CN108344552B - Separated experimental equipment for researching high-temperature high-speed impact response of structure - Google Patents
Separated experimental equipment for researching high-temperature high-speed impact response of structure Download PDFInfo
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- CN108344552B CN108344552B CN201810219362.8A CN201810219362A CN108344552B CN 108344552 B CN108344552 B CN 108344552B CN 201810219362 A CN201810219362 A CN 201810219362A CN 108344552 B CN108344552 B CN 108344552B
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- 230000004044 response Effects 0.000 title claims abstract description 17
- 238000012360 testing method Methods 0.000 claims abstract description 13
- 238000000926 separation method Methods 0.000 claims abstract description 12
- 238000002474 experimental method Methods 0.000 claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims description 49
- 238000007789 sealing Methods 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 9
- 238000004321 preservation Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 238000009413 insulation Methods 0.000 claims description 2
- 238000009863 impact test Methods 0.000 abstract description 7
- 230000002159 abnormal effect Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000011160 research Methods 0.000 description 3
- 238000012356 Product development Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 239000000428 dust Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000012634 fragment Substances 0.000 description 2
- 230000036544 posture Effects 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000009434 installation Methods 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
- 239000002915 spent fuel radioactive waste Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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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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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
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Abstract
The invention discloses separation type experimental equipment for researching high-temperature high-speed impact response of a structure, which belongs to the field of high-temperature high-speed impact dynamics of the structure and comprises an air cannon, a bullet holder separator and a target body which are sequentially arranged from back to front, wherein the air cannon comprises a cannon barrel, a loading cabin, a main air chamber and an auxiliary air chamber which are sequentially connected from front to back, and the cannon barrel, the loading cabin, the main air chamber and the auxiliary air chamber are positioned on the same central axis extension line. The device is a set of simple multipurpose high-speed high-temperature impact test device, can ensure that the impact target posture and the test temperature of a sample are adjustable, controllable and measurable, ensure the stability of the test, can ensure that an experiment object impacts the target body according to a preset angle under the given temperature and speed conditions, and has simple overall structure and very convenient operation.
Description
Technical Field
The invention belongs to the field of high-temperature high-speed impact dynamics of structures, and particularly relates to separation type experimental equipment for researching high-temperature high-speed impact response of the structures.
Background
With the progress of the age and the development of scientific technology, the safety of products, particularly under abnormal accidents, is increasingly concerned, and is one of the indispensable technical indexes in the product development process. Safety in abnormal accidents refers to the ability of a product to prevent explosion and leakage of harmful substances due to abnormal high-speed collision or/and burning. Radioisotope heat/power source such as deep space detection can be subjected to high-temperature and high-speed impact during accidental re-use, so that the outer shell of the radioisotope heat/power source is broken to leak reflective materials, and disasters are brought to ecology or mankind; the falling/burning of the spent fuel packing box of the nuclear power station can also induce serious safety accidents and the like. A great deal of research is being conducted at home and abroad. However, in the research of safety under the abnormal accident of the existing product, the safety of the structure under the high-speed impact and the high-temperature action is usually researched respectively, but the high-speed impact and the high-temperature action in the abnormal accident often happen simultaneously, so that the safety under the simultaneous action of the high-temperature high-speed impact of the product is very important.
The united states uses an Isotope energy impact tester (isope Fuels ImpactTester, IFIT) to achieve high temperature high speed impact testing of a single heat source of a light weight Isotope heat source (LWRHU) and a general purpose heat source Isotope battery (GPHS-RTG). In order to prevent leakage of harmful substances, the structural design of the IFIT is extremely complex and is mainly divided into five parts: the air cannon, the bullet, the excitation device, the collision chamber and the energy absorbing device are composed of a plurality of small parts. For the whole GPHS-RTG, a rocket sled acceleration method is adopted to realize a high-temperature high-speed impact test, the specific method is that firstly, the GPHS-RTG is heated to a set temperature (> 1000 ℃) by an electric furnace, then the GPHS-RTG is installed on a rocket sled through remote control, after the rocket sled is accelerated to the set speed, the GPHS-RTG is separated from the rocket sled by a blocking mechanism, and finally the GPHS-RTG and a target body collide freely; or the target body is accelerated to a set speed by a rocket sled by adopting an inverse trajectory method, and then the target body is impacted to the GPHS-RTG which is fixedly installed. The Chinese atomic energy science institute invents a device for high-temperature high-speed impact test (CN 203849118U). The device is a material performance detection device based on compressed air loading, can simulate the impact process of an isotope heat source with the ground under an imaginary accident environment more accurately, and can simulate the temperature more accurately by designing a heat-preserving bullet holder.
Although the IFIT, rocket sled and Chinese atomic energy institute device in the United states can realize high-speed high-temperature impact test of isotope heat/power, the device has the defects of complex structure, difficult operation, inconvenient test, poor expansibility and the like. The specific details of the test technology in the united states are not disclosed and are difficult to apply and popularize in engineering practice. The device developed by the Chinese atomic energy science institute is mainly used for researching the high-temperature high-speed impact mechanical property of materials, and is difficult to expand the high-temperature high-speed impact response of a research structure, in particular to the dynamic response under different postures; meanwhile, the thermal insulation bullet support and the simulated heat source cannot be completely separated, and fragments, dust and the like generated by separation of the bullet support are easy to influence the control of the target collision gesture of the test piece and the test of impact response. Therefore, developing a set of simple multipurpose high-performance high-speed high-temperature impact test device has become a urgent problem to be solved in engineering product development.
Disclosure of Invention
The invention aims to solve the problems and provide a separation type experimental device for researching high-temperature high-speed impact response of a structure.
The invention realizes the above purpose through the following technical scheme:
a separation type experimental device for researching high-temperature high-speed impact response of a structure comprises an air cannon, a bullet holder separator and a target body which are sequentially arranged from back to front;
the air cannon comprises a gun barrel, a loading cabin, a main air chamber and an auxiliary air chamber which are sequentially connected from front to back, wherein the gun barrel, the loading cabin, the main air chamber and the auxiliary air chamber are positioned on the same central axis extension line;
a double-headed piston is arranged between the main air chamber and the auxiliary air chamber, the double-headed piston is arranged along the front-back direction, the front piston of the double-headed piston is positioned in the main air chamber and serves as a valve of a rear port of the loading cabin, and the rear piston of the double-headed piston is positioned in the auxiliary air chamber;
the auxiliary air chamber is divided into an auxiliary air chamber I and an auxiliary air chamber II positioned in front of the auxiliary air chamber I through a rear piston of the double-headed piston, a piston rod of the double-headed piston penetrates through the front side wall of the auxiliary air chamber II, and sealing is formed between the piston rod of the double-headed piston and the front side wall of the auxiliary air chamber II;
the auxiliary air chamber I is provided with an air inlet pipe I and an air leakage pipe, and the auxiliary air chamber II and the main air chamber are respectively provided with an air inlet pipe II and an air inlet pipe III;
the loading cabin is internally provided with a missile-borne heating device for loading and heating samples, the missile-borne heating device is of a cylindrical structure which is arranged along the front-back direction, the rear end of the missile-borne heating device is closed, and the front end of the missile-borne heating device is provided with a sample outlet;
the center of the bullet support separator is provided with a through hole for passing through a sample, the through hole, the bullet heating device and the gun barrel are positioned on the same central axis extension line, and the aperture of the through hole is smaller than the outer diameter of the bullet heating device;
the target body is inclined towards the bullet support separator, and the projection in front of the center through hole of the bullet support separator is positioned on the target body.
As a technical scheme selected by the patent, the gun barrel, the loading cabin and the main air chamber are all supported by a support.
As a technical scheme of this patent selection, the front piston of double-end piston is towards the toper structure of loading cabin, its maximum diameter is greater than the back port bore of loading cabin.
As a technical scheme of this patent choice, the piston rod of double-end piston with seal through sealing washer I between the preceding lateral wall of vice air chamber II.
As a technical scheme of this patent selection, the loading cabin includes the loading cabin body, loading cabin cover, the loading cabin body communicates with each other around, and the front port with the barrel communicates, the back port with main air chamber intercommunication just is to the double-end piston, the open-top of the loading cabin body is installed the loading cabin cover, the loading cabin cover with seal through sealing washer II between the loading cabin body.
As a technical scheme of this patent choice, be provided with the heater in the missile-borne heating device, and the skin parcel has the heat preservation insulating layer.
As a technical scheme of this patent choice, the target body with the bullet holds in palm the separator and all installs in a target chamber, the barrel accesss to the target chamber, the target body is fixed through the target body installing support, the bullet holds in the palm the separator and is fixed through bullet holds in the palm the separator installing support.
As a technical scheme of this patent choice, bullet holds in palm the separator including the separating drum, connect the bottom plate of separating drum front end, simultaneously with the separating drum outer wall with a plurality of separating ribs of bottom plate welded, both ends opening around the separating drum, the front port of separating drum is led to the target body and back port is led to the barrel.
The invention has the beneficial effects that:
the device is a set of simple multipurpose high-speed high-temperature impact test device, can ensure that the impact target posture and the test temperature of a sample are adjustable, controllable and measurable, ensure the stability of the test, can ensure that an experiment object impacts the target body according to a preset angle under the given temperature and speed conditions, and has simple overall structure and very convenient operation.
Drawings
FIG. 1 is a schematic cross-sectional view of a separation type experimental apparatus according to the present invention;
FIG. 2 is a schematic view of the main sectional structure of the loading bay of the present invention;
FIG. 3 is a schematic side cross-sectional view of a loading bay according to the present invention;
FIG. 4 is a schematic view of the principal cross-sectional structure of the tray separator of the present invention;
FIG. 5 is a schematic side view of a tray splitter according to the present invention;
in the figure: 1-air inlet pipe I, 2-air inlet pipe II, 3-air inlet pipe III, 4-double-headed piston, 5-loading cabin, 6-missile-borne heating device, 7-sample, 8-gun barrel, 9-missile-borne separator, 10-missile-borne separator mounting bracket, 11-target body, 12-target body mounting bracket, 13-target chamber, 14-support, 15-main air chamber, 16-sealing ring I, 17-auxiliary air chamber II, 18-auxiliary air chamber I, 19-air release pipe, 20-loading cabin cover, 21-loading cabin body, 22-sealing ring II, 26-separating cylinder, 27-separating rib and 28-bottom plate.
Detailed Description
The invention is further described below with reference to the accompanying drawings:
referring to fig. 1 to 5, the present invention includes an air cannon, a sabot separator 9 and a target 11, which are installed in sequence from the rear to the front;
the air cannon comprises a gun barrel 8, a loading cabin 5, a main air chamber 15 and an auxiliary air chamber which are sequentially connected from front to back, wherein the gun barrel 8, the loading cabin 5, the main air chamber 15 and the auxiliary air chamber are positioned on the same central axis extension line;
a double-headed piston 4 is arranged between the main air chamber 15 and the auxiliary air chamber, the double-headed piston 4 is arranged along the front-back direction, the front piston of the double-headed piston is positioned in the main air chamber 15 and is used as a valve of the rear port of the loading cabin 5, and the rear piston of the double-headed piston is positioned in the auxiliary air chamber;
the auxiliary air chamber is divided into an auxiliary air chamber I18 and an auxiliary air chamber II 17 positioned in front of the auxiliary air chamber I18 through a rear piston of the double-headed piston 4, a piston rod of the double-headed piston 4 penetrates through the front side wall of the auxiliary air chamber II 17, and sealing is formed between the piston rod of the double-headed piston 4 and the front side wall of the auxiliary air chamber II 17;
the auxiliary air chamber I18 is provided with an air inlet pipe I1 and an air release pipe 19, and the auxiliary air chamber II 17 and the main air chamber 15 are respectively provided with an air inlet pipe II 2 and an air inlet pipe III 3;
a missile-borne heating device 6 is arranged in the loading cabin 5, the missile-borne heating device 6 is of a cylindrical structure which is transversely arranged, a heating bin for placing a sample is arranged in the missile-borne heating device 6, and the front side of the heating bin is open and faces to a gun barrel 8;
a missile-borne heating device 6 for loading and heating a sample 7 is arranged in the loading cabin 5, the missile-borne heating device 6 is of a cylindrical structure which is arranged along the front-back direction, the rear end of the missile-borne heating device is closed, and a sample outlet is arranged at the front end of the missile-borne heating device;
the center of the bullet support separator 9 is provided with a through hole for passing through the sample, the through hole, the bullet heating device 6 and the gun barrel 8 are positioned on the same central axis extension line, and the aperture of the through hole is smaller than the outer diameter of the bullet heating device 6;
the target 11, the target 11 inclines towards the bullet support separator 9, and the projection in front of the center through hole of bullet support separator 9 is located on target 11.
As an alternative to this patent, the gun barrel 8, loading bay 5 and main air chamber 15 are all supported by a support 14, the support 14 being supported on the ground during the experiment.
As an alternative to this patent, the front piston of the double-headed piston 4 has a conical structure facing the loading bay 5, and its maximum diameter is larger than the rear port caliber of the loading bay 5.
As a technical scheme selected by the patent, the piston rod of the double-headed piston 4 is sealed with the front side wall of the auxiliary air chamber II 17 through a sealing ring I16.
As a technical scheme selected by the patent, the loading cabin 5 comprises a loading cabin body 21 and a loading cabin cover 20, wherein the loading cabin body 21 is communicated with the front and the rear, the front port is communicated with the gun barrel 8, the rear port is communicated with the main air chamber 15 and is opposite to the double-headed piston 4, the top of the loading cabin body 21 is opened and is provided with the loading cabin cover 20, and the loading cabin cover 20 and the loading cabin body 21 are sealed through a sealing ring II 22.
As a technical scheme of this patent selection, be provided with the heater in the missile-borne heating device 6, and the skin parcel has the heat preservation insulating layer, and the heater is used for heating the sample, and the heat preservation insulating layer is used for reducing with outside other heat transfer between the structure. As the name suggests, the missile-borne heating device 6 is used for loading and heating the sample, and can be matched with other structures in the patent, so that the sample 7 and the missile-borne heating device 6 can be separated, and the structure is proposed herein.
As a technical scheme selected by the patent, the target 11 and the bullet support separator 9 are both arranged in a target chamber 13, the gun barrel 8 is led to the target chamber 13, the target 11 is fixed through the target mounting bracket 12, the bullet support separator 9 is fixed through the bullet support 24 separator mounting bracket 10, and the target mounting bracket 12 and the bullet support 24 separator mounting bracket 10 are both fixed through foundation bolts and supported on the foundation of the target chamber 13. In order to facilitate the observation of the impact situation, the target chamber 13 is provided with an observation window made of bullet-proof glass.
As an alternative to this patent, the bullet holder separator 9 includes a separating cylinder 26, a bottom plate 28 connected to the front end of the separating cylinder 26, and a plurality of separating ribs 27 welded to the outer wall of the separating cylinder 26 and the bottom plate 28, the separating cylinder 26 is open at the front and rear ends, the front port of the separating cylinder 26 opens into the target 11, and the rear port opens into the gun barrel 8. The action of the bullet holder separator 9 is to separate the sample from the bullet-loaded heating device 6 so that the sample can strike the target 11 in a free state; meanwhile, the device plays roles in blocking air flow, dust, fragments and the like, and avoids influencing the target collision state and testing of the sample.
The working principle of the invention is as follows:
FIG. 1 shows a diagram of the relative position of the components of a sample when it is heated or to be emitted;
in the implementation process, the control time of sample emission needs to be obtained by testing firstly, and the method is concretely as follows:
a sample 7 is selected and arranged in the missile-borne heating device 6, then the sample is arranged in the missile-borne chamber 5, the power supply of the missile-borne heating device 6, namely the power supply of a heater thereof is switched on, the sample 7 is heated, and the temperature T is kept 0 The target collision temperature T is higher than the experiment requirement 1 Then power is cut off, the surface temperature of the test sample 7 is changed from T 0 Down to T 1 And finally, cutting off the power for the required time delta t, taking out the missile-borne heating device 6 containing the sample 7 after the missile-borne heating device 6 is cooled, and controlling the emission of the sample 7 by the time delta t.
After the time Δt is obtained, an experiment is started, and the installation of the target 11 and the sabot separator 9 is completed according to the experimental conditions in accordance with the structure shown in fig. 1. The sample 7 is then placed in the missile-borne heating device 6. Then, the missile-borne heating device 6 containing the sample 7 is placed in the loading chamber 5, and the sample 7 is heated by switching on the power supply to make the surface temperature T of the sample 7 0 . During the heating of the sample 7, the auxiliary air chamber i 18 is inflated to a pressure P1 by the air intake pipe i 1, the double-headed piston 4 is pushed, the main air chamber 15 is sealed by the head of the double-headed piston 4 and the seal ring i 16, and then the main air chamber 15 is inflated up to a predetermined air pressure P3. When the sample 7 is heated, the auxiliary air chamber ii 17 is inflated to the set air pressure P2 by the air intake pipe i 1 and the air intake pipe ii 2. Cutting off the power supply to the missile-borne heating device 6Then, the loading bay 5 is provided with a loading bay cover 20, and the loading bay 5 is sealed by the loading bay cover 20 and a sealing ring II 22. Finally, the air release pipe 19 is opened to release air and reduce the air pressure of the auxiliary air chamber I18, so that the double-headed piston 4 moves backwards, the sealing of the main air chamber 15 is released, and the high-pressure air of the main air chamber 15 immediately enters the loading cabin 5 to drive the missile-borne device to move in the gun barrel 8 at a high speed. When the missile-borne heating device 6 is in contact with the missile-borne separator 9, the missile-borne heater is disengaged from the sample 7, and the sample 7 is free to fly and collide with the target 11.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (8)
1. A disconnect-type experimental facilities for studying high temperature high-speed striking response of structure, its characterized in that: comprises an air cannon, a bullet holder separator and a target body which are sequentially arranged from back to front;
the air cannon comprises a gun barrel, a loading cabin, a main air chamber and an auxiliary air chamber which are sequentially connected from front to back, wherein the gun barrel, the loading cabin, the main air chamber and the auxiliary air chamber are positioned on the same central axis extension line;
a double-headed piston is arranged between the main air chamber and the auxiliary air chamber, the double-headed piston is arranged along the front-back direction, the front piston of the double-headed piston is positioned in the main air chamber and serves as a valve of a rear port of the loading cabin, and the rear piston of the double-headed piston is positioned in the auxiliary air chamber;
the auxiliary air chamber is divided into an auxiliary air chamber I and an auxiliary air chamber II positioned in front of the auxiliary air chamber I through a rear piston of the double-headed piston, a piston rod of the double-headed piston penetrates through the front side wall of the auxiliary air chamber II, and sealing is formed between the piston rod of the double-headed piston and the front side wall of the auxiliary air chamber II;
the auxiliary air chamber I is provided with an air inlet pipe I and an air leakage pipe, and the auxiliary air chamber II and the main air chamber are respectively provided with an air inlet pipe II and an air inlet pipe III;
the loading cabin is internally provided with a missile-borne heating device for loading and heating samples, the missile-borne heating device is of a cylindrical structure which is arranged along the front-back direction, the rear end of the missile-borne heating device is closed, and the front end of the missile-borne heating device is provided with a sample outlet;
the center of the bullet support separator is provided with a through hole for passing through a sample, the through hole, the bullet heating device and the gun barrel are positioned on the same central axis extension line, and the aperture of the through hole is smaller than the outer diameter of the bullet heating device;
the target body is inclined towards the bullet support separator, and the projection right in front of the central through hole of the bullet support separator is positioned on the target body;
in the implementation process, the control time of sample emission needs to be obtained by testing firstly, and the method is concretely as follows:
selecting a sample, installing in a missile-borne heating device, placing in a loading cabin, switching on the power supply of the missile-borne heating device, namely switching on the power supply of a heater thereof, heating the sample, and enabling the temperature T to be equal to 0 The target collision temperature T is higher than the experiment requirement 1 Then power is cut off, the surface temperature of the test sample is changed from T 0 Down to T 1 And finally, cutting off the power for the required time delta t, taking out the missile-borne heating device containing the sample after the missile-borne heating device is cooled, and controlling the emission of the sample by the time delta t.
2. The separation type experimental facility for studying structural high temperature and high speed impact response according to claim 1, wherein: the gun barrel, the loading cabin and the main air chamber are all supported by the support.
3. The separation type experimental facility for studying structural high temperature and high speed impact response according to claim 1, wherein: the front piston of the double-headed piston is of a conical structure facing the loading cabin, and the maximum diameter of the front piston is larger than the caliber of the rear port of the loading cabin.
4. The separation type experimental facility for studying structural high temperature and high speed impact response according to claim 1, wherein: the piston rod of the double-headed piston is sealed with the front side wall of the auxiliary air chamber II through a sealing ring I.
5. The separation type experimental facility for studying structural high temperature and high speed impact response according to claim 1, wherein: the loading cabin comprises a loading cabin body and a loading cabin cover, the loading cabin body is communicated with each other in the front-back direction, a front port is communicated with the gun barrel, a rear port is communicated with the main air chamber and is opposite to the double-headed piston, the top opening of the loading cabin body is provided with the loading cabin cover, and the loading cabin cover and the loading cabin body are sealed through a sealing ring II.
6. The separation type experimental facility for studying structural high temperature and high speed impact response according to claim 1, wherein: the missile-borne heating device is internally provided with a heater, and the outer layer is wrapped with a heat preservation and insulation layer.
7. The separation type experimental facility for studying structural high temperature and high speed impact response according to claim 1, wherein: the target body and the bullet support separator are both installed in a target chamber, the gun barrel leads to the target chamber, the target body is fixed through the target body installing support, and the bullet support separator is fixed through the bullet support separator installing support.
8. The split-type experimental apparatus for studying the high-temperature high-speed impact response of a structure according to claim 1 or 7, wherein: the bullet holds in palm the separator including the separating drum, connect the bottom plate of separating drum front end, simultaneously with the separating drum outer wall with a plurality of separating ribs of bottom plate welded, both ends opening around the separating drum, the front port of separating drum is led to the target body and back port is led to the barrel.
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| Application Number | Priority Date | Filing Date | Title |
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| 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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| 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 true CN108344552B (en) | 2023-12-29 |
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| CN109855486B (en) * | 2019-01-25 | 2023-09-26 | 中国工程物理研究院总体工程研究所 | Quick filling air cannon |
| CN109959569B (en) * | 2019-02-14 | 2023-10-24 | 中国工程物理研究院总体工程研究所 | Missile-borne heating device for researching high-temperature high-speed impact response of structure |
| CN110440829B (en) * | 2019-08-19 | 2021-11-16 | 哈尔滨工业大学 | High-overload testing device and method for inertial device |
| MA47662B1 (en) * | 2019-12-16 | 2021-12-31 | Univ Internationale Dagadir Univ | Device for regulating the temperature of projectiles intended for dynamic impact tests |
| CN111238921A (en) * | 2020-03-06 | 2020-06-05 | 中国工程物理研究院总体工程研究所 | Integrated high-temperature air cannon for researching high-temperature and high-speed impact response of structure |
| CN111572820B (en) * | 2020-03-31 | 2021-07-30 | 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 |
| CN113959832B (en) * | 2021-07-20 | 2023-11-03 | 哈尔滨工业大学 | Rotary shaft type variable angle loading clamp based on light air cannon and mounting method thereof |
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