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On-orbit micro space debris multi-parameter measuring probe and method

A small space, measuring probe technology, applied in the direction of measuring devices, instruments, etc., can solve the problems of large volume power consumption, complex design, inability to measure speed, etc., to achieve the effect of simple structure, light weight, and easy integration and installation of the probe

Active Publication Date: 2021-02-02
BEIJING INST OF SPACECRAFT SYST ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The technical principle of the space debris plasma detector is: when the space debris hits the detector target at high speed, a large amount of plasma is generated, the electrons and ions in the plasma are separated by the electric field, and the electron or ion current is measured to obtain the space debris velocity. The "Dust Detector (DDS)" detector with advanced technology was carried on the Galileo satellite and the Ulysses satellite in 1987 and 1990 respectively, and the GORID plasma detector was carried on the Russian EXPRESS-2 satellite. large, complex design
[0006] The above measurement methods use electronic circuits (active) to obtain measurement data and information on orbit; while passive measurement methods are used on recyclable spacecraft, Chinese patent (CN201010522728.2) discloses a passive (circuit-free) measurement The way is to use the thin film exposed in space to capture tiny debris, then transport the detection film back to the ground, and use physical analysis methods to analyze the injection depth of tiny debris and the chemical composition of the debris. This method cannot measure the information of tiny space debris in real time, and cannot measure speed

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  • On-orbit micro space debris multi-parameter measuring probe and method
  • On-orbit micro space debris multi-parameter measuring probe and method
  • On-orbit micro space debris multi-parameter measuring probe and method

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Embodiment 1

[0067] The present invention proposes a multi-parameter tiny space debris measurement probe, the structure of which is shown in figure 2 As shown, it includes front film 1, rear film 2 placed in parallel, 20 front collecting electrodes 3, 20 rear collecting electrodes 4, 20 front collecting electrode charge amplifiers 5, 20 rear collecting electrode charge amplifiers 6, front film impact Trigger 7, high-frequency pulse counter 8, front collecting electrode charge signal addition amplifier 9, rear collection electrode charge signal addition amplifier 10, rear film impact trigger 11.

[0068] In this embodiment, the front film 1 and the rear film 2 of the probe use aluminized polyimide film as the impact carrier, and the high-speed space tiny debris hits the front film 1 and the rear film 2 to generate plasma, and the ions in the plasma are collected between the electrodes and Under the action of the electric field between the films, the ions are collected and a charge pulse sig...

Embodiment 2

[0127] The front film 1 and the rear film 2 are aluminized polyimide films, and the thickness refers to the data in Table 1, and the film thickness is 10 μm; p is the depth of the impact crater on the target (cm), d p is the diameter of incident tiny space debris (cm), B H is the Brinell hardness of the film material; ρ p is the film material density (g / cm 3 ); t is the density of tiny space debris (g / cm 3 ); V n is the incident velocity relative to the film (km / s); C is the sound velocity of the material, which is 5.1km / s, and the incident direction θ is 0. The thickness of the film is 20 μm, and the depth of the micro-debris impact crater should be twice the thickness of the film (40 μm). The corresponding minimum measurable space debris range is shown in Table 1 below.

[0128] Table 1 The impact crater depth of tiny space debris in polyimide (for space debris made of aluminum and iron, θ is 0)

[0129]

[0130] Iron tiny space debris with a diameter of 10 microns ...

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Abstract

The invention relates to an on-orbit micro space debris multi-parameter measuring probe and method, belongs to the field of space debris monitoring and measuring, and relates to an on-orbit passive micro debris size, speed and mass multi-parameter measuring method used for spacecraft on-orbit space debris measuring loads. The probe comprises front and rear film sensors, front and rear charge collection electrodes, a charge measurement amplifier and a high-frequency pulse counter. Metal films are plated on a front film and a rear film, equidistant charge collecting wires are arranged behind thefront film and in front of the rear film, and negative direct-current voltage is applied between the collecting electrodes and the films and used for collecting charge signals generated when tiny fragments impact the front film and the rear film. Charges generated by the front film and the rear film are collected by the collecting electrodes and amplified into voltage pulse signals by the chargeamplifier, the time difference of impact signals on the front film and the rear film is measured by the high-frequency pulse counter, and speed and direction information is obtained. Impact debris energy is obtained through the charge quantity signal, and the mass of the space debris can be obtained through the combination speed.

Description

technical field [0001] The invention belongs to the field of space debris monitoring and measurement, and relates to an on-orbit micro space debris multi-parameter measurement probe and a measurement method. The on-orbit passive impact method measures multiple parameters of the micro debris size, velocity and mass, and is used for spacecraft on-orbit micro Space debris measurement payload. Background technique [0002] At present, more and more space debris poses an increasingly serious threat to more and more spacecraft in orbit. The research on space debris has been highly valued by relevant fields at home and abroad. The observation and monitoring of space debris is the key to the development of space debris research. A large number of ground-based optical and radio observation equipment established at home and abroad can observe space debris above the centimeter level, which is the measurement of small space debris (submillimeter and below the size, "Space Debris" China ...

Claims

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Application Information

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IPC IPC(8): G01D21/02
CPCG01D21/02
Inventor 向宏文郝志华李衍孙华亮蔡震波张志平戴孟瑜秦珊珊闫军李怀锋
Owner BEIJING INST OF SPACECRAFT SYST ENG