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Autonomous orbit determination method of navigation satellite constellation

A technology for navigation satellites and autonomous orbit determination, which is applied to integrated navigators, navigation calculation tools, etc., and can solve problems such as rank deficiency

Inactive Publication Date: 2014-09-17
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Abstract
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  • Application Information

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Problems solved by technology

However, there is a rank deficit problem in the autonomous orbit determination of near-Earth satellite navigation systems only by using inter-satellite ranging

Method used

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  • Autonomous orbit determination method of navigation satellite constellation
  • Autonomous orbit determination method of navigation satellite constellation
  • Autonomous orbit determination method of navigation satellite constellation

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Embodiment Construction

[0052] In order to better understand the improvements made by the present invention relative to the prior art, before the specific implementation of the present invention is described in detail, the Earth-Moon Lagrangian orbit in the content of the invention is further supplemented.

[0053] For a navigation satellite operating in a Lagrangian orbit, the simplest model that can describe its dynamics is as follows figure 1 The model of the circular restricted three-body problem shown—suppose two large celestial bodies m 1 and m 2 Only move under the action of mutual gravitation, and the orbits between them are of radius r 12 circle. Assume a non-inertial coordinate system xyz (joint coordinate system), the origin of the coordinates is the center of mass of the two large celestial bodies, and the x-axis is defined by m 1 point to m 2 , the z-axis is perpendicular to m 2 around m 1 , the y-axis and the x- and z-axis satisfy the right-hand rule. In this coordinate system, m...

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Abstract

The invention belongs to the field of autonomous orbit determination of satellites and relates to an autonomous orbit determination method of a navigation satellite constellation. The autonomous orbit determination method of the navigation satellite constellation comprises the following steps: (1) starting autonomous orbit determination and initializing a system; (2) acquiring an inter-satellite ranging between satellites; (3) calculating an observation matrix of the inter-satellite ranging; (4) forecasting an orbit by using an orbit dynamical model; (5) updating measurement and estimating state by using a kalman filtering algorithm; and (6) judging whether the autonomous orbit determination is ended, operating the steps (2)-(6) again if the autonomous orbit determination is not ended, and conversely, ending and exiting an autonomous orbit determination program. Compared with the conventional autonomous orbit determination of navigation satellite constellation, the autonomous orbit determination method of the navigation satellite constellation has the advantages that the method is capable of avoiding the rank defect problem of autonomous orbit determination method of the navigation satellite constellation by using the inter-satellite ranging and is high in long-term autonomous orbit determination accuracy.

Description

technical field [0001] The invention belongs to the field of satellite autonomous orbit determination, in particular to a method for autonomous orbit determination of a navigation satellite constellation. Background technique [0002] The ability of autonomous orbit determination will be more and more important to the development of satellite navigation systems. The satellite navigation system with autonomous orbit determination capability does not need to provide support through the global deployment of stations, and at the same time, it can reduce the burden of limited ground stations and improve the safety of the satellite navigation system. [0003] The autonomous orbit determination of the satellite navigation system can use the single-satellite autonomous orbit determination method to realize the autonomous orbit determination of the entire navigation system through the independent autonomous orbit determination of each satellite in the system. Orbit determination of ...

Claims

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Application Information

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IPC IPC(8): G01C21/24
CPCG01C21/24G01C21/20
Inventor 高有涛徐波
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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