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Medium deep charging potential and internal charging electric field acquisition method and storage medium

A deep charging and acquisition method technology, applied in the direction of electrical digital data processing, instruments, calculations, etc., to achieve good reliability, guarantee high reliability requirements, and simple steps

Pending Publication Date: 2019-11-15
SHANGHAI INST OF SATELLITE EQUIP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Due to the dynamic characteristics of the radiation environment of the transfer orbit spacecraft, it is not suitable for the published analysis method of the deep charging of the medium

Method used

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  • Medium deep charging potential and internal charging electric field acquisition method and storage medium
  • Medium deep charging potential and internal charging electric field acquisition method and storage medium
  • Medium deep charging potential and internal charging electric field acquisition method and storage medium

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Embodiment 1

[0102] The present embodiment is a variation example of the basic embodiment, and provides a calculation method for the deep charging process of a GEO satellite entering orbit GEO from a parking orbit via a geosynchronous transfer orbit (GTO), specifically comprising the following steps:

[0103] Step 1. Obtain the orbital parameters of the spacecraft's parking orbital segment, transfer orbital segment, and working orbital segment. The orbital parameters include semi-major axis a, eccentricity e, orbital inclination i, right ascension of ascending node Ω, argument of perigee ω, and true anomaly ν. As shown in Table 1.

[0104] Set the orbital parameters of the berthing section, GTO section, and GEO section when the spacecraft is transferred. The semi-major axis of the parking section is 6578km (orbital height 200km); the semi-major axis of the GTO section is 24580km, and the eccentricity is 0.7324; 35786km); the rest of the parameters are default.

[0105] Table 1 Orbital pa...

Embodiment 2

[0114] This embodiment is a modification example of the basic embodiment, and provides a calculation method for the deep charging of the lunar probe during the phase-modulation transfer orbit operation before flying to the moon. The satellite specifically includes the following steps:

[0115] Step 1. Obtain the orbital parameters of the spacecraft's parking orbital segment, transfer orbital segment, and working orbital segment. The orbital parameters include semi-major axis a, eccentricity e, orbital inclination i, right ascension of ascending node Ω, argument of perigee ω, and true anomaly ν. As shown in table 2.

[0116] The star is first sent into the super-GTO orbit by the carrier rocket. After the star and rocket are separated, they will run on this orbit for 3 times. Change to 24h, run 3 laps; then carry out the third maneuver, the orbital period becomes 48h, run 1 lap. After the satellite is in orbit, it runs for a total of 7 days to meet the requirements of low orbi...

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Abstract

The invention provides a medium deep charging potential and internal charging electric field acquisition method and a storage medium. The medium deep charging potential and internal charging electricfield acquisition method includes the steps: converting the orbit parameters into real-time coordinates in a geographic coordinate system by utilizing an MATLAB program according to the orbit parameters of each transfer section of the transfer orbit spacecraft, converting the real-time coordinates into real-time geomagnetic coordinates by utilizing a geomagnetic field mode IGRF, and substituting the real-time geomagnetic coordinates into a radiation band electronic environment model to obtain a real-time electronic environment energy spectrum; and taking the particle energy spectrum as an input condition, calculating the real-time particle deposition dose rate and the injection current density in the medium in particle transport simulation software Geant4, establishing a differential equation set to calculate the real-time electric field intensity and the charging potential in the medium, and identifying the deep discharge risk of the medium during satellite orbit transfer. According to the medium deep charging potential and internal charging electric field acquisition method, the medium deep charging potential and the internal charging electric field in the dynamic operation process of the transfer orbit spacecraft can be calculated, and the deep charging and discharging risk of the spacecraft when the spacecraft passes through the radiation band orbit and performs orbit transfer can be effectively evaluated.

Description

technical field [0001] The invention relates to the field of general quality characteristics and reliability engineering of spacecraft, in particular, to a method for obtaining the charging potential of the deep layer of the medium and the internal charging electric field and the storage medium, and especially to the charging potential and charging electric field of a special orbital satellite medium material Calculation method. Background technique [0002] Transfer orbit spacecraft is a special type of spacecraft with a variable orbit, such as the Geosynchronous Transfer Orbit (GTO) during the orbiting process of a Geosynchronous Orbit (GEO) spacecraft, and the Phase Modulation Orbit (Phase Modulation Orbit) of the lunar probe after launch. orbit), etc., have the characteristics that orbital parameters change with mission requirements. [0003] This type of spacecraft will pass through the Earth's inner radiation belt, trough area and outer radiation belt many times while...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 苏京刘刚徐骏周博曹康丽李瑜婧潘阳阳
Owner SHANGHAI INST OF SATELLITE EQUIP
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