CN108072888B - Medium-Earth Orbit space environment and the integrated detection device of effect - Google Patents
Medium-Earth Orbit space environment and the integrated detection device of effect Download PDFInfo
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- CN108072888B CN108072888B CN201711347076.1A CN201711347076A CN108072888B CN 108072888 B CN108072888 B CN 108072888B CN 201711347076 A CN201711347076 A CN 201711347076A CN 108072888 B CN108072888 B CN 108072888B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
- G01T1/00—Measuring X-radiation, gamma radiation, corpuscular radiation, or cosmic radiation
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R19/00—Arrangements for measuring currents or voltages or for indicating presence or sign thereof
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
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- G01T1/02—Dosimeters
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Abstract
The invention discloses a kind of Medium-Earth Orbit space environments and the integrated detection device of effect, collimation barrier layer and each detecting element and functional layer of cylindrical interior of shell are set including tubular detector housing, lid, collimation barrier layer center has an opening for receiving incident space environment particle, metal layer and insulating layer are arranged alternately in shell, wherein, insulating layer forms an inner space, for accommodating susceptible-dose element, single-particle inversion detecting element and charge inside potential monitoring piece.The present invention has the function of the features such as structure is simple, more, light-weight, low in energy consumption.
Description
Technical field
The invention belongs to space environment and effect detection technology field, in particular to a kind of Medium-Earth Orbit space environment with
The integrated detection device of effect.
Background technique
Medium-Earth Orbit and referred to as MEO track refer to that height is about the Earth's orbit region of 21528km, the region point
It is furnished with a large amount of navigation satellite etc..
MEO orbital environment is other than vacuum, temperature, solar electromagnetic radiation, and there are also a large amount of charged particles.These band electrochondrias
The source of son is mainly outer radiation belt, solar cosmic ray and galactic cosmic rays of the radiation belt of the earth etc., and there are also a small amount of skies
Between fragment and micrometeroroid.
Space particle radiation environment is primarily referred to as the charged particle environment for the various energy that spacecraft in orbit is met with, by
Two major classes composition: a major class is natural particulates radiation environment, another kind of for nuclear radiation environment generated after nuclear explosion in high altitude.It
The main component of right particle radiation is electronics and proton, has the characteristics that energy spectrum width, intensity are big, mainly includes three aspect sources:
Radiation belt of the earth particle, solar cosmic ray and galactic cosmic rays.
Since the earth is there are magnetic field, the charged particle in space is captured by magnetic field, is gathered in earth surrounding space, by this
There is the regions of the charged particle of a large amount of earth magnetism capture to be known as the radiation belt of the earth, also referred to as " Fan Alun " band.Due to band electrochondria
Subspace Distribution is uneven, more intensively forms 2 radiation zones: inner radiation belt and outer radiation belt.The space in outer radiation belt
Range is very wide, and level about extends to 60000km from 10000km under the line, center about 20000~
25000km or so, latitude boundary are about 55 °~70 °.Its main component is low energy proton and electronics, and energy is lower than 1MeV, maximum
Flux reaches 10J/m2/s.
Solar chromosphere regional area short time blast phenomenon, referred to as solar flare frequent occurrence, are usually associated with a large amount of height
The eruption of energy particle, predominantly high energy proton, also include a small amount of α particle and heavy ion, and proton energy is 10~1000MeV.
Eruption will cause the increase of particle flux, it will usually continue several hours by one week or more, but continue 2~3 days in typical case.
Galactic cosmic rays is from ultramundane charged particle stream, and main component is high energy proton (accounting for about 88%)
And a small amount of α particle and heavy ion, particle energy are 100~104MeV, flux is 2~4/ (cm2s).
MEO track degree 20000km, is placed exactly in the center in outer radiation belt, particle radiation environment is mainly with proton and electricity
Based on son, proton flux ratio GEO will be higher by 1 times or more, and electronic environment is substantially suitable with GEO, but high energy electrical flux is higher.
MEO spacecraft passes through the central area of extraterrestrial radiation band, generally has the requirement of longer service life.Therefore,
Background high energy electron can cause inside satellite charge and discharge, and galactic comic ray and solar energetic particles also can cause spoke to satellite
Penetrate damage.
The electron energy range for causing charged effect in spacecraft is 100keV to several MeV, once the electricity of dielectric
The natural discharge threshold that lotus is accumulated over insulating materials can cause the electric discharge of dielectric, cause the interference to electronic system.Closely
Multiple spacecraft on-orbit fault over year is classified as caused by interior charged effect, such as solar array driving device (solar array
Drive assembly, SADA) power ring electric discharge etc..Interior charged effect occurs mainly in middle high orbit, wherein inside and outside radiation
With the risk highest charged in occurring, the track that interior charged effect occurs is as shown in Figure 1.MEO track is in outer radiation belt
The heart is the region of charged effect greatest risk in occurring.
Material, device on satellite can because caused by electric discharge ablation, dose of radiation damage and single particle effect etc. performance it is permanent
Decline is even failed, also can be because of recoverable negative effect in short-term caused by charge and discharge electrical interference and single particle effect.And single-particle is imitated
Ying Zhong, highest probability of occurrence is Single event upset effecf.
Therefore, high energy electron and proton and heavy ion etc. cause interior charged effect, Single event upset effecf, total dose effect
Etc. being to need the space environment and effect paid close attention to.
Currently, China mainly utilizes Beidou series of satellites in terms of MEO track, it is equipped with high-energy electronic detector, radiation
Dosemeter, surface potential detector detect electronics, satellite dose of radiation, satellite surface charging potential etc..These are visited
A kind of detection of function can only be realized by surveying device.Only have for the environment detection of MEO track and single detector in the world
The detection of simple function.
It cannot achieve one still without the integrated detection device for MEO orbit space environment and effect both at home and abroad at present
Kind detection device can carry out the detection of a variety of space environments and effect.
Summary of the invention
In order to solve the above-mentioned technical problem, the object of the present invention is to provide a kind of MEO space environment and effect detection device,
The detection that a variety of space environments and effect such as high energy electron, charge inside current potential, single-particle inversion, accumulated dose may be implemented, can
It is carried in batches on MEO Orbital Space Vehicle.
Present invention employs the following technical solutions:
Medium-Earth Orbit space environment and the integrated detection device of effect, including tubular detector housing, case top lid
If collimation barrier layer and cylindrical interior setting each detecting element and functional layer, collimation barrier layer center have one opening with
For receiving incident space environment particle, metal layer and insulating layer are arranged alternately in tubular detector housing, wherein setting exists
Insulating layer between upper layer and lower layer metal layer forms an inner space, for accommodating susceptible-dose element, single-particle inversion detection
Element and charge inside potential monitoring piece, and the opening at collimation barrier layer center is provided with susceptible-dose element.
Wherein, the number of plies of metal layer is greater than the number of plies of insulating layer, and agent is equally arranged below the metal layer of bottommost
Measure sensing element, single-particle inversion detecting element.
Wherein, the setting position of susceptible-dose element, single-particle inversion detecting element and charge inside potential monitoring piece
On direction in incident space environment particle.
Wherein, the area of metal layer wants that the area of insulating layer inner space can be covered.
Wherein, space environment particle is electronics, proton and heavy ion.
Wherein, the shell of detector uses metal as shielding construction.
Wherein, metal layer thickness is set according to the equivalent thickness of the bulkhead thickness and internal structure of spacecraft and instrument.
Wherein, susceptible-dose element and single-particle inversion sensing element are isolated arrangement.
Wherein, it is metal material that the 1st layer of metal layer, which selects spacecraft module wall material, with a thickness of spacecraft module wall thickness；
The support construction material that 2nd layer of metal layer is selected inside spacecraft is metal material, with a thickness of the support knot inside spacecraft
Structure equivalent thickness；3rd layer of metal layer selects spacecraft single machine or the cabinet of load or the material of single machine supporting element as metal material
Material, with a thickness of spacecraft single machine or the cabinet thickness of load；4th layer of metal layer selects internal typical shadow shield material as gold
Belong to layer material, with a thickness of typical shadow shield thickness degree.
Wherein, MOSFET field-effect tube can be selected in dosage sensor.It is placed respectively in the different location of detection device.
The present invention passes through multiple metal layers, susceptible-dose element, single-particle inversion sensing element and insulating circuit board ring
Combination lay, may be implemented the classification of the high energy electron of different-energy, while available generation spacecraft surface and interior
Single particle effect, total dose effect and inside occur for different location inside the total number evidence and spacecraft of portion's different location
The risk situation of charging and discharging effects (charged effect in abbreviation).The present invention has the function of that structure is simple, more, light-weight, low in energy consumption
The features such as.
Detailed description of the invention
The track schematic diagram that Fig. 1 occurs for interior charged effect under space environment in the prior art；
Fig. 2 is the Medium-Earth Orbit space environment and the integrated detection device structure of effect of the embodiment of the invention
Schematic diagram；
Wherein: 1 is collimation barrier layer；2 be metal layer；3 be insulating layer；4 be susceptible-dose element；5 be single-particle inversion
Sensing element；6 monitor piece for surface potential；
Fig. 3 is Medium-Earth Orbit space environment and the integrated detection device part of effect of the embodiment of the invention
Enlarged structure schematic diagram.
Specific embodiment
Below in conjunction with attached drawing, invention is further described in detail, but this is only exemplary, it is no intended to this
The protection scope of invention carries out any restrictions.Below with reference to accompanying drawings and embodiments, the present invention will be further described, needs to refer to
Out, embodiment described below is intended to convenient for the understanding of the present invention, and does not play any restriction effect to it.
Referring to figure 2-3, Fig. 2 shows the Medium-Earth Orbit space environment and effect collection of a specific embodiment of the invention
At detection device structural schematic diagram is changed, wherein the detection device includes that the collimation that sets of columnar shell, case top lid stops
Layer and each detecting element and functional layer of cylindrical interior setting, the effect on collimation barrier layer 1 is for space radiation environment
Collimation comprising the second layer that lid is located at the collimation barrier layer of first layer on shell and is layered on first layer collimation barrier layer
There is an opening to collimate layer with the space environment particle for receiving incidence and the second layer for collimation layer, the center of two layers of collimation layer
Area is less than the area of first layer, and metal layer 2 and insulating layer 3 are arranged alternately in tubular detector housing, wherein metal layer 2
It is provided with four layers altogether, is arranged in totally 3 layers of insulating layer 3 between 2 layers of upper layer and lower layer metal, each insulating layer 3 is formed in one
Portion space, for accommodating susceptible-dose element 4, single-particle inversion detecting element 5 and charge inside potential monitoring piece 6 (see figure
3), and the opening at collimation barrier layer center is additionally provided with susceptible-dose element.Specifically, first, explicitly for
The space environment of MEO track detection and the space environment effect of concern are high energy electron, accumulated dose, charge inside current potential, simple grain
Son overturning.
Second, it can use more metal layers and realize and divide energy section to detect high energy electron.
It is metal material that 1st layer of metal layer, which selects spacecraft module wall material, with a thickness of spacecraft module wall thickness；2nd layer
Metal layer select spacecraft inside support construction material be metal material, it is equivalent with a thickness of the support construction inside spacecraft
Thickness；3rd layer of metal layer selects spacecraft single machine or the cabinet of load or the material of single machine supporting element as metal material, thickness
For spacecraft single machine or the cabinet thickness of load；4th layer of metal layer selects internal typical shadow shield material as metal layer material
Material, with a thickness of typical shadow shield thickness degree.If it is desired, the metal layer number of plies can continue growing.
Since electronics can with the increase of metal layer thickness by off-energy during penetrating thin metal layer
The electron energy of prevention is higher and higher, and therefore, the energy for the electronics being deposited in different metal is respectively at different energy models
It encloses.Assuming that metal layer a, metal layer b, metal layer c, metal layer d, can stop to be respectively E1, E2, E3 and E4 to electron energy,
Then meet E1 < E2 < E3 < E4.According to the metal layer material and metal layer thickness of selection, the Particle Deliveries such as Geant4 analysis side is utilized
Method, can inverting obtain different-energy section electronics flux and energy section distribution.
Third, using electronic circuit plate material common in star as the detection of charge inside current potential.
Charge inside potential monitoring sheet material selects electronic circuit plate material in star, usually FR4 material or polyimides
Material.Position is used inside spacecraft according to electronic circuit board, monitoring piece is placed among different metal layers.Monitoring
Piece uses thickness with a thickness of electronic circuit board.The shape for monitoring piece is circle.
4th, the detection to total ionizing dose is realized using dosage sensor.
MOSFET field-effect tube can be selected in dosage sensor.It is placed respectively in the different location of detection device.Outermost
Face is the radiation ionization accumulated dose for detecting spacecraft outer surface, can be used for the dosage analysis of the outer expose material of spacecraft, internal
MOSFET accumulated dose meter can be used for analyzing different location in cabin accumulated dose distribution.
5th, the detection to single particle effect is realized using typical single-particle inversion sensing element.
Quasi- we selected typical single-particle inversion sensing element, such as SRAM device, to be monitored to single particle effect.It will be single
Particle overturns sensing element and presses certain rule setting internal logic position state, periodically inquires and record the overturning situation of logical bit.
6th, using the barrier layer feature different from the prevention ability of proton and heavy ion to electronics, by electronics and proton
It is distinguished with heavy ion, this is the key that structure design.
Since prevention ability of the metal layer to proton and heavy ion is strong, high energy proton and heavy ion will it is most of the 1st or
2nd layer is blocked.Therefore, the measured value of the thickness and dosimeter that can use different metal layer carries out proton and heavy ion
It rejects.
In addition, metal layer thickness is set according to the equivalent thickness of the bulkhead thickness and internal structure of spacecraft and instrument,
Each thin metal layer is fixed with insulating materials, keeps isolated.Susceptible-dose element and single-particle inversion sensing element are isolated
Arrangement.Surface potential monitors piece according to determining in spacecraft module using position and cabin screening-off position etc., material and size root
It is determined according to electronic circuit board common used material in spacecraft module.
The present apparatus can be realized the detection of a kind of space environment and 3 kinds of space environment effects, while can be in spacecraft module
Charging potential, accumulated dose and the single-particle inversion situation of different location are assessed.
Although giving detailed description and explanation to the specific design method and thinking of this patent above, it should be noted that
, we can the conception of patent according to the present invention various equivalent changes and modification are carried out to above embodiment, produced
It, should all be within protection scope of the present invention when the spirit that raw function is still covered without departing from specification and attached drawing.
Claims (8)
1. Medium-Earth Orbit space environment and the integrated detection device of effect, including tubular detector housing, case top lid are set
Collimation barrier layer and cylindrical interior setting each detecting element and functional layer, collimation barrier layer center have one opening with
In receiving incident space environment particle, metal layer and insulating layer are arranged alternately in tubular detector housing, wherein be arranged upper
Insulating layer between lower two metal layers forms an inner space, for accommodating susceptible-dose element, single-particle inversion detection member
Part and charge inside potential monitoring piece, and the opening at collimation barrier layer center is provided with susceptible-dose element, wherein agent
The setting position for measuring sensing element, single-particle inversion detecting element and charge inside potential monitoring piece is in incident space environment
On the direction of particle, space environment particle is proton and heavy ion.
2. Medium-Earth Orbit space environment as described in claim 1 and the integrated detection device of effect, wherein the layer of metal layer
Number is greater than the number of plies of insulating layer, and susceptible-dose element and single-particle inversion spy are equally arranged below the metal layer of bottommost
Survey element.
3. Medium-Earth Orbit space environment as claimed in claim 1 or 2 and the integrated detection device of effect, wherein metal layer
Area want that the area of insulating layer inner space can be covered.
4. such as the described in any item Medium-Earth Orbit space environments of claim 1-2 and the integrated detection device of effect, wherein visit
The shell for surveying device uses metal as shielding construction.
5. such as the described in any item Medium-Earth Orbit space environments of claim 1-2 and the integrated detection device of effect, wherein gold
Belong to thickness degree to be set according to the equivalent thickness of the bulkhead thickness and internal structure of spacecraft and instrument.
6. such as the described in any item Medium-Earth Orbit space environments of claim 1-2 and the integrated detection device of effect, wherein agent
It measures sensing element and single-particle inversion sensing element is isolated arrangement.
7. such as the described in any item Medium-Earth Orbit space environments of claim 1-2 and the integrated detection device of effect, wherein the
It is metal material that 1 layer of metal layer, which selects spacecraft module wall material, with a thickness of spacecraft module wall thickness；2nd layer of metal layer choosing
It is metal material with the support construction material inside spacecraft, with a thickness of the support construction equivalent thickness inside spacecraft；3rd layer
Metal layer selects spacecraft single machine or the cabinet of load or the material of single machine supporting element as metal material, with a thickness of spacecraft list
The cabinet thickness of machine or load；4th layer of metal layer selects internal typical shadow shield material as metal layer material, with a thickness of allusion quotation
Type shadow shield thickness degree.
8. such as the described in any item Medium-Earth Orbit space environments of claim 1-2 and the integrated detection device of effect, wherein agent
It measures sensor and selects MOSFET field-effect tube, placed respectively in the different location of detection device.
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| CN108802797B (en) * | 2018-06-14 | 2022-06-21 | 山东航天电子技术研究所 | On-orbit particle detection and single event effect monitoring system |
| CN109255143B (en) * | 2018-07-06 | 2023-01-31 | 中国人民解放军63921部队 | On-orbit spacecraft electrification risk assessment method based on multi-factor synergistic effect |
| CN110068856B (en) * | 2019-04-16 | 2021-04-13 | 东莞中子科学中心 | Neutron energy spectrum calculation method based on C + + language and ROOT data analysis |
| CN110531399B (en) * | 2019-09-02 | 2021-07-06 | 北京卫星环境工程研究所 | Spacecraft on-orbit fault early warning and discriminating device |
| CN113543615B (en) * | 2021-06-29 | 2022-11-01 | 中国科学院长春光学精密机械与物理研究所 | Irradiation protection method for space electronic equipment |
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