Minisatellite constant thrust orbit recursion method considering multiple perturbation forces

Abstract

The invention discloses a minisatellite constant thrust orbit recursion method considering multiple perturbation forces. The method comprises the following steps: establishing a kinetic model containing constant thrust and multiple perturbation forces according to the on-orbit operation condition of a minisatellite, performing orbit deduction by using a Runge-Kutta RK45 method based on a kinetic component equation, and comparing with the result of SKT simulation software, controlling the error of the orbit recursion method under the constant thrust within 1km. By using the method, the orbit ofthe minisatellite can be accurately given, and the position information of the minisatellite can be determined in time.

Description

technical field

[0001] The invention belongs to the technical field of on-orbit motion of space vehicles, and in particular relates to a small-satellite constant-value thrust orbit recursion method considering multiple perturbations. Background technique

[0002] In recent years, with the continuous improvement of small satellite technology, more and more small satellite missions are emerging. As a supplement to large satellites, small satellites must have a full understanding of the mechanical environment in orbit. This is a further implementation Prerequisites for small satellite missions. However, due to the weight limitation of the small satellite itself, the fuel it carries is limited, so it is impossible to use the pulse maneuvering method of the large satellite for orbital maneuvering. Constant thrust is undoubtedly an effective way for small satellites to perform orbital maneuvering. Therefore, based on the maneuvering mode of constant thrust, the research on the or...

Images