A high-precision dual-satellite formation orbit control method for earth observation
A technology for earth observation and orbit control, which is applied in space navigation equipment, space navigation equipment, space flight vehicles, etc., to achieve the effects of less fuel consumption, high-precision earth observation, and extended working life
Active Publication Date: 2021-12-21
SHANGHAI AEROSPACE CONTROL TECH INST
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[0004] The invention aims at the problem of high-precision earth observation, and solves the problem of hovering and holding control and natural elliptical orbit tracking control
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[0038] In order to describe the technical content, structural features, achieved goals and effects of the present invention in detail, the following will be described in detail in conjunction with the embodiments and accompanying drawings.
[0039] see Figure 1 to Figure 3 , the present invention a kind of high-precision long-term orbit control method to specific area observation, mainly comprises two modes of hovering and holding control and natural ellipse fly-around control (see figure 1 ), including the following steps:
[0040] 1) Establish the relative error equation of the active star relative to the hovering point, and design a feedforward plus feedback composite controller to ensure that the active star hovers directly above the target star (target star orbit system - Z axis direction).
[0041] The origin o of the geocentric inertial system i at the center of the earth, x i Axis points to equinox, z i Axis perpendicular to the equatorial plane points to the Nort...
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The invention discloses a method for controlling an earth observation orbit of a high-precision double-star formation. The invention provides a dual-mode combination control method that performs high-precision hovering and holding control when the double star is working, and adopts natural ellipse flying control when it is not working. In the high-precision hovering and holding control, a real-time closed-loop orbit controller combining feedforward and feedback is designed to ensure that the active star hovers above the target star and realize high-precision earth observation tasks. When the natural ellipse is flying around, design a real-time closed-loop orbit controller to ensure that the active star can track the designed natural ellipse orbit with rough precision, and reduce the fuel consumption of the active star. Through the above-mentioned scheme, high-precision observation of a specific area on the ground can be realized during operation, and less fuel consumption is required during non-operation.
Description
technical field [0001] The invention relates to a method for controlling the orbit of a spacecraft, which includes hovering and maintaining control and natural ellipse flying around control. Background technique [0002] In the double-star formation earth observation mission, the active star needs to hover above the target star with high precision, but due to the influence of the gravity gradient, the active star needs real-time orbit control to ensure that the active star always hovers above the target star, but due to the limited fuel carried by the satellite , will greatly reduce the service life of the satellite. [0003] In order to improve the service life of the satellite, when the double-star formation does not observe a specific area on the ground, it switches to an elliptical natural orbiting configuration, and the fuel consumption required to maintain this configuration is much smaller than the fuel consumption required to maintain the hovering configuration, so t...
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IPC IPC(8): B64G1/24
CPCB64G1/242
Inventor 刘付成孙俊武海雷朱文山韩飞宋婷
Owner SHANGHAI AEROSPACE CONTROL TECH INST