A rendezvous and approach method with minimum velocity increment

Abstract

The invention provides a rendezvous approach method with the minimum speed increment. The method comprises the steps that the position and speed of a mooring track and a target track are acquired according to the parameters of a maneuvering satellite and a target satellite; the intersection vector of the mooring track and the target track and related parameters are solved; the intersection point of a maneuvering satellite and a target satellite is calculated; the optimal track control point is determined according to single-pulse track design under perturbation; phase is controlled and adjusted by closing the tracks; and the maneuvering satellite and the target satellite eventually intersect and approach at the intersection point.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a method for a maneuvering satellite to rendezvous and approach a target satellite with a minimum speed increment. Background technique [0002] The rendezvous and approach in the present invention means that the position of the mobile satellite and the target satellite is the same through orbit control, but the speed is not restricted. Whether it is the rendezvous approach of the same orbit or the rendezvous approach of different orbits, it can be attributed to the Lambert problem, which is to determine the relative gravitational position vector of two points in space. When the time or the appropriate semi-major axis is given, the passing The transfer orbit of these two points. The Lambert problem is also common in space activities such as missile / satellite interception, interstellar navigation, and debris approach, and is one of the research hotspots in the field of spacefl...

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Problems solved by technology

The former, such as Dr. Zhang Pengyu's "Space Interception Optimal Orbit Design", is to study the transfer orbit with the smallest velocity increment in a given time. However, this analysis does not start from the orbital characteristics of the mobile satellite and the target satellite. The velocity increment It can only be the minimum under a certain time constraint, and another time constraint will give another result. For general satellites, the fuel carried is limited, and the time constraint is not as important as the fuel constraint. Therefore, the primary consideration is the constraint It is the minimum fuel consumption, that is, the latter research direction, that is, the energy optimization problem without time constraints

In Dr. Qi Yinghong's "Study on Small Satellite Tracking, Interception and Guidance", this situation was initially discussed, but only for the case where the mobile satellite and the target satellite are in the same circular orbit, it is concluded that the Hohman transfer orbit is the smallest speed increment The transfer orbit is not applicable to the situation that the mobile satellite and the target satellite are in non-circular orbits and the orbits are different planes, etc.

In addition, factors such as perturbation and limited thrust must be considered for rendezvous and approach. If they are not considered, the accuracy of the maneuvering satellite approaching the target satellite will be difficult to meet the standard

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