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Method for relieving spacecraft communication blackout

A technology of spacecraft and black barriers, which is applied to space navigation equipment, space navigation vehicles, space vehicle radiation protection devices, etc., and can solve the problems of low reliability of spacecraft measurement and control, heavy system weight, and large power demand. Achieve the effect of reducing the total weight and volume, improving reliability and improving utilization rate

Active Publication Date: 2016-02-17
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The present invention aims to solve the problems of large system weight, large power demand and low reliability of spacecraft measurement and control existing in the existing methods for alleviating communication blackouts. The present invention provides a method for alleviating spacecraft communication blackouts

Method used

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  • Method for relieving spacecraft communication blackout
  • Method for relieving spacecraft communication blackout
  • Method for relieving spacecraft communication blackout

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specific Embodiment approach 1

[0024] Specific implementation mode one: see figure 1 and 2 Describe this embodiment, a method for alleviating spacecraft communication blackout described in this embodiment, this method is based on controllable pulse power supply system, pulse magnet 9 and local machine controller 14 Realize, the specific process of this method is : The controllable pulse power supply system is controlled by the local controller 14 to provide pulse current to the pulse magnet 9, so that the pulse magnet 9 generates a magnetic field above 1T in the order of several milliseconds, and the magnetic field magnetizes the electrons around the spacecraft antenna to produce magnetic freezing Effect, so that the electromagnetic wave passes through the window of the plasma sheath, and relieves the communication black barrier of the spacecraft.

specific Embodiment approach 2

[0025] Embodiment 2: The difference between this embodiment and the method for alleviating the communication blackout of spacecraft described in Embodiment 1 is that the pulse magnet 9 is a cylindrical structure with multilayer copper conductors;

[0026] The controllable pulse power supply system includes battery pack 1, main discharge switch 2, No. 1 current-sharing adjustable resistor 3, No. 1 fuse 4, No. 2 fuse 5, DC circuit breaker 6, freewheeling diode 7, and freewheeling resistor 8 , pulse magnet 9, commutation switch 10, commutation inductance 11, commutation resistance 12 and commutation capacitor 13;

[0027] The negative pole of the battery pack 1 is connected to the power ground, and its positive pole is connected to the electrical input terminal of the main discharge switch 2 and one end of the commutation capacitor 13 at the same time, and the electrical output terminal of the main discharge switch 2 is connected to one end of the No. 1 current-sharing adjustable ...

specific Embodiment approach 3

[0032]Embodiment 3: The difference between this embodiment and the method for alleviating spacecraft communication blackout described in Embodiment 1 is that the pulse current peak value provided to the pulse magnet through the controllable pulse power supply system is 5000A, The peak value of the magnetic field generated by the center of the pulse magnet is 5T, and the rise time, peak duration, and fall time of the pulse magnetic field are 4ms, 2ms, and 4ms, respectively.

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Abstract

The invention provides a method for relieving spacecraft communication blackout, and belongs to the field of communication blackout relief. The method solves problems that an existing method for relieving communication blackout is large in system weight, large in electric energy requirement, and low in spacecraft tracking telemetry and control reliability. The method is realized based on a controlled pulsed power supply system, a pulsed magnet, and a local controller. The specific process of the method comprises: through the local controller, controlling the controlled pulsed power supply system to provide pulse current to the pulsed magnet, so that the pulsed magnet generates a magnetic field of more than 1T in a plurality of millisecond magnitude, the magnetic field magnetizes electrons near an antenna of the spacecraft, to generate a magnetic freezing effect, so as to form electromagnetic waves to pass through a window of plasma sheath, and relieve communication blackout of the spacecraft. The method is mainly used on a spacecraft.

Description

technical field [0001] The invention belongs to the field of alleviating communication blackouts. Background technique [0002] When the spacecraft re-enters the high-speed flight in the atmosphere, the shock wave generated by the head will convert part of the kinetic energy of the spacecraft into the heat energy of the surrounding gas, and the surrounding gas molecules are in a viscous state, and the heat is not easy to dissipate, which will make the spacecraft A high temperature zone with a temperature of several thousand degrees Celsius is formed around it. The gas in the high temperature area and the molecules of the surface material of the spacecraft are decomposed and ionized to form a plasma sheath, which completely wraps the spacecraft and can absorb and reflect electromagnetic waves, so that the communication signals between the spacecraft and the ground command station or satellite are affected. Severe interference or even interruption, this phenomenon is called c...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/54B64G1/66
CPCB64G1/54B64G1/66
Inventor 鄂鹏凌文斌吴绍朋毛傲华
Owner HARBIN INST OF TECH
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