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Method and device for autonomous orbit determination of lunar probe

An autonomous orbit determination and detector technology, applied in the field of lunar and deep space measurement and navigation, can solve the problems of long distance of lunar probes and low received signal strength, achieve broad practical engineering application prospects and improve application capabilities

Active Publication Date: 2021-04-30
NO 63921 UNIT OF PLA
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

However, due to the long distance of the lunar probe, the navigation satellite signal received by the GNSS receiver is 25dB lower than that received by the ground receiver, which puts high demands on the design of the spaceborne GNSS receiver

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  • Method and device for autonomous orbit determination of lunar probe
  • Method and device for autonomous orbit determination of lunar probe
  • Method and device for autonomous orbit determination of lunar probe

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Embodiment Construction

[0096] At present, the use of ground station measurement data does not support the autonomous orbit determination of the lunar probe, and when using the GNSS system to autonomously navigate the lunar probe, the spaceborne GNSS receiver must have the ability to capture and track weak signals. The embodiment of this application uses multiple The pseudo-range measurement of the ground station can be used for real-time autonomous orbit determination of the moon and other probes. Under the condition of the signal receiving ability of the existing near-Earth receiver, the pseudo-range measurement of multiple ground stations can be used to realize the orbit determination of the moon and other probes, improving the It has demonstrated the application capability of ground stations in real-time autonomous navigation of lunar and deep space probes, and has broad practical engineering application prospects.

[0097] The embodiment of the present application takes the lunar probe as an exam...

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Abstract

The invention discloses a method and a device for autonomous orbit determination of a lunar probe. The method comprises the steps that multiple ground stations transmit signals of modulated pseudo code ranging, station addresses, ranging correction amount and other auxiliary information; a satellite-borne receiver receives and processes ground station signals, realizes pseudo-range measurement of the lunar probe by the multiple ground stations and performs error correction by using auxiliary information; a state equation is established and linearized; a measurement equation is established and linearized; and the state parameters of the detector are estimated by using adaptive extended Kalman filtering. The method improves an application capability of the ground stations in real-time autonomous navigation of deep space probes such as the moon and the like, and has a wide actual engineering application prospect.

Description

technical field [0001] The embodiments of the present application relate to lunar and deep space measurement and navigation technologies, and in particular to a method and device for autonomous orbit determination of lunar probes by using ground multi-station pseudo-range measurements. Background technique [0002] Due to its high reliability and stable measurement accuracy, the ground-based integrated measurement system has always been the main navigation system used in lunar and deep space exploration missions. It has the capabilities of distance measurement, velocity measurement and very long baseline interferometry (VLBI). At present, the National Space Administration (NASA), the European Space Agency (ESA), and space agencies of Russia, China, and Japan have gradually built a ground-based deep space network. However, the use of the ground-based orbit determination system does not support the autonomous orbit determination / positioning of the lunar probe, which is not con...

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Application Information

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IPC IPC(8): G01S19/50
CPCG01S19/50
Inventor 樊敏李海涛程承陈少伍
Owner NO 63921 UNIT OF PLA
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