Method for determining in-place unfolding posture of inflatable solar wing on orbit

Abstract

One embodiment of the invention discloses a method for in-orbit determination of an unfolding attitude of an inflatable solar wing. The method comprises the following steps: S101, establishing a reference coordinate system of a test point on a satellite body; S103, determining inflatable solar wing test points, arranging sensors at the test points and performing grouping and numbering; S105, determining a position coordinate value of the test point sensor when the inflatable solar wing is unfolded to an ideal posture; S107, measuring the position coordinates of the sensors at the test points in an on-orbit manner; S109, measuring the attitude stability of X, Y and Z axes at the positions of each group of test point sensors by adopting a square error analysis method, further judging that the inflatable solar wing is unfolded in place, and carrying out on-orbit stiffening. According to the method, only the position coordinates of the sensors pasted on the test points on the surface of the solar wing need to be read, the ideal design values of the test points in the unfolding in-place state are compared, and a square error analysis method is adopted to determine whether the posture of the inflatable solar wing meets the unfolding in-place requirement or not.

Description

technical field [0001] The invention relates to the field of on-orbit testing of an inflatable solar wing, and more particularly, relates to a method for on-orbit testing of the deployment attitude of an inflatable solar wing. Background technique [0002] The inflatable solar wing is a new type of satellite solar power supply device. Compared with the traditional rigid solar wing, the wingspan area of ​​the inflatable solar wing can be made larger to meet the higher power consumption demand of the satellite. The inflatable solar wing can be folded after vacuuming the ground. Compared with the traditional rigid solar wing, its initial volume after folding is smaller and lighter. It is an ideal solar power supply device for satellites. [0003] Although the inflatable solar wing has many advantages, the in-orbit engineering application of the inflatable solar wing is still facing great challenges. Compared with the traditional rigid solar wing mechanical deployment method, th...

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Problems solved by technology

[0003] Although the inflatable solar wing has many advantages, the in-orbit engineering application of the inflatable solar wing is still facing great challenges. Compared with the traditional rigid solar wing mechanical deployment method, the inflatable solar wing deployment process is more time-varying. And it takes a certain amount of time for in-orbit rigidification to ensure that its structural rigidity meets the basic design requirements

Before rigidizing the inflatable solar wing, it is necessary to ensure that its on-orbit deployment attitude meets the design requirements and maintains a stable attitude. At present, spaceborne cameras are used to monitor the deployment process of the inflatable solar wing. The attitude and the method of judging the stability of its attitude have great disadvantages. The surface of the inflatable solar wing is very easy to reflect light. When the light is strong, due to the limitation of the dynamic range of the camera photosensitive element, the lens image will appear overexposed and "deadly white". Phenomenon, unable to correctly judge the deployment attitude of the solar wing

On the other hand, for the Z-type folding inflatable solar wing, the spaceborne camera cannot calibrate the linearity of the deployment of the inflatable solar wing, and then cannot track the deployment angle of the far end of the solar wing. Once the deployment angle is wrongly judged In addition, false rigidization will greatly reduce the conversion efficiency of solar energy, which will seriously affect the mission of satellites.

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