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Autonomous orbit determination method of Lagrange navigational satellite

A technology for autonomous orbit determination and navigation satellites, which can be applied in directions such as integrated navigators to solve problems such as limiting the application range of filtering algorithms, and achieve the effects of high orbit determination accuracy, simple measurement methods, and improved model accuracy.

Active Publication Date: 2017-06-23
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

In addition, the filtering algorithms currently used all assume the types of system noise and observation noise, which also limits the application range of filtering algorithms

Method used

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  • Autonomous orbit determination method of Lagrange navigational satellite
  • Autonomous orbit determination method of Lagrange navigational satellite
  • Autonomous orbit determination method of Lagrange navigational satellite

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Embodiment Construction

[0035] In order to facilitate the understanding of those skilled in the art, the present invention will be further described below in conjunction with the embodiments and accompanying drawings, and the contents mentioned in the embodiments are not intended to limit the present invention.

[0036] refer to Figure 5 Shown, a kind of Lagrangian navigation satellite autonomous orbit determination method of the present invention comprises steps as follows:

[0037] Obtain three sets of inter-satellite ranging information through a navigation constellation containing at least four satellites;

[0038] Utilize inter-satellite ranging information to update neural network weights;

[0039] Estimate the nonlinear perturbation term according to the above neural network weights;

[0040] The neural network state observer is constructed by using the nonlinear perturbation term obtained above, and the orbit information of the Lagrangian satellite is estimated.

[0041] In the embodiment...

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Abstract

The invention discloses an autonomous orbit determination method of a Lagrange navigation satellite. The method comprises the following steps: acquiring three groups of inter-satellite ranging information by virtue of a navigation constellation containing at least four satellites; updating a neural network weight by utilizing the inter-satellite ranging information; estimating a nonlinear perturbing term according to the neural network weight; and structuring a neural network state observer by utilizing the obtained nonlinear perturbing term, and estimating orbit information of the Lagrange satellite. Based on elliptic restrictive three-body problems, the perturbing force suffered by the Lagrange navigation satellite is precisely estimated by virtue of the neural network, so that the model precision of the determined orbit is improved; and the state observer is used for precisely estimating the state of the Lagrange navigation satellite, so that no limitation is made for the system noise and the observation noise, and the universality is better.

Description

technical field [0001] The invention belongs to the technical field of positioning, navigation and control, and specifically refers to a method for autonomous orbit determination of a Lagrangian navigation satellite based on a neural network state observer. Background technique [0002] Deep space exploration is currently a research hotspot in the aerospace field. Since deep space probes are far away from the earth, it is difficult to rely on ground station navigation to meet the real-time and high precision requirements of deep space probes. The special dynamic properties of the Lagrangian points of the Earth-Moon system determine that the deployment of navigation satellite constellations at Lagrangian points can provide powerful navigation support for deep space exploration. The prerequisite for Lagrangian navigation satellite constellation to provide accurate navigation information is that Lagrangian navigation satellite itself can achieve precise orbit determination. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/24
CPCG01C21/24
Inventor 高有涛金冰煜徐波周建华
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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