸣赵川李昊张栖诚
Owner SHANGHAI SATELLITE ENG INST