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Deep space probe UPF celestial self-navigation method based on starlight angle

A technology of deep space detectors and starlight angular distance, applied in the field of aerospace navigation, can solve the problems of difficult control and low navigation accuracy, and achieve the effect of improving utilization efficiency

Inactive Publication Date: 2007-07-11
BEIHANG UNIV
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Problems solved by technology

[0008] Using the vector direction as the measurement information can get better filtering accuracy and convergence effect, but there is a coupling relationship between the vector direction and the attitude of the detector, and the measurement accuracy of the vector direction is affected by the attitude accuracy. Therefore, the existing deep space detectors independently The celestial navigation method has the defects of low navigation accuracy and difficult control

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  • Deep space probe UPF celestial self-navigation method based on starlight angle
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  • Deep space probe UPF celestial self-navigation method based on starlight angle

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Embodiment Construction

[0022] As shown in Fig. 1 and Fig. 2, the deep space probe that present embodiment adopts is a kind of Mars probe, and concrete method of the present invention is as follows:

[0023] 1. Establish the state equation (i.e. the multi-body orbital dynamics model) of the Mars probe on the transfer orbit, and the state model among the present invention is considered to be a circular restricted four-body model. The circular restrictive four-body model needs to consider the interaction among the probe, the central gravity of the sun, the central gravity of Mars and the central gravity of the earth, and the influence of other perturbations is not considered.

[0024] Assume that Mars moves in a circular motion at a uniform speed around the sun, with a radius equal to the average distance r between the sun and Mars sm ; The earth moves in a uniform circular motion around the sun with a radius of 1 astronomical length unit AU. In the general restricted four-body model, the state equati...

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Abstract

The invention relates to an UPF automatic astrogation based on the star angular distance. It starts with precise modeling of the UPF track dynamics, using the star angular distance as the measuring unit, and optimizing the estimation based on the UPF (unscented particle filter) for the guide parameter. It applies to UPF guide location on the track transfer for the guide parameter determination.

Description

technical field [0001] The invention relates to the technical field of aerospace navigation, and can be applied to the determination of navigation parameters of deep space probes in the transfer orbit section, in particular to a UPF (UnscentedParticle Filter) autonomous astronomical navigation method for deep space probes based on starlight angular distance, which is suitable for transfer Navigation and positioning of deep space probes in orbit. Background technique [0002] At present, deep space exploration is a research hotspot in the international aerospace field, and my country has also made deep space exploration one of the goals of recent aerospace development. Since the deep space probes have been running in the transfer orbit for a long time, one of the characteristics of the transfer orbit is the long distance and fast speed, and the extended round-trip time of electromagnetic waves. It is very difficult for the ground station to perform telemetry and measurement a...

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Application Information

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IPC IPC(8): G01C21/00G01C21/24G01C21/02G01C21/20
Inventor 房建成宋婷婷宁晓琳杨照华
Owner BEIHANG UNIV
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