CN108106667B - Geostationary orbit space environment and the integrated detection device of effect - Google Patents
Geostationary orbit space environment and the integrated detection device of effect Download PDFInfo
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- CN108106667B CN108106667B CN201711347065.3A CN201711347065A CN108106667B CN 108106667 B CN108106667 B CN 108106667B CN 201711347065 A CN201711347065 A CN 201711347065A CN 108106667 B CN108106667 B CN 108106667B
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- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
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- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
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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 geostationary orbit space environment and the integrated detection device of effect, each detecting elements and functional layer of two layers of the collimation layer and cylindrical interior setting that are located on shell including tubular detector housing, lid；Two layers of collimation layer has central opening for receiving incident space environment particle, metal layer and insulating layer are arranged alternately in tubular detector housing, wherein, other detecting elements are respectively set on the surface on two layers of collimation barrier layer for accommodating susceptible-dose element, single-particle inversion detecting element and charge inside potential monitoring piece in the inner space of insulating layer.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 geostationary orbit space environment
With the integrated detection device of effect.
Background technique
Geostationary orbit and referred to as GEO track.Refer to that height is the Earth's orbit region of 35786km.The region point
It is furnished with a large amount of navigation satellite, telecommunication satellite etc..
GEO 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.
Wherein, space particle radiation environment is primarily referred to as the charged particle ring for the various energy that spacecraft in orbit is met with
Border is made of two major classes: a major class is natural particulates radiation environment, another kind of for nuclear radiation ring generated after nuclear explosion in high altitude
Border.The main component of natural particulates radiation is electronics and proton, has the characteristics that energy spectrum width, intensity are big, main to include three aspects
Source: 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).
GEO Orbital Space Vehicle running track height is 35786km, higher than the centre-height (20000km- in outer radiation belt
30000km), close to outer radiation belt outer edge, radiation environment is affected by interplanetary magnetic field, close with solar activity situation
It is related.The main component of GEO track radiation belt of the earth environment is capture electronics, energy catching within the scope of 0.04MeV-5MeV
Obtain the overwhelming majority that electronics accounts for sum.When big environmental perturbation event occurs, the high energy electrical flux in radiation zone can be big
Big enhancing will also result in spacecraft and interior charged effect occur.
The solid particles that micrometeroroid refers to originating from comet and asteroid belt and moves in interstellar space.Micrometeroroid
May occur to hit and cause the damage of spacecraft with spacecraft, the type and degree of damage depend on spacecraft size, configuration,
The characteristics such as working time and micrometeroroid quality, density, speed.This impact damage includes the rupture of pressure vessel, porthole
Degeneration, thermal control coating layer split, the reduction of thermal protective performance and the damage of antenna system etc..
" space junk " (also known as space trash) is mankind's solar-system operation abandonment in the waste in space, is space environment
Primary pollution source.Since emitting first man made earth satellite from nineteen fifty-seven, space junk sum alreadys exceed 4,000 ten thousand, always
Quality has reached millions of kilograms, and the space junk that ground-based telescope and radar can observe increases about 200 every year on average, greatly
9200 are had been over now in 10 centimetres of space junks.Wherein, geostationary orbit be space junk severely afflicated area it
One, and spececraft charging electric current is mainly from space plasma environment and solar extreme ultraviolet radiation environment, spatial peripheral
Plasma includes electronics, proton and other ions, we only consider electronics and proton here.All these charged particles all have
There is energy, is generally characterized with kinetic temperature T (eV).
Currently, the electron energy range of charged effect in spacecraft is caused to be 100keV to several MeV, once dielectric
Charge accumulation be more than that the natural discharge threshold of insulating materials can cause the electric discharge of dielectric, cause to do electronic system
It disturbs.Multiple spacecraft on-orbit fault in recent years 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 in,
The interior risk highest charged occurs for outer radiation belt, such as shown in Figure 1, as seen from the figure, GEO track is in the side in outer radiation belt
Edge, it may have higher interior electrification risk class.
In addition, Single event upset effecf caused by high energy electron and proton and heavy ion etc., total dose effect etc. are desirable
The space environment and effect paid close attention to.The average stroke speed of space junk and spacecraft is up to 10 kilometers per second, seriously
Threaten the safe operation of in-orbit spacecraft.It can cause Spacecraft Material and device that a series of particle impact damage effects occur.
The main physical features that space junk endangers spacecraft safety are the mechanical damage effect as caused by hypervelocity impact, spacecraft
The object of security protection is mainly grade and micron-sized space debris.Space junk greater than 10 centimetres will lead to spacecraft and ruin
Going out property damage, due to that can have at present by ground telescope or radar measuring its track, the strategy that early warning can be taken to evade
Prevent its injury to effect；Centimeter Level space junk can also cause spacecraft thoroughly to damage, and there is no practicable protection at present
Measure, unique method are on Spacecraft guidance and control and operation, and trying to reduce makes spacefarer and spacecraft that mortality damage occur
Risk；Grade space junk, which can result in spacecraft surface and generate to hit to cheat, even makes bulkhead perforate, and impact site is different, harm
Degree also have very big difference.By taking 10 kilometers of stroke speed per second as an example, 1mm aluminum space junk can penetrate about 2mm
Aluminium alloy plate, penetration hole diameter reaches about 4mm；The space junk of 10mm can puncture about 20mm aluminium alloy plate, and perforation is straight
The nearly 50mm of diameter；The single impact of micron-sized space debris not will cause direct influence to the structural strength of spacecraft, but it is tired
Product knock-on effect will lead to the decline of the device functions such as photosensitive, temperature-sensitive.Having a size of 1 micron of impact from space debris aluminum bulkhead, it is hit
Hole diameter is hit up to 4 microns, about 2 microns of depth；Hit about 100 microns of its damage field diameter of glass porthole, impact crater depth
About 3 microns；About 7 microns of hole can be formed by hitting thermal control thermal insulation layer.Although lesion size is smaller, it may still be made
At small influence, such as reduce the finish of optical surface, the radiation characteristic of change thermal control radiating surface, breakdown protection atom
Protective film of oxygen corrosion etc..Since the space debris population of this size is huge, such as in 800 kilometers high of sun synchronization rail
On road, the fluence for being greater than 1 micrometer air space fragment on every 1 square metre of area for 1 year is 30000 about nearly, damage accumulation effect
Optical surface should be will lead to chemical contamination occurs, is recessed and degrades or be broken, destroy the circuit and thermal protection system of solar battery array
The quick-wear surface of equal spacecrafts, makes spacecraft function reduction or failure.
In GEO track, China mainly utilizes DFH series platform satellite, is equipped with Solar Soft X-Ray detector, high energy matter
Sub- detector, high-energy electronic detector and static potential difference meter, to electronics, proton, X-ray, spececraft charging current potential etc.
It is detected.These detectors can only realize a kind of detection of function.
Still develop the integrated detection device of special space environment and effect without being directed to GEO track both at home and abroad at present,
Cannot achieve a kind of 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 geostationary orbit space environment and effects
Integrated detection device, may be implemented temperature, pollution, minute fragments, high energy electron, surface charging potential, charge inside current potential,
The detection of a variety of space environments and effect such as single-particle inversion, accumulated dose can carry in batches on GEO Orbital Space Vehicle.
Present invention employs the following technical solutions:
Geostationary orbit space environment and the integrated detection device of effect, including tubular detector housing, lid are located at shell
First layer collimation barrier layer and the second layer collimation layer and cylindrical interior that are layered on first layer collimation barrier layer are set on body
Each detecting element and functional layer set；The center of two layers of collimation layer has an opening for receiving incident space environment particle
And the area of the second layer collimation layer close to the setting of tubular central axes is less than the area of first layer, hands in tubular detector housing
For setting metal layer and insulating layer, wherein the insulating layer being arranged between upper layer and lower layer metal layer forms an inner space, is used for
Accommodate susceptible-dose element, single-particle inversion detecting element and charge inside potential monitoring piece, wherein in collimation barrier layer
The opening of the heart is provided with susceptible-dose element, be provided on the exposed surface of first layer collimation layer quartz crystal microbalance and
Temperature-monitoring element is provided with minute fragments monitoring piece and the table that stacks by insulating layer on the exposed surface of second layer collimation layer
Face charging potential monitors piece.
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).Outside is filled using exposed insulating materials or the realization of isolated material
The monitoring of electric potential.Using temperature-sensitive element, pressure cell and quartz crystal microbalance realize respectively to temperature, minute fragments and
The monitoring of contaminant capacity.
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 geostationary orbit space environment and the integrated detection device knot of effect of the embodiment of the invention
Structure 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 be charge inside potential monitoring piece；7 monitor piece for surface potential；8 monitor piece for minute fragments；9 be quartz-crystal
Body microbalance；10 be monitoring temperature element.
The integrated detection device part of the geostationary orbit space environment and effect of Fig. 3 embodiment of the invention
Structural 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 fig. 2, Fig. 2 shows the geostationary orbit space environment and effect collection of a specific embodiment of the invention
At detection device schematic diagram is changed, wherein the detection device include the collimation barrier layer that sets of columnar shell, case top lid with
And each detecting element and functional layer of cylindrical interior setting, the effect on collimation barrier layer 1 is for the standard to space radiation environment
Directly comprising lid is located at first layer collimation barrier layer and the second layer collimation being layered on first layer collimation barrier layer on shell
Layer, the center of two layers of collimation layer have an opening with the area for receiving incident space environment particle and second layer collimation layer
It is less than the area of first layer, metal layer 2 and insulating layer 3 is arranged alternately in tubular detector housing, wherein metal layer 2 has altogether
Provided with four layers, it is arranged in totally 3 layers of insulating layer 3 between 2 layers of upper layer and lower layer metal, it is empty that each insulating layer 3 forms an inside
Between, for accommodating susceptible-dose element 4, single-particle inversion detecting element 5 and charge inside potential monitoring piece 6 (see Fig. 3), and
Opening at collimation barrier layer center is additionally provided with susceptible-dose element, is arranged on the exposed surface of first layer collimation layer
There are quartz crystal microbalance 7 and temperature-monitoring element 8, is provided with minute fragments monitoring on the exposed surface of second layer collimation layer
Piece 9 and the surface charging potential monitoring piece 10 stacked by insulating layer.Specifically, the present invention can carry out following consider:
First, explicitly for GEO track detection space environment and concern space environment effect be space micro-debris,
Temperature, high energy electron, pollution, surface charging potential, charge inside current potential, accumulated dose, single-particle inversion etc..
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 is penetrating gold
By off-energy during category thin layer, with the increase of metal layer thickness, the electron energy that can be prevented is higher and higher, because
This, the energy for the electronics being deposited in different metal is respectively at different energy ranges.Assuming that metal layer 1, metal layer 2, gold
Belong to layer 3, metal layer 4, can stop to be respectively E1, E2, E3 and E4 to electron energy, then meet E1 < E2 < E3 < E4.According to selection
Metal layer material and metal layer thickness, using the Particle Deliveries analysis method such as Geant4, can inverting obtain different-energy section
Electronics flux and energy section distribution.
Third commonly uses exposed heat controlled thin film material as the detection of surface charging potential using spacecraft.
Surface charging potential is mainly caused due to plasma and sunlight irradiation etc., is affected by temperature simultaneously.Therefore,
While monitoring surface potential, need also to be monitored temperature.Outside the material proposed adoption spacecraft that surface potential detection uses
Reveal common heat controlled thin film material.Its size is according to 1cm2It designs, while to insulate with surrounding.
4th, 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.
5th, 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.
6th, 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.
7th, 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.
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.
8th, the analysis to accumulation of pollutants amount is realized using quartz crystal microbalance.
Utilize the quality for the pollutant that the variation of the vibration frequency of quartz crystal microbalance deposits come its surface of inverting.
9th, the statistics to space micro-debris flux and size is realized using pressure cell.
One piece of minute fragments receiver board is placed on pressure cell surface.When the minute fragments of certain mass impinge upon Yan Minyuan
After on part receiver board, the change of corresponding signal can occur for pressure cell (such as varistor) first, i.e., recordable primary small broken
Piece is hit, and the size of minute fragments is judged further according to signal magnitude.
Tenth, the detection to space temperature is realized using temperature-sensitive element.
For temperature-sensitive element (such as thermistor), the variation of temperature will lead to the variation of the parameters such as its resistance, by right
It applies a constant voltage, when electric current is changed, can the parameters such as inverting resistance change, and then the change of inverting temperature
Change.Since prevention ability of the metal layer to proton and heavy ion is strong, high energy proton and heavy ion will be most of at the 1st or the 2nd layer
It is blocked.Therefore, the measured value of the thickness and dosimeter that can use different metal layer carries out the rejecting of proton and heavy ion.
In addition, metal layer thickness is set according to the equivalent thickness of the bulkhead thickness and internal structure of spacecraft and instrument, each metal
Thin layer is fixed with insulating materials, keeps isolated.Susceptible-dose element and single-particle inversion sensing element are isolated arrangement.Surface
Potential monitoring piece determines that material and size are according to spacecraft module using position and cabin screening-off position etc. according in spacecraft module
Interior electronic circuit board common used material determines.
The device of the invention can be realized the detection of 6 kinds of space environments and 4 kinds of space environment effects, while can be to space flight
The charging potential of different location, accumulated dose and single-particle inversion situation are assessed in device cabin.
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 the protection scope of this patent when the spirit that raw function is still covered without departing from specification and attached drawing.
Claims (10)
1. geostationary orbit space environment and the integrated detection device of effect, including tubular detector housing, lid are located at shell
Upper first layer collimation barrier layer and the second layer collimation layer being layered on first layer collimation barrier layer and cylindrical interior setting
Each detecting element and functional layer；The center of two layers of collimation layer have an opening with for receive incident space environment particle and
It is less than the area of first layer, alternating in tubular detector housing close to the area of the second layer collimation layer of tubular central axes setting
Metal layer and insulating layer are set, wherein the insulating layer being arranged between upper layer and lower layer metal layer forms an inner space, for holding
Receive susceptible-dose element, single-particle inversion detecting element and charge inside potential monitoring piece, wherein at collimation barrier layer center
Opening be provided with susceptible-dose element, be provided with quartz crystal microbalance and temperature on the exposed surface of first layer collimation layer
Spend monitoring element, the surface for being provided with minute fragments monitoring piece on the exposed surface of second layer collimation layer and stacking by insulating layer
Charging potential monitors piece.
2. geostationary orbit space environment as described in claim 1 and the integrated detection device of effect, wherein metal layer
The number of plies is greater than the number of plies of insulating layer, and susceptible-dose element, single-particle inversion are equally arranged below the metal layer of bottommost
Detecting element.
3. geostationary orbit space environment as described in claim 1 and the integrated detection device of effect, wherein susceptible-dose
The setting position of element, single-particle inversion detecting element and charge inside potential monitoring piece is in incident space environment particle
On direction.
4. geostationary orbit space environment as described in any one of claims 1-3 and the integrated detection device of effect, wherein
The area of metal layer wants that the area of insulating layer inner space can be covered.
5. geostationary orbit space environment as described in any one of claims 1-3 and the integrated detection device of effect, wherein
Space environment particle is electronics, proton and heavy ion.
6. geostationary orbit space environment as described in any one of claims 1-3 and the integrated detection device of effect, wherein
The shell of detector uses metal as shielding construction.
7. geostationary orbit space environment as described in any one of claims 1-3 and the integrated detection device of effect, wherein
Metal layer thickness is set according to the equivalent thickness of the bulkhead thickness and internal structure of spacecraft and instrument.
8. geostationary orbit space environment as described in any one of claims 1-3 and the integrated detection device of effect, wherein
Susceptible-dose element and single-particle inversion sensing element are isolated arrangement.
9. geostationary orbit space environment as described in any one of claims 1-3 and the integrated detection device of effect, wherein
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 of metal layer
The support construction material selected inside spacecraft is metal material, 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
The cabinet thickness of single machine or load；4th layer of metal layer selects internal typical shadow shield material as metal layer material, with a thickness of
Typical shadow shield thickness degree.
10. geostationary orbit space environment as described in any one of claims 1-3 and the integrated detection device of effect,
In, dosage sensor selects MOSFET field-effect tube, places respectively in the different location of detection device.
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