An Optimization Method for Spacecraft Iterative Guidance

Abstract

The invention provides an optimization method for spacecraft iterative guidance, and belongs to the field of space orbit transfer vehicle transfer orbital control. The optimization method comprises the steps of firstly determining an initial boot point and a shutdown point of a main engine; according to the boot point and the shutdown point and a terminal constraint weight factor, using an optimal guidance algorithm to perform iterative guidance simulation calculation; and finally, after a shutdown point condition is satisfied, ending iterative guidance, and obtaining deviation data. When the position deviation of the shutdown point in the X direction exceeds a threshold, the shutdown point is adjusted, so as to reduce the position deviation of the shutdown point in the X direction; and then iterative guidance simulation is performed until the shutdown point satisfies the requirement, and the optimization is over. The optimization method for the spacecraft iterative guidance provided by the invention gets rid of small angle correction hypothesis of traditional iterative guidance, and meanwhile, a terminal constraint under an orbit injection point orbit coordinate system is transformed into an equivalent terminal constraint under a geocentric inertial coordinate system, and appropriate weight adjustment is performed, so that the accuracy of numerical solution and the adaptability of the guidance method are improved, so as to ensure a spacecraft to finally reach the requirement of a task point.

Description

Technical field: [0001] The invention relates to an optimization method for iterative guidance of a spacecraft, and belongs to the field of space orbit transfer aircraft orbit change control. Background technique: [0002] In order to complete the scheduled space mission, the space orbit transfer vehicle needs guidance to complete the transfer between different orbits. Traditional guidance methods such as perturbation guidance have the disadvantages of complex pre-launch binding data and poor orbital accuracy. Traditional iterative guidance usually considers five terminal constraints, including two directions, when the thrust of the spacecraft’s main engine is not adjustable. Position constraint and speed constraint in three directions, firstly solve the control angle that satisfies the speed constraint, and then assume that the angle change caused by the position constraint is a small amount. This assumption is no longer valid in some orbital changes, so it is necessary to itera...

AI Technical Summary

Problems solved by technology

Traditional guidance methods such as perturbation guidance have disadvantages such as complex data before shooting and poor orbital accuracy, while traditional iterative guidance usually considers five terminal constraints, including two-direction Position constraints and velocity constraints in three directions, first solve the control angle that satisfies the velocity constraints, and then assume that the angle change caused by the position constraints is small, this assumption is no longer true in some orbit change situations, so it is necessary to The guidance method is improved to ensure that the spacecraft enters the orbit accurately and finally reaches the target point

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