Judgment method for successful orbiting of low-orbit and near-circular orbit satellites based on propellant budget

Abstract

Disclosed is a method for determining a successful orbit injection of a low-earth-orbit near-circular orbiting satellite based on propellant budget. By obtaining a relation between semi-major axis adjusting amount, eccentricity adjusting amount, inclination angle adjusting amount and propellant consumption amount, a successful orbit injection determination formula comprising the semi-major axis adjusting amount, the eccentricity adjusting amount and the inclination angle adjusting amount can be obtained based on total propellant consumption amount provided by satellite orbital transfer; initial orbital transfer propellant dosage which is allowed to be provided by the satellite is determined according to constraint of each side; and offsets of the semi-major axis, the eccentricity and the inclination angle of the satellite are determined after the satellite and a rocket are separated, and determination on whether successful orbit injection of the satellite can be realized or not is performed according to the determination formula. By adoption of an orbital maneuvering theory and formula, the obtained analytic calculation formula is accurate, reasonable, simple and effective, easy to operate, and particularly suitable for rapid determination on whether the carrying launch is successful or not; after a problem occurs in the carrying launch, basis and guidance can be provided for a first-aid measure for the satellite; and in addition, the method also can be popularized to direct orbit injection of a medium-high-orbit near-circular orbiting satellite.

Description

technical field [0001] The invention relates to a method for judging the successful entry into orbit of a low-orbit near-circular orbit satellite based on a propellant budget, in particular to a calculation method for a successful criterion for launching a low-orbit near-circular 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 ...

AI Technical Summary

Problems solved by technology

[0005] The technical problem solved by the present invention is: aiming at the error of launching into the orbit and the large deviation that may occur, a theoretical algorithm and applicable conditions for engineering application are proposed to judge whether the satellite can successfully enter the orbit by using the satellite propellant margin and other part of the propellant. , taking the propellant that can be used for initial orbit adjustment as the adjustable range of launch-into-orbit deviation, deduce the relational expression expressed by semi-major axis deviation, inclination deviation and eccentricity deviation, this method can be used for launch vehicle launch When satellites in low-orbit and near-circular orbits are used, the total propellant consumption provided by satellite orbit changes can be used to judge whether the satellite can successfully enter orbit

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