Orbit planning method for large elliptical orbit and small-inclination-angle circular orbit

A technology of orbital inclination and large ellipse, applied in the direction of integrated navigator, etc., can solve the problem of not comprehensively considering the launch orbit model, orbital regression characteristics, illumination condition constraints, and the complex motion model of the earth.

Pending Publication Date: 2021-04-09
NO 63921 UNIT OF PLA
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Problems solved by technology

[0004] The traditional emergency satellite launch orbit planning is mainly aimed at the planning and design of the satellite orbit after orbiting, usually without comprehensive consideratio...

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  • Orbit planning method for large elliptical orbit and small-inclination-angle circular orbit
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  • Orbit planning method for large elliptical orbit and small-inclination-angle circular orbit

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Embodiment Construction

[0151] The present invention will be described in detail below with reference to the accompanying drawings and examples.

[0152] The problem to be solved in this satellite orbit planning and design is based on the selected target area information, the constraints of the orbit regression characteristics, the constraints of the reconnaissance load, the launch deployment parameters (including the location of the launch point, the completion time of launch deployment, and the launch orbit data, etc.) parameters) and accurate earth motion model data, to complete the planning and design of small-inclination circular orbits and large elliptical orbits for the detection of different types of target areas. In order to verify the correctness of the satellite orbit planning and design method, the present invention also needs to solve the problem of evaluating the reconnaissance window of the target area by the satellite orbit scheme and the evaluation of the tracking arc section of the s...

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Abstract

The invention discloses an orbit planning method for a large elliptical orbit and a small-inclination-angle circular orbit, belongs to the technical field of orbit planning, and aims at solving the problem of orbit planning according to selected target area information, constraint conditions of orbit regression characteristics, constraint conditions of reconnaissance loads, launching deployment parameters, an accurate earth motion model and other data. And planning and designing of a large elliptical orbit and a small-inclination-angle circular orbit for detection of different types of target areas are completed. According to the design of the large elliptical orbit and the small-inclination-angle circular orbit, traversal is carried out at specific intervals for angle values within an effective inclination angle range, and longitude values of sub-satellite point trajectories of a satellite orbit corresponding to each inclination angle value i on latitude circles of multiple transit target points are calculated; and the difference between the geocentric longitude of the target point and the geocentric longitude value is calculated when the sub-satellite point trajectory passes through the latitude circle of the punctuation. According to the invention, orbit scheme design can be carried out on a large ellipse (small-dip-angle circle) orbit, and rapid and effective detection of a target area is realized.

Description

technical field [0001] The invention relates to the technical field of orbit planning, in particular to an orbit planning method for a large elliptical orbit and a small inclination circular orbit. Background technique [0002] The difference between conventional earth observation satellite orbit planning and emergency satellite launch orbit planning lies in the different mission design concepts. The conventional earth observation mission first launches the earth observation satellite, and after the specific observation target is given, the satellite is sent into the observation orbit through orbital maneuvering to observe the target. Satellite orbit planning for emergency satellite launch missions is driven by the needs of space missions. Satellite orbit planning is usually carried out according to the requirements of reconnaissance target missions, and the parameters of satellite launch orbits and operating orbits are weighed so that they can be quickly launched under the ...

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 吴枫牟莹洁张爱良黄晓明王敏刘阳刘鹰刘秀罗王佳
Owner NO 63921 UNIT OF PLA
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