CN116882071A - Initiating explosive device impact isolation method using periodic structure rod - Google Patents
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Abstract
The invention belongs to the technical field of initiating explosive device impact, and particularly relates to an initiating explosive device impact isolation method utilizing a periodic structure rod. The method comprises the following steps: according to the impact isolation problem that the actual impact response size of the satellite-rocket separation exceeds the allowable impact response size, obtaining the corresponding actual impact response size and allowable impact response size; calculating a band gap characteristic calculation model of the periodic structure rod according to a transmission matrix method and a one-dimensional wave equation; according to the band gap characteristic calculation model of the periodic structure and the impact requirement, a band gap calculation model and a geometric model of the periodic structure of the variable material and a band gap calculation model and a geometric model of the periodic structure of the variable cross section are obtained, and the geometric model set of the satellite-rocket interface is improved; and verifying whether the improved geometric model meets the impact requirement. The invention utilizes the band gap characteristic of the periodic structure, can prevent the propagation of stress wave in the band gap range, realizes the effective isolation and inhibition of the initiating explosive device impact, and improves the traditional satellite and rocket connection method.
Description
Technical Field
The invention belongs to the technical field of initiating explosive device impact, and particularly relates to an initiating explosive device impact isolation method utilizing a periodic structure rod.
Background
In the aerospace engineering practice, a large number of fire separation devices (such as separation nuts, explosion bolts, wrapping belts and the like) are required to drive various flying actions such as satellite and rocket separation in the process of executing a flying task, and a severe impact environment with high frequency, transient state and high magnitude generated during detonation of a fire work is called fire work impact and is one of the most severe mechanical environments experienced by the spacecraft. The high-frequency impact response generated by the initiating explosive device impact is easy to resonate with the electronic components, so that the components are invalid, the smooth proceeding of the flight task is further affected, and the space launching task is further failed.
The traditional impact isolation mode mainly comprises a flexible energy absorption method and a rigid isolation method, and the two traditional modes have respective defects although having good impact isolation performance. The flexible energy absorption method has the defect of insufficient rigidity, and the nonmetallic rubber such as the multilayer rubber gasket, the silicon rubber gasket and the like has the problem of easy aging, so that the spacecraft is difficult to execute the flight task; although the rigid isolation method can provide enough rigidity, the isolation device has large mass, which can cause the emission burden of the aircraft and increase the task cost. It is therefore necessary to introduce a new type of isolation method to solve the drawbacks of the traditional approach.
The periodic structure has band gap characteristics, can prevent the propagation of stress waves in a band gap range, has wide and mature application in vibration reduction and noise reduction, but lacks application in impact isolation. Therefore, the invention is based on phonon crystal theory, and introduces the periodic structure into the isolation scheme of the initiating explosive shock problem generated when the space vehicle is separated by the satellite and the rocket by utilizing the band gap characteristic of the phonon crystal theory.
Disclosure of Invention
In order to overcome the problems in the prior art, the invention provides a method for isolating the impact of a fire worker by using a periodic structure rod.
The technical scheme for solving the technical problems is as follows:
a method of isolating an initiating explosive device impact using a periodic structure rod, comprising the steps of:
step 1, obtaining corresponding actual impact response size and allowable impact response size according to the impact isolation problem that the actual impact response size of satellite-rocket separation exceeds the allowable impact response size;
step 2, calculating a band gap characteristic calculation model of the periodic structure rod according to a transmission matrix method and a one-dimensional wave equation, wherein the periodic structure rod comprises a variable material periodic structure rod and a variable section periodic structure rod;
step 3, according to the band gap characteristic calculation model of the periodic structure and the impact requirement, obtaining a band gap calculation model and a geometric model of a periodic structure rod of a variable material and a band gap calculation model and a geometric model of a periodic structure rod of a variable cross section, and improving the geometric model of a satellite-rocket interface;
step 4, carrying out finite element analysis on the improved geometric model of the satellite-rocket interface, then carrying out a test, guiding the test to be carried out by the finite element analysis, supplementing the test, verifying the finite element analysis result by the test, verifying whether the improved geometric model meets the impact requirement by the conclusion jointly obtained by the finite element analysis and the test, if so, obtaining the improved geometric model, and ending the design; if not, the model parameter correction proposal is re-proposed or improved, and the steps are repeated until the impact requirement is met.
Further, the material-changing periodic structure rod is made of two materials alternately, and the cross-section radiuses of the two materials are the same; the variable cross-section periodic structure rod is made of a single material and is of a variable cross-section phonon crystal structure with thick parts and thin parts alternately.
Further, the band gap characteristic calculation model of the periodic structure rod is as follows: and according to the actual inflection point range of the impulse response spectrum, the band gap range of the periodic structure rod is preset by combining the allowable impulse response spectrum, and the band gap of the periodic structure rod is calculated.
Further, the calculating the band gap of the periodic structure includes the steps of:
s1, representing displacement continuity conditions between and within the stem cells of the periodic structure by using amplitude:
（1）
in U%x) The amplitude is derived by a one-dimensional wave equation, P + Representing propagation in the forward direction, P - Indicating that the propagation in the reverse direction is to be performed,irepresenting the units of an imaginary number,xrepresenting a variable, alpha being the wave number;
s2, the band gap of the material-changing periodic structure rod is expressed by adopting a dispersion relation between a wave vector q and a frequency omega:
（2）
in the method, in the process of the invention,qis wave vector;Lthe total length of the periodic structure rod is changed into the material;α A wavenumber for material a;α B material B wave number;d A is the length of material a in one cycle;d B is the length of material B in one cycle; f is the wave resistance ratio; c 1 Is the wave velocity of material A, c 2 Is the wave velocity of the material B;ρ 1 the density of the material a is the density of the material a,ρ 2 is the density of the B material, ω is the frequency;
s3, the band gap of the variable section periodic structure rod is expressed by adopting a dispersion relation between a wave vector q and a frequency omega:
（3）
in the method, in the process of the invention,qis wave-shapedVector;Lthe total length of the periodic structure rod with the variable cross section is;αwavenumbers for materials; a is that 1 The cross-sectional area of the thick part of the rod is the variable cross-section periodic structure; a is that 2 A detail cross-sectional area of the variable cross-section periodic structure rod; d, d A1 Is the length of the thick part in one period, d A2 For the length of the detail in one cycle, c is the wave velocity of the A material.
Further, the material-changing periodic structure rod comprises a first periodic structure rod and a second periodic structure rod, the material of the first periodic structure rod is a No. 45 steel plate, the material of the second periodic structure rod is epoxy resin, the cross section radiuses of the first periodic structure rod and the second periodic structure rod are 25mm, and the part ratio of the first periodic structure rod to the second periodic structure rod is 5:4, i.e. the cycle number is 4.5, the length ratio of the first cycle structure rod to the second cycle structure rod in one cycle is 1:1, the lattice constant is 200mm, and the total length of the variable material cycle structure rod is 900mm.
Further, the variable cross-section periodic structure rod material is a 45-number steel plate, the variable cross-section periodic structure rod comprises a third periodic structure rod and a fourth periodic structure rod, the cross-section radius of the third periodic structure rod is 25mm, the cross-section radius of the fourth periodic structure rod is 12.5mm, the lattice constant is 200mm, and the part ratio of the third periodic structure rod to the fourth periodic structure rod in the whole variable cross-section periodic structure rod is 5:4, namely the cycle number is 4.5, the length ratio of the third cycle structure rod to the fourth cycle structure rod in one cycle is 1:1, and the total length of the variable section cycle structure rod is 900mm.
Compared with the prior art, the invention has the following technical effects:
the invention closely combines the practical characteristics of aerospace engineering, aims at the problem of overlarge impact response caused by the impact load of a fire machine at the separation moment of a spacecraft satellite and an arrow, and adds the periodic structure rod between a spacecraft satellite and a spacecraft satellite joint, thereby increasing the transmission distance of the impact wave, increasing the attenuation of the impact load and reducing the impact environment on the satellite. By utilizing the band gap characteristic of the periodic structure, the propagation of stress waves can be prevented within the band gap range, the effective isolation and inhibition of the initiating explosive device impact can be realized, the traditional spacecraft star connection method is improved, the weight of the spacecraft is reduced while the rigidity is ensured, and the emission cost is reduced.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions and advantages of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are only some embodiments of the invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic flow chart of the present invention;
FIG. 2 is an assembly view of the device after the material-changing cyclic rod is connected with a spacecraft satellite counterweight, a spacecraft satellite joint and a carrier rocket side joint;
FIG. 3 is an assembly view of the device after the variable cross section cyclic rod is connected with a spacecraft satellite counterweight, a spacecraft satellite joint and a carrier rocket side joint;
FIG. 4 is a schematic illustration of a geometric model of a periodic rod of varying material;
FIG. 5 is a schematic illustration of a geometric model of a variable section periodic rod;
FIG. 6 is an impulse response spectrum of a finite element analysis of a period rod of varying material;
FIG. 7 is an impact response spectrum of an impact test of a material-changing periodic rod;
FIG. 8 is a graph showing the results of a variable material period bar Er;
FIG. 9 is a graph showing the results of a material-changing periodic bar Mr;
FIG. 10 is an impulse response spectrum of a finite element analysis of a variable cross-section periodic rod;
FIG. 11 is an impact response spectrum of an impact test of a variable section periodic rod;
FIG. 12 is a graph showing the results of a variable cross-section periodic bar Er;
fig. 13 is a schematic diagram of the variable section periodic bar Mr results.
In the drawings, the list of component names indicated by the respective reference numerals is as follows:
1. a spacecraft satellite; 2. a periodic structure rod, a 3 and a spacecraft satellite connector; 4. a carrier rocket side joint; 5. an explosive bolt; 6. a first periodic structural rod; 7. a second cycle structure rod; 8. a third cycle structure lever; 9. fourth cycle structural bar.
Detailed Description
In order to further describe the technical means and effects adopted by the present invention to achieve the preset purpose, the following detailed description is given below of the specific implementation, structure, features and effects of the technical solution according to the present invention with reference to the accompanying drawings and preferred embodiments. The particular features, structures, or characteristics of one or more embodiments may be combined in any suitable manner. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.
According to the invention, on the basis of a traditional spacecraft satellite-rocket connection method, the periodic structure rod is added between the spacecraft satellite and the spacecraft satellite joint, so that the transmission distance of shock waves is increased, the attenuation of impact load is increased, the impact environment on the satellite is reduced, the propagation of stress waves can be prevented within the band gap range by utilizing the band gap characteristic of the periodic structure rod, and the effective isolation and inhibition of the initiating explosive shock are realized.
In one embodiment of the present invention, referring to FIG. 1, there is provided a method of initiating explosive device impact isolation using a periodic structure rod, comprising the steps of:
and step 1, obtaining corresponding actual impact response size and allowable impact response size according to the impact isolation problem that the actual impact response size of the satellite-rocket separation exceeds the allowable impact response size.
And 2, calculating a band gap characteristic calculation model of the periodic structure rod according to a transmission matrix method and a one-dimensional wave equation, wherein the periodic structure rod comprises a variable material periodic structure rod and a variable section periodic structure rod.
The material-changing periodic structure rod is made of two materials alternately, and the cross-section radiuses of the two materials are the same; the variable cross-section periodic structure rod is made of a single material and is of a variable cross-section phonon crystal structure with thick parts and thin parts alternately.
According to the actual inflection point range of the impulse response spectrum (ShockResponse Spectrum, SRS), the band gap range of the periodic structure rod is preset by combining the allowable impulse response spectrum, and the band gap of the periodic structure rod is calculated, wherein the band gap of the periodic structure rod comprises the band gap of the periodic structure of the variable material and the band gap of the periodic structure of the variable section.
In this embodiment, the calculation of the band gap of the periodic structure rod specifically includes the steps of:
s1, representing displacement continuity conditions between and within the stem cells of the periodic structure by using amplitude:
（1）
in U%x) The amplitude is derived by a one-dimensional wave equation, P + Representing propagation in the forward direction, P - Indicating that the propagation in the reverse direction is to be performed,irepresenting the units of an imaginary number,xrepresenting a variable, alpha being the wave number;
s2, the band gap of the material-changing periodic structure rod is expressed by adopting a dispersion relation between a wave vector q and a frequency omega:
（2）
in the method, in the process of the invention,qis wave vector;Lthe total length of the periodic structure rod is changed into the material;α A wavenumber for material a;α B material B wave number;d A is the length of material a in one cycle;d B is the length of material B in one cycle; f is the wave resistance ratio; c 1 Is the wave velocity of material A, c 2 Is the wave velocity of the material B;ρ 1 the density of the material a is the density of the material a,ρ 2 is the density of the B material, ω is the frequency;
s3, the band gap of the variable section periodic structure rod is expressed by adopting a dispersion relation between a wave vector q and a frequency omega:
（3）
in the method, in the process of the invention,qis wave vector;Lthe total length of the periodic structure rod with the variable cross section is;αwavenumbers for materials; a is that 1 The cross-sectional area of the thick part of the rod is the variable cross-section periodic structure; a is that 2 A detail cross-sectional area of the variable cross-section periodic structure rod; d, d A1 Is the length of the thick part in one period, d A2 For the length of the detail in one cycle, c is the wave velocity of the material.
And 3, obtaining a band gap calculation model and a geometric model of the periodic structure of the variable material and a band gap calculation model and a geometric model of the periodic structure of the variable cross section according to the band gap characteristic calculation model and the impact requirement of the periodic structure rod, and improving the geometric model of the star interface.
The lattice constant and the proportion of each component jointly determine the total length of the periodic structure rod, and in the improvement process, the required periodic structure rod structure is finally determined according to the band gap changed by controlling a single variable and then calculating different parameters.
Step 4, carrying out finite element analysis on the improved geometric model of the satellite-rocket interface, then carrying out a test, guiding the test to be carried out by the finite element analysis, supplementing the test, verifying the finite element analysis result by the test, verifying whether the improved geometric model meets the impact requirement by the conclusion jointly obtained by the finite element analysis and the test, if so, obtaining the improved geometric model, and ending the design; if not, the model parameter correction proposal is re-proposed or improved, and the steps are repeated until the impact requirement is met.
And applying triangular wave load to the right end of the improved geometric model to perform finite element analysis, and analyzing the attenuation condition of an impact response spectrum. Pendulum experiments are carried out on the improved geometric model, and the purpose of the pendulum experiments is to simulate excitation during the impact of a fire and analyze the attenuation condition of an impact response spectrum.
In a specific embodiment, referring to fig. 4, the material-changing periodic structure rod includes a first periodic structure rod 6 and a second periodic structure rod 7 in the whole material-changing periodic structure rod, the material of the first periodic structure rod 6 is a 45-number steel plate, the material of the second periodic structure rod 7 is epoxy resin, the cross-section radiuses of the first periodic structure rod 6 and the second periodic structure rod 7 are 25mm, the lattice constant is 200mm, and the part ratio of the first periodic structure rod 6 to the second periodic structure rod 7 is 5:4, namely the cycle number is 4.5, the length ratio of the first cycle structure rod 6 to the second cycle structure rod 7 in one cycle is 1:1, and the total length of the material-changing cycle structure rods is 900mm.
Referring to fig. 5, the variable cross-section periodic structure rod is made of a single material, the variable cross-section periodic structure rod material is a 45-number steel plate, the variable cross-section periodic structure rod comprises a third periodic structure rod 8 and a fourth periodic structure rod 9, the radius of the cross section of the third periodic structure rod 8 is 25mm, the radius of the cross section of the fourth periodic structure rod 9 is 12.5mm, the lattice constant is 200mm, and the part ratio of the third periodic structure rod 8 to the fourth periodic structure rod 9 in the whole variable cross-section periodic structure rod is 5:4, namely the cycle number is 4.5, the length ratio of the third cycle structure rod 8 to the fourth cycle structure rod 9 in one cycle is 1:1, and the total length of the variable section cycle structure rods is 900mm.
The rod with the phonon crystal periodic structure has good isolation performance on the impact load of a fire power, and the component proportion, the lattice constant and the period number can have great influence on the impact isolation performance of the rod.
The assembly diagrams after the periodic structure rod is connected with the spacecraft satellite counterweight, the spacecraft satellite connector and the carrier rocket side connector are shown in fig. 2-3.
Before launching the spacecraft satellite, the counterweight of the spacecraft satellite 1 is fixedly connected with one side of the periodic structure rod 2 through a flange plate and 6 bolts, then the other side of the periodic structure rod 2 is fixedly connected with the spacecraft satellite connector 3 through the flange plate and 6 bolts, and the spacecraft satellite connector 3, the carrier rocket side connector 4 and the initiating explosive device explosion bolt 5 are fixedly connected, so that satellite-rocket connection is realized.
At the moment of separating the satellite and the rocket, the explosion bolt 5 is detonated, and the spacecraft satellite 1, the periodic structure rod 2 and the spacecraft satellite connector 3 are combined and separated from the carrier rocket. At this time, the shock wave generated by the initiating explosive device is transmitted to one side of the cyclic structure rod 2 through the spacecraft satellite connector 3, and then transmitted to the spacecraft satellite 1 through the entire cyclic structure rod 2. When the shock wave is transmitted to the spacecraft satellite connector 3, the attenuation of the shock load is increased through the limitation of partial stress wave in the periodic structure rod 2.
In order to verify the buffering effect of the periodic structure rod, transient dynamics simulation and pendulum impact test double verification are adopted.
The finite element analysis results and experimental results are represented by an impulse response spectrum.
Since the exact same excitation cannot be applied in the test, in order to obtain the quantized impact response spectrum attenuation rate, two dimensionless coefficients are introduced which do not consider frequency:
in the method, in the process of the invention,Erfor the average relative coefficient of the impulse response spectrum over the entire frequency range,Mrfor the maximum relative coefficient of the impulse response spectrum,SRSa(f) The SRS to be analyzed (target) is transmitted,SRS b (f) As basis/datumSRS，fRepresentative frequency，The impulse response spectrum of the original structure is defined as a basic impulse response spectrum, the original structure is of a limited period, the theory is calculated as an infinite period model, and the period number only affects the transmission of stress waves and does not affect the position and the range of a band gap.
FIG. 6 is an impulse response spectrum of a finite element analysis of a period rod of varying material; FIG. 7 is an impact response spectrum of an impact test of a material-changing periodic rod; FIG. 8 is a graph showing the results of a variable material period bar Er; fig. 9 is a schematic diagram of the results of the material-changing periodic bar Mr. As shown in fig. 6-7, the finite element simulation results and pendulum impact test results of the periodic structure of the variable material show that: as shown in fig. 8, in contrast to the excitation end, the Er of the simulation data and the experimental data response end of the variable material period structure rod are respectively reduced by about 70% and 65%, and the maximum error between the simulation and experimental data is not more than 5%; as shown in FIG. 9, compared with the excitation end, the Mr of the simulation data and the test data of the variable material period structure rod is respectively reduced by 30% and 50%, and the requirement of the actual emission task on impact isolation is met.
FIG. 10 is an impulse response spectrum of a finite element analysis of a variable cross-section periodic rod; FIG. 11 is an impact response spectrum of an impact test of a variable section periodic rod; FIG. 12 is a graph showing the results of a variable cross-section periodic bar Er; fig. 13 is a schematic diagram of the variable section periodic bar Mr results. As shown in fig. 10 to 11, the finite element simulation results and pendulum impact test results of the variable section periodic structure rod show that: as shown in fig. 12, at the comparative excitation end, the simulation data of the variable material period structure rod and the Er at the test data response end are respectively reduced by about 50% and 42%, and the maximum error is not more than 8%; as shown in FIG. 13, compared with the excitation end, the Mr of the simulation data and the test data response end of the variable material period structure rod are respectively reduced by 40% and 43%, and the maximum error is not more than 3%. The results show that the periodic structure rod used in the invention already meets the requirement of the actual emission task on impact isolation.
Analysis results show that compared with SRS, er and Mr of the two-period structure rod, the impact response attenuation of the variable material period rod under the same structural size is improved by about 15% -20% compared with that of the variable section period rod. The test results also demonstrate that the structure has good impact isolation properties. The material-variable periodic structure rod has better impact resistance, is suitable for a small-sized spacecraft flight mission scene, ensures structural rigidity and strength, can ensure good impact attenuation effect, and is suitable for a large-sized spacecraft flight mission scene.
The above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention, and are intended to be included in the scope of the present invention.
Claims (6)
1. A method of isolating an impact from a fire using a periodic structure rod, comprising the steps of:
step 1, obtaining corresponding actual impact response size and allowable impact response size according to the impact isolation problem that the actual impact response size of satellite-rocket separation exceeds the allowable impact response size;
step 2, calculating a band gap characteristic calculation model of the periodic structure rod according to a transmission matrix method and a one-dimensional wave equation, wherein the periodic structure rod comprises a variable material periodic structure rod and a variable section periodic structure rod;
step 3, according to the band gap characteristic calculation model of the periodic structure and the impact requirement, obtaining a band gap calculation model and a geometric model of a periodic structure rod of a variable material and a band gap calculation model and a geometric model of a periodic structure rod of a variable cross section, and improving the geometric model of a satellite-rocket interface;
step 4, carrying out finite element analysis on the improved geometric model of the satellite-rocket interface, then carrying out a test, guiding the test to be carried out by the finite element analysis, supplementing the test, verifying the finite element analysis result by the test, verifying whether the improved geometric model meets the impact requirement by the conclusion jointly obtained by the finite element analysis and the test, if so, obtaining the improved geometric model, and ending the design; if not, the model parameter correction proposal is re-proposed or improved, and the steps are repeated until the impact requirement is met.
2. A method of isolating an initiating explosive device impact using a periodic structure rod according to claim 1, wherein the periodic structure rod is made of two materials alternately, the two materials having the same cross-sectional radius; the variable cross-section periodic structure rod is made of a single material and is of a variable cross-section phonon crystal structure with thick parts and thin parts alternately.
3. The method for isolating an initiating explosive device impact using a cyclic structure rod according to claim 2, wherein the band gap characteristic calculation model of the cyclic structure rod is: and according to the actual inflection point range of the impulse response spectrum, the band gap range of the periodic structure rod is preset by combining the allowable impulse response spectrum, and the band gap of the periodic structure rod is calculated.
4. A method of isolating a fire shock using a periodic structure rod according to claim 3, wherein said calculating the bandgap of the periodic structure comprises the steps of:
s1, representing displacement continuity conditions between and within the stem cells of the periodic structure by using amplitude:
（1）
in U%x) The amplitude is derived by a one-dimensional wave equation, P + Representing propagation in the forward direction, P - Indicating that the propagation in the reverse direction is to be performed,irepresenting the units of an imaginary number,xrepresenting a variable, alpha being the wave number;
s2, the band gap of the material-changing periodic structure rod is expressed by adopting a dispersion relation between a wave vector q and a frequency omega:
（2）
in the method, in the process of the invention,qis wave vector;Lthe total length of the periodic structure rod is changed into the material;α A wavenumber for material a;α B material B wave number;d A is the length of material a in one cycle;d B is the length of material B in one cycle; f is the wave resistance ratio; c 1 Is the wave velocity of material A, c 2 Is the wave velocity of the material B;ρ 1 the density of the material a is the density of the material a,ρ 2 is the density of the B material, ω is the frequency;
s3, the band gap of the variable section periodic structure rod is expressed by adopting a dispersion relation between a wave vector q and a frequency omega:
（3）
in the method, in the process of the invention,qis wave vector;Lthe total length of the periodic structure rod with the variable cross section is;αwavenumbers for materials; a is that 1 The cross-sectional area of the thick part of the rod is the variable cross-section periodic structure; a is that 2 A detail cross-sectional area of the variable cross-section periodic structure rod; d, d A1 Is the length of the thick part in one period, d A2 For the length of the detail in one cycle, c is the wave velocity of the material.
5. The method for isolating an initiating explosive device impact by utilizing a periodic structure rod according to claim 4, wherein the periodic structure rod with a variable material comprises a first periodic structure rod and a second periodic structure rod, the material of the first periodic structure rod is a No. 45 steel plate, the material of the second periodic structure rod is epoxy resin, the lattice constant is 200mm, the radius of the cross section of the first periodic structure rod and the second periodic structure rod is 25mm, and the part ratio of the first periodic structure rod to the second periodic structure rod is 5:4, namely the cycle number is 4.5, the length ratio of the first cycle structure rod to the second cycle structure rod in one cycle is 1:1, and the total length of the material-changing cycle structure rod is 900mm.
6. The method for isolating an initiating explosive device impact by using a periodic structure rod according to claim 4, wherein the material of the periodic structure rod with a variable cross section is a steel plate with the number of 45, the lattice constant is 200mm, the periodic structure rod with a variable cross section comprises a third periodic structure rod and a fourth periodic structure rod, the radius of the cross section of the third periodic structure rod is 25mm, the radius of the cross section of the fourth periodic structure rod is 12.5mm, and the part ratio of the third periodic structure rod to the fourth periodic structure rod in the whole periodic structure rod with the variable cross section is 5:4, namely the cycle number is 4.5, the length ratio of the third cycle structure rod to the fourth cycle structure rod in one cycle is 1:1, and the total length of the variable section cycle structure rod is 900mm.
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| RU2819664C1 (en) * | 2023-12-19 | 2024-05-22 | Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" | High-speed compartment separation device |
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| US20110210229A1 (en) * | 2009-11-02 | 2011-09-01 | Airbus Operations (S.A.S) | Structural rod incorporating a vibration filtration mode |
| CN113094812A (en) * | 2021-04-01 | 2021-07-09 | 烟台大学 | Fire impact isolation method using variable cross-section rod structure |
| CN114861325A (en) * | 2022-06-08 | 2022-08-05 | 烟台大学 | Fire impact isolation method using honeycomb porous material |
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| US20110210229A1 (en) * | 2009-11-02 | 2011-09-01 | Airbus Operations (S.A.S) | Structural rod incorporating a vibration filtration mode |
| CN113094812A (en) * | 2021-04-01 | 2021-07-09 | 烟台大学 | Fire impact isolation method using variable cross-section rod structure |
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