Low-thrust phase modulation maneuvering method among coplanar circular orbits

A coplanar circle, small thrust technology, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of inability to predict the direction of phase modulation, inability to rapidly design phase modulation orbits with small thrust, etc., to improve the design The effect of efficiency

Inactive Publication Date: 2012-06-20
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

[0005] Aiming at the problems that the current design method cannot quickly design the small-thrust phase-modulation orbit and cannot predict the phase-modulation direction, the present invention provides a low-thrust phase-modulation dynamic method between coplanar circular orbits, which is suitable for coplanar circular orbits. Small Thrust Phasing Problem Between Surface Circular Orbits

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  • Low-thrust phase modulation maneuvering method among coplanar circular orbits
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  • Low-thrust phase modulation maneuvering method among coplanar circular orbits

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Embodiment Construction

[0024] The low-thrust phase adjustment maneuver method between coplanar circular orbits is divided into three parts: initial phase difference calculation, internal and external rotation strategy maneuver parameter calculation, and phase adjustment maneuver parameter determination.

[0025] The tracking spacecraft A and the target spacecraft B are running on the same circular orbit, the semi-major axis of the orbit is a, and the orbit mean anomaly angle is used to describe the phase angle of the spacecraft on the orbit. The initial mean anomaly angle of the spacecraft A is m A (t 0 ), the initial mean anomaly angle of spacecraft B is M B (t 0 ). Spacecraft A is equipped with a constant low-thrust engine, and it is required to use the small-thrust engine to adjust the phase of spacecraft A so that it can achieve the rendezvous with spacecraft B in the shortest time, that is, satisfy M A (t f ) = M B (t f ).

[0026] According to the Gaussian planetary motion equation, th...

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Abstract

The invention discloses a low-thrust phase modulation maneuvering method among coplanar circular orbits. The method comprises the following steps of: calculating an initial phase difference; 2, calculating a maneuvering parameter of an internal and external spinning strategy; and 3, determining a phase modulation maneuvering parameter. According to the method, a phase relation between a tracking spacecraft and a target spacecraft is described by mean anomalies of the orbits, so that a relation of parameters, such as the initial phase difference, a thrust direction and the like, is acquired; two feasible phase modulation strategies are acquired according to a characteristic of a phase modulation task on the basis of the relation, so that the complexity of an algorithm is simplified; a nonlinear equation group which is met by the phase modulation turnaround time and a mean semi-major axis is built by using an orbit meaning technology; and the equation group can be solved through simple Newton iteration, so that the robustness of the algorithm is enhanced, and the design efficiency is improved. In the method, a method for quickly judging a phase modulation direction is provided, so that a rational and feasible initial value forecast is supplied to a precise design of a low-thrust phase modulation orbit.

Description

technical field [0001] The invention relates to a small-thrust phase-modulation maneuver method between coplanar circular orbits, which is suitable for the initial design of the low-thrust phase-modulation orbit of earth satellites, and belongs to the technical field of spacecraft orbit maneuvers. Background technique [0002] Phase adjustment motion has a wide range of applications in space exploration missions, and is a necessary way for the realization of space rendezvous and docking, geosynchronous satellite orbiting and other tasks. Compared with traditional pulse engines, the use of high-efficiency small-thrust engines to achieve orbital phase adjustment of spacecraft can effectively reduce fuel consumption during missions. Design presents a conundrum. When the traditional pulse engine is used for orbital phase adjustment maneuver, it is only necessary to search for the phase adjustment time on the basis of solving the Lambert problem according to the current orbital ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 尚海滨崔平远王帅徐瑞朱圣英
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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