Thermal deformation testing system of high-precision star sensor support

A star sensor and test system technology, applied in the direction of instruments, measuring devices, etc., can solve the problems of multiple measurement links, complicated operation, and inability to meet the pointing accuracy test requirements of arc-second-level star sensors, and achieve high precision and automation high effect

Inactive Publication Date: 2018-11-06
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

In the ground verification test of the thermal stability design of the star sensor support, the traditional test method uses an electroni...

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  • Thermal deformation testing system of high-precision star sensor support
  • Thermal deformation testing system of high-precision star sensor support
  • Thermal deformation testing system of high-precision star sensor support

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Embodiment Construction

[0021] The implementation of the present invention will be described in detail below, and the implementation of specific steps is carried out on the premise of the technical solution of the present invention, and the detailed implementation and specific operation process are given here.

[0022] Such as figure 1 As shown, the embodiment of the present invention provides a high-precision star sensor bracket thermal deformation test system, including a temperature control system and a thermal deformation measurement system, and the temperature control system includes a temperature loading system and a temperature measurement system, which is used to The feedback control of the temperature load accurately simulates the on-orbit temperature field of the star sensor bracket; the thermal deformation measurement system uses an angle measurement system based on a photoelectric autocollimator, which is used to align the star sensor reference prism under specified measurement conditions....

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Abstract

The invention provides a thermal deformation testing system of a high-precision star sensor support. The thermal deformation testing system comprises a temperature control system and a thermal deformation measuring system, wherein the temperature control system comprises a temperature loading system and a temperature measuring system and is used for accurately simulating a star sensor support in-orbit temperature field through feedback control of temperature loading load. The thermal deformation measuring system adopts an angle measuring system based on a photoelectric auto-collimator and usedfor measuring an optical axial vector of a star sensor standard prism under the specified measurement conditions, utilizing the optical axis of the standard prism to represent a pointing angle of thestar sensor, obtains the pointing change situation of the star sensor through data analyzing treatment and verifies the rationality of thermal stability design of the star sensor support. The high-precision thermal deformation ground verification test demand for arc-second-level pointing change of a satellite star sensor due to thermal deformation of the support is met by adopting the system.

Description

technical field [0001] The invention relates to a star sensor bracket test system, in particular to a high-precision star sensor bracket thermal deformation test system. Background technique [0002] In recent years, the demand for high-resolution earth observation has shown a growing trend, which puts forward higher requirements for the spatial resolution, time resolution, spectral resolution and positioning accuracy of optical remote sensing satellites. Structural thermal deformation is one of the important factors affecting the resolution and positioning accuracy of optical remote sensing satellites for earth observation. Rail deformation thermal stability requirements. In order to ensure the normal operation of the payload and the realization of satellite performance indicators, the pointing accuracy of the payload must be controlled and tested in the process of ground design, development, and testing. [0003] The magnitude of thermal deformation of satellite star sen...

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Application Information

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IPC IPC(8): G01C25/00
CPCG01C25/00
Inventor 庞亚飞赵旭枫王志国周春华赵海斌
Owner SHANGHAI SATELLITE ENG INST
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