CN103940566A - Electronic control type aimable bird shot impact testing device - Google Patents
Electronic control type aimable bird shot impact testing device Download PDFInfo
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- CN103940566A CN103940566A CN201410131276.3A CN201410131276A CN103940566A CN 103940566 A CN103940566 A CN 103940566A CN 201410131276 A CN201410131276 A CN 201410131276A CN 103940566 A CN103940566 A CN 103940566A
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Abstract
The invention discloses an electronic control type aimable bird shot impact testing device and belongs to the technical field of aeronautical facilities. The electronic control type aimable bird shot impact testing device comprises an air storage tank, an electronic control valve, a sighting device, a bird shot filling and launching compartment, a bird shot launching tube, bird shot supporting rods, a bird shot inlet, a sliding valve groove, a bird shot inlet sliding valve and a bird bolt casing stripping device, wherein the inlet of the bird shot launching tube is connected with the bird shot filling and launching compartment, the bird shot supporting rods are arranged in the bird shot filling and launching compartment evenly, the bird shot inlet and the sliding valve groove are formed in the same lateral wall of the bird shot filling and launching compartment, and the bird bolt casing stripping device is fixedly connected with the outlet of the bird shot launching tube. By means of the electronic control type aimable bird shot impact testing device, impact force is applied on bird shots by controlling high-pressure air, and therefore, the bird shots fly to a target quickly to achieve bird shot impact effect. The electronic control type aimable bird shot impact testing device is simple, parts are purchased or manufactured easily, the whole electronic control type aimable bird shot impact testing device can be implemented easily, and cost is low.
Description
Technical field
The invention belongs to air equipment technical field, specifically, be a kind ofly by controlling gases at high pressure, to come bird bullet to produce impulsive force, thereby make the trainable electronic control type bird bullet impact test device of the quick target target of bird bullet.
Background technology
Fanjet full name is that turbofan is a kind of of aircraft engine, by turbojet development, is formed.With turbojet comparison, principal feature is that the area of chopped-off head compressor is much larger, is used as air propeller simultaneously, and the air that part is sucked passes through the periphery of injection engine to pusher.The part of engine core part air process is called main duct, only has the core engine Outboard Sections of fan air process to be called by-pass air duct.During 400 to 1000 kilometers of the most applicable flying speeds of turbofan engine, use, therefore most aeroengine all adopts turbofan as power resources now.Fanjet has that thrust is large, propulsive efficiency is high, noise is low, fuel consumption is low, the advantage that aircraft range is far away.
Present aircraft much all uses turbofan, and probably by the powerful suction of this jet engine, inhaled in the past during Bird Flight, then inevitably sever (being not definitely can sever) the top structure of jet engine-blade of calming the anger, appearance is as a lot of fan of flabellum.After wherein a slice severs, the flabellum that this segment is fallen flies to engine interior along the suction of engine, and because suction is very large, aircraft speed is forward also fast, and relative velocity is very large thus, has directly damaged engine.Engine is directly connecting Bunker, so abnormally dangerous.This has also likely damaged the fuselage of aircraft simultaneously, causes the more serious damage of aircraft even to disintegrate.When high-altitude, ice cube is similar to birds to the destruction of turbofan.
Through the retrieval to prior art, number of patent application is 200710177013.6, name is called the patent of invention of a kind of turbofan and method for designing thereof, proposed a kind of method for designing of all-New Turbofan, but it does not provide the device of simulation ice cube or birds shock turbofan.In the design process of modern turbofan, the device that simulation ice cube or birds are clashed into turbofan is indispensable.
Summary of the invention
The present invention is directed to above-mentioned deficiency, a kind of trainable electronic control type bird bullet impact test device is provided, it can come bird bullet to produce impulsive force by controlling gases at high pressure, thereby makes the quick target target of bird bullet, the effect of clashing into realize bird bullet.
The present invention is achieved through the following technical solutions, the present invention includes high pressure tank, gases at high pressure draft tube, gases at high pressure escape pipe, flange, electronic control valve, alignment clamp, bird bullet is filled launching pod, bird bullet, bird bullet power valve, bird bullet shell, bird bullet pressure pin, bird springs into mouth, slide valve slot, bird springs into a mouthful guiding valve, handle and bird bullet shell stripper, the gas outlet of gases at high pressure draft tube, the air intake opening of gases at high pressure escape pipe is all connected with high pressure tank, and the air intake opening of gases at high pressure draft tube is connected with pneumatic plant gas outlet, electronic control valve by valve respectively with the gas outlet of gases at high pressure escape pipe, the air intake opening that bird bullet is filled launching pod links together, the entrance of bird bullet power valve is filled launching pod with bird bullet and is connected, bird bullet pressure pin is arranged in bird bullet and fills in launching pod, alignment clamp is arranged in bird bullet and fills on launching pod, bird bullet is arranged in bird bullet power valve, bird bullet shell is arranged in the inside of bird bullet power valve, and bird springs into mouth, slide valve slot is arranged in bird bullet and fills on the identical sidewall of launching pod, and bird springs into a mouthful guiding valve and is arranged in slide valve slot, and handle and bird spring into a mouthful guiding valve and be consolidated, the outlet of bird bullet shell stripper and bird bullet power valve links together, bird bullet shell stripper is by top guide bar, lower guide rod, the first buffer spring, the second buffer spring, slider support plate, baffle plate back up pad, shell baffle plate, slide block, steel bar, front end-plate and end plate form, top guide bar, lower guide rod, steel bar is arranged between front end-plate and end plate, the first buffer spring is arranged in top guide bar, the left end of lower guide rod, the second buffer spring is arranged in top guide bar, the right-hand member of lower guide rod, top guide bar is through slider support plate, the upper end of baffle plate back up pad, lower guide rod is through slider support plate, the lower end of baffle plate back up pad, shell baffle plate and baffle plate back up pad link together, slide block is arranged in slider support plate, the first buffer spring and front end-plate, slider support plate links together, the second buffer spring and end plate, baffle plate back up pad links together.
In the present invention, the xsect of bird bullet power valve is circular, and the number of bird bullet pressure pin is three, and the two ends that spring into mouthful guiding valve bird are all provided with O-ring seal.
Further, in the present invention, the number of steel bar is three, and the number of slide block is six, and steel bar, slide block are symmetrical expression and distribute.
Out-of-shape due to bird, if directly bird is put into power valve transmitting, the irregularly shaped flight resistance that will make of bird sharply increases so, and flying speed is significantly reduced, so added the shell of a regular shape to bird bullet, thereby reduced the flight resistance of bird bullet in power valve.But bird bullet shell can not clash into target together with bird bullet, so must remove bird bullet shell when bird bullet flies out power valve, allly at power valve tail end, increased a bird bullet shell stripper, as shown in Figure 6.After bird bullet and shell case one superhigh speed penetrate, by three smooth steel bars, led, forward flight, fly in Fig. 6 near A-A face, encounter on the inclined-plane of slide block in shell case forward position, and slide block is compressed by stage clip, after slide block inclined-plane is hit, open, shell case continues horizontal flight together with bird bullet.Flight near B-B cross section in Fig. 6, shell case outward flange and the collision of shell baffle plate, shell baffle plate is fixed in baffle plate back up pad, baffle plate back up pad and the second buffer spring connect together, the second buffer spring is led by two spring guide pillars.After shell case outward flange and the collision of shell baffle plate, compression the second buffer spring, shell case travelling speed reduces simultaneously, and bird bullet, under inertia effect, departs from shell case and continues high-speed flight.And shell case under the drag effect of spring to the right speed reduce to zero, now the second buffer spring pressurized, promotes shell case high-speed cruising left, bump against the right side of slide block, first buffer spring on the compression left side, and so forth after motion repeatedly, shell case is static, and shell case is retained down finally.Then extract the steel bar of top to the right out, can take out shell case standby.
In the present invention, the process of shooting is: pneumatic plant is quit work, and it is normal pressure that bird bullet is filled in launching pod; By handle, pull bird to spring into mouthful guiding valve bird is sprung into and mouthful opened, bird bullet is placed on bird bullet pressure pin and as far as possible near bird bullet power valve porch; Close hatch door, bird bullet filling process is complete.Seal process is: bird bullet is filled the hatch door of launching pod and closed, and hatch door upper surface is close to internal weapon bays, passes through seal with O ring between the two.Bird bullet emission process is: unlocking electronic operation valve, gases at high pressure impact bird bullet, and the speed of bird bullet in power valve is constantly increased, and have reached the required speed of test to power valve exit, the bird bullet target target after power valve that flies out, thus the simulation of bird bullet knockout process completed.Whole process is all controlled by travel switch or other elements, guarantees that job order can not make mistakes, and makes mistakes and can not carry out next step action, and have bomp signal.
The invention has the beneficial effects as follows: the present invention is simple in structure, parts are easily bought or are processed, and whole device is all easily implemented, and cost is lower; Bird bullet shell of the present invention can improve flying speed and the security of bird bullet, and bird bullet shell stripper can be peeled off bird bullet shell safely and effectively; The pressure of gases at high pressure of the present invention is controlled, so the stroke speed of bird egg also can be controlled; Electronic control valve reliability is high, and stability is strong, and therefore the safety and reliability of whole test is also very good; This test unit, with alignment clamp, can improve the hit rate of bird bullet; Process of the test of the present invention is safe and reliable, without obvious potential safety hazard.
Accompanying drawing explanation
Fig. 1 is the structural representation of state on the way in the present invention;
Fig. 2 is the partial enlarged drawing of Fig. 1;
Fig. 3 is the cabin inner structure schematic diagram that in the present invention, bird bullet is filled launching pod;
Fig. 4 is the structural representation that in the present invention, bird springs into mouthful closed condition;
Fig. 5 is the structural representation that in the present invention, bird springs into mouthful open mode;
Fig. 6 is the structural representation of bird bullet shell stripper in the present invention;
Fig. 7 is the partial enlarged drawing of Fig. 6;
Fig. 8 is the structural representation of three sections in Fig. 6;
Label in accompanying drawing is respectively: 1, high pressure tank, 2, gases at high pressure draft tube, 3, gases at high pressure escape pipe, 4, flange, 5, electronic control valve, 6, alignment clamp, 7, bird bullet is filled launching pod, 8, bird bullet, 9, bird bullet power valve, 10, bird bullet shell, 11, bird bullet pressure pin, 12, bird springs into mouth, 13, slide valve slot, 14, bird springs into a mouthful guiding valve, 15, handle, 16, top guide bar, 17, lower guide rod, 18, the first buffer spring, 19, the second buffer spring, 20, slider support plate, 21, baffle plate back up pad, 22, shell baffle plate, 23, slide block, 24, steel bar, 25, front end-plate, 26, end plate.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are elaborated, the present embodiment be take technical solution of the present invention as prerequisite, provided detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
embodiment
Embodiments of the invention as shown in Figures 1 to 8, the present invention includes high pressure tank 1, gases at high pressure draft tube 2, gases at high pressure escape pipe 3, flange 4, electronic control valve 5, alignment clamp 6, bird bullet is filled launching pod 7, bird bullet 8, bird bullet power valve 9, bird bullet shell 10, bird bullet pressure pin 11, bird springs into mouth 12, slide valve slot 13, bird springs into mouthful guiding valve 14, handle 15 and bird bullet shell stripper, the gas outlet of gases at high pressure draft tube 2, the air intake opening of gases at high pressure escape pipe 3 is all connected with high pressure tank 1, and the air intake opening of gases at high pressure draft tube 2 is connected with pneumatic plant gas outlet, electronic control valve 5 by valve 4 respectively with the gas outlet of gases at high pressure escape pipe 3, the air intake opening that bird bullet is filled launching pod 7 links together, the entrance of bird bullet power valve 9 is filled launching pod 7 with bird bullet and is connected, bird bullet pressure pin 11 is arranged in bird bullet and fills in launching pod 7, alignment clamp 6 is arranged in bird bullet and fills on launching pod 7, bird bullet 8 is arranged in bird bullet power valve 9, bird bullet shell 10 is arranged in the inside of bird bullet power valve 9, and bird springs into mouth 12, slide valve slot 13 is arranged in bird bullet and fills on the identical sidewall of launching pod 7, and bird springs into mouthful guiding valve 14 and is arranged in slide valve slot 13, and handle 15 springs into mouthful guiding valve 14 with bird and is consolidated, the outlet of bird bullet shell stripper and bird bullet power valve 9 links together, bird bullet shell stripper is by top guide bar 16, lower guide rod 17, the first buffer spring 18, the second buffer spring 19, slider support plate 20, baffle plate back up pad 21, shell baffle plate 22, slide block 23, steel bar 24, front end-plate 25 and end plate 26 form, top guide bar 16, lower guide rod 17, steel bar 24 is arranged between front end-plate 25 and end plate 26, the first buffer spring 18 is arranged in top guide bar 16, the left end of lower guide rod 17, the second buffer spring 19 is arranged in top guide bar 16, the right-hand member of lower guide rod 17, top guide bar 16 is through slider support plate 20, the upper end of baffle plate back up pad 21, lower guide rod 17 is through slider support plate 20, the lower end of baffle plate back up pad 21, shell baffle plate 22 links together with baffle plate back up pad 21, slide block 23 is arranged in slider support plate 20, the first buffer spring 18 and front end-plate 25, slider support plate 20 links together, the second buffer spring 19 and end plate 26, baffle plate back up pad 21 links together, the xsect of bird bullet power valve 9 is circular, and the number of bird bullet pressure pin 11 is three, and the two ends that spring into mouthful guiding valve 14 bird are all provided with O-ring seal, the number of steel bar 24 is three, and the number of slide block 23 is six, and steel bar 24, slide block 23 are symmetrical expression and distribute.
In the present invention, the process of shooting is: pneumatic plant is quit work, and it is normal pressure that bird bullet is filled in launching pod 7; By handle 15, pulling bird to spring into mouthful guiding valve 14 springs into mouthfuls 12 by bird and opens, bird bullet 8 is placed on bird bullet pressure pin 11 and as far as possible near bird bullet power valve 9 porch; Close hatch door, bird bullet filling process is complete.Seal process is: seal process is: bird bullet is filled the hatch door of launching pod 7 and closed, and hatch door upper surface is close to internal weapon bays, passes through seal with O ring between the two.Bird bullet emission process is: unlocking electronic operation valve 5, gases at high pressure impact bird egg 8, and the speed of bird egg 8 in bird egg power valve 9 is constantly increased, and have reached the required speed of test to power valve exit, the bird egg 8 target target after power valve that flies out, thus the simulation of bird egg knockout process completed.Whole process is all controlled by travel switch or other elements, guarantees that job order can not make mistakes, and makes mistakes and can not carry out next step action, and have bomp signal.
Claims (3)
1. a trainable electronic control type bird bullet impact test device, comprise high pressure tank (1), gases at high pressure draft tube (2), gases at high pressure escape pipe (3) and flange (4), the gas outlet of gases at high pressure draft tube (2), the air intake opening of gases at high pressure escape pipe (3) is all connected with high pressure tank (1), the air intake opening of gases at high pressure draft tube (2) is connected with pneumatic plant gas outlet, it is characterized in that, also comprise electronic control valve (5), alignment clamp (6), bird bullet is filled launching pod (7), bird bullet (8), bird bullet power valve (9), bird bullet shell (10), bird bullet pressure pin (11), bird springs into mouthful (12), slide valve slot (13), bird springs into a mouthful guiding valve (14), handle (15) and bird bullet shell stripper, electronic control valve (5) by valve (4) respectively with the gas outlet of gases at high pressure escape pipe (3), the air intake opening that bird bullet is filled launching pod (7) links together, the entrance of bird bullet power valve (9) is filled launching pod (7) with bird bullet and is connected, bird bullet pressure pin (11) is arranged in bird bullet and fills in launching pod (7), alignment clamp (6) is arranged in bird bullet and fills on launching pod (7), bird bullet (8) is arranged in bird bullet power valve (9), bird bullet shell (10) is arranged in the inside of bird bullet power valve (9), bird springs into mouthful (12), slide valve slot (13) is arranged in bird bullet and fills on the identical sidewall of launching pod (7), bird springs into a mouthful guiding valve (14) and is arranged in slide valve slot (13), handle (15) springs into a mouthful guiding valve (14) with bird and is consolidated, the outlet of bird bullet shell stripper and bird bullet power valve (9) links together, and bird bullet shell stripper is by top guide bar (16), lower guide rod (17), the first buffer spring (18), the second buffer spring (19), slider support plate (20), baffle plate back up pad (21), shell baffle plate (22), slide block (23), steel bar (24), front end-plate (25) and end plate (26) form, top guide bar (16), lower guide rod (17), steel bar (24) is arranged between front end-plate (25) and end plate (26), and the first buffer spring (18) is arranged in top guide bar (16), the left end of lower guide rod (17), the second buffer spring (19) is arranged in top guide bar (16), the right-hand member of lower guide rod (17), top guide bar (16) is through slider support plate (20), the upper end of baffle plate back up pad (21), lower guide rod (17) is through slider support plate (20), the lower end of baffle plate back up pad (21), shell baffle plate (22) links together with baffle plate back up pad (21), and slide block (23) is arranged in slider support plate (20), the first buffer spring (18) and front end-plate (25), slider support plate (20) links together, the second buffer spring (19) and end plate (26), baffle plate back up pad (21) links together.
2. trainable electronic control type bird bullet impact test device according to claim 1, it is characterized in that, the xsect of bird bullet power valve (9) is circle, and the number of bird bullet pressure pin (11) is three, and the two ends that spring into a mouthful guiding valve (14) bird are all provided with O-ring seal.
3. trainable electronic control type bird bullet impact test device according to claim 1, is characterized in that, the number of steel bar (24) is three, and the number of slide block (23) is six, and steel bar (24), slide block (23) are symmetrical expression and distribute.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201410131276.3A CN103940566B (en) | 2014-04-02 | 2014-04-02 | Trainable electronic control type bird bullet impact test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410131276.3A CN103940566B (en) | 2014-04-02 | 2014-04-02 | Trainable electronic control type bird bullet impact test device |
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| CN103940566A true CN103940566A (en) | 2014-07-23 |
| CN103940566B CN103940566B (en) | 2016-11-23 |
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| CN201410131276.3A Expired - Fee Related CN103940566B (en) | 2014-04-02 | 2014-04-02 | Trainable electronic control type bird bullet impact test device |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266814A (en) * | 2014-10-17 | 2015-01-07 | 苏州世力源科技有限公司 | Gas gun type impact response spectrum testing machine |
| CN104776970A (en) * | 2015-04-27 | 2015-07-15 | 中国直升机设计研究所 | Method for verifying bird strike resistance performance of pitch link of main blade of helicopter |
| CN104896005A (en) * | 2015-06-09 | 2015-09-09 | 西安交通大学 | Novel high-speed light-gas gun muzzle bullet-separating vibration damping system |
| CN105258900A (en) * | 2015-10-30 | 2016-01-20 | 中国建材检验认证集团股份有限公司 | Bird impact test device and method |
| CN106649937A (en) * | 2016-09-27 | 2017-05-10 | 南京航空航天大学 | Method for analyzing bird ingestion airworthiness compliance of aero-engine fan |
| CN108716979A (en) * | 2018-08-07 | 2018-10-30 | 中电科芜湖通用航空产业技术研究院有限公司 | Centrifugal bird impact tests system |
| CN108776001A (en) * | 2018-08-07 | 2018-11-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Centrifugal bird impact tests method |
| CN110823491A (en) * | 2019-11-21 | 2020-02-21 | 安徽文质信息科技有限公司 | Anti-collision performance detection device for forming machining of aviation aircraft shell |
| CN111579190A (en) * | 2020-04-27 | 2020-08-25 | 南京航空航天大学 | Horizontal ejection-impact type blade bird-cutting test device and test method |
| CN113740019A (en) * | 2021-10-08 | 2021-12-03 | 长沙天映航空装备有限公司 | Unmanned aerial vehicle horizontal impact test system |
| CN114838621A (en) * | 2022-03-21 | 2022-08-02 | 西北工业大学 | Multistage bullet device that takes off of air bubble |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1168465A (en) * | 1996-05-24 | 1997-12-24 | 南京理工大学 | Firing equipment for flying bird imitating shell |
| CN201196551Y (en) * | 2008-04-08 | 2009-02-18 | 中国建筑材料科学研究总院 | Hulling apparatus of bird-bumping experiment cannonball |
| JP2011021981A (en) * | 2009-07-15 | 2011-02-03 | Ihi Corp | Ejection tester |
| JP2011153987A (en) * | 2010-01-28 | 2011-08-11 | Ihi Corp | Ejection testing apparatus |
-
2014
- 2014-04-02 CN CN201410131276.3A patent/CN103940566B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1168465A (en) * | 1996-05-24 | 1997-12-24 | 南京理工大学 | Firing equipment for flying bird imitating shell |
| CN201196551Y (en) * | 2008-04-08 | 2009-02-18 | 中国建筑材料科学研究总院 | Hulling apparatus of bird-bumping experiment cannonball |
| JP2011021981A (en) * | 2009-07-15 | 2011-02-03 | Ihi Corp | Ejection tester |
| JP2011153987A (en) * | 2010-01-28 | 2011-08-11 | Ihi Corp | Ejection testing apparatus |
Non-Patent Citations (1)
| Title |
|---|
| 林长亮等: "直升机桨叶鸟撞试验方法的数值模拟", 《振动工程学报》 * |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104266814A (en) * | 2014-10-17 | 2015-01-07 | 苏州世力源科技有限公司 | Gas gun type impact response spectrum testing machine |
| CN104776970B (en) * | 2015-04-27 | 2018-04-27 | 中国直升机设计研究所 | A kind of anti-bird of Helicopter Main blade pitch-change-link hits performance verification method |
| CN104776970A (en) * | 2015-04-27 | 2015-07-15 | 中国直升机设计研究所 | Method for verifying bird strike resistance performance of pitch link of main blade of helicopter |
| CN104896005A (en) * | 2015-06-09 | 2015-09-09 | 西安交通大学 | Novel high-speed light-gas gun muzzle bullet-separating vibration damping system |
| CN105258900A (en) * | 2015-10-30 | 2016-01-20 | 中国建材检验认证集团股份有限公司 | Bird impact test device and method |
| CN105258900B (en) * | 2015-10-30 | 2018-03-13 | 中国建材检验认证集团股份有限公司 | Bird impact tests devices and methods therefor |
| CN106649937A (en) * | 2016-09-27 | 2017-05-10 | 南京航空航天大学 | Method for analyzing bird ingestion airworthiness compliance of aero-engine fan |
| CN106649937B (en) * | 2016-09-27 | 2020-04-21 | 南京航空航天大学 | Aero-engine fan bird-sucking airworthiness analysis method |
| CN108716979A (en) * | 2018-08-07 | 2018-10-30 | 中电科芜湖通用航空产业技术研究院有限公司 | Centrifugal bird impact tests system |
| CN108776001A (en) * | 2018-08-07 | 2018-11-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Centrifugal bird impact tests method |
| CN110823491A (en) * | 2019-11-21 | 2020-02-21 | 安徽文质信息科技有限公司 | Anti-collision performance detection device for forming machining of aviation aircraft shell |
| CN110823491B (en) * | 2019-11-21 | 2021-07-02 | 苏州甫腾智能科技有限公司 | Anti-collision performance detection device for forming machining of aviation aircraft shell |
| CN111579190A (en) * | 2020-04-27 | 2020-08-25 | 南京航空航天大学 | Horizontal ejection-impact type blade bird-cutting test device and test method |
| CN113740019A (en) * | 2021-10-08 | 2021-12-03 | 长沙天映航空装备有限公司 | Unmanned aerial vehicle horizontal impact test system |
| CN114838621A (en) * | 2022-03-21 | 2022-08-02 | 西北工业大学 | Multistage bullet device that takes off of air bubble |
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