Regression track design method in high-precision gravitational field

A technology of regression trajectory and design method, applied in design optimization/simulation, special data processing application, constraint-based CAD, etc., can solve problems such as low precision, long time-consuming orbital integration calculation, long calculation time, etc.

Pending Publication Date: 2020-10-23
AEROSPACE DONGFANGHONG SATELLITE
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Problems solved by technology

2. The orbital integral calculation takes a long time
Therefore, for space missions with long return period

Method used

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  • Regression track design method in high-precision gravitational field
  • Regression track design method in high-precision gravitational field
  • Regression track design method in high-precision gravitational field

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Embodiment Construction

[0057] In order to make the object, technical solution and advantages of the present invention clearer, the embodiments disclosed in the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0058] Accurate initial value of orbit design is a necessary condition for forming long-term return orbit, so it is necessary to consider various orbit factors in the design stage to realize accurate design of return orbit. In response to this demand, the present invention provides a return orbit in a high-precision gravitational field (considering non-conservative perturbation factors such as high-order non-central gravitational perturbation and atmospheric resistance, solar radiation pressure, and sun-moon gravitational perturbation) Design method, and solve the high-order Poincaré map through differential algebraic operations to accurately approximate the orbit recurrence in one or more regression cycles, avoiding the complex calcula...

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Abstract

The invention discloses a regression track design method in a high-precision gravitational field. The method comprises the steps of building a regression track design coordinate system; setting a regression orbit condition according to the precision requirement of task implementation; constructing high-order Poincare mapping of orbital state change of the satellite after a regression period from an initial state; and according to the constructed high-order Poincare mapping and set regression orbit conditions, solving an optimization problem to obtain a design initial value of a regression orbit. According to the invention, high-precision and rapid track design is realized.

Description

technical field [0001] The invention belongs to the technical field of satellite orbit design, in particular to a method for designing a regression orbit in a high-precision gravitational field. Background technique [0002] The return orbit has the characteristics of making the spacecraft regularly follow the same flight trajectory relative to the central celestial body. Since the adjacent sub-satellite point trajectories are equally spaced on the same latitude circle, it can meet the periodic observation requirements for specific areas and targets. In fact, the return orbit is the periodic orbit under the fixed coordinate system of the central celestial body. This type of orbit has been widely used in various earth remote sensing missions such as ground survey, reconnaissance and scientific exploration, such as space missions such as Landsat in the United States, Envisat in Europe, SPOT in France and TerraSAR-X in Germany. [0003] The periodic repeating characteristic of...

Claims

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Application Information

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IPC IPC(8): G06F30/20G06F111/04G06F111/10
CPCG06F30/20G06F2111/04G06F2111/10
Inventor 何艳超张磊徐明李志武黄镐谢松于灵慧
Owner AEROSPACE DONGFANGHONG SATELLITE
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