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Minisatellite constant thrust orbit recursion method considering multiple perturbation forces

A technology of satellite orbit and perturbation, which is applied in the direction of motor vehicles, space navigation equipment, and space navigation vehicles, etc., and can solve the problem of low precision

Active Publication Date: 2021-02-23
NORTHWESTERN POLYTECHNICAL UNIV +1
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Problems solved by technology

At present, in the research on the orbit evolution of small satellites under constant thrust, many recursive methods are not very accurate due to ignoring the existence of various perturbations

Method used

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  • Minisatellite constant thrust orbit recursion method considering multiple perturbation forces
  • Minisatellite constant thrust orbit recursion method considering multiple perturbation forces
  • Minisatellite constant thrust orbit recursion method considering multiple perturbation forces

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Embodiment Construction

[0051] The technical solutions of the present invention will be described in further detail below with reference to the accompanying drawings and embodiments.

[0052] The present invention considers the small satellite constant value thrust orbit recursion method of multiple perturbation force, comprises the following steps:

[0053]Step 1. Establish two coordinate systems, which are respectively the earth inertial coordinate system EXYZ and the satellite orbit coordinate system Sxyz, and combine the above two coordinate systems to establish the Cartesian dynamic model of the small satellite;

[0054] Step 2. According to the Cartesian dynamic model of the small satellite, the perturbation force applied to the small satellite is added to the dynamic equation in the earth inertial coordinate system. The perturbation force includes constant value thrust, solar light pressure, third-body gravity and The perturbation force such as the shape of the earth constructs the dynamic com...

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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...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/24
CPCB64G1/242Y02T90/00
Inventor 安效民张军华郑子轩
Owner NORTHWESTERN POLYTECHNICAL UNIV
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