Judgment Method for Successful Orbiting of LEO Elliptical Orbit Satellites Based on Propellant Budget

Abstract

A propellant budge-based low orbit elliptic track satellite successful injection determining method is provided. Through acquisition of relationships between propellant waste and apogee, perigee, eccentricity ratio and inclination angle adjustment amount, an injection success determination formula containing the apogee, perigee, eccentricity ratio and inclination angle adjustment amount can be achieved via total propellant waste provided by satellite orbital transferring; primary orbital transferring propellant amount allowed by a satellite can be determined according to limitations of each party; the apogee, perigee, eccentricity ratio and inclination angle deviation value of the satellite can be determined after separation of the satellite and a rocket; and whether the satellite successfully enters an orbit is determined via the determination formula. An orbital maneuver theory and formula are employed to achieve an analytic calculation formula, so accuracy, rationality, simplicity and high efficiency can be achieved; easy operation is provided and the method is in particular suitable for quick determination of success carry launch; and basis and instruction are provided for implements of emergency measures of the satellite upon problems during the carrying launch.

Description

technical field [0001] The invention relates to a method for judging successful entry into orbit of a low-orbit elliptical orbit satellite based on a propellant budget, in particular to a method for calculating a successful criterion for launching a low-orbit elliptical orbit satellite into orbit by a carrier rocket. Background technique [0002] When the launch vehicle performs the launch mission, due to its own reasons, it may cause errors in orbit or even launch failure. There are two main consequences that may be caused by a failure of a launch vehicle during launch. One is that the mission fails completely, and the spacecraft falls or loses all functions; the other is that the spacecraft does not fall and enters a different orbit. In the case that the spacecraft does not directly fail to launch, depending on the situation, it is possible to use the propellant carried by the spacecraft itself to change orbit to the mission orbit, but some capabilities or life may be los...

AI Technical Summary

Problems solved by technology

This requires high timeliness, and it is usually necessary to make a judgment within a few minutes after the separation of the satellite and the rocket. However, there is currently no unified standard for the success criteria of the launch, and there are gaps in the readability and operability of the usual success criteria. , it is easy to be confused and make mistakes in parameter interpretation and criterion implementation, which is not conducive to quick judgment

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