CN103698796A - Extravehicular radiation dose measurement device for spacecraft - Google Patents
Extravehicular radiation dose measurement device for spacecraft Download PDFInfo
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- CN103698796A CN103698796A CN201310625130.XA CN201310625130A CN103698796A CN 103698796 A CN103698796 A CN 103698796A CN 201310625130 A CN201310625130 A CN 201310625130A CN 103698796 A CN103698796 A CN 103698796A
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Abstract
The invention belongs to the technical field of space radiation effects and reinforcement, and particularly relates to an extravehicular radiation dose measurement device for a spacecraft. The extravehicular radiation dose measurement device for the spacecraft comprises a dose sensor, a constant current source, a voltage follower, an analogue-to-digital converter, a microcontroller, a memory and an upper computer. According to the measurement device, the wide-range and high-dose radiation dose measurement in space can be realized; a universal method is provided for further realizing space radiation dose measurement; the high-dose and high-accuracy measurement is realized; the powerful support can be provided for protective design of the spacecraft; meanwhile, the requirement for the development of spacecraft engineering can be met.
Description
Technical field
The invention belongs to Space Radiation Effects and reinforcement technique field, be specifically related to a kind of spacecraft module external radiation health-monitoring installation.
Background technology
Operate in the spacecraft in space radiation environment, the materials and devices on charged particle and spacecraft surface interacts and causes tatal ionizing dose effects, causes materials and devices to occur hydraulic performance decline, dysfunction even, and serious meeting causes spacecraft mission failure.
In recent years, along with the development of spationautics, not only spacecraft quantity in orbit increases, and orbit space is also constantly to external expansion.Compare with spacecraft in the past, the space environment of its experience is more severe, as operates in the Navsat of geostationary orbit, and because electron flux is large, the radiation dose of accumulation also can be very large, and the ionization total-dose radiation hazard of spacecraft also will be more serious.Therefore, the radiation dose radiation hazard of spacecraft and spacecraft being suffered at different orbital positions for the radiation environment that can know exactly spacecraft orbit, need real-time measuring radiation dosage, also can provide data supporting for the database of space radiation environment.In addition, " 12 " and after, along with the spacecraft continuous growth in life-span in-orbit, make its accumulative total radiation dose also by more much bigger more in the past than the dosage that spacecraft suffered, as spacecraft flies 15 years in-orbit, the radiation dose outside spacecraft module can reach 10
8-10
9rad (Si), even if the radiation dose after shielding processing can reach 10
7rad (Si), so heavy dose of ionising radiation has proposed higher demand to device and material protection.Meanwhile, from spacecraft engineering application point, need to obtain the integrated radiation dose of flying for long time, to provide Data support for the radiation shield of follow-up spacecraft.Therefore, in order to meet the demand of spacecraft long-life operation, designed a kind of heavy dose of proving installation being applicable to outside spacecraft module, this device has high dose measurement (can reach 3 * 10
7rad (Si)), high measurement accuracy (1mV/rad (Si)), the wide feature of measurement range, can manage and provide support in-orbit for spacecraft, simultaneously for spacecraft radiation protection design provides engineering reference.
Summary of the invention
The object of the invention is to overcome the defect existing in prior art, a kind of spacecraft module external radiation health-monitoring installation is provided, this device can meeting spatial heavy dose radiation protection demand, there is wide dynamic range, feature that precision is high, can realize the space radiation dosage of different orbital environments, can meet the protection works demand of spacecraft, also can further instruct radiation dose ground experiment method simultaneously.
To achieve these goals, technical scheme of the present invention is a kind of spacecraft module external radiation health-monitoring installation of design, comprises dose sensor, constant current source, voltage follower, analog to digital converter, microcontroller, storer, host computer;
Its annexation is: one end of described dose sensor is connected with described constant current source, the other end ground connection of described dose sensor, one end of described voltage follower is connected with the tie point of described dose sensor and constant current source, the other end of described voltage follower is connected with described analog to digital converter, described analog to digital converter is also connected with described microcontroller, and described microcontroller is also connected with host computer with described storer;
Described dose sensor is used for receiving ionizing radiation, and is translated into threshold voltage simulating signal, and described constant current source carries out steady current processing to described threshold voltage simulating signal;
Described dose sensor is sent to described voltage follower by the threshold voltage simulating signal of processing through described constant current source;
Described voltage follower will transmit constant current source processing threshold voltage simulating signal for receiving described dose sensor, and this signal is carried out, after impedance transformation, being sent to described analog to digital converter;
Described digital to analog converter receives the simulating signal after impedance transformation, is converted into digital signal and is sent to described microcontroller;
Described microprocessor receives the read instruction of described host computer, for described analog to digital converter provides conversion instruction, receives described digital signal simultaneously, and sends it to described storer and host computer;
Described storer is used for storing described digital signal;
Described host computer is for demonstration and store described digital signal.
Also comprise electric power system, described electric power system is connected with described microprocessor.
Described constant current source is chosen 490 μ A.
Described microcontroller is connected with described host computer by RS485/RS232.
Advantage of the present invention and beneficial effect are:
One, can implementation space wide region, the radiation dose measurement of high dose, for further implementation space radiation dose measurement provides a kind of method of versatility, high dose, high-acruracy survey, can be spacecraft shield design provides and provides powerful support for, and can meet the growth requirement of spacecraft engineering simultaneously.Described Constant Current-Source Design is the key point of whole device, and it has directly determined the measuring accuracy of device.By precision, feed back the constant current source of realizing, ripple is little, and measuring accuracy is high.The design of described dose sensor, makes measuring accuracy maximum, makes sensor temperature coefficient minimum simultaneously.
Two, owing to also comprising electric power system, described electric power system is connected with described microprocessor.Be used to described microprocessor power supply.
Three, because described constant current source is chosen 490 μ A.Can make temperature ignore the impact of measuring accuracy, make its measuring accuracy also can reach mV magnitude.
Four, because described microcontroller is connected with described host computer by RS485/RS232.Can guarantee the stable of signal.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present invention.
Embodiment
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is further described, following examples are only for technical scheme of the present invention is more clearly described, and can not limit the scope of the invention with this.
As shown in Figure 1, the concrete technical scheme of implementing of the present invention is: a kind of spacecraft module external radiation health-monitoring installation, comprises dose sensor, constant current source, voltage follower, analog to digital converter, microcontroller, storer, host computer;
Its annexation is: one end of described dose sensor is connected with described constant current source, the other end ground connection of described dose sensor, one end of described voltage follower is connected with the tie point of described dose sensor and constant current source, the other end of described voltage follower is connected with described analog to digital converter, described analog to digital converter is also connected with described microcontroller, and described microcontroller is also connected with host computer with described storer;
Described dose sensor is used for receiving ionizing radiation, and is translated into threshold voltage simulating signal, and described constant current source carries out steady current processing to described threshold voltage simulating signal;
Described dose sensor is sent to described voltage follower by the threshold voltage simulating signal of processing through described constant current source;
Described voltage follower will transmit constant current source processing threshold voltage simulating signal for receiving described dose sensor, and this signal is carried out, after impedance transformation, being sent to described analog to digital converter;
Described digital to analog converter receives the simulating signal after impedance transformation, is converted into digital signal and is sent to described microcontroller;
Described microprocessor receives the read instruction of described host computer, for described analog to digital converter provides conversion instruction, receives described digital signal simultaneously, and sends it to described storer and host computer;
Described storer is used for storing described digital signal;
Described host computer is for demonstration and store described digital signal.
Also comprise electric power system, described electric power system is connected with described microprocessor.
Described constant current source is chosen 490 μ A.
Described microcontroller is connected with described host computer by RS485/RS232.
Described host computer is Measurement &control computer.
When the radiation dose of measurement space environment, measurement mechanism divides irradiation pattern and two mode of operations of data reading pattern.First radiation dose measurement device of the present invention is placed in to test environment, system power-up initializing then, and then carry out radiation dose measurement.Detailed process is as follows:
1. parameter initialization.
2. dosage is read to part and be placed in tested radiation environment, system is under irradiation pattern, and now, the grid of dose sensor, source electrode are combined into one end ground wire, and drain electrode and substrate are combined into also ground wire of one end.
3. (this time interval is adjustable) after irradiation certain hour, microcontroller sends steering order, make test macro under data reading pattern, now, the grid of dose sensor and one end of drain electrode be ground wire still, and this termination of source electrode and substrate enters constant current source, constant electric current makes to flow through between the drain-source of dose sensor.Under the acquisition instructions of microcontroller, voltage follower is transferred to analog to digital converter by dose sensor source voltage equivalence, obtains after data, and the source electrode of dose sensor and substrate one end be ground wire again, waits for next image data.
4. under the instruction of microcontroller, analog to digital converter converts the simulating signal collecting to digital signal, and is transferred to microcontroller and processes.
5. by the digital signal after processing, via serial bus, RS485/RS232 is uploaded to host computer, graphically shows and stores.
6. via above-mentioned steps, complete a data acquisition and processing (DAP), then through accumulation irradiation certain hour interval after, repeating step 3., 4., 5., until reach the dosage range of testing requirements, off-test.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, do not departing under the prerequisite of the technology of the present invention principle; can also make some improvements and modifications, these improvements and modifications also should be considered as protection scope of the present invention.
Claims (4)
1. a spacecraft module external radiation health-monitoring installation, comprises dose sensor, constant current source, voltage follower, analog to digital converter, microcontroller, storer, host computer;
It is characterized in that: one end of described dose sensor is connected with described constant current source, the other end ground connection of described dose sensor, one end of described voltage follower is connected with the tie point of described dose sensor and constant current source, the other end of described voltage follower is connected with described analog to digital converter, described analog to digital converter is also connected with described microcontroller, and described microcontroller is also connected with host computer with described storer;
Described dose sensor is used for receiving ionizing radiation, and is translated into threshold voltage simulating signal, and described constant current source carries out steady current processing to described threshold voltage simulating signal;
Described dose sensor is sent to described voltage follower by the threshold voltage simulating signal of processing through described constant current source;
Described voltage follower will transmit constant current source processing threshold voltage simulating signal for receiving described dose sensor, and this signal is carried out, after impedance transformation, being sent to described analog to digital converter;
Described digital to analog converter receives the simulating signal after impedance transformation, is converted into digital signal and is sent to described microcontroller;
Described microprocessor receives the read instruction of described host computer, for described analog to digital converter provides conversion instruction, receives described digital signal simultaneously, and sends it to described storer and host computer;
Described storer is used for storing described digital signal;
Described host computer is for demonstration and store described digital signal.
2. a kind of spacecraft module external radiation health-monitoring installation according to claim 1, is characterized in that: also comprise electric power system, described electric power system is connected with described microprocessor.
3. a kind of spacecraft module external radiation health-monitoring installation according to claim 1 and 2, is characterized in that: described constant current source is chosen 490 μ A.
4. a kind of spacecraft module external radiation health-monitoring installation according to claim 1 and 2, is characterized in that: described microcontroller is connected with described host computer by RS485/RS232.
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| CN201310625130.XA CN103698796A (en) | 2013-11-28 | 2013-11-28 | Extravehicular radiation dose measurement device for spacecraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111418492A (en) * | 2020-05-06 | 2020-07-17 | 吉林进取空间科技有限公司 | Space breeding radiation dose control method and device |
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| US5338938A (en) * | 1993-04-09 | 1994-08-16 | Martin Marietta Energy Systems, Inc. | Gamma radiation field intensity meter |
| CN1227926A (en) * | 1997-11-28 | 1999-09-08 | 佳能株式会社 | Radiation detecting device and radiation detecting method |
| CN1605886A (en) * | 2004-11-17 | 2005-04-13 | 中国科学院新疆理化技术研究所 | Geminate transistors type PMOS radiation dose meter with difference output |
| CN101458337A (en) * | 2007-12-12 | 2009-06-17 | 中国科学院微电子研究所 | Silicic double probe PMOS radiation dose meter based on insulator |
| CN201654242U (en) * | 2010-04-08 | 2010-11-24 | 无锡大禹科技有限公司 | Radiation signal sensor |
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2013
- 2013-11-28 CN CN201310625130.XA patent/CN103698796A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5338938A (en) * | 1993-04-09 | 1994-08-16 | Martin Marietta Energy Systems, Inc. | Gamma radiation field intensity meter |
| CN1227926A (en) * | 1997-11-28 | 1999-09-08 | 佳能株式会社 | Radiation detecting device and radiation detecting method |
| CN1605886A (en) * | 2004-11-17 | 2005-04-13 | 中国科学院新疆理化技术研究所 | Geminate transistors type PMOS radiation dose meter with difference output |
| CN101458337A (en) * | 2007-12-12 | 2009-06-17 | 中国科学院微电子研究所 | Silicic double probe PMOS radiation dose meter based on insulator |
| CN201654242U (en) * | 2010-04-08 | 2010-11-24 | 无锡大禹科技有限公司 | Radiation signal sensor |
Non-Patent Citations (1)
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| 薛玉雄等: "《中国宇航学会深空探测技术专业委员会第六届学术年会暨863计划"深空探测与空间实验技术"重大项目学术研讨会论文集》", 1 December 2009, article "月球载人探测器舱内环境辐射剂量监测技术" * |
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| CN111418492A (en) * | 2020-05-06 | 2020-07-17 | 吉林进取空间科技有限公司 | Space breeding radiation dose control method and device |
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Application publication date: 20140402 |