Orbit planning method for sun-synchronous circular regression orbit

Abstract

The invention discloses an orbit planning method for a sun-synchronous circular regression orbit. The design of the sun-synchronous circular regression orbit needs to meet two index requirements of ascending node right ascension derivative constraint and regression coefficient constraint of the sun-synchronous orbit. According to the two index requirements, the two important parameters of the orbit semi-major axis and the orbit inclination angle of the sun-synchronous circular regression orbit can be obtained through iterative calculation; the position of a launching point near the central position of a launching area is traversed and selected according to the calculated semi-major axis of the orbit, the calculated inclination angle of the orbit, the central position of the designated launching area and other parameters; and deviation distribution of subsatellite point geocentric longitude and target point geocentric longitude are calculated when the sun-synchronous circular regression orbit subsatellite point passes through the target latitude circle for multiple times corresponding to different launching point positions, the orbit design with the minimum deviation value is selected to carry out threshold judgment, and the effective orbit design is stored. According to the invention, rapid and effective detection of the target area can be realized.

Description

technical field [0001] The invention relates to the technical field of orbit planning, in particular to an orbit planning method for a sun-synchronous circular return 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 premise of meeting emerg...

AI Technical Summary

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 consideration of the influence of various factors such as the launch orbit model, orbit return characteristics, illumination conditions constraints of optical loads, and the complex motion model of the earth.

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