An optimal design method for co-trajectory emergency reconnaissance constellation based on sun-synchronous return orbit

Abstract

The invention provides an optimal design method for a common-track emergency reconnaissance constellation based on a sun-synchronous return orbit. First, the latitude and longitude coordinates of the target center position, the satellite over-the-top time and the reconnaissance frequency requirements are input; secondly, the orbit height, eccentricity and orbit of the satellite are calculated. The inclination angle; again, calculate the Greenwich sidereal hour angle according to the time of the satellite passing over the top; then, calculate the true anomaly angle, the ascending node right ascension of the base satellite and the number of satellites in the constellation at the time when the base satellite passes over the top; True anomaly angle, reconnaissance frequency, and optimally design the ascending node right ascension of each satellite in the constellation; finally, output the orbital height, eccentricity, orbit inclination, argument of perigee, ascending node right ascension, true proximity of each satellite in the constellation point corner. Using this method, an emergency reconnaissance constellation that meets the coverage requirements of the target area can be quickly designed.

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

Images