CN106989644B - A kind of rainfall bullet initiator flight recovery test device - Google Patents
A kind of rainfall bullet initiator flight recovery test device Download PDFInfo
- Publication number
- CN106989644B CN106989644B CN201710345813.8A CN201710345813A CN106989644B CN 106989644 B CN106989644 B CN 106989644B CN 201710345813 A CN201710345813 A CN 201710345813A CN 106989644 B CN106989644 B CN 106989644B
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- CN
- China
- Prior art keywords
- initiator
- detonation
- bullet
- loading part
- test device
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- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42C—AMMUNITION FUZES; ARMING OR SAFETY MEANS THEREFOR
- F42C21/00—Checking fuzes; Testing fuzes
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention discloses a kind of rainfall bullet initiator flight recovery test device, including the loading part for loading initiator, the power set that are arranged at the bullet of loading part front end, are arranged at loading part tail end, the initiator includes housing, the power supply unit being arranged in housing, the controller being connected with power supply unit, the detonation circuit being connected with controller, detonation is connected with detonation sensing element in circuit, the loading part includes matrix, at least one blind hole opened up in matrix, the cover board for covering blind hole, and an initiator can be at least housed in the blind hole；The detonation sensing element is electric igniter, and the two poles of the earth of electric igniter are connected in detonation circuit.The advantages of experimental rig of the present invention has securely and reliably, recycles and checks beneficial to initiator, and experimentation cost is low.
Description
Technical field
The invention belongs to civilian rainfall bullet correlation equipment measuring technology, and in particular to a kind of rainfall bullet initiator is used and flown back
Acceptance test device.
Background technology
Nowadays, civilian rainfall bullet is widely used, using rocket launching technology, to make rainfall resilience energy enough fly to predetermined
Height is detonated, it is necessary to design an initiator for rainfall bullet in due course.And, it is necessary to initiator in initiator design process
Performance parameter carries out test flight.
Since the detonation sensing element used in current initiator is detonator, there are following defect：
1. after the completion of initiator work, since blasting cap detonation power is very big, suffer the initiator after test flight experiment
To destruction, it is impossible to carry out recycling inspection, performance judgement can not be carried out to components such as the circuit boards in initiator.
If 2. initiator there are the failures such as circuit can not detonating capsule, then there are security risk in removal process,
In the case of failure cause can not being predicted, contact firing device, may postpone to cause casualties igniting because of initiator rashly.
3. actual rainfall bullet product can only be used to carry out test flight experiment every time, and live shell can only assemble one every time
Initiator is sent out, causes the header body of test flight experiment consumption and rocket-powered number of components more, causes to waste.
Therefore, during the initiator development of rainfall bullet or test result analysis, the experiment of initiator test flight exists
The problem of initiator quantity that recycling is difficult, once tests is few, of high cost, security risk is big.
The content of the invention
In view of the above-mentioned problems, the present invention is intended to provide a kind of securely and reliably, beneficial to the low rainfall of recycling inspection, cost upspring
Quick-fried device flight recovery test device.
The technical solution of the present invention that solves the problems, such as is：A kind of rainfall bullet initiator flight recovery test device, including with
In the loading part for loading initiator, the power set that are arranged at the bullet of loading part front end, are arranged at loading part tail end, described
Quick-fried device includes housing, the power supply unit being arranged in housing, the controller being connected with power supply unit, the detonation being connected with controller
Circuit, is connected with detonation sensing element in circuit of detonating, the loading part include matrix, opened up in matrix it is at least one blind
Hole, the cover board for covering blind hole, can at least house an initiator in the blind hole；
The detonation sensing element is electric igniter, and the two poles of the earth of electric igniter are connected in detonation circuit.
After the completion of experimental rig transmitting, bullet and the power set of work completion are pulled down.Then loading part is torn open
Solution, takes out initiator and is checked, the various performance parameters of the components such as its circuit board are detected.Meanwhile to loading part
Blind hole is cleared up, so that experiment next time uses.
In the scheme of the prior art, the detonation sensing element connected in circuit of detonating is detonator, in order to avoid blasting cap detonation
The destruction brought, electric igniter is substituted for by detonator.After detonation, whether it is under fire by electric igniter and judges that initiator work is
It is no normal.Since electric igniter is under fire to initiator entirety almost without injury, so the initiator after recycling can carry out
The detection of the various performance parameters of the components such as circuit board.Without worry initiator because failure not detonate and caused by life
Safety.
Specifically, being provided with three blind holes in described matrix, four initiators are stacked in each blind hole successively from bottom to top, often
Separated between a initiator by gasket.
Blind hole quantity and the quantity for placing initiator, are decided according to the actual requirements, it can be achieved that at the same time to multiple civilian rainfalls
The initiator performance parameter of bullet carries out flight recycling test.
Further, loss of weight fabrication hole is offered on matrix.
Preferably, described matrix is made of 2A12 aluminium alloys.Manufactured using this shock proof metal material, beneficial to protection
Initiator is without damage.
Preferably, the emulation detonator for counterweight is additionally provided with the housing.Emulation detonator may be disposed at original place very
The position of detonator, preferably to simulate true environment.
The present invention remarkable result be：
1. due to electric igniter be under fire it is overall to initiator almost without injury, so initiator after recycling can be into
The detection of the various performance parameters of the components such as row circuit board.
If 2. initiator occur the failures such as circuit can not detonating capsule, since electric igniter will not explode in itself, can not
In the case of predicting failure cause, contact firing device, safe without life caused by worry rashly.
3. loading part can realize recycling and reuse, cost is reduced.And, it can be achieved that at the same time to multiple civilian rainfalls
The initiator performance parameter of bullet carries out flight recycling test, and test efficiency is high.
Brief description of the drawings
The invention will be further described below in conjunction with the accompanying drawings.
Fig. 1 is the flight recovery test device appearance schematic diagram of the present invention.
Fig. 2 is loading part cut-away view.
Fig. 3 is matrix schematic diagram.
Fig. 4 is cover plate schematic diagram.
Fig. 5 is initiator front schematic view.
Fig. 6 is initiator side schematic view.
In figure：1- electric igniters, 2- emulation detonators, 3- detonations circuit, 4- housings, 5- initiators, 6- loading parts, 7- bullets
Head, 8- power set, 61- matrixes, 62- blind holes, 63- cover boards, 64- fabrication holes.
Embodiment
As shown in figs. 1 to 6, a kind of rainfall bullet initiator flight recovery test device, including for loading initiator 5
Loading part 6, the bullet 7 for being arranged at 6 front end of loading part, the power set 8 for being arranged at 6 tail end of loading part.Power set 8 can borrow
The power part of standard rainfall bullet, control acceleration and propulsion time.
The loading part 6 include made of 2A12 aluminium alloys matrix 61, the blind hole 62 opened up in matrix 61, for sealing
The cover board 63 of lid blind hole 62.Three blind holes 62 are provided with described matrix 61, four are stacked successively from bottom to top in each blind hole 62
Initiator 5, is separated by gasket between each initiator 5.Loss of weight fabrication hole 64 is offered on matrix 61.
The initiator 5 include housing 4, be arranged in housing 4 power supply unit, be connected with power supply unit controller,
The detonation circuit 3 being connected with controller.Detonation is connected with detonation sensing element in circuit 3.The detonation sensing element is electric point
Duration and degree of heating 1, the two poles of the earth of electric igniter 1 are connected in detonation circuit 3.The emulation detonator 2 for counterweight is additionally provided with the housing 4.
After the completion of experimental rig transmitting, bullet 7 and the power set 8 of work completion are pulled down.Then loading part 6 is carried out
Disassemble, take out initiator 5 and checked, the various performance parameters of the components such as its circuit board are detected.Meanwhile to loading
The blind hole 62 in portion 6 is cleared up, so that experiment next time uses.
Claims (5)
1. a kind of rainfall bullet initiator flight recovery test device, including for loading initiator（5）Loading part（6）, set
It is placed in loading part（6）The bullet of front end（7）, be arranged at loading part（6）The power set of tail end（8）, the initiator（5）Including
Housing（4）, be arranged at housing（4）Interior power supply unit, the controller being connected with power supply unit, the detonation that is connected with controller are returned
Road（3）, circuit of detonating（3）In be connected with detonation sensing element, it is characterised in that：The loading part（6）Including matrix（61）,
Matrix（61）At least one blind hole inside opened up（62）, for covering blind hole（62）Cover board（63）, the blind hole（62）Inside extremely
An initiator can be housed less（5）；
The detonation sensing element is electric igniter（1）, electric igniter（1）The two poles of the earth be connected on detonation circuit（3）In.
2. rainfall bullet initiator according to claim 1 flight recovery test device, it is characterised in that：Described matrix
（61）On be provided with three blind holes（62）, each blind hole（62）Inside stack four initiators successively from bottom to top（5）, each initiator
（5）Between separated by gasket.
3. rainfall bullet initiator according to claim 2 flight recovery test device, it is characterised in that：In matrix（61）
On offer loss of weight fabrication hole（64）.
4. rainfall bullet initiator according to claim 1 flight recovery test device, it is characterised in that：Described matrix
（61）It is made of 2A12 aluminium alloys.
5. rainfall bullet initiator according to claim 1 flight recovery test device, it is characterised in that：The housing
（4）Inside it is additionally provided with the emulation detonator for counterweight（2）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710345813.8A CN106989644B (en) | 2017-05-17 | 2017-05-17 | A kind of rainfall bullet initiator flight recovery test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710345813.8A CN106989644B (en) | 2017-05-17 | 2017-05-17 | A kind of rainfall bullet initiator flight recovery test device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106989644A CN106989644A (en) | 2017-07-28 |
| CN106989644B true CN106989644B (en) | 2018-05-11 |
Family
ID=59419801
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710345813.8A Expired - Fee Related CN106989644B (en) | 2017-05-17 | 2017-05-17 | A kind of rainfall bullet initiator flight recovery test device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106989644B (en) |
Citations (12)
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|---|---|---|---|---|
| US4294172A (en) * | 1978-06-02 | 1981-10-13 | Diehl Gmbh & Co. | Projectile with recoverable detonator |
| US4333400A (en) * | 1980-02-01 | 1982-06-08 | The United States Of America As Represented By The Secretary Of The Navy | Two stage parachute fuze recovery system |
| CN201302427Y (en) * | 2008-11-17 | 2009-09-02 | 长安汽车（集团）有限责任公司 | Secure man-made rail shell fusee |
| US8006936B1 (en) * | 2006-05-31 | 2011-08-30 | Farr Iii Warren W | Parachute deployment control |
| CN102914222A (en) * | 2012-09-24 | 2013-02-06 | 杭州航海仪器有限公司 | Electric ignition head online detection and launch control system |
| CN105659803B (en) * | 2010-04-30 | 2013-11-20 | 北京理工大学 | Influence fuse height of burst test macro |
| CN205482635U (en) * | 2016-03-30 | 2016-08-17 | 中国人民解放军军械工程学院 | Wound packages guided missile radio fuse test system |
| CN105890473A (en) * | 2014-11-24 | 2016-08-24 | 重庆长安工业(集团)有限责任公司 | Fuze device for artificial precipitation projectile |
| CN105890462A (en) * | 2016-04-07 | 2016-08-24 | 江资成 | Ignition time measuring system of electric ignition head |
| US9528802B1 (en) * | 2015-11-19 | 2016-12-27 | The United States Of America As Represented By The Secretary Of The Army | Indirect fire munition non-lethal cargo carrier mortar |
| CN106338224A (en) * | 2016-10-27 | 2017-01-18 | 南京理工大学 | Time detonating fuse of antiaircraft gun hail-suppression precipitation increasing bomb |
| CN206818072U (en) * | 2017-05-17 | 2017-12-29 | 江南工业集团有限公司 | A kind of rainfall bullet initiator flight recovery test device |
-
2017
- 2017-05-17 CN CN201710345813.8A patent/CN106989644B/en not_active Expired - Fee Related
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4294172A (en) * | 1978-06-02 | 1981-10-13 | Diehl Gmbh & Co. | Projectile with recoverable detonator |
| US4333400A (en) * | 1980-02-01 | 1982-06-08 | The United States Of America As Represented By The Secretary Of The Navy | Two stage parachute fuze recovery system |
| US8006936B1 (en) * | 2006-05-31 | 2011-08-30 | Farr Iii Warren W | Parachute deployment control |
| CN201302427Y (en) * | 2008-11-17 | 2009-09-02 | 长安汽车（集团）有限责任公司 | Secure man-made rail shell fusee |
| CN105659803B (en) * | 2010-04-30 | 2013-11-20 | 北京理工大学 | Influence fuse height of burst test macro |
| CN102914222A (en) * | 2012-09-24 | 2013-02-06 | 杭州航海仪器有限公司 | Electric ignition head online detection and launch control system |
| CN105890473A (en) * | 2014-11-24 | 2016-08-24 | 重庆长安工业(集团)有限责任公司 | Fuze device for artificial precipitation projectile |
| US9528802B1 (en) * | 2015-11-19 | 2016-12-27 | The United States Of America As Represented By The Secretary Of The Army | Indirect fire munition non-lethal cargo carrier mortar |
| CN205482635U (en) * | 2016-03-30 | 2016-08-17 | 中国人民解放军军械工程学院 | Wound packages guided missile radio fuse test system |
| CN105890462A (en) * | 2016-04-07 | 2016-08-24 | 江资成 | Ignition time measuring system of electric ignition head |
| CN106338224A (en) * | 2016-10-27 | 2017-01-18 | 南京理工大学 | Time detonating fuse of antiaircraft gun hail-suppression precipitation increasing bomb |
| CN206818072U (en) * | 2017-05-17 | 2017-12-29 | 江南工业集团有限公司 | A kind of rainfall bullet initiator flight recovery test device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106989644A (en) | 2017-07-28 |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20180511 |
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| CF01 | Termination of patent right due to non-payment of annual fee |