CN109211512B - Fire impact environment simulation device - Google Patents
Fire impact environment simulation device Download PDFInfo
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- CN109211512B CN109211512B CN201811020328.4A CN201811020328A CN109211512B CN 109211512 B CN109211512 B CN 109211512B CN 201811020328 A CN201811020328 A CN 201811020328A CN 109211512 B CN109211512 B CN 109211512B
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- sliding grooves
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- plate sliding
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- 238000004088 simulation Methods 0.000 title claims abstract description 29
- 239000002360 explosive Substances 0.000 claims abstract description 46
- 239000002131 composite material Substances 0.000 claims description 6
- 229910001209 Low-carbon steel Inorganic materials 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000000725 suspension Substances 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 239000000835 fiber Substances 0.000 claims 1
- 230000000977 initiatory effect Effects 0.000 abstract description 25
- 230000004044 response Effects 0.000 description 29
- 238000001228 spectrum Methods 0.000 description 16
- 230000035939 shock Effects 0.000 description 15
- 238000000034 method Methods 0.000 description 13
- 238000000926 separation method Methods 0.000 description 10
- 238000004880 explosion Methods 0.000 description 9
- 238000005474 detonation Methods 0.000 description 8
- 238000012360 testing method Methods 0.000 description 6
- 230000010355 oscillation Effects 0.000 description 5
- 230000001133 acceleration Effects 0.000 description 4
- 230000009471 action Effects 0.000 description 4
- 239000007789 gas Substances 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 230000005284 excitation Effects 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- TZRXHJWUDPFEEY-UHFFFAOYSA-N Pentaerythritol Tetranitrate Chemical compound [O-][N+](=O)OCC(CO[N+]([O-])=O)(CO[N+]([O-])=O)CO[N+]([O-])=O TZRXHJWUDPFEEY-UHFFFAOYSA-N 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- 238000009863 impact test Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000003595 spectral effect Effects 0.000 description 2
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 1
- 239000000026 Pentaerythritol tetranitrate Substances 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 229910010293 ceramic material Inorganic materials 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 229910052739 hydrogen Inorganic materials 0.000 description 1
- 239000001257 hydrogen Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229960004321 pentaerithrityl tetranitrate Drugs 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G99/00—Subject matter not provided for in other groups of this subclass
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
An initiating explosive device for simulating an impact environment relates to the technical field of initiating explosive device impact environment simulation of spacecrafts. The invention aims to solve the problem that the application range of the existing fire impact environment ground simulation device is limited. The invention is a double-plate loading structure, the outer cover of the explosive at the bottom of the loading plate is provided with a safety cover, and the bottom surface of the safety cover is provided with a pressure relief hole; four resonant board sliding grooves are formed in the resonant board and extend from the four corners of the resonant board to the center direction of the resonant board respectively; the four loading plate sliding grooves are respectively opposite to the four resonant plate sliding grooves up and down; the four connecting rods are in one-to-one correspondence with the four resonant plate sliding grooves respectively, one ends of the connecting rods are embedded in the resonant plate sliding grooves, the other ends of the connecting rods are embedded in the loading plate sliding grooves below the resonant plate sliding grooves, the connecting rods can support the loading plate and the resonant plate to keep a fixed distance, and can slide along the extending direction of the resonant plate sliding grooves and the loading plate sliding grooves.
Description
Technical Field
The invention belongs to the technical field of spacecraft fire impact environment simulation.
Background
In order to realize the connection-separation action in the aerospace engineering, the initiating explosive separation devices such as initiating explosive cutting cables, explosion bolts, initiating explosive separation nuts and the like are widely used on spacecrafts. When a separation instruction is received, the initiating explosive devices in the initiating explosive separation devices ignite detonation to generate detonation product gas, and the separation action is realized by doing work. Due to the strong impact action of the detonation of the initiating explosive device, strong shock waves can be generated near the initiating explosive device and transmitted to a far-field spacecraft structure, so that the shock response of the spacecraft structure is caused. This shock response is characterized by high frequencies, transients and high amplitudes, commonly referred to as the shock environment for the payload. Generally, the impact on the main structure of the spacecraft is small, but the damage on components sensitive to impact, such as shaking of a relay, cracking of ceramic materials, falling of brazing and the like, is often caused, so that the failure of the space mission is possibly caused. Therefore, many devices containing shock-sensitive components need to be subjected to ground shock environment simulation tests before being launched, so that the shock resistance of the devices can be checked.
The common initiating explosive impact environment ground simulation device mainly comprises a real initiating explosive device explosion excitation type device, a real mechanical impact type device and a real vibration table. The complex oscillation impact generated by real explosive device explosion can be reproduced by adopting real explosive device explosion excitation, but the application range is limited to a certain extent because the application of the explosive device impact has certain danger, and the influence rule of a large number of explosive device impact test exploration device parameters on the impact environment on the resonance plate can not be developed. Mechanical impact is the impact environment on the resonant device similar to the explosive impact of an initiating explosive device by impacting a resonant rod or a resonant plate with a hydrogen cannon or a drop hammer. The method is widely researched and used because of its simplicity, easy operation and good consistency. But the obvious disadvantage of the method is that the mechanical impact still has certain deficiency in simulating complex oscillation impact of explosion impact. In the process of testing by adopting the method, phenomena of 'over low frequency, under high frequency' and the like often occur, and the test design needs to be carried out under the condition of binding force limit. The method for simulating the vibrating table has the advantages of easiness in operation, controllable spectrum shape and the like, but the method also has technical bottleneck in high-frequency-band impact simulation and is generally only used for impact signals with the frequency lower than 5 KHz.
In conclusion, in the practical application process, the three methods are limited in use, and the purpose of the experiment cannot be better achieved.
Disclosure of Invention
The invention provides an initiating explosive device impact environment simulation device, aiming at solving the problem that the application range of the existing initiating explosive device impact environment ground simulation device is limited.
A fire impact environment simulation device is of a double-plate loading structure, an explosive 3 at the bottom of a loading plate 6 is covered by a safety cover 4, the bottom surface of the safety cover 4 is provided with a pressure relief hole 5,
the resonant plate 1 is provided with four resonant plate sliding grooves 11, the four resonant plate sliding grooves 11 respectively extend from four corners of the resonant plate 1 to the center of the resonant plate 1,
four loading plate sliding grooves 61 are arranged on the loading plate 6, the four loading plate sliding grooves 61 are respectively opposite to the four resonant plate sliding grooves 11 from top to bottom,
the four connecting rods 2 are respectively in one-to-one correspondence with the four resonant plate sliding grooves 11, one ends of the connecting rods 2 are embedded in the resonant plate sliding grooves 11, the other ends of the connecting rods 2 are embedded in the loading plate sliding grooves 61 below the resonant plate sliding grooves 11, and the connecting rods 2 can support the loading plate 6 and the resonant plate 1 to keep a fixed distance and can slide along the extending direction of the resonant plate sliding grooves 11 and the loading plate sliding grooves 61.
The four corners of the double-plate loading structure are respectively hung on the bracket through flexible hanging parts 7.
The fundamental frequency of the flexible cord of the flexible suspension element 7 should be less than 5 Hz.
The resonance plate 1 is a carbon fiber composite material paving plate.
The dimensions of the resonator plate 1 are 700mm × 700mm × 6 mm.
The loading plate 6 is made of low-carbon steel.
The size of the above-mentioned loading plate 6 is 1000 mm. times.1000 mm. times.10 mm.
The invention improves the traditional initiating explosive device impact environment simulation device and obtains a real initiating explosive device explosion double-plate type impact environment simulation device considering the safety. In the invention, the position of the connecting point of the loading plate and the resonance plate is adjustable. Different connecting point positions can influence the low-frequency slope of the impact response spectrum of the resonance plate, namely different impact environments are obtained through different connecting point positions, and the application range is expanded. The invention simulates the explosive impact environment of the initiating explosive device on the spacecraft through the complex oscillation type impact generated by the real detonation of the initiating explosive device on the resonance plate, and can quickly and accurately reproduce the given standard impact environment, thereby carrying out impact assessment on spacecraft equipment or components.
Drawings
FIG. 1 is a front sectional view of a pyrotechnic impact environment simulation apparatus;
FIG. 2 is a schematic view of a pyrotechnic impact environment simulation apparatus as viewed from a top perspective;
FIG. 3 is a schematic view of a pyrotechnic impact environment simulation apparatus as viewed from a low elevation;
FIG. 4 is a graph of real satellite-rocket separation impact time domain acceleration;
FIG. 5 is a time domain acceleration curve diagram of a measurement point of a fire impact environment simulation device;
FIG. 6 is a comparison graph of a real firer impact response spectrum and an impact response spectrum (SRS) of a measuring point on a resonance plate, wherein a curve A represents +6dB of a result of the measuring point of the device, a curve B represents a result of a separation impact of a real star and arrow, a curve C represents a result of the measuring point of the device, and a curve D represents-6 dB of the result of the measuring point of the device.
Detailed Description
The method for simulating the impact environment of the initiating explosive device by adopting real initiating explosive device explosion is the most reliable method in engineering, but the use of the method is limited to a certain extent due to certain dangerousness of the initiating explosive device in the use process. On the other hand, in order to realize the impact environmental condition during the fire impact test, the tester needs to perform adjustment of the device parameters with great time and effort. Based on the above two points, the present invention firstly improves the safety of the conventional fire impact environment simulation device from the safety point of view, specifically as described in the following embodiments.
The first embodiment is as follows: referring to fig. 1 to 6, this embodiment is specifically described, and the device in this embodiment is a double-plate loading structure, and the double-plate loading structure includes: the device comprises a resonance plate 1 and a loading plate 6, wherein the resonance plate 1 is positioned above the loading plate 6 and arranged in parallel, the resonance plate 1 and the loading plate 6 are connected with each other through four connecting rods 2, the four connecting rods 2 can support the loading plate 6 and the resonance plate 1 to keep a fixed distance, a fixed distance is reserved between the loading plate 6 and the resonance plate 1, and explosives 3 are arranged on the lower surface of the loading plate 6.
The outer cover of the explosive 3 at the bottom of the loading plate 6 is provided with a safety cover 4, so that the safety of testing personnel and equipment is fully protected. On the basis of ensuring the safety, the additionally arranged safety cover 4 is provided with pressure relief holes 5 at the bottom of the safety cover 4 to realize the functions of detonation gas emission, detonator wiring and the like in order not to influence the wiring of the detonation detonator and the explosive detonation gas emission.
Four resonant board sliding grooves 11 are formed in the resonant board 1, and the four resonant board sliding grooves 11 extend from the four corners of the resonant board 1 to the center of the resonant board 1 respectively; four loading plate sliding grooves 61 are formed in the loading plate 6, and the four loading plate sliding grooves 61 are respectively opposite to the four resonant plate sliding grooves 11 from top to bottom; the four connecting rods 2 are respectively in one-to-one correspondence with the four resonant plate sliding grooves 11, one ends of the connecting rods 2 are embedded in the resonant plate sliding grooves 11, and the other ends of the connecting rods 2 are embedded in the loading plate sliding grooves 61 below the resonant plate sliding grooves 11 and can slide along the extending directions of the resonant plate sliding grooves 11 and the loading plate sliding grooves 61.
The principle of the initiating explosive device for simulating the impact environment is as follows: the explosion impact excitation generated by the explosion of real initiating explosive devices such as explosives acts on the resonance plate 1 to cause real complex oscillation type initiating explosive shock waves, so that test equipment is examined.
Due to the complexity of the fire impact time domain response and the difference of the response duration, the impact time domain response is generally not used as a comparison reference in practical engineering, but an impact response spectrum (SRS) irrelevant to the response duration is used as an assessment index. The impact response spectrum is a frequency domain analysis method, and the method is specifically operated in such a way that impact time domain signals are loaded on a series of single degree of freedom System (SDOF) substrates to obtain the maximum value of the single degree of freedom system response under different frequencies, and then the inherent frequency of the single degree of freedom system is taken as an abscissa, and the maximum value of the response is a curve drawn by the ordinate of the corresponding frequency. In the present embodiment, the response maximum value is referred to as an absolute acceleration response maximum value, and is also referred to as an absolute acceleration shock response spectrum.
Thus, in the test the explosive 3 is detonated by the detonator and the detonation gases of the explosive 3 instantaneously impact the load plate 6 and cause an explosive shock wave on the structure. The shock wave is transmitted to the connecting position of the resonator plate 1 and the load plate 6 along the connecting rod 2 to the resonator plate 1, and causes a shock wave having transient, high-frequency and high-magnitude characteristics on the resonator plate 1.
Furthermore, the chutes of the connecting rods 2 are designed on the loading plate 6 and the resonator plate 1 of the device, namely: four resonant plate slide slots 11 and four load plate slide slots 61. The connecting rod 2 can slide along the extending direction of the resonant plate sliding groove 11 and the loading plate sliding groove 61, that is, the position of the connecting point of the loading plate 6 and the resonant plate 1 can be changed. Different positions of the connecting points can influence the low frequency slope of the shock response spectrum SRS of the resonator plate 6, i.e. different shock environments are obtained by different positions of the connecting points.
In this embodiment, the explosive material is PETN (pentaerythritol tetranitrate) explosive. Research shows that the explosive loading can effectively change the SRS spectral value of the impact environment on the resonance plate without changing the spectral shape.
In the present embodiment, the loading plate 6 is made of a low-carbon steel material because the explosive 3 exerts a strong explosive impact action on the loading plate 6. The dimensions of the loading plate are 1000mm × 1000mm × 10 mm.
In actual aerospace engineering, in order to reduce weight, many supports and plate structures are made of carbon fiber laminated composite materials. Therefore, in order to simulate the transmission characteristics of the thermal shock wave in the composite material more truly, the resonance plate 1 in the embodiment adopts a carbon fiber composite material paving plate. The dimensions of the resonator plate 1 are 700mm x 6 mm. Meanwhile, the thickness of the resonance plate is adjusted by designing the resonance plate 1 with different thicknesses. Research shows that the inflection point frequency of the impact response spectrum on the resonance plate 1 can be effectively adjusted by adjusting the thickness of the composite material resonance plate 1.
In summary, the present embodiment can effectively adjust the low frequency slope, the inflection frequency and the spectrum value of the impulse response spectrum of the fire on the resonator plate. The influence rule of three main adjusting parameters of the initiating explosive device on an impact response spectrum is shown in table 1:
TABLE 1 rule of impact response spectrum influence of adjustable parameters of device
And comparing the separated near-field impact response of the real star and arrow in the figure 4 with the impact time-domain response of a measuring point on the firer impact environment simulation device in the figure 5. As can be seen from the figure, the impact response of the measuring point of the fire impact environment simulation device is similar to the oscillation form of the real impact response and has similar amplitude. FIG. 6 is a comparison graph of impact response spectra of a real satellite-rocket separation near-field impact response and a measuring point of a firer impact environment simulation device. As can be seen from the graph, the impulse response spectrum of the measuring point on the device can envelop the real star-arrow separation impulse response spectrum within the range of +/-6 dB. The above analysis shows that the fire impact environment simulation device according to the embodiment can quickly realize a given impact environment.
Claims (7)
1. A fire impact environment simulation device is a double-plate loading structure and is characterized in that a safety cover (4) is covered outside an explosive (3) at the bottom of a loading plate (6), a pressure relief hole (5) is formed in the bottom surface of the safety cover (4),
four resonant plate sliding grooves (11) are formed in the resonant plate (1), the four resonant plate sliding grooves (11) respectively extend from the four corners of the resonant plate (1) to the center direction of the resonant plate (1),
four loading plate sliding grooves (61) are arranged on the loading plate (6), the four loading plate sliding grooves (61) are respectively opposite to the four resonant plate sliding grooves (11) up and down,
the four connecting rods (2) are respectively in one-to-one correspondence with the four resonant plate sliding grooves (11), one ends of the connecting rods (2) are embedded in the resonant plate sliding grooves (11), the other ends of the connecting rods (2) are embedded in loading plate sliding grooves (61) below the resonant plate sliding grooves (11), and the connecting rods (2) can support the loading plate (6) and the resonant plate (1) to keep a fixed distance and can slide along the extending direction of the resonant plate sliding grooves (11) and the loading plate sliding grooves (61).
2. A fire impact environment simulation device according to claim 1, wherein the double plate loading structure is suspended from the support by flexible suspension members (7) at each of the four corners of the double plate loading structure.
3. A fire impact environment simulation device according to claim 2, wherein the flexible cord fundamental frequency of the flexible suspension member (7) should be less than 5 Hz.
4. A pyrotechnic impact environment simulation device according to claim 1, characterised in that the resonator plate (1) is a carbon fibre composite laminate.
5. A fire impact environment simulation device according to claim 4, wherein the dimensions of the resonator plate (1) are 700mm x 6 mm.
6. A pyrotechnic impact environment simulation device in accordance with claim 1, characterised in that the loading plate (6) is made of a low carbon steel material.
7. A fire impact environment simulation device according to claim 6, wherein the size of the loading plate (6) is 1000mm x 10 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811020328.4A CN109211512B (en) | 2018-09-03 | 2018-09-03 | Fire impact environment simulation device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811020328.4A CN109211512B (en) | 2018-09-03 | 2018-09-03 | Fire impact environment simulation device |
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| CN109211512A CN109211512A (en) | 2019-01-15 |
| CN109211512B true CN109211512B (en) | 2020-09-08 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110132520B (en) * | 2019-06-20 | 2020-07-28 | 清华大学 | Fire impact simulation device |
| CN110375943A (en) * | 2019-06-24 | 2019-10-25 | 航天科工防御技术研究试验中心 | A kind of horizontal impact response spectra table top and its design method based on emulation |
| CN110285176B (en) * | 2019-07-19 | 2024-06-18 | 厦门大学 | Initiating explosive device separation impact reduction device based on inverse wavelength characteristics and preparation process thereof |
| CN114136576A (en) * | 2021-11-26 | 2022-03-04 | 北京中科宇航技术有限公司 | Explosion bolt impact response testing arrangement |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPS57147028A (en) * | 1981-03-09 | 1982-09-10 | Mitsubishi Heavy Ind Ltd | Vibrating table for experiment of vibration resistance |
| US4567772A (en) * | 1985-03-29 | 1986-02-04 | Honeywell Inc. | Vibration shaker/slip plate interface hardware |
| SU1629771A1 (en) * | 1988-05-26 | 1991-02-23 | Институт Проблем Машиностроения Ан Усср | Two coordinate vibration-testing machine |
| RU2011174C1 (en) * | 1990-07-09 | 1994-04-15 | Всероссийский научно-исследовательский институт экспериментальной физики | Method of dynamically testing buildings and structures |
| CN100447547C (en) * | 2006-04-14 | 2008-12-31 | 苏州试验仪器总厂 | Resonance device for vibration experiment |
| CN103662104B (en) * | 2013-11-29 | 2015-09-23 | 北京空间机电研究所 | A kind of unblock releasing mechanism of non-firer's mode |
| CN105760613A (en) * | 2016-03-01 | 2016-07-13 | 北京空间飞行器总体设计部 | Load prediction method for pyrotechnic impact source of spacecraft |
| CN108225708A (en) * | 2017-12-28 | 2018-06-29 | 天津航天瑞莱科技有限公司 | A kind of gas big gun shock testing machine control pressurer system |
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