Spacecraft orbit characteristic point analysis calculation method

Abstract

The invention provides a spacecraft orbit characteristic point analysis calculation method which includes the steps: changing orbit parameters of a current time point and acquiring six elements of a first orbit; calculating flight time according to current parameters of a spacecraft and orbit characteristic points under a two-body theory; calculating parameters of false characteristic points by the aid of an extrapolation algorithm based on a middle orbit theory according to the flight time; changing the parameters of the false characteristic points according to the two-body theory and acquiring six elements of a second orbit; calculating parameters of true characteristic points according to the parameters of the false characteristic points and the six elements of the second orbit. The flight time of the spacecraft from a current position to a two-body orbit characteristic point is calculated by the aid of the two-body theory, the parameters of the false characteristic points are acquired by the extrapolation algorithm based on the middle orbit theory, and the parameters of the true characteristic points are acquired by taking the parameters of the false characteristic points as astarting point by the aid of the two-body theory. Compared with the prior art, the calculation method can greatly improve the calculation speed of the orbit characteristic points on the premise of ensuring precision.

Description

technical field [0001] The present invention relates to space vehicles. More specifically, it relates to an analytical calculation method of orbit feature points of spacecraft. Background technique [0002] When designing the orbit of a spacecraft, it is often necessary to calculate orbital feature points such as perigee, apogee, and intersection with the equator plane according to the flight parameters at the current moment. The time, position, and speed of these orbital feature points will be used as the input for the orbit suitability check. Therefore, its calculation speed and accuracy have a great influence on the efficiency of orbit design. [0003] The traditional calculation method generally adopts the integral method. In order to meet the calculation accuracy, it is necessary to set a small calculation step size. This calculation speed is acceptable when the flight time is short, but when the flight time is long, the calculation time will be too long to meet the re...

AI Technical Summary

Problems solved by technology

[0003] The traditional calculation method generally adopts the integral method. In order to meet the calculation accuracy, it is necessary to set a small calculation step size. This calculation speed is acceptable when the flight time is short, but when the flight time is long, the calculation time will be too long to meet the requirements. Requirements, especially in the case of a large number of orbital design tasks

Images