An on-orbit calibration method for aerodynamic shape differences between satellites in a formation satellite system

An aerodynamic shape and satellite system technology, applied in the field of formation satellites, can solve the problems of lack of satellite formation influence control, etc., and achieve the effect of clear whole process, high calculation accuracy and strong realizability

Active Publication Date: 2021-10-01
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0004] The technical problem solved by the present invention is: in view of the lack of control technology that can reduce the impact of the difference in the shape of the formation satellites on the formation of satellite formations to meet the needs of users in the current prior art, a formation satellite system inter-satellite aerodynamic control technology is proposed. On-orbit calibration method of shape difference

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  • An on-orbit calibration method for aerodynamic shape differences between satellites in a formation satellite system
  • An on-orbit calibration method for aerodynamic shape differences between satellites in a formation satellite system
  • An on-orbit calibration method for aerodynamic shape differences between satellites in a formation satellite system

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[0024] An on-orbit calibration method for the aerodynamic shape difference between satellites in a formation satellite system. The real-time relative state data between the required formations is obtained through the GNSS receiver carried by the formation satellites, and at the same time, it is calculated by calculating the relative semi-major axis fluctuation slope of the satellites and the current mass of the satellites. The aerodynamic shape of the satellite is calibrated on-orbit. Among them, the real-time relative state data between the required formations is also called the formation configuration parameter, which can be found in relevant technical documents of formation satellites, such as figure 1 As shown, the specific steps are:

[0025] (1) The auxiliary star of the formation outputs the real-time measurement information of its own star relative to the main star of the formation according to the on-board GNSS receiver, and obtains the current relative semi-major axis...

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Abstract

An on-orbit calibration method for the aerodynamic shape difference between satellites in a formation satellite system. Through real-time relative measurement of formation satellites by GNSS, the real-time on-board data of the required formation main star and formation auxiliary satellite are obtained, and the star position of each satellite at the current moment is determined by calculation. On-orbit calibration of the aerodynamic shape of satellites based on the difference in aerodynamic shape between satellites solves the need for quantitative identification and evaluation of the difference in aerodynamic shape between formation satellites, and further improves the quality of on-orbit mission operation of formation satellites. The whole process of the method is clear, the method is simple and reliable, and the calculation accuracy is higher.

Description

technical field [0001] The invention relates to an on-orbit calibration method for aerodynamic shape differences between satellites of a formation satellite system, and belongs to the technical field of formation satellites. Background technique [0002] With the continuous successful application of formation satellite missions in orbit and the continuous increase in the complexity and demand of application tasks, the control tasks of formation satellite systems will face pressures such as high control accuracy, high control accuracy stability, and long life. [0003] The factors affecting the control accuracy of short-range flying formation are complex, mainly including the measurement error of the measurement sensor, the error of the dynamic model, and the related error of the actuator. In fact, the impact of the existing research results on the difference in the aerodynamic shape between the satellites is often ignored as a small amount after making the assumption that th...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/10
CPCB64G1/1085
Inventor 陈桦刘美师万亚斌完备王文妍杜耀珂王嘉轶崔佳龚腾上王禹贾艳胜杨盛庆朱郁婓
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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