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Pulsar navigation method with single detector

A pulsar navigation, single-detector technology, applied in the direction of combined navigator, etc., can solve the problems of difficult implementation, large load and high cost

Inactive Publication Date: 2013-04-03
NAT TIME SERVICE CENT CHINESE ACAD OF SCI
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AI Technical Summary

Problems solved by technology

More than 4 large-area X-ray detectors, heavy load, high power consumption, high cost, difficult to implement
Its essence is still an integrated navigation technology based on inertial navigation system and pulsar timing observation as a constraint. The main problem is that the navigation accuracy is low

Method used

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  • Pulsar navigation method with single detector
  • Pulsar navigation method with single detector
  • Pulsar navigation method with single detector

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Embodiment Construction

[0058] The present invention comprises the following steps:

[0059]Step 1: According to the preset observation sequence, the X-ray detector on the spacecraft observes four millisecond pulsars in sequence. The observation process of each pulsar is as follows: the X-ray detector receives the X-ray photons from the observation target, combines with the on-board atomic clock to measure the moment when the photons arrive at the detector, and saves the original observation data of the arrival time;

[0060] Step 2, using the estimated values ​​of the position and velocity of the spacecraft to correct the Doppler effect, relativistic effect, and Shapiro delay of the original observation signal;

[0061] Step 3: On the basis of completing the preprocessing of the original observation signal, the observation signal is superimposed according to the rotation period of the observed pulsar to give a clear pulse profile, and then the arrival time of the reference point of the pulse profile...

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Abstract

The invention provides a pulsar navigation method with a single detector, which comprises the steps that an X-ray detector on a spacecraft receives X-ray photons from four millisecond pulsars one by one and measures times when the X-ray photons arrive at the X-ray detector; the arrival times are saved as original observation signals; a doppler effect, a relativistic effect and Shapiro delay correction are performed; the arrival time of a pulse profile datum point is obtained; an observation equation of each corresponding pulsar is formed; and independent timing and positioning of the spacecraft are realized after resolving. The pulsar navigation method can accomplish absolute positioning of the pulsars with the single detector, and the positioning accuracy is high without secular error accumulation.

Description

technical field [0001] The invention relates to an astronomical autonomous navigation method for a spacecraft, in particular to a combined navigation method applied to the combination of inertial navigation and astronomical navigation technology of a deep space exploration aircraft. Background technique [0002] Among the autonomous navigation technologies currently used in spacecraft, inertial navigation is the most widely used technology, and it is also a completely autonomous spacecraft positioning and navigation technology. Given the initial motion state of the carrier, the angular velocity and linear acceleration of the carrier relative to the inertial space can be measured by using the inertial measurement element of the inertial navigation system, and various navigation parameters of the carrier can be obtained through integral calculation. The inertial navigation system is mainly composed of gyroscopes, accelerometers, navigation computers, and servo circuits. The i...

Claims

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Application Information

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IPC IPC(8): G01C21/24
Inventor 高玉平
Owner NAT TIME SERVICE CENT CHINESE ACAD OF SCI
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