A remote rendezvous guidance method for a space vehicle

Abstract

The invention discloses a long-range rendezvous guidance method of a space vehicle, which comprises the following steps: calculating an initial gain speed according to flight parameters and rendezvousposition of the aircraft; According to the flight parameters, gain velocity and rendezvous position of the aircraft, the rendezvous deviation is extrapolated. According to the flight parameters, terminal position and velocity of the aircraft, the partial derivatives of the current position and velocity are calculated, and the partial derivative matrix is obtained. Using the partial derivative matrix and the intersection deviation, the corrected gain speed is calculated. The invention provides a long-range rendezvous guidance method of a space vehicle. The method can give consideration to thecalculation precision and the calculation speed for the long-range rendezvous guidance of the space vehicle, can ensure that the calculation precision of the long-range rendezvous guidance is 100 meters, and the calculation time is equivalent to the two-body analysis algorithm, can be used on-line, and the method is simple and feasible.

Description

technical field [0001] The invention relates to the technical field of space remote guidance. More specifically, it relates to a remote rendezvous guidance method for a spacecraft. Background technique [0002] The rendezvous guidance method of spacecraft is greatly affected by terminal constraints, one of which is fixed flight time and fixed terminal position. For such constraints, the existing guidance method is the Lambert algorithm based on the two-body orbit theory. The accuracy of this algorithm is acceptable in short-range or medium-range rendezvous guidance, but when it is applied to long-range rendezvous guidance, the rendezvous error is relatively large. However, the requirements cannot be met, so the Lambert algorithm needs to be corrected during long-range rendezvous guidance. [0003] In the current existing algorithms, the precise calculation of orbit extrapolation generally adopts the integral algorithm, and in order to ensure the calculation accuracy, it is...

AI Technical Summary

Problems solved by technology

For such constraints, the existing guidance method is the Lambert algorithm based on the two-body orbit theory. The accuracy of this algorithm is acceptable in short-range or medium-range rendezvous guidance, but when it is applied to long-range rendezvous guidance, the rendezvous error is relatively large. However, the requirements cannot be met, so the Lambert algorithm needs to be corrected during remote rendezvous guidance

[0003] In the existing algorithms, the precise calculation of orbit extrapolation generally adopts the integral algorithm, and in order to ensure the calculation accuracy, it is often necessary to select a small calculation step size, which leads to the long calculation period of the remote rendezvous guidance and cannot realize the online use of the aircraft ; The calculation of the partial derivative matrix generally adopts the difference method, that is, first calculate the orbital extrapolation results of the position and velocity at the initial moment, and then calculate the orbital extrapolation after the three components of the position vector and the three components of the velocity vector have undergone slight changes. As a result, the difference of the extrapolation results is obtained to obtain the partial derivative matrix. This method requires up to 7 orbital extrapolations, and the calculation period is long, which cannot meet the requirements.

[0004] Therefore, the existing calculation methods still cannot meet the calculation requirements of rendezvous guidance

Images