Stargazing Test Apparatus and Method for Assessing Thermal Stability of Star Sensors

Abstract

The invention relates to a star gazing testing device for evaluating the thermal stability of star sensors. The device comprises an integrated support, a precise temperature control instrument, a wind-proof protection cover and a testing industrial personal computer. The integrated support is of an axisymmetric structure, included angles of the normal between every two mounting faces on the integrated support are identical, and the same star sensors are correspondingly arranged on all the mounting faces; the precise temperature control instrument comprises an electric heating sheet and a thermistor, the electric heating sheet and the thermistor are pasted to the mounting faces of the outer side faces and bottom faces of shading covers of all the star sensors, and temperature collection andloop control are conducted; the wind-proof protection cover covers the exterior of the integrated support provided with the star sensors and is installed on an out-field star gazing testing platform;the testing industrial personal computer and the integrated support are arranged at intervals and connected with all the star sensors through cables. The invention further provides a star gazing testing method for evaluating the thermal stability of the star sensors. According to the device, through technical means such as common mounting reference, initiative temperature control and heat insulation and wind prevention, by using the characteristic of consistent thermal stability of the same star sensors, the accurate and effective quantitative evaluation method for the thermal stability of the star sensors is provided.

Description

technical field [0001] The invention relates to a device and method for evaluating the thermal stability of a star sensor, in particular to a star observation test device and method for evaluating the thermal stability of a star sensor, and belongs to the field of ground test technology for space photoelectric sensors. Background technique [0002] The star sensor is a high-precision spacecraft attitude measurement stand-alone machine, which uses the star as the detection target, and outputs three-axis attitude information after internal optical system, electronic components and software processing. Due to the influence of the external heat flow and the deep cold space background, the temperature field of the star sensor generally presents the fluctuation of the orbital period, and the low-frequency error of the orbital period is generated due to the thermal deformation. Generally, the temperature of the mounting surface of the star sensor is used as a reference temperature ...

AI Technical Summary

Problems solved by technology

The disadvantage of this method is that the deformation of the structure cannot be equivalent to the change of the measurement result of the optical measuring instrument

The other is to use the on-orbit data of the star sensor to analyze the low-frequency error within the orbit period, but in this process, it is still impossible to separate the influence of the stability of the satellite platform and the thermal deformation of other installation structures

Therefore, neither of the above two methods can directly and effectively evaluate the thermal stability of the star sensor

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