CN108344552A - Separate type experimental facilities for research structure high temperature and high speed impact response - Google Patents
Separate type experimental facilities for research structure high temperature and high speed impact response Download PDFInfo
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- CN108344552A CN108344552A CN201810219362.8A CN201810219362A CN108344552A CN 108344552 A CN108344552 A CN 108344552A CN 201810219362 A CN201810219362 A CN 201810219362A CN 108344552 A CN108344552 A CN 108344552A
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- 238000011160 research Methods 0.000 title claims abstract description 22
- 230000004044 response Effects 0.000 title claims abstract description 17
- 238000000926 separation method Methods 0.000 claims abstract description 34
- 238000010438 heat treatment Methods 0.000 claims description 36
- 238000007789 sealing Methods 0.000 claims description 16
- 238000009413 insulation Methods 0.000 claims description 4
- 210000003205 muscle Anatomy 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 2
- 238000012360 testing method Methods 0.000 abstract description 12
- 238000002474 experimental method Methods 0.000 abstract description 6
- 238000009863 impact test Methods 0.000 abstract description 3
- 230000002159 abnormal effect Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 3
- 230000036544 posture Effects 0.000 description 3
- 238000012356 Product development Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000428 dust Substances 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004321 preservation Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000003556 assay Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 235000019628 coolness Nutrition 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 239000000383 hazardous chemical Substances 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 230000002285 radioactive effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/08—Shock-testing
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention discloses a kind of separate type experimental facilities for research structure high temperature and high speed impact response, belong to structured high temperature high speed impact dynamics research field, include from rear to the preceding air bubble installed successively, separation of the projectile seat device and target body, the air bubble include from front to back sequentially connected gun tube, shoot cabin, main air chamber and accessory air-space, the gun tube, cabin, the main air chamber and the accessory air-space of shooting are located in same extended axis of the horse.The equipment is the high-speed and high-temperature impact test device of a set of simple multipurpose high-performance, can ensure sample touch target posture and test temperature is adjustable, controllable and can survey, ensure the stability of experiment, it can ensure experimental subjects at given temperature and velocity conditions, target body is hit according to predetermined angular, overall structure is simple, and operation is very easy.
Description
Technical field
The invention belongs to structured high temperature high speed impact dynamics research fields, and in particular to one kind being used for research structure high temperature
The separate type experimental facilities of high-speed impact response.
Background technology
With the development of the progress and science and technology in epoch, the safety day under the safety especially abnormal accident of product
Benefit attracts attention, and is increasingly becoming indispensable one of technical indicator during product development.Safety under abnormal accident
Property to refer to product prevent because of abnormal high velocity impact or/and under burning explosion and hazardous materials spillage ability.Such as survey of deep space
Radioactive isotope heat/power supply may undergo high temperature and high speed when surprisingly reentering and hit, cause its outer housing to rupture and occur anti-
Penetrating property material leaks, and disaster is brought to ecology or the mankind；Nuclear Power Station's Exhausted Fuels packing case falls/burns, it is also possible to induce tight
The safety accident etc. of weight.A large amount of research is carried out to this both at home and abroad.But safety grinds under existing procucts abnormal accident
In studying carefully, usually the safety of high-speed impact and high temperature action lower structure is studied respectively, but abnormal accident high speed collision and
High temperature action is often simultaneous, therefore the safety carried out under product high temperature and high speed hits while acting on seems particularly heavy
It wants.
The U.S. is realized gently using isotope energy ram tester (Isotope Fuels ImpactTester, IFIT)
The high temperature and high speed of quality isotope heat source (LWRHU) and the single heat source of general heat source isotope battery (GPHS-RTG) hits examination
It tests.The leakage of harmful substance in order to prevent, the structure design complex of IFIT, is broadly divided into five parts：Air bubble, swashs at bullet
Transmitting apparatus, collision cell and energy absorbing device are made of several widgets again per part.For entire GPHS-RTG, then use
Rocket sledge accelerated method realizes high temperature and high speed bump test, and specific method is to be heated to GPHS-RTG first with electric furnace
Set temperature (>1000 DEG C), then remote control is installed in rocket sledge, after rocket sledge accelerates to setting speed, profit
GPHS-RTG is set to be detached with rocket sledge with blocking mechanism, last GPHS-RTG is freely collided with target body；Or using " inverse trajectory "
Method target body is accelerated into setting speed using rocket sledge after, hit the GPHS-RTG of fixed installation.Chinese atomic energy science
Research institute has invented " a kind of device for high temperature and high speed bump test " (CN 203849118U).The device is based on compression
A kind of " the material property detection device " of air load " can accurately simulate isotope heat source under illusion accident environment
With the knockout process on ground ", design " heat preservation bullet support " can " more precisely analog temperature ".
Although isotope heat/power supply may be implemented in the device of the IFIT in the U.S., rocket sledge and Chinese Atomic Energy Research Institute
High-speed and high-temperature bump test, but there are it is complicated, operation be not easy, test inconvenience and autgmentability it is poor the deficiencies of.The U.S.
The not disclosed announcement of detail of experimental technique, it is difficult to apply and promote in practice in engineering.Chinese atomic energy science research
The device of institute's research and development is mainly used for research material high temperature and high speed and hits mechanical property, it is difficult to which it is high that expansion is applied to research structure high temperature
Dynamic response under fast impact response, particularly different postures；Simultaneously because heat preservation bullet support and simulation heat source can not be kept completely separate,
The easy test for influencing testpieces and touching control and the shock response of target posture such as fragment and dust that separation of the projectile seat generates.Therefore,
The high-speed and high-temperature impact test device for developing a set of simple multipurpose high-performance has become urgently to be resolved hurrily in engineering product development ask
Topic.
Invention content
The purpose of the present invention is that solve the above-mentioned problems and provides a kind of for the shock of research structure high temperature and high speed
The separate type experimental facilities of response.
The present invention is achieved through the following technical solutions above-mentioned purpose：
A kind of separate type experimental facilities for research structure high temperature and high speed impact response, including installed successively from rear to preceding
Air bubble, separation of the projectile seat device and target body；
The air bubble include from front to back sequentially connected gun tube, shoot cabin, main air chamber and accessory air-space, the gun tube,
Cabin, the main air chamber and the accessory air-space of shooting is located in same extended axis of the horse；
Double-head piston is installed between the main air chamber and the accessory air-space, the double-head piston is arranged along the longitudinal direction,
Its secondary piston is located in the main air chamber and as the valve for shooting cabin rear port, and piston is located at the accessory air-space thereafter
It is interior；
The accessory air-space is divided into accessory air-space I and the secondary gas in front of accessory air-space I by the rear piston of the double-head piston
Room II, the piston rod of the double-head piston pass through the front side wall of the accessory air-space II, the piston rod of the double-head piston with it is described
Sealing is formed between the front side wall of accessory air-space II；
The accessory air-space I is provided with air inlet pipe I and gas outlet, the accessory air-space II and the main air chamber be respectively arranged with into
Tracheae II and air inlet pipe III；
Described shoot is provided in cabin for loading and the missile-borne heating device of heating sample, and missile-borne heating device is along preceding
Rear direction arranges cylinder-like structure, its rear end closing and front end setting sample outlet；
The centrally disposed through-hole being useful for through sample of the separation of the projectile seat device, the through-hole and the missile-borne heating device
It is located in same extended axis of the horse with the gun tube, aperture is less than the outer diameter of the missile-borne heating device；
The target body is tilted towards the separation of the projectile seat device, and the front projection of the central through hole of the separation of the projectile seat device
On the target body.
As this patent selection a kind of technical solution, the gun tube, it is described shoot cabin, the main air chamber passes through bearing
Support.
As a kind of technical solution of this patent selection, the secondary piston of the double-head piston is the cone that cabin is shot described in
Shape structure, maximum gauge are more than the rear port bore for shooting cabin.
As a kind of technical solution of this patent selection, the front side of the piston rod of the double-head piston and the accessory air-space II
It is sealed by sealing ring I between wall.
As a kind of technical solution of this patent selection, the cabin that shoots includes shooting nacelle, shooting hatchcover, described to shoot
It being communicated before and after nacelle, and front port is connected to the gun tube, rear port is connected to double-head piston described in simultaneously face with the main air chamber,
The open top for shooting nacelle and be equipped with it is described shoot hatchcover, it is described to shoot hatchcover and described shoot passes through between nacelle
Sealing ring II seals.
As a kind of technical solution of this patent selection, having heaters, and outer layer packet are set in the missile-borne heating device
It is wrapped with heat insulation layer.
As a kind of technical solution of this patent selection, the target body and the separation of the projectile seat device are mounted on a target chamber
Interior, the gun tube leads to the target chamber, and the target body is fixed by target body mounting bracket, and the separation of the projectile seat device passes through bullet support point
It is fixed from device mounting bracket.
As a kind of technical solution of this patent selection, the separation of the projectile seat device includes cylinder, is connected to the separation
The bottom plate of cylinder front end while detaching drum outer wall and the several of bottom plate welding detach muscle with described, the cylinder it is front and back
The front port of both ends open, the cylinder leads to the target body and rear port leads to the gun tube.
The beneficial effects of the present invention are：
The equipment is the high-speed and high-temperature impact test device of a set of simple multipurpose high-performance, it can be ensured that sample touches target
Posture and test temperature are adjustable, controllable and can survey, it is ensured that the stability of experiment, can ensure experimental subjects in given temperature and
Under velocity conditions, target body is hit according to predetermined angular, overall structure is simple, and operation is very easy.
Description of the drawings
Fig. 1 is the schematic cross-sectional view of separate type experimental facilities of the present invention；
Fig. 2 is the main cross section structure diagram of the present invention for shooting cabin；
Fig. 3 is the side schematic cross-sectional view of the present invention for shooting cabin；
Fig. 4 is the main cross section structure diagram of separation of the projectile seat device of the present invention；
Fig. 5 is the side structure schematic view of separation of the projectile seat device of the present invention；
In figure：1- air inlet pipe I, 2- air inlet pipe II, 3- air inlet pipe III, 4- double-head pistons, 5- shoot cabin, 6- missile-bornes heating dress
It sets, 7- samples, 8- gun tubes, 9- separation of the projectile seat devices, 10- separation of the projectile seat device mounting brackets, 11- target bodys, 12- target body mounting brackets,
13- target chambers, 14- bearings, 15- main air chamber, 16- sealing rings I, 17- accessory air-spaces II, 18- accessory air-spaces I, 19- gas outlets, 20- are shot
Hatchcover, 21- shoot nacelle, 22- sealing rings II, 26- cylinders, 27- separation muscle, 28- bottom plates.
Specific implementation mode
The invention will be further described below in conjunction with the accompanying drawings：
In conjunction with shown in Fig. 1 to Fig. 5, the present invention includes from rear to the preceding air bubble installed successively, separation of the projectile seat device 9 and target body
11；
Air bubble include from front to back sequentially connected gun tube 8, shoot cabin 5, main air chamber 15 and accessory air-space, gun tube 8 is shot
Cabin 5, main air chamber 15 and accessory air-space are located in same extended axis of the horse；
Double-head piston 4 is installed, double-head piston 4 is arranged along the longitudinal direction, secondary piston between main air chamber 15 and accessory air-space
In the main air chamber 15 and as the valve for shooting 5 rear port of cabin, piston is located in accessory air-space thereafter；
Accessory air-space is divided into accessory air-space I 18 and the accessory air-space II in front of accessory air-space I 18 by the rear piston of double-head piston 4
17, the piston rod of double-head piston 4 passes through the front side wall of accessory air-space II 17, the piston rod of double-head piston 4 with before accessory air-space II 17
Sealing is formed between side wall；
Accessory air-space I 18 is provided with air inlet pipe I 1 and gas outlet 19, and accessory air-space II 17 and main air chamber 15 are respectively arranged with air inlet
Pipe II 2 and air inlet pipe III 3；
It shooting and is provided with missile-borne heating device 6 in cabin 5, missile-borne heating device 6 is the cylindrical structure of lateral arrangement, in
Portion is provided with the heating cabinet for placing sample, front openings of the heating cabinet and towards gun tube 8；
It shoots and is provided in cabin 5 for loading and the missile-borne heating device 6 of heating sample 7, missile-borne heating device 6 is along preceding
Rear direction arranges cylinder-like structure, its rear end closing and front end setting sample outlet；
The centrally disposed through-hole being useful for through sample of separation of the projectile seat device 9, the through-hole and missile-borne heating device 6 and gun tube
8 are located in same extended axis of the horse, and aperture is less than the outer diameter of missile-borne heating device 6；
Target body 11, target body 11 are tilted towards separation of the projectile seat device 9, and the front projection of the central through hole of separation of the projectile seat device 9
On target body 11.
As this patent selection a kind of technical solution, gun tube 8, shoot cabin 5, main air chamber 15 is supported by bearing 14,
In experiment, bearing 14 is supported on ground.
As a kind of technical solution of this patent selection, the secondary piston of double-head piston 4 is towards the taper knot for shooting cabin 5
Structure, maximum gauge are more than the rear port bore for shooting cabin 5.
As a kind of technical solution of this patent selection, the piston rod of double-head piston 4 and the front side wall of accessory air-space II 17 it
Between pass through sealing ring I 16 seal.
As a kind of technical solution of this patent selection, it includes shooting nacelle 21, shooting hatchcover 20 to shoot cabin 5, shoots cabin
It is communicated before and after body 21, and front port is connected to gun tube 8, rear port is connected to main air chamber 15 and face double-head piston 4, shoots nacelle
21 open top is simultaneously equipped with and shoots hatchcover 20, shoots hatchcover 20 and shoots and is sealed by sealing ring II 22 between nacelle 21.
As a kind of technical solution of this patent selection, having heaters is set in missile-borne heating device 6, and outer layer covers have
Heat insulation layer, heater are used to heat sample, and the heat that heat insulation layer is used to reduce between external other structures is transmitted.
As its name suggests, missile-borne heating device 6 is used to load sample and heat sample, and can be with other structures in this patent
Match, realizes the separation of sample 7 and missile-borne heating device 6, and this structure presented herein.
As a kind of technical solution of this patent selection, target body 11 and separation of the projectile seat device 9 are mounted in a target chamber 13,
Gun tube 8 leads to target chamber 13, and target body 11 is fixed by target body mounting bracket 12, and separation of the projectile seat device 9 is installed by 24 separator of bullet support
Holder 10 is fixed, and target body mounting bracket 12 and 24 separator mounting bracket 10 of bullet support are fixed by foundation bolt and be supported on target
On the ground of room 13.For the ease of observing impact events, target chamber 13 is equipped with the observation window that bulletproof glass makes.
As this patent selection a kind of technical solution, separation of the projectile seat device 9 include cylinder 26, be connected to cylinder 26 before
The bottom plate 28 at end at the same with 26 outer wall of cylinder and bottom plate 28 weld it is several detach muscle 27, the rear and front end of cylinder 26 is opened
Mouthful, the front port of cylinder 26 leads to target body 11 and rear port leads to gun tube 8.The effect of separation of the projectile seat device 9 is by sample and bullet
It carries heating device 6 to detach, sample is made to hit target body 11 with free state；The effects that playing blocking air-flow, dust, fragment simultaneously,
Avoid influence sample touches target state and its test.
Working principle of the present invention is as follows：
Fig. 1 given expression to sample be in heating or it is to be launched when, the relative position relation figure of each parts；
In implementation process, need first to test the control time for obtaining sample emissions, it is specific as follows：
A sample 7 is selected, is installed in missile-borne heating device 6, is then placed into and shoots in cabin 5, missile-borne heating is connected
The power supply of device 6 connects its heater power source, heated to sample 7, and makes temperature T0Target temperature is touched higher than requirement of experiment
Spend T1, then power off, 7 surface temperature of test sample is by T0It is down to T1Required time Δ t, finally powers off, waits for missile-borne heating device
The missile-borne heating device 6 containing sample 7 is taken out after 6 coolings, with the transmitting of time Δ t Control Assay 7.
After getting time Δ t, start to test, target body 11 and bullet are completed according to structure shown in Fig. 1 according to experiment condition
Hold in the palm the installation of separator 9.Then sample 7 is seated in missile-borne heating device 6.Then by the missile-borne heating device 6 containing sample 7
Loading is shot in cabin 5, is powered on and is heated to sample 7, makes the surface temperature T of sample 70.During heating sample 7, profit
It is inflated to pressure P1 to accessory air-space I 18 with air inlet pipe I 1, pushes double-head piston 4, the head by double-head piston 4 and sealing ring I
16 sealing main air chamber 15, then give the inflation of main air chamber 15 until preset air pressure P3.When sample 7 is completed to heat, air inlet pipe I is utilized
1 and air inlet pipe II 2 the air pressure P2 of setting is inflated to accessory air-space II 17.After the power supply for cutting off missile-borne heating device 6, to shooting cabin
5 shoot hatchcover 20, using shoot hatchcover 20 and sealing ring II 22 sealing shoot cabin 5.Finally, the discouraged drop of gas outlet 19 is opened
The air pressure of low accessory air-space I 18 so that moved after double-head piston 4, release the sealing of main air chamber 15, the high pressure gas of main air chamber 15 is immediately
It rapidly enters and shoots cabin 5, driving missile-borne device is in 8 medium-high speed sports of gun tube.When missile-borne heating device 6 and separation of the projectile seat device 9 connect
When touching, missile-borne heater is detached from sample 7, and sample 7 bumps against by free flight and with target body 11.
The above is merely preferred embodiments of the present invention, be not intended to limit the invention, it is all the present invention spirit and
All any modification, equivalent and improvement made by within principle etc., should be included within the scope of the present invention.
Claims (8)
1. a kind of separate type experimental facilities for research structure high temperature and high speed impact response, it is characterised in that：Including from it is rear to
The preceding air bubble installed successively, separation of the projectile seat device and target body；
The air bubble include from front to back sequentially connected gun tube, shoot cabin, main air chamber and accessory air-space, it is the gun tube, described
Cabin, the main air chamber and the accessory air-space is shot to be located in same extended axis of the horse；
Double-head piston is installed between the main air chamber and the accessory air-space, the double-head piston is arranged along the longitudinal direction, before
Piston is located in the main air chamber and as the valve for shooting cabin rear port, and piston is located in the accessory air-space thereafter；
The accessory air-space is divided into accessory air-space I and the accessory air-space II in front of accessory air-space I by the rear piston of the double-head piston,
The piston rod of the double-head piston passes through the front side wall of the accessory air-space II, the piston rod of the double-head piston and the accessory air-space
Sealing is formed between II front side wall；
The accessory air-space I is provided with air inlet pipe I and gas outlet, and the accessory air-space II and the main air chamber are respectively arranged with air inlet pipe
II and air inlet pipe III；
Described shoot is provided in cabin for loading and the missile-borne heating device of heating sample, and missile-borne heating device is along front and back
To arrangement cylinder-like structure, its rear end closing and front end setting sample outlet；
The centrally disposed through-hole being useful for through sample of the separation of the projectile seat device, the through-hole and the missile-borne heating device and institute
It states gun tube to be located in same extended axis of the horse, aperture is less than the outer diameter of the missile-borne heating device；
The target body is tilted towards the separation of the projectile seat device, and the front projection of the central through hole of the separation of the projectile seat device is located at
On the target body.
2. being used for the separate type experimental facilities of research structure high temperature and high speed impact response according to claim 1, feature exists
In：The gun tube, it is described shoot cabin, the main air chamber passes through seat supports.
3. being used for the separate type experimental facilities of research structure high temperature and high speed impact response according to claim 1, feature exists
In：The secondary piston of the double-head piston is the pyramidal structure that cabin is shot described in, and maximum gauge shoots cabin more than described
Rear port bore.
4. being used for the separate type experimental facilities of research structure high temperature and high speed impact response according to claim 1, feature exists
In：It is sealed by sealing ring I between the piston rod of the double-head piston and the front side wall of the accessory air-space II.
5. being used for the separate type experimental facilities of research structure high temperature and high speed impact response according to claim 1, feature exists
In：The cabin that shoots includes shooting nacelle, shooting hatchcover, and described shoot communicates before and after nacelle, and front port connects with the gun tube
Logical, rear port is connected to double-head piston described in simultaneously face with the main air chamber, and the open top for shooting nacelle is simultaneously installed
It states and shoots hatchcover, it is described to shoot hatchcover and described shoot is sealed by sealing ring II between nacelle.
6. being used for the separate type experimental facilities of research structure high temperature and high speed impact response according to claim 1, feature exists
In：Having heaters is set in the missile-borne heating device, and outer layer covers have heat insulation layer.
7. being used for the separate type experimental facilities of research structure high temperature and high speed impact response according to claim 1, feature exists
In：The target body and the separation of the projectile seat device are mounted in a target chamber, and the gun tube leads to the target chamber, and the target body is logical
It crosses target body mounting bracket to fix, the separation of the projectile seat device is fixed by separation of the projectile seat device mounting bracket.
8. according to claim 1 or the 7 separate type experimental facilities for being used for research structure high temperature and high speed impact response, feature
It is：The separation of the projectile seat device includes cylinder, is connected to the bottom plate of the cylinder front end while detaching drum outer wall with described
With several separation muscle of bottom plate welding, the rear and front end opening of the cylinder, the front port of the cylinder leads to institute
It states target body and rear port leads to the gun tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810219362.8A CN108344552B (en) | 2018-03-16 | 2018-03-16 | Separated experimental equipment for researching high-temperature high-speed impact response of structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810219362.8A CN108344552B (en) | 2018-03-16 | 2018-03-16 | Separated experimental equipment for researching high-temperature high-speed impact response of structure |
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| CN108344552B CN108344552B (en) | 2023-12-29 |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109855486A (en) * | 2019-01-25 | 2019-06-07 | 中国工程物理研究院总体工程研究所 | Quickly filling air bubble |
| CN109959569A (en) * | 2019-02-14 | 2019-07-02 | 中国工程物理研究院总体工程研究所 | Missile-borne heating device for research structure high temperature and high speed impact response |
| CN110440829A (en) * | 2019-08-19 | 2019-11-12 | 哈尔滨工业大学 | A kind of inertia device high overload test device and method |
| CN111572820A (en) * | 2020-03-31 | 2020-08-25 | 上海卫星工程研究所 | Hierarchical low-power-consumption thermal control method for deep space high-speed impactor |
| CN112923788A (en) * | 2021-03-04 | 2021-06-08 | 中国兵器装备集团兵器装备研究所 | Bullet holder and bullet head separating device |
| WO2021125926A1 (en) * | 2019-12-16 | 2021-06-24 | Unversité Internationale D'agadir - Universiapolis | Device for adjusting the temperature of projectiles for dynamic impact testing |
| CN113959832A (en) * | 2021-07-20 | 2022-01-21 | 哈尔滨工业大学 | Rotating shaft type variable-angle loading clamp based on light gas gun and mounting method thereof |
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