CN111152941B - High-performance material optimization method suitable for space debris protection structure - Google Patents

High-performance material optimization method suitable for space debris protection structure Download PDF

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CN111152941B
CN111152941B CN202010004519.2A CN202010004519A CN111152941B CN 111152941 B CN111152941 B CN 111152941B CN 202010004519 A CN202010004519 A CN 202010004519A CN 111152941 B CN111152941 B CN 111152941B
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CN111152941A (en
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武强
宋光明
李明
龚自正
张品亮
曹燕
田东波
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Beijing Institute of Spacecraft Environment Engineering
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Abstract

The invention discloses a high-performance material optimization method suitable for a space debris protective structure, which comprises the following steps of: a. selecting a protective material, looking up a table to obtain the Railuoneau and thermodynamic parameters of the material, and b, screening the protective material according to an impact pressure criterion, an internal energy conversion criterion, a minimum thickness criterion and a kinetic energy absorption criterion to obtain a preferred material. According to the method, the protection mechanism of the protection material under the action of ultra-high-speed impact is deeply analyzed, the mechanical and thermodynamic characteristics of the protection material are comprehensively considered, the impact pressure, internal energy conversion, the minimum thickness and the kinetic energy absorption characteristics of the protection material are taken as the optimization criteria, and a performance coefficient model capable of quantitatively representing the wave impedance characteristics and the thermodynamic characteristics of the protection material is combined, so that the high-performance material optimization method suitable for the space debris protection structure is obtained, the optimization of various protection materials can be realized, the test cost for material selection is effectively reduced, and theoretical guidance can be provided for the design and preparation of a novel high-performance protection material.

Description

High-performance material optimization method suitable for space debris protection structure
Technical Field
The invention relates to the technical field of space debris protection, in particular to a high-performance material optimization method suitable for a space debris protection structure.
Background
The shield concept was first proposed by the astronomical scientist Whipple in the United states, to be placed outside and spaced from the spacecraft bulkhead. The protective screen, the rear wall and a certain distance form a basic configuration of the spacecraft space debris protective structure, namely a Whipple protective structure. The protective screen is added on the outer side of the cabin wall of the spacecraft, so that incident fragments collide with the protective screen at a high speed and are crushed, melted and even gasified to form secondary fragment cloud, the kinetic energy of the incident fragments is reduced and dispersed to the maximum extent, the collision energy flux density acting on the cabin wall of the spacecraft is obviously reduced, and the damage and damage effects of the rear target plate are relieved. Research shows that the quality of the whispple protective structure is only 20% of that of a single-layer plate structure under the same protective capacity, namely, the quality can be saved by 80%. In order to improve the survivability of a spacecraft in a severe space debris environment, since the last 80 century, a large number of ultrahigh-speed impact experimental researches are carried out on NASA, ESA, JAXA and the like based on a traditional Whipple protection structure, and various high-performance protection structures are developed and mainly comprise a multilayer impact protection structure, a grid double-layer protection screen protection structure, a filling type protection structure, a flexible deployable protection structure, a foam material protection structure, a honeycomb sandwich plate protection structure and the like. The materials are selected from high-strength aluminum alloy plate, aluminum mesh, foamed aluminum, honeycomb plate, Kevlar fiber cloth, Nextel ceramic cloth and the like. The research work of the spacecraft space debris protection in China starts late, and high-performance protective materials are strictly forbidden to be transported in China abroad all the time, and in the current situation that the demand of space debris protection engineering is becoming strong, the research work of the high-performance protective materials is carried out by many families in China, but the engineering application and the protection capability of the space debris protective materials are very different from those of foreign countries.
The protective performance of the space debris protective structure not only depends on the protective structure, but also depends on the physical, chemical and mechanical characteristics of the protective material to a great extent, even the geometric configuration of the material is closely related, the excellent single performance cannot meet the optimal requirement, how to accurately evaluate the protective characteristics of the protective material, and the optimization of the high-performance protective material is realized, thus having important significance for the exploration design of the high-performance protective material in China and the performance improvement of the space debris protective structure.
Disclosure of Invention
The invention aims to: in order to solve the problem that the protective performance of the space debris protective structure not only depends on the protective structure, but also depends on the physical, chemical and mechanical properties of the protective material to a great extent, the method for optimizing the high-performance material suitable for the space debris protective structure is provided.
In order to achieve the purpose, the invention adopts the following technical scheme:
a preferred method of selecting a high performance material suitable for use in space debris guard structures, comprising the steps of: a. selecting a protective material, looking up a table to obtain Railuo and thermodynamic parameters of the material, b, primarily screening the protective material according to an impact pressure criterion and an internal energy conversion criterion, c, further optimizing the protective material through a performance coefficient model, d, screening the protective screen material according to a minimum thickness criterion to obtain an optimized protective screen material, e, screening a filling layer material according to a kinetic energy absorption criterion to obtain an optimized filling layer material, and f, performing test verification on the optimized protective screen material and the filling layer material.
As a further description of the above technical solution:
the formula for calculating the impact pressure criterion in the step b is as follows:
for the projectile:
P1＝ρ1Us1μp1
for the target plate:
P2＝ρ2Us2μp2
the corresponding state equations of the projectile and the target plate are respectively as follows:
Us1＝C1+S1μp1
Us2＝C2+S2μp2
the bonding interface continuity conditions can be:
P1＝ρ1(C1+S1μp1)μp1＝ρ1C1μp1+S1μp1 2
P2＝ρ2(C2+S2μp2)μp2＝ρ2C2μp2+S1μp2 2。
as a further description of the above technical solution:
the internal energy conversion criterion in the step b is as follows:
the internal energy produced by the material during impact compression, which can be derived from the Hugoniot relationship, is:
eH＝PH(v0-vH)/2
the specific internal energy released after the material is unloaded to zero pressure in an isentropic manner:
Figure BDA0002354741520000031
specific energy required for initial melting of the material:
Figure BDA0002354741520000032
as a further description of the above technical solution:
the performance coefficient model in the step c is as follows:
Figure BDA0002354741520000033
as a further description of the above technical solution:
the minimum thickness criterion calculation formula in the step d is as follows:
Top＝Tot+Tt+Tp
wherein:
Figure BDA0002354741520000034
the above relationships taken together can be:
Figure BDA0002354741520000035
as a further description of the above technical solution:
the calculation formula of the kinetic energy absorption criterion in the step e is as follows:
w＝0.5σTεT＝0.5σT 2/E。
in summary, due to the adoption of the technical scheme, the invention has the beneficial effects that:
according to the method, the protection mechanism of the protection material under the action of ultra-high-speed impact is deeply analyzed, the mechanical and thermodynamic characteristics of the protection material are comprehensively considered, the impact pressure, internal energy conversion, the minimum thickness and the kinetic energy absorption characteristics of the protection material are taken as the optimization criteria, and a performance coefficient model capable of quantitatively representing the wave impedance characteristics and the thermodynamic characteristics of the protection material is combined, so that the high-performance material optimization method suitable for the space debris protection structure is obtained, the optimization of various protection materials can be realized, the test cost for material selection is effectively reduced, and theoretical guidance can be provided for the design and preparation of a novel high-performance protection material.
Drawings
FIG. 1 is a schematic diagram of a preferred flow structure of a preferred method for producing high performance materials suitable for space debris protective structures according to the present invention;
FIG. 2 is a schematic structural diagram of an impact pressure impedance matching method of a preferred method of high performance materials suitable for space debris protective structures according to the present invention;
FIG. 3 is a schematic structural view of impact pressure as a function of material density for a preferred method of high performance materials for space debris guard structures in accordance with the present invention;
FIG. 4 is a schematic structural view of the initial melting rate of the protective material as a function of the melting heat for a preferred method of forming a high performance material suitable for use in space debris protective structures in accordance with the present invention;
fig. 5 is a schematic structural diagram of the change of the optimal areal density with the material density of a preferred method of the invention for a high performance material suitable for use in space debris guard structures.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1
Referring to fig. 1-5, a preferred method of forming a high performance material suitable for use in space debris shielding structures includes the steps of: a. selecting a protective material, looking up a table to obtain Railuo and thermodynamic parameters of the material, b, primarily screening the protective material according to an impact pressure criterion and an internal energy conversion criterion, c, further optimizing the protective material through a performance coefficient model, d, screening the protective screen material according to a minimum thickness criterion to obtain an optimized protective screen material, e, screening a filling layer material according to a kinetic energy absorption criterion to obtain an optimized filling layer material, and f, performing test verification on the optimized protective screen material and the filling layer material;
the impact pressure criterion is as follows: the impact pressure depends on parameters such as impact speed, density of an incident projectile and a target plate, an impact compression factor and the like, the impact pressure determines residual internal energy, temperature and a state of the incident projectile after collision to a great extent, the higher the impact pressure is, the larger the residual internal energy of the incident projectile is, the higher the temperature is, and the more the state of the incident projectile tends to be gaseous, researches show that compared with liquid particles and gaseous particles, the threat of solid particles to a rear wall is the largest, and therefore the selection of the material of the buffer screen is based on the principle that higher impact pressure can be generated in the incident projectile;
internal energy conversion criterion: the melting and gasification proportion of the shot and the protective screen under the ultra-high speed impact is an important index for evaluating the protective performance of the protective screen material, so the protective screen is selected on the principle that the internal energy conversion proportion in the impact process is as large as possible;
coefficient of performance criterion: the damage capability of the debris cloud composition material can be effectively reduced through the phase change effect, so that in order to enable the protective screen material to be easily melted and gasified, the protective screen material should have lower melting temperature, melting heat, gasification temperature and gasification heat.
Minimum thickness criterion: the impact peak pressure and internal energy conversion of the protective screen material under ultra-high speed impact have important influence on the protective performance, but the thickness of the protective screen is also important for the overall protective performance of the protective structure, and the thickness of the protective screen is too small, so that the impact waves can be chased and unloaded before reaching the back surface of the projectile, the projectile cannot be crushed, melted and gasified fully, and the penetration capability to the back wall is increased; the protective screen thickness is too big and can reduce the average impact pressure in the protective screen, leads to the protective screen breakage not fully to produce jumbo size piece, and both kinds of circumstances can reduce the protective efficiency of protective screen material, so there is optimum protective screen thickness, and optimum protective screen thickness can guarantee self breakage and phase transition effect, also can make the shot shock wave have enough time to cover whole shot.
Kinetic energy absorption criterion: the filling layer protection material is required to have higher impact pressure and specific internal energy conversion so as to further break, melt and gasify the fragment cloud, and the filling layer protection material is required to absorb the kinetic energy of the fragment cloud to the maximum extent and block residual fragments, so that the filling layer protection material has the characteristics of high strength, high modulus and low density, namely higher specific strength and specific modulus.
Different from the embodiment 1
Example 2
Referring to fig. 2 and 3, the impact pressure criterion in step b is based on the one-dimensional shock wave theory, neglecting the initial pressure before impact of the projectile, and using the momentum conservation equation to calculate the pressure in the projectile and the target plate, and the calculation formula is:
for the projectile:
P1＝ρ1Us1μp1
for the target plate:
P2＝ρ2Us2μp2
the corresponding state equations of the projectile and the target plate are respectively as follows:
Us1＝C1+S1μp1
Us2＝C2+S2μp2
the bonding interface continuity conditions can be:
P1＝ρ1(C1+S1μp1)μp1＝ρ1C1μp1+S1μp1 2
P2＝ρ2(C2+S2μp2)μp2＝ρ2C2μp2+S1μp2 2。
according to the known material state equation parameters, the material impact pressure is calculated by using an impedance matching method, the change relation between the impact pressure of the aluminum shot impacting different protective materials at the speed of 7km/s and the material density is referred to, so that the high-density material can generate higher impact pressure, and the material capable of initially melting the aluminum alloy shot is selected, namely the impact pressure is more than 65 GPa.
Different from the embodiment 1
Example 3
Referring to fig. 4, it can be known from the shockwave heating theory that whether the material is melted or gasified is determined by the residual specific internal energy remained in the material after shockwave compression and isentropic unloading, a strong shockwave generated by ultra-high-speed impact can cause irreversible entropy increase of the target material in the propagation process, the entropy increase process can be regarded as adiabatic, the unloading process under the action of rarefaction is isentropic, the entropy increase of the material after two processes, i.e., the internal energy of the material is increased, the energy released in the unloading process is subtracted from the increase of the internal energy in the impact loading process to be the residual internal energy in the material, when the residual specific internal energy of the material is greater than the melting specific internal energy, the material is melted, when the residual specific internal energy is greater than the gasification specific internal energy, the internal energy generated by the material in the impact compression process can be obtained from the relationship of Hugoniot:
eH＝PH(v0-vH)/2
the specific internal energy released after the material is unloaded to zero pressure in an isentropic manner:
Figure BDA0002354741520000071
specific energy required for initial melting of the material:
Figure BDA0002354741520000072
in the formula, vH、vCSpecific volumes, T, of the material after shock wave loading and unloading, respectivelymIs the melting point of the material, CPIs the specific heat at zero pressure of the material.
When the target materials are the same, the initial melting speed of the protective material is shown in relation to the change of the melting heat with reference to fig. 4, and the initial melting speed is increased in a similar power function form as the melting heat is increased.
Different from the embodiment 1
Example 4
The impact pressure model can know that the wave impedance characteristic of the protective material is closely related to the material performance material, the internal energy conversion model can know that the melting and gasification characteristics of the protective material are also closely related to the thermodynamic parameters of the material, in order to comprehensively consider the wave impedance characteristic and the thermodynamic characteristic of the material and quantitatively describe the phase change performance of the material under impact, the following performance coefficient (FOM) model is adopted, and the performance coefficient model in the step c is as follows:
Figure BDA0002354741520000073
where ρ' ═ ρAL/ρ，ρALIs the density of the aluminum alloy, and rho is the density of the contrast material;
Hm＝Hf(AL)/Hf，Hf(AL) is the heat of fusion of the aluminum alloy, HfThe heat of fusion for the comparative material;
Tm＝Tf(AL)/Tf，Tf(AL) is the melting temperature of the aluminum alloy, TfAs a comparative material melting temperature;
HV＝HV(AL)/HV，HV(AL) is heat of vaporization of aluminum alloy, HVThe heat of vaporization for the control material;
TV＝TV(AL)/TV，TV(AL) is the vaporization temperature, T, of the aluminum alloyVThe gasification temperature of the comparative material is shown;
R＝[C/CAL]0.67[H/HAL]0.25[ρ/PAL]0.5c is the elastic wave velocity of the contrast material, CALIs the elastic wave velocity of the aluminum alloy, H is the Brinell hardness of the contrast material, HALThe brinell hardness of the aluminum alloy.
The smaller the value of the thermodynamic parameter, the easier the material is to melt or vaporize and the smaller the danger of forming fragments, therefore, the material of the buffer screen should be selected on the principle of high FOM value, and it can be seen from the table that the protective properties of magnesium, tin, cadmium and lead are better and the protective properties of tungsten and tantalum are poorer compared with aluminum, which is consistent with the test results.
TABLE 1 part of the coefficient of performance of metallic materials
Material Coefficient of performance Material Coefficient of performance
Magnesium alloy 2.4 Titanium (IV) 0.56
Tin (Sn) 1.99 Steel 0.46
Lead (II) 1.90 Copper (Cu) 0.42
Cadmium (Cd) 1.86 Nickel (II) 0.42
Aluminium alloy 1.25 Tungsten 0.17
Antimony (Sb) 0.87 Tantalum 0.15
Different from the embodiment 1
Example 5
Referring to FIG. 5, the thickness of the shield is defined as the minimum shield thickness when the rarefaction wave meets the shock wave at the back surface of the projectile, where the propagation time T of the shock wave in the projectile is definedopExactly with the shock wave propagation time T in the shieldotSparse wave transmission time TtAnd the back surface rarefaction wave transit time T in the projectilepAnd d, the minimum thickness criterion calculation formula in the step d is as follows:
Top＝Tot+Tt+Tp
wherein:
Figure BDA0002354741520000081
the above relationships taken together can be:
Figure BDA0002354741520000091
after the above formula is obtained, the length L of the shot is usedpAnd obtaining the minimum protective screen thickness corresponding to the sparse wave which can not catch up with the shock wave in the projectile.
The mass of the aluminum alloy shot is 1g, the minimum thickness corresponding to the impact of different protective screen materials at the speed of 7km/s is obtained by using a minimum thickness model, and the optimal surface density corresponding to the protective screen under the condition of the minimum thickness is obtained. Referring to fig. 5, it can be seen that the optimal areal density of the material increases with the increase of the density, that is, the greater the density of the material of the protective shield, the greater the required optimal density of the protective shield, and the greater the total mass corresponding to the protective structure, and the smaller the optimal areal density is, the better the optimal areal density is under the condition of preferentially ensuring the breakage, melting and gasification of the projectile, so that cadmium and lead have better impact pressure characteristics and melting and gasification characteristics, but the greater the optimal areal density is not suitable for the protective material.
Different from the embodiment 1
Example 6
Assuming that the stress-strain relation of the material of the filling layer is linearly changed, the strain energy of the material fracture failure pair is the absorbable maximum kinetic energy, and the calculation formula of the kinetic energy absorption criterion in the step d is as follows:
w＝0.5σTεT＝0.5σT 2/E
where w is the strain energy per unit volume of the material, σTThe tensile strength of the material and the elastic modulus of the material are E.
Table 2 shows the evaluation results of several high-strength fiber materials and high-strength aluminum alloys, and it can be seen by comparison that the high-strength fiber material has a stronger kinetic energy absorption capability than the metal material, and can be preferentially used as a filler material.
TABLE 2 absorption of kinetic energy by the Filler layer Material
Figure BDA0002354741520000092
Figure BDA0002354741520000101
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.

Claims (3)

1. A preferred method of selecting high performance materials suitable for use in space debris protective structures, comprising the steps of:
a. selecting a protective material, and looking up a table to obtain the Railuoniao and thermodynamic parameters of the material;
b. primarily screening the protective material according to an impact pressure criterion and an internal energy conversion criterion;
c. the protective material is further optimized through a performance coefficient model;
d. screening the protective screen material according to the minimum thickness criterion to obtain an optimal protective screen material;
e. screening the filling layer material according to a kinetic energy absorption criterion to obtain an optimal filling layer material;
f. carrying out test verification on the optimized protective screen material and the optimized filling layer material;
wherein the calculation formula of the impact pressure criterion in the step b is as follows:
for the projectile:
P1＝ρ1Us1μp1
for the target plate:
P2＝ρ2Us2μp2
the corresponding state equations of the projectile and the target plate are respectively as follows:
Us1＝C1+S1μp1
Us2＝C2+S2μp2
the bonding interface continuity conditions can be:
P1＝ρ1(C1+S1μp1)μp1＝ρ1C1μp1+S1μp1 2
P2＝ρ2(C2+S2μp2)μp2＝ρ2C2μp2+S1μp2 2；
the internal energy conversion criterion in the step b is as follows:
the internal energy produced by the material during impact compression, which can be derived from the Hugoniot relationship, is:
eH＝PH(v0-vH)/2
the specific internal energy released after the material is unloaded to zero pressure in an isentropic manner:
Figure FDA0003260633640000011
specific energy required for initial melting of the material:
Figure FDA0003260633640000021
the minimum thickness criterion calculation formula in the step d is as follows:
Top＝Tot+Tt+Tp
wherein:
Figure FDA0003260633640000022
the above relationships taken together can be:
Figure FDA0003260633640000023
wherein: l ispIs the diameter of the projectile, LtThickness of protective screen material, UpIs the velocity of the shock wave in the projectile, UtFor the velocity, rho, of the shock wave in the shield materialtFor protecting the material of the screen from the impact wave, the density, rhootIs the initial density of the protective shield material, rhopIs the density of the shot material after impact wave, rhoopIs the initial density of the protective screen material, CtAcoustic velocity of material for shielding, CpIs the speed of sound of the projectile material.
2. The method for optimizing high-performance material suitable for space debris protective structure as claimed in claim 1, wherein the coefficient of performance model in the step c is
Figure FDA0003260633640000024
3. The method of claim 1, wherein the calculation formula of the kinetic energy absorption criterion in the step e is as follows:
w＝0.5σTεT＝0.5σT 2/E。
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