An optimal design method of common trajectory emergency reconnaissance constellation based on sun synchronous return orbit

Abstract

The invention provides an optimization design method of a common track emergency reconnaissance constellation based on a sun synchronous return orbit. Firstly, the longitude and latitude coordinates of a target center position, the satellite overhead time and the reconnaissance frequency requirements are inputted. Secondly, the orbital altitude, eccentricity and orbital inclination of the satellite are calculated. Thirdly, the Greenwich star time angle is calculated according to the satellite overhead time. Then, the true nearest point angle, the right ascension of the reference satellite andthe number of satellites in the constellation are calculated. Then, the right ascension of each satellite in the constellation is optimized according to the right ascension of the ascending intersection point of the reference satellite, the true nearest point angle and the reconnaissance frequency. Finally, the orbital altitude, eccentricity, orbital inclination, perigee amplitude, right ascensionand true proximity of each satellite in the constellation are output. By using the method, the emergency reconnaissance constellation which meets the requirement of target area coverage can be designed quickly.

Description

technical field [0001] The invention belongs to the field of optimal design of emergency reconnaissance constellations, and in particular relates to a method for optimal design of co-trajectory emergency reconnaissance constellations based on sun-synchronous return orbits. Background technique [0002] With the development of aerospace technology, countries around the world have put forward higher requirements for the emergency response capabilities of aerospace in order to deal with emergencies, and emergency response technology has become a research hotspot in various countries. Emergency response technology involves many key technologies, such as rapid testing technology, modularized common platform technology, modularized standardized payload technology, launch point selection and rapid emergency track selection and design, etc. Most of these technologies belong to key technologies such as improving the performance of spacecraft and payloads, while the design of emergenc...

AI Technical Summary

Problems solved by technology

[0004] Aiming at the problem that the existing constellation design technology is not very pertinent to the emergency reconnaissance problem, the present invention proposes a co-trajectory emergency reconnaissance constellation optimization design method based on the sun-synchronous return orbit, which makes full use of the advantages of the sun-synchronous orbit and the return orbit, and at the same time Using the characteristics of co-trajectory to achieve multiple coverage of the specified target, it can use fewer satellites to achieve multiple coverage of the specified target at the specified time, strong engineering practicability

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