CN204646453U - Portable missile rocket motor the cannot-harm-detection device - Google Patents
Portable missile rocket motor the cannot-harm-detection device Download PDFInfo
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- CN204646453U CN204646453U CN201520297577.3U CN201520297577U CN204646453U CN 204646453 U CN204646453 U CN 204646453U CN 201520297577 U CN201520297577 U CN 201520297577U CN 204646453 U CN204646453 U CN 204646453U
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Abstract
The utility model discloses a kind of portable missile rocket motor the cannot-harm-detection device, comprise probe and detection case, detection case is made up of the testing circuit of casing and its inside, described testing circuit comprises synchronous circuit, high voltage direct current source circuit, ultrasonic transmit circuit, ultrasound receiving circuit and data acquisition circuit, and described ultrasound receiving circuit comprises limiter protection circuit, high-frequency amplifier circuit and eliminator; The utility model delicate structure, is easy to carry, and is applicable to the individual soldier's air defence missile and the antitank missile that detect current various model, missile measure when facilitating army's field target practice to train.
Description
Technical field
The utility model relates to a kind of guided missile rocket motor the cannot-harm-detection device, and specifically a kind of portable missile rocket motor the cannot-harm-detection device, belongs to missile check-out equipment field.
Background technique
Missile propulsive plant is generally made up of metal shell, heat insulation layer, clad and powder column.Powder column is bonded together by clad, heat insulation layer and shell, and therefore, bonding interface plays a part very crucial, and the quality of its performance is directly connected to structural integrity and the reliability of guided missile.If have unsticking chamber to exist on powder column and clad (or heat insulation layer) interface, will directly injure the reliability of guided missile work.After igniting, the combustion gas produced in body makes the pressure in firing chamber raise.Pressure official post combustion gas in firing chamber and unsticking chamber enters in unsticking chamber, and the grain surface temperature of debonding interface raises, and when the heat energy of grain surface deposits to a certain degree, powder column starts pyrolysis and final burning.Unsticking cavity pressure increases along with burning, if pressure load is greater than the bonding force in face at the stress value that unsticking costal field produces, unsticking face, by with certain speed expanded, makes combustion face area increase, likely causes the catastrophic effect that chamber pressure increase is even exploded.According to adding up in the world, the transmitting accident that coated quality (mainly the bonding quality of clad material) causes accounts for 50% of the total accident of rocket motor, therefore the diagnosis of guided missile heat insulation layer and clad bonding quality is the emphasis of state's researchs such as the United States, Russia for many years always.U.S. NASA " spacecraft design code " points out: cause the reason of heat run or abortive launch mainly due to the destruction of structural integrity.A large amount of Dissection test shows, the unsticking destruction of the bonding interface between guided missile powder column/clad/heat insulation layer/housing is one of critical forms of its structural integrity destruction.
Therefore, guided missile rocket motor must carry out non-destructive inspection in production with in using, and study the extent of injury of defect, the rule of development and failure mechanism, the intensity of evaluating material and the integrity of structure, characterize its internal structure performance, evaluate its reliability.If there is unsticking also to continue to be on active service, then likely bring safety issue.
But existing guided missile rocket motor the cannot-harm-detection device all becomes one with other measuring abilities, is large-scale plant, is adapted at factory, ammunition depot carries out missile measure, be not easy to army's field exercise target practice and use.
Summary of the invention
The utility model object is to provide a kind of portable guided missile rocket motor the cannot-harm-detection device being applicable to use when army's field exercise is practiced shooting.
For achieving the above object, the utility model one comprises probe and detection case, detection case is made up of the testing circuit of casing and its inside, described testing circuit comprises acquisition controller, synchronous circuit, high voltage direct current source circuit, ultrasonic transmit circuit, ultrasound receiving circuit and data acquisition circuit, and described ultrasound receiving circuit comprises limiter protection circuit, high-frequency amplifier circuit and eliminator, synchronous circuit produces lock-out pulse and gives ultrasonic transmit circuit and data acquisition circuit respectively, high voltage direct current source circuit provides 600V high pressure activation power supply for ultrasonic transmit circuit, echo signal enters after limiter protection circuit through high-frequency amplifier circuit and eliminator, send into data acquisition circuit, data acquisition circuit lock-out pulse synchronous under carry out data capture, the pulse signal that ultrasonic transmit circuit is formed sends through probe, echo signal receives laggard excess of imports acoustic receiver circuit through probe, acquisition controller controls high-frequency amplifier circuit by decoding control circuit and data acquisition circuit settling signal amplifies and data capture.
The utility model delicate structure, is easy to carry, and is applicable to the individual soldier's air defence missile and the antitank missile that detect current various model, missile measure when facilitating army's field target practice to train.
Accompanying drawing explanation
Fig. 1 is the utility model theory diagram;
Fig. 2 is the utility model ultrasound emission circuit composition frame chart;
Fig. 3 is the utility model filtering and amplifying circuit schematic diagram.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As shown in Figure 1, a kind of portable missile rocket motor the cannot-harm-detection device, comprise probe and detection case, detection case is made up of the testing circuit of casing and its inside, described testing circuit comprises acquisition controller, synchronous circuit, high voltage direct current source circuit, ultrasonic transmit circuit, ultrasound receiving circuit and data acquisition circuit, and described ultrasound receiving circuit comprises limiter protection circuit, high-frequency amplifier circuit and eliminator, synchronous circuit produces lock-out pulse and gives ultrasonic transmit circuit and data acquisition circuit respectively, high voltage direct current source circuit provides 600V high pressure activation power supply for ultrasonic transmit circuit, echo signal enters after limiter protection circuit through high-frequency amplifier circuit and eliminator, send into data acquisition circuit, data acquisition circuit lock-out pulse synchronous under carry out data capture, the pulse signal that ultrasonic transmit circuit is formed sends through probe, echo signal receives laggard excess of imports acoustic receiver circuit through probe, acquisition controller controls high-frequency amplifier circuit by decoding control circuit and data acquisition circuit settling signal amplifies and data capture.
What emitting circuit was the most frequently used has resonant mode and disresonance type two class, and wherein the emissino frequency of resonant mode emitting circuit is determined by the resonant frequency of circuit, and the emissino frequency of disresonance type emitting circuit is determined by the free frequency that pop one's head in (piezoelectric crystal) is own.As shown in Figure 2, native system adopts disresonance type emitting circuit, comprise internal trigger circuit, trigger selection circuit, high-voltage control circuit, circuit for producing high voltage, pulse width control circuit, impulse output circuit and pulse oscillator, internal trigger circuit produces trigger impulse and enters pulse oscillator through trigger selection circuit, high-voltage control circuit controls circuit for producing high voltage and gives pulse oscillator high-voltage power, pulse oscillator, under the effect of trigger impulse and pulse width control circuit, exports through impulse output circuit after forming high pressure Transmitted pulse.
The effect of amplification circuit is exactly that the small electrical signals exported by receiving transducer obtains enough large signal, to drive various control and display circuit through fully amplifying.The original received signal order of magnitude of transceiver circuit is mV even μ V.As shown in Figure 3, AD8045 is the high speed amplifier of a function admirable, there is the advantages such as highi degree of accuracy, low noise, wide band, be applicable to ultrasound detection, adopting in circuit with AD8045 is the amplification circuit of core, gain control is adjustable between 20 ~ 120dB, can obtain the amplification output signal of about tens V.
Described probe is double crystal probe.Double crystal probe is launched wafer T also known as associating dual probe or partition type TR(, is received wafer R) probe.This probe contains two piezoelectric chips, is contained in same housing, and a wafer is launched, another wafer receipt.Further, transmit and receive wafer can respectively with the high piezoelectric material (as lead zirconate titanate) of transmitting sensitivity and the high piezoelectric material (as lithium sulfate) of receiving sensitivity obtained.Therefore, the transmitting and receiving sensitivity of this probe is all very high, and single crystal probe cannot accomplish this point.In addition, separate with sound absorption properties Sound insulating layer that is strong, good insulating between double crystal probe two wafers, initial spike can not enter reception amplifier, overcomes choking phenomenon, also effectively prevents the interface clutter between Transmitted pulse and delay block to enter reception wafer.And with plexiglass delay block before wafer, make acoustical impedance a period of time enter workpiece.Because transmitting and receiving separate, and employ delay block, so substantially reduce blind area, be beneficial to the detection of Near surface defect.
Claims (4)
1. portable missile rocket motor the cannot-harm-detection device, comprise probe and detection case, detection case is made up of the testing circuit of casing and its inside, it is characterized in that, described testing circuit comprises acquisition controller, synchronous circuit, high voltage direct current source circuit, ultrasonic transmit circuit, ultrasound receiving circuit and data acquisition circuit, and described ultrasound receiving circuit comprises limiter protection circuit, high-frequency amplifier circuit and eliminator, synchronous circuit produces lock-out pulse and gives ultrasonic transmit circuit and data acquisition circuit respectively, high voltage direct current source circuit provides 600V high pressure activation power supply for ultrasonic transmit circuit, echo signal enters after limiter protection circuit through high-frequency amplifier circuit and eliminator, send into data acquisition circuit, data acquisition circuit lock-out pulse synchronous under carry out data capture, the pulse signal that ultrasonic transmit circuit is formed sends through probe, echo signal receives laggard excess of imports acoustic receiver circuit through probe, acquisition controller controls high-frequency amplifier circuit by decoding control circuit and data acquisition circuit settling signal amplifies and data capture.
2. portable missile rocket motor the cannot-harm-detection device according to claim 1, it is characterized in that, described ultrasonic transmit circuit adopts disresonance type emitting circuit, comprise internal trigger circuit, trigger selection circuit, high-voltage control circuit, circuit for producing high voltage, pulse width control circuit, impulse output circuit and pulse oscillator, internal trigger circuit produces trigger impulse and enters pulse oscillator through trigger selection circuit, high-voltage control circuit controls circuit for producing high voltage and gives pulse oscillator high-voltage power, pulse oscillator is under the effect of trigger impulse and pulse width control circuit, export through impulse output circuit after forming high pressure Transmitted pulse.
3. portable missile rocket motor the cannot-harm-detection device according to claim 1, is characterized in that, described high-frequency amplifier circuit adopts AD8045.
4. portable missile rocket motor the cannot-harm-detection device according to claim 1, is characterized in that, described probe is double crystal probe.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520297577.3U CN204646453U (en) | 2015-05-08 | 2015-05-08 | Portable missile rocket motor the cannot-harm-detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520297577.3U CN204646453U (en) | 2015-05-08 | 2015-05-08 | Portable missile rocket motor the cannot-harm-detection device |
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| Publication Number | Publication Date |
|---|---|
| CN204646453U true CN204646453U (en) | 2015-09-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520297577.3U Expired - Fee Related CN204646453U (en) | 2015-05-08 | 2015-05-08 | Portable missile rocket motor the cannot-harm-detection device |
Country Status (1)
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| CN (1) | CN204646453U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107144631A (en) * | 2017-04-13 | 2017-09-08 | 上海理工大学 | Retire real-time detecting system and method in a kind of solid rocket propellant combustion face |
| CN111983277A (en) * | 2020-07-29 | 2020-11-24 | 普源精电科技股份有限公司 | Test equipment, signal measuring device, signal generating device and synchronous control method |
| CN111997786A (en) * | 2020-07-17 | 2020-11-27 | 沈阳航天新光集团有限公司 | Portable measurement and control system box of rocket engine |
-
2015
- 2015-05-08 CN CN201520297577.3U patent/CN204646453U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107144631A (en) * | 2017-04-13 | 2017-09-08 | 上海理工大学 | Retire real-time detecting system and method in a kind of solid rocket propellant combustion face |
| CN107144631B (en) * | 2017-04-13 | 2023-11-07 | 上海理工大学 | Real-time detection system and method for solid rocket propellant combustion surface retreating |
| CN111997786A (en) * | 2020-07-17 | 2020-11-27 | 沈阳航天新光集团有限公司 | Portable measurement and control system box of rocket engine |
| CN111983277A (en) * | 2020-07-29 | 2020-11-24 | 普源精电科技股份有限公司 | Test equipment, signal measuring device, signal generating device and synchronous control method |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhu Xunzhi Inventor after: Song Mingming Inventor after: Li Jianzeng Inventor after: Zhang Hui Inventor after: Xie Zhigang Inventor before: Zhu Xun Inventor before: Song Mingming Inventor before: Li Jianzeng Inventor before: Zhang Hui Inventor before: Xie Zhigang |
|
| COR | Change of bibliographic data | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150916 Termination date: 20160508 |