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X-ray pulsar navigation ground test system

A ground test system and pulsar navigation technology, applied in the direction of measuring devices, instruments, etc., can solve problems such as inability to receive

Inactive Publication Date: 2013-04-17
CHINA ACADEMY OF SPACE TECHNOLOGY
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Problems solved by technology

[0004] The purpose of the present invention is to: overcome the problems and difficulties that the ground cannot receive X-ray signals radiated by pulsars, and provide a ground distributed, full-channel, semi-physical, closed-loop test and verification system, which simulates large-scale dynamic environments realistically Under the pulsar X-ray photon signal radiation characteristics, closed-loop test pulsar navigation detector performance, examine pulsar navigation algorithm and verify the feasibility of pulsar navigation system design

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  • X-ray pulsar navigation ground test system

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[0027] The technical solution will now be further explained in conjunction with the accompanying drawings;

[0028] Signal control subsystem, mathematical simulation area, photon detection area and navigation demonstration subsystem 5 (see Figure 2). The signal control subsystem is a set of network monitoring and management equipment, including 1 management control server, 1 signal controller, 2 switches, and other network equipment. It is mainly responsible for the state monitoring and command scheduling of the entire system; the mathematical simulation area In terms of hardware and functional partitions, it includes orbit data generation subsystem 6, navigation database subsystem 7, pulse contour extraction subsystem 8, navigation parameter estimation subsystem 9, large-scale dynamic effect subsystem 10, and computers for these subsystems to run simulation software The equipment consists of 5 simulation computers including navigation parameter estimation computer, pulse cont...

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Abstract

The invention relates to an X-ray pulsar navigation ground test system, which comprises a signal control sub-system, an orbital data generation sub-system, a navigation database sub-system, a pulse contour extraction sub-system, a navigation parameter estimation sub-system, a large-scale dynamic effect sub-system, an X-ray pulsar signal simulation sub-system, a detector sub-system and a navigation demonstration sub-system, wherein the orbital data generation sub-system comprises a Walker constellation satellite orbit module, a lunar exploration module and a Mars exploration orbit module; the large-scale dynamic effect sub-system comprises a large-scale space effect simulation module and an in-orbit dynamic effect simulation module; and the X-ray pulsar signal simulation sub-system comprises an X-ray generator and a vacuum channel. By realistically simulating the radiation characteristics of pulsar X-ray photon signals in a large-scale dynamic environment, the performance of a pulsar navigation probe is subjected to a closed loop test, the pulsar navigation algorithm is examined, and the feasibility of the scheme design of the pulsar navigation system is verified.

Description

technical field [0001] The invention belongs to the technical field of autonomous navigation of X-ray pulsar spacecraft, and relates to an X-ray pulsar navigation ground test system. Background technique [0002] The radiation of pulsars in the X-ray frequency band is mainly concentrated at 0.1~15keV, but due to the strong absorption of X-rays in this frequency band in the earth's atmosphere, the X-ray signals radiated by pulsars cannot be received on the ground; therefore, it is necessary to break through pulsars Key technologies such as analog source, large-scale space-time reference, high-stability pulse waveform modulation and time retention, etc., build a ground distributed, full-channel, semi-physical, closed-loop test and verification system to meet the ground test verification and program design of key technologies of the pulsar navigation system The demand for quantitative demonstration of feasibility lays the foundation for the space flight test of pulsar navigatio...

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Application Information

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IPC IPC(8): G01C25/00
Inventor 贝晓敏徐立宏帅平吴耀军
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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