Energy safeguard design method for an inertial space observation satellite

An inertial space and observation satellite technology, applied in the overall design field of space astronomy satellites, can solve problems such as unsatisfactory energy demand, different laws of relative relationship between sunlight and stars, etc., to reduce design difficulty, ensure energy supply, and simplify the system The effect of the design

Active Publication Date: 2019-04-19
BEIJING INST OF SPACECRAFT SYST ENG
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Problems solved by technology

Under different attitude control modes, the law of the relative relationship between sunlight and stars will also be d

Method used

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  • Energy safeguard design method for an inertial space observation satellite
  • Energy safeguard design method for an inertial space observation satellite
  • Energy safeguard design method for an inertial space observation satellite

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Embodiment

[0089] In conjunction with the accompanying drawings, the present invention will be further described through the embodiment of the Hard X-ray Tuning Telescope (HXMT) satellite.

[0090] The observation requirements of the HXMT satellite basically cover various requirements of inertial observations, including three types: fixed-point observations for long-term observations of specific inertial target points, regional observations for regional target coverage, and sky survey observations for full-sky coverage observations. At the same time, switching between different observations needs to be done through attitude maneuvering. Since the attitude maneuver is a changing process and the time is short, there are three working states that need to be designed for energy protection: fixed-point mode, small sky area mode, and sky survey mode.

[0091] The HXMT satellite uses a single-axis solar wing, and the energy design requirement is that the angle between the normal of the solar wi...

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Abstract

The invention provides an energy safeguard design method for an inertial space observation satellite. The energy safeguard design method comprises the following steps: (1) determining an inertial space observation satellite body coordinate system and a fixed sun-facing surface according to a satellite basic configuration and a solar wing mounting direction; (2) designing an attitude control algorithm on the basis of a fixed sun alignment surface, and minimizing an included angle between a solar vector and a vertical plane of a sailboard mounting shaft in a single observation process on the premise of ensuring observation direction and observation coverage required by observation; (3) designing a solar wing tracking algorithm according to the change rule of solar vectors based on an attitude control algorithm design result, so that the whole satellite obtains the maximum energy in the whole observation process; And (4) judging whether the energy design requirement is met by the satellites in the whole observation process or not, if so, ending, and otherwise, re-executing the steps (1)-(4). Excellent solar cell illumination conditions can be provided for the satellite system, the design difficulty of the satellite energy system is reduced, and energy supply of the whole satellite is ensured.

Description

technical field [0001] The invention relates to an energy guarantee design method for inertial space observation satellites, a satellite attitude mode and a single-axis solar wing control scheme design, which is suitable for the overall design of satellites with various orbits and various inertial orientation attitude requirements, especially suitable for all over the world. The overall design of space astronomy satellites for long-term observations by inertial celestial body sources in space. Background technique [0002] The satellite energy guarantee design refers to providing good design conditions for the satellite power system through the satellite overall scheme design (such as orbit, working mode, etc.). It is within a certain angle range with the normal line of the solar cells, and the smaller the angle, the higher the efficiency of the energy system. [0003] At present, solar cells are mostly installed on satellites through solar wings, and some satellites are in...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20
Inventor 顾荃莹倪润立潘腾张龙王颖王晓磊王瑶
Owner BEIJING INST OF SPACECRAFT SYST ENG
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