CN105182290A - Spacecraft micro meteor and space debris bump positioning method on-track verification device - Google Patents
Spacecraft micro meteor and space debris bump positioning method on-track verification device Download PDFInfo
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- CN105182290A CN105182290A CN201510576267.XA CN201510576267A CN105182290A CN 105182290 A CN105182290 A CN 105182290A CN 201510576267 A CN201510576267 A CN 201510576267A CN 105182290 A CN105182290 A CN 105182290A
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- sensor
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- meteor
- micrometeor
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S5/00—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations
- G01S5/18—Position-fixing by co-ordinating two or more direction or position line determinations; Position-fixing by co-ordinating two or more distance determinations using ultrasonic, sonic, or infrasonic waves
- G01S5/22—Position of source determined by co-ordinating a plurality of position lines defined by path-difference measurements
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- General Physics & Mathematics (AREA)
- Radar, Positioning & Navigation (AREA)
- Remote Sensing (AREA)
- Investigating Or Analyzing Materials By The Use Of Ultrasonic Waves (AREA)
- Geophysics And Detection Of Objects (AREA)
Abstract
The invention discloses a spacecraft micro meteor and space debris bump positioning method on-track verification device. The device is an opened box type structure, an opening is sealed through a flexible piezoelectric film sensor, the bottom face is a sensor mounting substrate, and the outer side face of the sensor mounting substrate is provided with a sound emission sensor. According to the spacecraft micro meteor and space debris bump positioning method on-track verification device, two types of sensors are combined to filter interference signals of the sound emission sensor, so the spacecraft micro meteor and space debris sound bump positioning method is a relatively high-credibility on-track verification method.
Description
Technical field
The present invention relates to space equipment technical field, especially a kind of spacecraft micrometeor and space micro-debris calibrate AE sensor clash into localization method validating in orbit device, are mainly used in the manned spacecraft micrometeors such as space station and the early warning of space micro-debris shock.
Background technology
Based on spacecraft micrometeor and the space micro-debris shock quick location technique of calibrate AE sensor, there is the outstanding advantage of lossless detection, real-time response, light little low-power consumption, but, because calibrate AE sensor is very sensitive to vibration responding, and space station belongs to large-scale manned spacecraft, complex structure, the undesired signal that various instrument and cosmonaut's activity cause all can cause the early warning of acoustic emission system to respond, this just makes this location technology validating in orbit confidence level not high, cannot determine whether signal is that real micrometeor and space micro-debris clash into signal.
Summary of the invention
The present invention is directed to the deficiencies in the prior art, propose a kind of spacecraft micrometeor and space micro-debris shock localization method validating in orbit device, structure is ingenious, easy to use.
In order to realize foregoing invention object, the invention provides following technical scheme: a kind of spacecraft micrometeor and space micro-debris clash into localization method validating in orbit device, for the case structure of opening, this opening part flexible piezoelectric thin film sensor seals, bottom surface is sensor installation base plate, and the lateral surface of this sensor installation base plate is provided with calibrate AE sensor.
Further, this calibrate AE sensor is provided with at least four, is evenly distributed on sensor installation base plate.
Further, this flexible piezoelectric thin film sensor adopts Kynoar both sides plating constructed of aluminium.
Further, this sensor installation base plate is the aluminium alloy or titanium alloy metal substrate that 1mm ~ 15mm is thick.
Compared with prior art, the present invention has the following advantages: by two kinds of sensors combined come filtering calibrate AE sensor undesired signal, thus clash into localization method for spacecraft micrometeor and space micro-debris acoustic emission the validating in orbit method with higher confidence level be provided.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
In figure, 1 is flexible piezoelectric thin film sensor, and 2 is crust of the device structures, and 3 is calibrate AE sensor installation base plates, and 4 is calibrate AE sensors.
Embodiment
Describe the present invention below in conjunction with accompanying drawing, the description of this part is only exemplary and explanatory, should not have any restriction to protection scope of the present invention.
A kind of spacecraft micrometeor and space micro-debris shock localization method validating in orbit device with higher confidence level as shown in Figure 1, by flexible piezoelectric thin film sensor 1 and framework, calibrate AE sensor 4, sensor installation base plate 3 and structure 2 four part composition.Flexible piezoelectric film 1 is pasted onto after on framework and is installed in foremost, after be that corner is provided with calibrate AE sensor substrate for clashing into location test, two parts sensor is arranged in a cube structure, adopt cable be connected not too much with data processing.。
Adopt preposition flexible piezoelectric thin film sensor 1 as space micro-debris and micrometeoroid sensor, place calibrate AE sensor 4 array below as shock position locator, only have when having shock signal to produce after preposition flexible piezoelectric thin film sensor 1 is penetrated by micrometeor and space micro-debris shock, just can record the signal that alignment sensor is clashed in acoustic emission, by two kinds of sensors combined come filtering calibrate AE sensor undesired signal, thus clash into localization method for spacecraft micrometeor and space micro-debris acoustic emission the validating in orbit method with higher confidence level is provided.
During apparatus of the present invention are mounted in and the spacecrafts such as space station fly in-orbit, when micrometeor or space micro-debris impinge upon after on flexible piezoelectric film 1, because film is very thin, only have 10 μm thick, micrometeor or space micro-debris speed very fast, at about 3km/s-20km/s, momentum is very high, therefore can penetrate easily flexible piezoelectric film 1 then impinge upon after for clash into locating verification test metal substrate 3, substrate is impacted and can produces vibration wave, mistiming of signal is received by four sensors 4 and respective position just can be determined to clash into the position occurred after vibration wave is accepted by calibrate AE sensor.By setting at data processing circuit, the acoustic emission signal not having flexible piezoelectric film to clash into signal being filtered, just can obtain the validating in orbit test findings of higher confidence level.
Adopt 10 μm of thick Kynoar both sides plating aluminium as electrode, as flexible piezoelectric thin film sensor, be pasted onto on framework, then integral installation is to detector leading portion, after detection, the thick aluminium alloy base plate of a 3mm is installed in rear end, or is the titanium alloy metal substrate that 1mm ~ 15mm is thick, and substrate surrounding installs four calibrate AE sensors, except detector front section, other each adopts aluminium alloy cover plate to seal.Rear end is reserved cable splice and is connected with data processing section.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the premise without departing from the principles of the invention; 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 micrometeor and space micro-debris clash into localization method validating in orbit device, it is characterized in that: be the case structure of opening, this opening part flexible piezoelectric thin film sensor seals, bottom surface is sensor installation base plate, and the lateral surface of this sensor installation base plate is provided with calibrate AE sensor.
2. spacecraft micrometeor and space micro-debris clash into localization method validating in orbit device as claimed in claim 1, it is characterized in that: this calibrate AE sensor is provided with at least four, are evenly distributed on sensor installation base plate.
3. spacecraft micrometeor and space micro-debris clash into localization method validating in orbit device as claimed in claim 1, it is characterized in that: this flexible piezoelectric thin film sensor adopts Kynoar both sides plating constructed of aluminium.
4. spacecraft micrometeor and space micro-debris clash into localization method validating in orbit device as claimed in claim 1, it is characterized in that: this sensor installation base plate is the aluminium alloy or titanium alloy metal substrate that 1mm ~ 15mm is thick.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510576267.XA CN105182290A (en) | 2015-09-11 | 2015-09-11 | Spacecraft micro meteor and space debris bump positioning method on-track verification device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510576267.XA CN105182290A (en) | 2015-09-11 | 2015-09-11 | Spacecraft micro meteor and space debris bump positioning method on-track verification device |
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| CN105182290A true CN105182290A (en) | 2015-12-23 |
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| CN201510576267.XA Pending CN105182290A (en) | 2015-09-11 | 2015-09-11 | Spacecraft micro meteor and space debris bump positioning method on-track verification device |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107589459A (en) * | 2017-08-22 | 2018-01-16 | 北京卫星环境工程研究所 | Electric capacity ionization manifold type space micron order fragment detection device |
| CN108459351A (en) * | 2018-03-29 | 2018-08-28 | 北京卫星环境工程研究所 | Resistive type space debris detection device and detection method |
| CN108828073A (en) * | 2018-05-21 | 2018-11-16 | 长沙学院 | A kind of acoustic emission detection system based on fiber grating |
| CN112304349A (en) * | 2020-09-24 | 2021-02-02 | 航天东方红卫星有限公司 | Space debris detection device and method |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103487513A (en) * | 2013-09-06 | 2014-01-01 | 中国运载火箭技术研究院 | Method for identifying types of acoustic emission signals of space debris impact damage |
| US20140202248A1 (en) * | 2011-08-22 | 2014-07-24 | Bae Systems Plc | Impact detection and acoustic emission data processing |
| CN104749558A (en) * | 2013-12-30 | 2015-07-01 | 北京强度环境研究所 | Acoustic emission based positioning method for debris cloud impact source |
-
2015
- 2015-09-11 CN CN201510576267.XA patent/CN105182290A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140202248A1 (en) * | 2011-08-22 | 2014-07-24 | Bae Systems Plc | Impact detection and acoustic emission data processing |
| CN103487513A (en) * | 2013-09-06 | 2014-01-01 | 中国运载火箭技术研究院 | Method for identifying types of acoustic emission signals of space debris impact damage |
| CN104749558A (en) * | 2013-12-30 | 2015-07-01 | 北京强度环境研究所 | Acoustic emission based positioning method for debris cloud impact source |
Non-Patent Citations (5)
| Title |
|---|
| Z LIU等: ""A method based on acoustic emission for locating debris cloud impact"", 《PROCEEDINGS OF SPIE- THE INTERNATIONAL SOCIETY FOR OPTICAL ENGINEERING》 * |
| 刘武刚等: ""天基在轨空间碎片撞击监测技术的进展"", 《强度与环境》 * |
| 刘武刚等: ""高速撞击的声发射源定位"", 《无损检测》 * |
| 庞宝君等: ""空间碎片撞击在轨感知技术研究综述"", 《航天器环境工程》 * |
| 王青林: ""基于PVDF的空间碎片在轨感知技术研究"", 《中国优秀硕士学位论文全文数据库工程科技||辑》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107589459A (en) * | 2017-08-22 | 2018-01-16 | 北京卫星环境工程研究所 | Electric capacity ionization manifold type space micron order fragment detection device |
| CN108459351A (en) * | 2018-03-29 | 2018-08-28 | 北京卫星环境工程研究所 | Resistive type space debris detection device and detection method |
| CN108459351B (en) * | 2018-03-29 | 2019-10-08 | 北京卫星环境工程研究所 | Resistive type space debris detection device and detection method |
| CN108828073A (en) * | 2018-05-21 | 2018-11-16 | 长沙学院 | A kind of acoustic emission detection system based on fiber grating |
| CN112304349A (en) * | 2020-09-24 | 2021-02-02 | 航天东方红卫星有限公司 | Space debris detection device and method |
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Application publication date: 20151223 |
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