CN105676255B - The multi-direction detecting device of high energy proton between a kind of distributed space - Google Patents
The multi-direction detecting device of high energy proton between a kind of distributed space Download PDFInfo
- Publication number
- CN105676255B CN105676255B CN201410675829.1A CN201410675829A CN105676255B CN 105676255 B CN105676255 B CN 105676255B CN 201410675829 A CN201410675829 A CN 201410675829A CN 105676255 B CN105676255 B CN 105676255B
- Authority
- CN
- China
- Prior art keywords
- detection device
- semiconductor transducer
- sensor
- satellite
- signal
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Measurement Of Radiation (AREA)
Abstract
A kind of distributed multidirectional high energy proton detection device based on multiple satellites, it include: the matched multiple sub- detection devices of number of satellite, every sub- detection device includes direction sensor, electronics component and housing part, wherein: direction sensor includes: no less than a piece of semiconductor transducer, evokes electric signal pulse in its two lateral electrode due to off-energy when Space Particle enters the semiconductor transducer；Electronics component, for handling the electric signal that direction sensor provides, to provide the signal of reflection Space Particle sedimentary energy in semiconductor transducer；And the normal direction of each direction sensor semiconductor transducer for being included when satellite is by the same position in approximately the same plane, the normal direction of each sensor when same position by not being overlapped, and a normal direction at least within is directed toward towards terrace.
Description
Technical field
The present invention relates to Space Particle detection technology fields, are to be related to a kind of use based on multi-satellite more specifically
In the device of multi-direction detecting Spacial Proton.
Background technique
Space charged particle is the most important composition of space environment, and to the safety of satellite threaten it is direct because
Element, especially Spacial Proton are widely present in cosmic space, therefore space charged particle is mainly grinding in space environment research
Study carefully object.Space charged particle detects the history of existing decades, therefore has certain base to the understanding of space charged particle
Plinth.But with space science research deeply, the extensive infiltration of space technology, the mankind are to space charged particle and its effect
Understanding constantly crosses over New step, becomes hence for the demand of the multi-direction detecting of all kinds of charged particles including Spacial Proton
It obtains more and more important.
High energy charged particles are to induce spacecraft single particle effect, dose of radiation effect and deep layer charging and discharging effects in space
Principal element, be the primary protection object of radiation hardening.The multicomponent of space charged particle, wide power spectrum and it is strong it is each to
The opposite sex increases difficulty for protection design assessment, especially in the Spacial Proton multidirectional of low orbit.The sky of space charged particle
Between distribution, the Pitch angle distribution of relative magnetic line, spectral distribution and they change with time, be each class model of space environment
The basic content of building research and its effect harm research.
Since space charged particle can cause all kinds of effects to interfere harm on satellite, the satellite development stage,
In-orbit management and subsequent fault diagnosis stage, it is a kind of for carrying out the assessment of the satellite radiation effect as caused by space charged particle
The important means of harm reduction.And carrying out the assessment of satellite radiation effect needs the direct measurement acquisition of all kinds of particles in in-orbit space
Data, the data including direction and power spectrum.Due to, there is the constraint in earth's magnetic field, leading to space charged particle in terrestrial space
Distribution shows anisotropy (especially on the low orbit of terrestrial space), and then charged particle is caused to imitate the radiation of satellite
Should be there is also respectively to difference, thus the multidirectional high energy proton for needing to carry out for satellite in orbit detects.
Detection for multidirectional high energy proton of satellite in orbit can carry out in single satellite, but this needs satellite
The platform resource such as weight, power consumption, installation dimension it is relatively more, naturally it is also possible to based on the same time with the more of altitude
Satellite carries out distributed measurement, to reduce the demand to satellite platform resource and realize the detection on multi-direction.
Summary of the invention
For solve presently, there are assessment satellite dose of radiation and the radiation effects such as single event need multidirectional sky
Between high energy proton gamma-spectrometric data the problem of, the present invention provides a kind of distributed multidirectional high energy matter based on multi-satellite
The detection device of son.
To achieve the above object, distributed multidirectional high energy proton detection device of the invention based on multiple satellites
Include: with the matched multiple sub- detection devices of number of satellite, every sub- detection device include direction sensor, electronics component and
Housing part, in which:
Direction sensor includes: no less than a piece of semiconductor transducer, when Space Particle enters the semiconductor transducer
Evoke electric signal pulse in its two lateral electrode due to off-energy；
Electronics component is existed for handling the electric signal that direction sensor provides with providing reflection Space Particle
The signal of sedimentary energy in semiconductor transducer；
And the normal direction of each direction sensor semiconductor transducer for being included in satellite by being in when the same position
The normal direction of approximately the same plane, each sensor is not overlapped when passing through same position, and a normal direction at least within is directed toward
Towards terrace.
According to one embodiment of present invention, direction sensor further includes preamplifier and wave-shaping circuit, preposition amplification
Device is used to amplify the charge signal for the reaction charged particle sedimentary energy that every chip semiconductor sensor exports respectively and turn
Become voltage pulse signal, the voltage pulse signal forming output that wave-shaping circuit exports preamplifier.
According to one embodiment of present invention, electronics component includes: main amplifier, for that wave-shaping circuit will export all the way
Signal or the signal that is exported after adder circuit of signal of two-way wave-shaping circuit output amplify；Circuit is protected at peak, is used for
Peak value of pulse holding is carried out respectively to the amplified signal of each main amplifier；A/D Acquisition Circuit, after to peak holding
Signal carries out analog-to-digital conversion；FPGA circuitry, digital signal for obtaining all A/D Acquisition Circuits carry out height analysis and
Data processing, wherein different amplitudes represents high energy proton difference sedimentary energy.
According to one embodiment of present invention, the sub- detection device also includes satellite interface circuit, is used for and satellite
Bus carries out data communication.
According to one embodiment of present invention, the semiconductor transducer of the direction sensor uses with a thickness of being greater than
0.1mm, it is less than the silicon or diamond class sensor of 3mm, sensitive area not less than 2mm × 2mm.The direction sensor is corresponding
Preamplifier use integrated transporting discharging capacitive feedback mode.
According to one embodiment of present invention, collimator is respectively provided with before the semiconductor transducer.
According to one embodiment of present invention, it is all provided in front of each collimator light-blocking not less than the metal of 1um thickness
Layer, for preventing visible light from injecting.
According to one embodiment of present invention, the sub- detection device is mounted within satellite covering, only direction sensing
Device part is open by covering to be stretched out.
According to one embodiment of present invention, semiconductor transducer is if it exceeds 1 is then put down between each semiconductor transducer
Row degree is not less than 20 degree.
The present invention has the advantages that for radiation effects such as research satellite dose of radiation effect and single events for sky
Between particle multi-direction detecting demand can be reduced pair using of the invention distributed multi-party to space high energy proton detection device
In resource requirements such as weight, the power consumptions of single satellite platform, and multidirectional high energy proton detection may be implemented, consequently facilitating
It is applied in aerospace engineering.
Detailed description of the invention
Fig. 1 carries multi-direction high energy proton detection device of the invention with three satellites by same position to be exemplary
Schematic diagram when setting.
Fig. 2 is the structural schematic diagram of the direction sensor of the sub- detection device of detection device of the invention.
Fig. 3 is the electrical schematics using the sub- detection device of multi-direction high energy proton detection device of the invention.
Appended drawing reference:
1, multi-direction detecting device 2, satellite 3, collimator
4, metal light blocking layer 5, semiconductor transducer 6, casing
Specific embodiment
Distributed multidirectional dose of radiation to of the invention based on multiple satellites with reference to the accompanying drawings and examples
The detection device of rate is described in detail.
Fig. 1 carries multi-direction radiation dose rate detection device of the invention with three satellites by same to be exemplary
Schematic diagram when position, i.e., contain three sub- detection devices in this multi-direction detecting device 1, every sub- detection device corresponds to three
One in satellite 2.Fig. 2 is the structural schematic diagram of the direction sensor of the sub- detection device in Fig. 1.Root as shown in Figure 1
According to one embodiment of the present of invention, three satellites 2 are separately contained in the side in three sub- detection devices when by same position
At the normal direction for the semiconductor transducer 5 for including into sensor in the same plane, in the present embodiment, at three satellites
When the overhead of equator, the normal direction of the semiconductor transducer of one of them sub- detection device towards day, other two sub- detection devices
The normal direction of semiconductor transducer differs from it by -45 and+45 degree respectively.
In Fig. 2, distributed multidirectional radiation agent according to an embodiment of the invention based on multiple satellites
The direction sensor of the sub- detection device of the multi-direction detecting device 1 of dose rate includes two panels semiconductor transducer 5.In this embodiment
In, semiconductor transducer 5 is also configured with collimator 3,4 device of metal light blocking layer and casing 6, here, the function of collimator 3 be by
Within measurement range angle required for space scattering high energy proton is constrained to；Metal light blocking layer 4 enters half for blocking visible light
Conductor sensor 5, and space high energy proton can then penetrate metal light blocking layer 4 hence into semiconductor transducer 5；Space high energy
Proton meeting off-energy after entering in semiconductor transducer 5, therefore electric signal pulse will be evoked in every two lateral electrodes,
Treated that signal can reflect the different-energy of Spacial Proton in the devices through appropriate, in conjunction with two panels semiconductor transducer
The combination of sedimentary energy can obtain surveyed high energy proton energy.
Preferably, the metal light blocking layer 4 and semiconductor transducer 5 are slab organization.Metal light blocking layer 4 uses specific
Material category and the thickness track according to locating for satellite and measurement range are designed selection.The material of semiconductor transducer 5
It can be needed according to test with number to determine, specifically, when each direction sensor contains only a piece of semiconductor transducer
When only need mating electronics processing circuit all the way, the then corresponding every sensing when each direction sensor contains multi-disc sensor
Device protects circuit equipped with corresponding preamplifier, wave-shaping circuit, main amplifier and peak, is finally uniformly connected to A/D Acquisition Circuit.Half
Conductor sensor 5 can using silicon or diamond, while silicon sensor can choose ion implantation type or gold silicon surface barrier
Type etc..
In an embodiment of the present invention, each sub- detection device of multi-direction detecting device 1 is respectively embedded into formula and is mounted on three
The surface of satellite 2, i.e., sub- detection device are separately mounted within satellite covering, and only direction sensor part is stretched by covering opening
Out.Each sub- detection device of the multi-direction detecting device 1 is not blocked towards the direction of space.
In a preferred embodiment, metal light blocking layer 4 with a thickness of 15 μm, using aluminum alloy materials, for absorbing visible light,
It avoids causing measuring result error excessive due to illumination.
Fig. 3 show the electricity of a sub- detection device of multi-direction detecting device 1 according to an embodiment of the invention
Gas realization principle block diagram, wherein all parts in dotted line constitute the sub- detection device.Specifically, the side of this sub- detection device
It include two chip semiconductor sensors 5 and 5 ' to sensor, it is preferable that the depth of parallelism between two chip semiconductor sensors is not less than 20
Degree.High energy proton successively enters two panels semiconductor transducer 5 and 5 ' after penetrating metal light blocking layer 4, in two panels semiconductor transducer
5 and 5 ' internal loss energy then evoke electric signal pulse in two lateral electrodes of semiconductor transducer 5 and 5 '.It is utilized respectively preposition
The electric signal that amplifier, wave-shaping circuit, main amplifier generate semiconductor transducer 5 and 5 ' amplifies and shaping, finally again
Circuit is protected using peak and obtains variation peak value, and the variation peak value that will acquire gives A/D Acquisition Circuit.A/D Acquisition Circuit output end
It is connected with the input terminal of FPGA circuitry, FPGA circuitry is combined processing to signal, and then FPGA circuitry passes through satellite interface electricity
Road transmits the data to satellite electron system.
The structure setting of multi-direction space high energy proton detection device of the invention is illustrated by taking three satellites as an example above
Feature and working principle.Obviously, when number of satellite is two, two sub- detection devices can be set that normal orientation is protected
The normal direction for demonstrate,proving sub- detection device when satellite is by equator overhead on one satellite is vertically sky, is in addition defended for one
The normal direction of sub- detection device on star and the former normal direction at an angle, the angular range be greater than 0 degree and less than 90 degree, compared with
It well is 45 degree；When number of satellite is four, four sub- detection devices can be set to make normal orientation guarantee and work as satellite
Normal direction by the sub- detection device of at least one satellite when the overhead of equator is vertically sky, in addition three satellites
The normal direction of the sub- detection device of the normal direction of sub- detection device and first satellite respectively at an angle, and these three angles that
This is not identical, which is greater than 0 degree less than 90 degree, preferably the sub- detection device of these three angles and Lesson One satellite
Normal direction between be in 25 degree, 50 degree and 75 degree；When other quantity satellite, similarly, it should be ensured that when satellite is by equator overhead
When, the normal direction of the sub- detection device of a satellite is vertically sky, to obtain maximum direction high energy proton flux.
It should be noted last that the above examples are only used to illustrate the technical scheme of the present invention and are not limiting.Although ginseng
It is described the invention in detail according to embodiment, those skilled in the art should understand that, to technical side of the invention
Case is modified or replaced equivalently, and without departure from the spirit and scope of technical solution of the present invention, should all be covered in the present invention
Scope of the claims in.
Claims (9)
1. a kind of distributed multidirectional high energy proton detection device based on multiple satellites, characterized by comprising: with defend
The flux matched multiple sub- detection devices of star number, each sub- detection device are separately mounted within satellite covering, every height detection dress
It sets comprising direction sensor, electronics component and housing part, in which:
Direction sensor includes: no less than a piece of semiconductor transducer, when Space Particle enter the semiconductor transducer when due to
Off-energy and evoke electric signal pulse in its two lateral electrode；
The direction sensor includes two panels semiconductor transducer (5)；Wherein, the semiconductor transducer is also configured with: collimation
Space scattering high energy proton is constrained within required measurement range angle by device (3)；Metal light blocking layer (4), can for blocking
It is light-exposed to enter semiconductor transducer；With casing (6)；Space high energy proton penetrates metal light blocking layer (4), passes hence into semiconductor
Sensor (5) obtains surveyed high energy proton energy in conjunction with the combination of the sedimentary energy of two panels semiconductor transducer (5)；
Direction sensor further includes preamplifier and wave-shaping circuit, and preamplifier is used to export every chip semiconductor sensor
The charge signal of reaction charged particle sedimentary energy amplify and be transformed into voltage pulse signal respectively, wave-shaping circuit will before
Set the voltage pulse signal forming output of amplifier output；
Electronics component is partly being led for handling the electric signal that direction sensor provides with providing reflection Space Particle
The signal of sedimentary energy in body sensor；
And the normal direction of each direction sensor semiconductor transducer for being included when satellite is by the same position in same
The normal direction of a plane, each sensor is not overlapped when passing through same position, and a normal direction at least within is directed toward towards day
Face.
2. detection device according to claim 1, it is characterised in that: electronics component includes: main amplifier, is used for one
The signal that the signal of road wave-shaping circuit output or the signal of two-way wave-shaping circuit output export after adder circuit amplifies；
Circuit is protected at peak, for carrying out peak value of pulse holding respectively to the amplified signal of each main amplifier；A/D Acquisition Circuit, is used for
Analog-to-digital conversion is carried out to the signal after peak holding；FPGA circuitry, the digital signal for obtaining all A/D Acquisition Circuits
Height analysis and data processing are carried out, wherein different amplitudes represents high energy proton difference sedimentary energy.
3. detection device according to claim 1, it is characterised in that: sub- detection device also includes satellite interface circuit, is used
In with satellite bus carry out data communication.
4. detection device according to claim 1, it is characterised in that: the semiconductor transducer of direction sensor uses thickness
For the silicon or diamond class sensor for being not less than 2mm × 2mm greater than 0.1mm, less than 3mm, sensitive area.
5. detection device according to claim 1, it is characterised in that: the corresponding preamplifier of direction sensor is using collection
At amplifier capacitive feedback mode.
6. detection device according to claim 1, it is characterised in that: be respectively provided with collimator before semiconductor transducer.
7. detection device according to claim 6, it is characterised in that: be all provided with thick not less than 1um in front of each collimator
Metal light blocking layer, for preventing visible light from injecting.
8. detection device according to claim 1, it is characterised in that: sub- detection device is mounted within satellite covering, only
Direction sensor part is open by covering to be stretched out.
9. detection device according to claim 1, it is characterised in that: semiconductor transducer is if it exceeds 1 then fifty-fifty is led
The depth of parallelism is not less than 20 degree between body sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410675829.1A CN105676255B (en) | 2014-11-21 | 2014-11-21 | The multi-direction detecting device of high energy proton between a kind of distributed space |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410675829.1A CN105676255B (en) | 2014-11-21 | 2014-11-21 | The multi-direction detecting device of high energy proton between a kind of distributed space |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105676255A CN105676255A (en) | 2016-06-15 |
| CN105676255B true CN105676255B (en) | 2018-12-04 |
Family
ID=56958276
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410675829.1A Active CN105676255B (en) | 2014-11-21 | 2014-11-21 | The multi-direction detecting device of high energy proton between a kind of distributed space |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105676255B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108345022B (en) * | 2017-01-22 | 2019-08-20 | 中国科学院国家空间科学中心 | A kind of measuring device and method of space charged particle dose of radiation |
| CN113126142B (en) * | 2021-04-16 | 2022-04-01 | 应急管理部国家自然灾害防治研究院 | High-energy particle detector performance evaluation method and system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6614867B1 (en) * | 2000-02-14 | 2003-09-02 | The United States Of America As Represented By The Secretary Of The Army | Dodecahedron neutron spectrometer with titanium proton absorber for spacecraft |
| CN102183779A (en) * | 2010-12-29 | 2011-09-14 | 中国科学院空间科学与应用研究中心 | Multidirectional high energy particle detector |
| CN102967871A (en) * | 2012-11-12 | 2013-03-13 | 中国航天科技集团公司第五研究院第五一〇研究所 | Detection method for space low-energy electrons and protons |
| CN102981180A (en) * | 2012-12-12 | 2013-03-20 | 中国科学院国家天文台 | Water Cerenkov light high-energy particle detector |
-
2014
- 2014-11-21 CN CN201410675829.1A patent/CN105676255B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6614867B1 (en) * | 2000-02-14 | 2003-09-02 | The United States Of America As Represented By The Secretary Of The Army | Dodecahedron neutron spectrometer with titanium proton absorber for spacecraft |
| CN102183779A (en) * | 2010-12-29 | 2011-09-14 | 中国科学院空间科学与应用研究中心 | Multidirectional high energy particle detector |
| CN102967871A (en) * | 2012-11-12 | 2013-03-13 | 中国航天科技集团公司第五研究院第五一〇研究所 | Detection method for space low-energy electrons and protons |
| CN102981180A (en) * | 2012-12-12 | 2013-03-20 | 中国科学院国家天文台 | Water Cerenkov light high-energy particle detector |
Non-Patent Citations (4)
| Title |
|---|
| Multiple agent-based autonomy for satellite Constellations;Thomas Schetter et al;《Artificial Intelligence》;20031231;第145卷;第147末段至148页首段 * |
| 中高能粒子探测器的设计与研制;张珅毅;《中国博士学位论文全文数据库 基础科学辑》;20060815(第8期);第80-88页第5.3.3-5.3.7节 * |
| 张珅毅.中高能粒子探测器的设计与研制.《中国博士学位论文全文数据库 基础科学辑》.2006,(第8期), * |
| 面向效能优化的复杂多卫星系统综合建模与仿真方法研究;贺勇军;《中国博士学位论文全文数据库 工程科技Ⅱ辑》;20061115(第11期);第2页第1.1.2节 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105676255A (en) | 2016-06-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102183779A (en) | Multidirectional high energy particle detector | |
| CN105676255B (en) | The multi-direction detecting device of high energy proton between a kind of distributed space | |
| CN109828300A (en) | A kind of miniaturization omnidirectional particles detection | |
| Sakaguchi et al. | LET distribution measurement with a new real-time radiation monitoring device-III onboard the Space Shuttle STS-84 | |
| CN104221157A (en) | A solid state radiation detector with enhanced gamma radiation sensitivity | |
| Grove et al. | The calorimeter of the Fermi large area telescope | |
| Tran et al. | 3D radiation detectors: Charge collection characterisation and applicability of technology for microdosimetry | |
| CN106610500B (en) | A kind of multidirectional high energy electron detection device based on distributed multiple satellites | |
| Grimani et al. | A Hydrogenated amorphous silicon detector for Space Weather Applications | |
| US8729489B2 (en) | Radiation detecting device to measure gamma-ray and neutron discriminately | |
| CN105629287B (en) | A kind of multi-direction radiation dose rate measuring device of distributed satellites | |
| Belushkin et al. | Development of gas-filled position-sensitive detectors of thermal neutrons at the Frank Laboratory of Neutron Physics of the Joint Institute for Nuclear Research | |
| McKenna-Lawlor et al. | The energetic NeUtral Atom Detector Unit (NUADU) for China's Double Star Mission and its calibration | |
| US11802982B2 (en) | Directional and prompt radiation dose sensor | |
| YuGuang et al. | Energetic electron detection packages on board Chinese navigation satellites in MEO | |
| Bidoli et al. | Experimental beam test of the SilEye2 apparatus | |
| Meier et al. | Development of an ASIC for charged particle counting with silicon radiation detectors | |
| Segui et al. | Characterization and first beam loss detection with one ESS-nBLM system detector | |
| Meier et al. | Development of an ASIC for the Readout of CZT/CdTe Radiation Detectors in Space | |
| Ritter et al. | A small active dosimeter for applications in space | |
| Koshiishi et al. | Space Environment Data Acquisition Equipment Board Mission Demonstration Test Satellite-1 | |
| Evdokimov et al. | The ALICE CPV Detector | |
| Kroupa et al. | Modern semiconductor pixel detectors used as radiation monitors | |
| JP2001027674A (en) | Neutron dose rate meter | |
| Pinsky et al. | Summary of the first year of medipix-based space radiation monitors on the ISS |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 100190 No. two south of Zhongguancun, Haidian District, Beijing 1 Patentee after: NATIONAL SPACE SCIENCE CENTER, CAS Address before: 100190 No. two south of Zhongguancun, Haidian District, Beijing 1 Patentee before: Space Science & Applied Research Centre, Chinese Academy of Sciences |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220525 Address after: 215300 508a, building 1, No. 268, Dengyun Road, Yushan Town, Kunshan City, Suzhou City, Jiangsu Province Patentee after: Kunshan Zhongke Space Technology Co.,Ltd. Address before: 100190 No. two south of Zhongguancun, Haidian District, Beijing 1 Patentee before: NATIONAL SPACE SCIENCE CENTER, CAS |