CN108072888A - 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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- 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
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- 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
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- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
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Abstract
The invention discloses a kind of Medium-Earth Orbit space environments and the integrated detection device of effect, the collimation barrier layer of housing and each detecting element and functional layer of cylindrical interior are set including tubular detector housing, lid, collimating barrier layer center has an opening for receiving incident space environment particle, metal layer and insulating layer are arranged alternately in housing, 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 simple in structure, more, light-weight, low in energy consumption.
Description
Technical field
The invention belongs to space environment and effect detection technology field, more particularly to a kind of Medium-Earth Orbit space environment with
The integrated detection device of effect.
Background technology
Medium-Earth Orbit and referred to as MEO tracks, it is about the Earth's orbit region of 21528km to refer to height, which divides
It is furnished with substantial amounts of aeronautical satellite etc..
MEO orbital environments also have substantial amounts of charged particle in addition to vacuum, temperature, solar electromagnetic radiation.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., also has a small amount of sky
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 form：One major class be natural particulates radiation environment, the another kind of nuclear radiation environment by being generated after nuclear explosion in high altitude.My god
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
Region there is the charged particle of a large amount of earth magnetism capture is known as the radiation belt of the earth, also referred to as " model Allan " 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
Scope is very wide, and level about extends to 60000km from 10000km under the line, center about 20000~
25000km or so, latitude border are about 55 °~70 °.Its main component is low energy proton and electronics, and energy is less than 1MeV, maximum
Flux reaches 10J/m2/s.
Regional area short time blast phenomenon often occurs for solar chromosphere, is known as solar flare, is usually associated with a large amount of height
The eruption of energy particle, predominantly high energy proton, also including a small amount of α particles and heavy ion, proton energy is 10~1000MeV.
Eruption can 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 88%)
And a small amount of α particles and heavy ion, particle energy are 100~104MeV, flux is 2~4/ (cm2s).
MEO track degree 20000km, are placed exactly in the center in outer radiation belt, particle radiation environment is mainly with proton and electricity
Based on son, proton flux is higher by 1 times or more than GEO, and electronic environment is substantially suitable with GEO, but high energy electrical flux higher.
MEO spacecrafts pass through the central area of extraterrestrial radiation band, general with longer service life requirement.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.
Cause the electron energy scope of charged effect in spacecraft for 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 risk highest charged in occurring, the track that interior charged effect occurs is as shown in Figure 1.MEO tracks are in outer radiation belt
The heart is the region of charged effect greatest risk in occurring.
Material, device on satellite can caused by electric discharge ablation, dose of radiation damage and single particle effect etc. performance it is permanent
Decline and even fail, it also can the 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.
At present, in terms of MEO tracks, China mainly using Big Dipper series of satellites, 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 and single detector of MEO tracks in the world
The detection of simple function.
At present one can not be realized still without the integrated detection device for MEO orbit spaces environment and effect both at home and abroad
Kind detection device can carry out the detection of a variety of space environments and effect.
The content 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 environments and effect detection device,
It can realize the detection of a variety of space environments such as high energy electron, charge inside current potential, single-particle inversion, accumulated dose and effect, it can
It is carried in batches on MEO Orbital Space Vehicles.
Present invention employs 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 set 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, it is arranged on
Insulating layer between upper and lower two metal layers 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 equally sets agent below the metal layer of bottommost
Measure sensing element, single-particle inversion detecting element.
Wherein, the installation position of susceptible-dose element, single-particle inversion detecting element and charge inside potential monitoring piece
On the direction of incident space environment particle.
Wherein, the area of metal layer will can cover the area of insulating layer inner space.
Wherein, space environment particle is electronics, proton and heavy ion.
Wherein, the shell of detector is by the use of metal as shielding construction.
Wherein, metal layer thickness is set according to the bulkhead thickness and internal structure of spacecraft and the equivalent thickness of 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, and thickness is spacecraft module wall thickness；
2nd layer of metal layer selects the support construction material inside spacecraft as metal material, and thickness is the support knot inside spacecraft
Structure equivalent thickness；3rd layer of metal layer selects spacecraft unit or the cabinet of load or the material of unit supporting item as metal material
Material, thickness are spacecraft unit or the cabinet thickness of load；4th layer of metal layer selects internal typical shadow shield material as gold
Belong to layer material, thickness is typical shadow shield layer thickness.
Wherein, MOSFET field-effect tube can be selected in dosage sensor.It is placed respectively in the different position 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, can realize the classification of the high energy electron of different-energy, while can obtain that spacecraft surface and interior occurs
Single particle effect, total dose effect and inside occur for different position inside the total number evidence and spacecraft of portion's different position
The risk situation of charging and discharging effects (charged effect in abbreviation).The present invention has the function of simple in structure, more, light-weight, low in energy consumption
The features such as.
Description of the drawings
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 of the embodiment of the invention and the integrated detection device structure of effect
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 the Medium-Earth Orbit space environment detection device part integrated with effect of the embodiment of the invention
Enlarged structure schematic diagram.
Specific embodiment
Below in conjunction with attached drawing the present invention is described in further detail, but this is merely exemplary, it is no intended to this
The protection domain of invention carries out any restrictions.Below with reference to accompanying drawings and embodiments, the present invention will be further described, it is necessary to refer to
Go 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 Fig. 2-3, Fig. 2 shows the Medium-Earth Orbit space environment of the specific embodiment of the present invention and effect collection
Into detection device structure diagram is changed, the collimation that wherein detection device includes columnar housing, case top lid is set stops
Each detecting element and functional layer that layer and cylindrical interior are set, the effect on collimation barrier layer 1 is for space radiation environment
Collimation, the second layer for being located at the collimation barrier layer of first layer on housing including lid and being layered on first layer collimation barrier layer
Layer is collimated, there is an opening to collimate layer for the incident space environment particle of reception and the second layer at two layers of center for collimating 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
Four layers are provided with altogether, and totally 3 layers of insulating layer 3 being arranged between upper and lower 2 layers of double layer of 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 tracks detection and the space environment effect of concern are high energy electron, accumulated dose, charge inside current potential, simple grain
Son overturning.
Second, more metal layers can be utilized to realize and energy section is divided to detect high energy electron.
It is metal material that 1st layer of metal layer, which selects spacecraft module wall material, and thickness is spacecraft module wall thickness；2nd layer
Metal layer select the support construction material inside spacecraft thickness be equivalent for the support construction inside spacecraft for metal material
Thickness；3rd layer of metal layer selects spacecraft unit or the cabinet of load or the material of unit supporting item as metal material, thickness
For spacecraft unit or the cabinet thickness of load；4th layer of metal layer selects internal typical shadow shield material as metal layer material
Material, thickness are typical shadow shield layer thickness.If it is desired, the metal layer number of plies can continue to increase.
Due to electronics during thin metal layer is penetrated by off-energy, can with the increase of metal layer thickness
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, it can stop that electron energy is respectively E1, E2, E3 and E4,
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, you can inverting obtains the flux of the electronics of different-energy section and the distribution of energy section.
3rd, by the use of star in commonly use electronic circuit plate material as charge inside current potential detection.
Charge inside potential monitoring sheet material selects electronic circuit plate material in star, is usually FR4 materials or polyimides
Material.Position is used inside spacecraft according to electronic circuit board, monitoring piece is placed among different metal layers.Monitoring
The thickness of piece uses thickness for electronic circuit board.The shape of piece is monitored as circle.
4th, realize the detection to total ionizing dose using dosage sensor.
MOSFET field-effect tube can be selected in dosage sensor.It is placed respectively in the different position of detection device.Outermost
Face is the radiation ionization accumulated dose for detecting spacecraft outer surface, internal available for the dosage analysis of expose material outside spacecraft
MOSFET accumulated doses meter can be used for analysis cabin in different position accumulated dose distribution.
5th, realize the detection to single particle effect using typical single-particle inversion sensing element.
Intend we selected typical single-particle inversion sensing element, such as SRAM device, to be monitored to single particle effect.It will be single
Particle overturning sensing element is periodically inquired about by certain rule setting internal logic position state and is recorded the overturning situation of logical bit.
6th, using barrier layer it is different from the prevention ability of proton and heavy ion to electronics the characteristics of, by electronics and proton
It is distinguished with heavy ion, this is the key that structure design.
Since metal layer is strong to the prevention ability of proton and heavy ion, high energy proton and heavy ion will it is most of the 1st or
2nd layer is blocked.Therefore, proton and heavy ion can be carried out using the thickness of different metal layer and the measured value of dosimeter
It rejects.
In addition, metal layer thickness is set according to the bulkhead thickness and internal structure of spacecraft and the equivalent thickness of 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 is monitored piece and is determined according in spacecraft module using position and nacelle 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 realize 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 position 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 carry out various equivalent changes and modification to the above embodiment according to the conception of patent of the present invention, be produced
It, should all be within protection scope of the present invention during the spirit that raw function is still covered without departing from specification and attached drawing.
Claims (10)
1. Medium-Earth Orbit space environment and the integrated detection device of effect, set including tubular detector housing, case top lid
Collimation barrier layer and cylindrical interior set 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, it is arranged on
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.
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 below the metal layer of bottommost susceptible-dose element, single-particle inversion is equally set to visit
Survey element.
3. Medium-Earth Orbit space environment as described in claim 1 and the integrated detection device of effect, wherein, susceptible-dose member
The installation position of part, single-particle inversion detecting element and charge inside potential monitoring piece is in the side of incident space environment particle
Upwards.
4. such as claim 1-3 any one of them Medium-Earth Orbit space environments and the integrated detection device of effect, wherein, gold
Belong to the area that the area of layer will can cover insulating layer inner space.
5. such as claim 1-3 any one of them Medium-Earth Orbit space environments and the integrated detection device of effect, wherein, it is empty
Between environmental particles be electronics, proton and heavy ion.
6. such as claim 1-3 any one of them Medium-Earth Orbit space environments and the integrated detection device of effect, wherein, it visits
The shell of device is surveyed by the use of metal as shielding construction.
7. such as claim 1-3 any one of them Medium-Earth Orbit space environments and the integrated detection device of effect, wherein, gold
Belong to layer thickness to be set according to the bulkhead thickness and internal structure of spacecraft and the equivalent thickness of instrument.
8. such as claim 1-3 any one of them Medium-Earth Orbit space environments and the integrated detection device of effect, wherein, agent
It is isolated arrangement to measure sensing element and single-particle inversion sensing element.
9. such as claim 1-3 any one of them Medium-Earth Orbit space environments 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, and thickness is spacecraft module wall thickness；2nd layer of metal layer choosing
It is metal material with the support construction material inside spacecraft, thickness is the support construction equivalent thickness inside spacecraft；3rd layer
Metal layer selects spacecraft unit or the cabinet of load or the material of unit supporting item, and as metal material, thickness is spacecraft list
The cabinet thickness of machine or load；4th layer of metal layer selects internal typical shadow shield material, and as metal layer material, thickness is allusion quotation
Type shadow shield layer thickness.
10. such as claim 1-3 any one of them Medium-Earth Orbit space environments and the integrated detection device of effect, wherein,
Dosage sensor selects MOSFET field-effect tube, is placed respectively in the different position of detection device.
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| CN108802797A (en) * | 2018-06-14 | 2018-11-13 | 山东航天电子技术研究所 | A kind of in-orbit particle detection monitors system with single particle effect |
| CN109255143A (en) * | 2018-07-06 | 2019-01-22 | 中国人民解放军63921部队 | Methods of risk assessment is charged in in-orbit spacecraft based on multifactor synergistic effect |
| CN110068856A (en) * | 2019-04-16 | 2019-07-30 | 东莞中子科学中心 | A kind of inversion program analyzed based on C Plus Plus and ROOT data |
| CN110531399A (en) * | 2019-09-02 | 2019-12-03 | 北京卫星环境工程研究所 | The early warning of spacecraft on-orbit fault and screening device |
| CN113543615A (en) * | 2021-06-29 | 2021-10-22 | 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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