Damage determination method and device for space debris impacting satellite structure

Abstract

The invention provides a damage determination method and device for space debris impacting a satellite structure. The method comprises the steps that the number of laminate structures of the satellite structure is determined; through a pre-constructed fragment cloud theoretical model of the multi-layer plate structure, determining the mass center movement speed and the radial expansion speed of the fragment cloud after the fragment cloud impacts each layer plate structure; inputting the movement speed and the radial expansion speed of each mass center to a pre-constructed load distribution model of multiple times of impact of debris cloud on a satellite backboard, and outputting a load distribution curve on each laminate structure; based on the load distribution curve, the damage area of the debris cloud to each laminate structure is determined, whether the backboard in the laminate structure is perforated or not is determined, and damage caused by impact of the debris cloud to the satellite structure can be rapidly determined in the mode that the debris cloud hits the load distribution model of the satellite backboard for multiple times; and the method is suitable for calculation of various satellite structures, and compared with repeated simulation tests, the cost is reduced, and the efficiency is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite structure damage determination, and in particular to a method and device for determining damage to a satellite structure caused by space debris impacting the structure. Background Art

[0002] The impact of space debris can pose a fatal threat to spacecraft. The average collision speed between space debris and spacecraft in low Earth orbit (LEO) is about 10km / s. With the increase of human space activities, the amount of space debris has increased dramatically, and the probability of spacecraft being hit has increased rapidly. The space debris environment is formed by human space activities. With the rapid development of the space industry in various countries, the space debris environment is deteriorating. After a satellite is hit by space debris, the satellite structure will be damaged, and perforation and rupture may occur. The debris may also penetrate the satellite and generate more debris. The degree of damage to the satellite after the impact is crucial to assessing the satellite status and the debris environment.

[0003] At present, the extent of damage to satellites caused by impacts is mainly assessed through hypervelocity impact tests, but repeated testing methods result in relatively low work efficiency. Summary of the invention

[0004] The present invention provides a method and device for determining damage caused by space debris impacting a satellite structure, so as to solve the defect in the prior art that damage determination of space debris impacting a satellite can only rely on repeated simulation tests, resulting in low efficiency.

[0005] In a first aspect, the present invention provides a method for determining damage caused by space debris impacting a satellite structure, comprising:

[0006] Determine the number of laminate structures of the satellite structure;

[0007] Determine the mass center movement speed and radial expansion speed of the debris cloud after the debris cloud impacts each of the layered plate structures by using a pre-constructed debris cloud theoretical model of the debris cloud impacting the multi-layered plate structure;

[0008] Input each of the mass center moving speeds and the radial expansion speeds into a pre-constructed load distribution model of multiple debris clouds impacting a satellite backplane, and output a load distribution curve on each of the layer structures;

[0009] Based on the load distribution curve, the damage area of ​​each layer structure caused by the debris cloud is determined, and it is determined whether a back plate in the layer structure is perforated.

[0010] According to a method for determining damage to a satellite structure caused by space debris impact provided by the present invention, before determining the number of laminate structures of the satellite structure, the method further includes:

[0011] Determining the mass relationship between the perforation mass of each of the layer structures and the mass center movement speed and radial expansion speed of the debris cloud;

[0012] determining a kinetic energy relationship between the kinetic energy of each of the layer structures and the velocity of movement of the center of mass and the velocity of radial expansion of the debris cloud;

[0013] determining a momentum relationship between the momentum of each of the layer structures and the velocity of movement of the center of mass and the velocity of radial expansion of the debris cloud;

[0014] A theoretical model of a debris cloud of debris impacting a multilayer plate structure is constructed based on the mass relationship, the kinetic energy relationship and the momentum relationship.

[0015] According to a method for determining damage of a satellite structure caused by space debris impacting the satellite structure provided by the present invention, the mass relationship is:

[0016]

[0017] Among them, m bn Indicates the perforation quality of the nth layer of board, t bn represents the thickness of the nth layer, ρ b Indicates the density of the buffer screen material, S n Indicates the distance between the nth layer and the n-1th layer, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v r(n-1) represents the radial expansion speed of the n-1th debris cloud.

[0018] According to a method for determining damage of a satellite structure caused by space debris impacting the satellite structure provided by the present invention, the kinetic energy relationship is:

[0019]

[0020] Among them, m p represents the mass of the fragment, m bn Indicates the perforation quality of the nth layer of board, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v r(n-1) represents the radial expansion speed of the n-1th debris cloud, E in represents the internal energy increment of the nth fragment and the n-1th plate during the impact process, E fn It represents the energy absorbed by the crushing of the nth fragment and the n-1th plate.

[0021] According to a method for determining damage caused by space debris impacting a satellite structure provided by the present invention, the momentum relationship is:

[0022] m p v c(n-1) =m p v cn +mbn v cn ;

[0023] Among them, m p represents the fragment mass, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v cn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, m bn Indicates the perforation quality of the nth layer of board.

[0024] According to a method for determining damage to a satellite structure caused by space debris impact provided by the present invention, before determining the number of laminate structures of the satellite structure, the method further includes:

[0025] Determine the distance between the position of the annular microelement of each debris cloud on the backplane and the impact center;

[0026] Determine the impulse density of the annular microelement of each debris cloud on the backboard based on the distance between the position of the annular microelement of each debris cloud on the backboard and the impact center, and the moving speed of the center of mass of each debris cloud and the radial expansion speed;

[0027] Based on the impulse density of the annular microelement of each debris cloud on the backplate, a load distribution model of multiple debris clouds impacting the satellite backplate is constructed.

[0028] According to a method for determining damage to a satellite structure caused by space debris impact provided by the present invention, the distance between the position of the annular microelement of the debris cloud on the backplane and the impact center each time is:

[0029]

[0030] Among them, R n S represents the distance between the position of the annular element of the nth debris cloud on the backplane and the impact center. n Indicates the distance between the nth layer and the n-1th layer, v cn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, and θ represents the angle between the debris cloud and the axis on the sphere.

[0031] According to a method for determining damage to a satellite structure caused by space debris impacting the satellite structure provided by the present invention, the impulse density of the annular microelement of the debris cloud on the backplane each time is:

[0032]

[0033] Among them, ρ In represents the impulse density of the annular microelement of the nth debris cloud on the backplane, m n represents the mass of the nth debris cloud, vcn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, θ represents the angle between the debris cloud and the axis on the sphere, R n Represents the distance between the position of the annular element of the nth debris cloud on the backplane and the impact center.

[0034] According to a method for determining damage caused by space debris impacting a satellite structure provided by the present invention, the damage area of ​​each layer structure caused by the debris cloud is determined based on the load distribution curve, and whether a back plate in the layer structure is perforated, including:

[0035] Based on the load distribution curve on each layer of the plate, the load distribution curve is compared with the critical failure load density of each layer of the plate to determine the number of effectively destroyed layers and obtain the damage area of ​​each layer of the plate;

[0036] Based on the load distribution curve of the back plate, a comparison is made with the critical failure load density of the back plate. If the load distribution curve is greater than the critical failure load density of the back plate, it is determined that the back plate is perforated, otherwise, there is no perforation.

[0037] In a second aspect, the present invention further provides a device for determining damage caused by space debris impacting a satellite structure, comprising:

[0038] A first determination module is used to determine the number of laminate structures of the satellite structure;

[0039] A second determination module is used to determine the mass center movement speed and radial expansion speed of the debris cloud after the debris cloud impacts each of the layer plate structures by using a pre-constructed debris cloud theoretical model of the debris impacting the multi-layer plate structure;

[0040] An output module, used for inputting each of the mass center moving speeds and the radial expansion speeds into a pre-built load distribution model of multiple debris clouds impacting a satellite back panel, and outputting a load distribution curve on each of the layer plate structures;

[0041] The third determination module is used to determine the damage area of ​​each layer plate structure caused by the debris cloud based on the load distribution curve, and determine whether the back plate in the layer plate structure is perforated.

[0042] In a third aspect, the present invention further provides an electronic device comprising a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein when the processor executes the program, it implements any of the above-described methods for determining damage caused by space debris impacting a satellite structure.

[0043] In a fourth aspect, the present invention further provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements a method for determining damage caused by space debris impacting a satellite structure as described in any one of the above.

[0044] In a fifth aspect, the present invention further provides a computer program product, comprising a computer program, which, when executed by a processor, implements any of the above-described methods for determining damage caused by space debris impacting a satellite structure.

[0045] The present invention provides a method and device for determining damage caused by space debris impacting a satellite structure, comprising: determining the number of layer plate structures of the satellite structure; determining the center of mass movement speed and radial expansion speed of the debris cloud after the debris cloud impacts each layer plate structure through a pre-constructed debris cloud theoretical model of debris impacting a multi-layer plate structure; inputting each center of mass movement speed and radial expansion speed into a pre-constructed load distribution model of multiple debris clouds impacting a satellite back plate, and outputting a load distribution curve on each layer plate structure; based on the load distribution curve, determining the damage area of ​​each layer plate structure caused by the debris cloud, and determining whether the back plate in the layer plate structure is perforated. The load distribution model of multiple debris clouds impacting a satellite back plate can be used to quickly determine the damage caused by the debris cloud impacting the satellite structure, and is suitable for calculations of various satellite structures. Compared with repeated simulation tests, it reduces costs and improves efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0047] Figure 1 is a schematic flow chart of a method for determining damage caused by space debris impacting a satellite structure provided in this embodiment;

[0048] Figure 2 is a schematic diagram of a space debris impact satellite structure provided by this embodiment;

[0049] Figure 3 is a schematic diagram of the load distribution of the debris cloud on each layer of the plate structure provided in this embodiment;

[0050] Figure 4 Schematic diagram of load distribution curves on each layer provided in this embodiment.

[0051] Figure 5 It is a schematic diagram of the structure of the device for determining damage to a satellite structure caused by space debris impacting the satellite structure provided in this embodiment.

[0052] Figure 6 It is a schematic diagram of the structure of the electronic device provided in this embodiment. DETAILED DESCRIPTION

[0053] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0054] Figure 1 It is a flowchart of the method for determining damage caused by space debris impacting a satellite structure provided in this embodiment.

[0055] like Figure 1 As shown, the damage determination method of space debris impacting a satellite structure provided by an embodiment of the present invention mainly includes the following steps:

[0056] 101. Determine the number of laminate structures of the satellite structure.

[0057] In a specific implementation process, the number of layers of different satellite structures may be different, so the number of layers of the satellite structure needs to be determined first. For example, the number of layer structures is n, where n is a natural number.

[0058] 102. The debris cloud theoretical model of debris impacting a multi-layer plate structure is constructed in advance to determine the center of mass moving speed and radial expansion speed of the debris cloud after the debris cloud impacts each layer plate structure.

[0059] Debris cloud refers to the debris that will break after hitting the satellite thin plate, producing a cloud of a large number of small fragments. When the debris hits the satellite front plate at ultra-high speed, it will produce ultra-high shock wave pressure, causing the debris and the front plate material to break. The debris and the front plate fragments form a debris cloud that moves forward at high speed. It can be considered that the debris cloud (1st debris cloud) generated by the debris hitting the front plate is composed of a sphere. The debris and the front plate fragments are evenly distributed on the sphere, and the center of mass of the sphere moves forward at high speed while also having an expansion speed.

[0060] After the number of satellite plate structures is determined, it is input into the pre-built debris cloud theoretical model of debris impacting multi-layer plate structures. Through automatic calculation, the center of mass moving speed and radial expansion speed of the debris cloud after the debris cloud impacts each layer structure can be calculated, and both are used as the characteristic speed of the debris cloud. Among them, the debris cloud theoretical model of debris impacting multi-layer plate structures is universal, that is, it can calculate the characteristic speed of the debris cloud n times.

[0061] 103. Input each center of mass moving speed and radial expansion speed to the pre-built load distribution model of multiple debris clouds impacting the satellite backplane, and output the load distribution curve on each layer structure.

[0062] After obtaining the characteristic velocities of the debris cloud n times, they are input into the pre-constructed load distribution model of multiple debris clouds impacting the satellite backplane. The model can output the load distribution curve on each layer structure through internal automatic calculations, and also obtain the load distribution curves on the n layer structures. The load distribution curves can reflect the different stress conditions at different positions of each layer structure, and finally the load distribution of the debris cloud on the backplane is calculated.

[0063] 104. Based on the load distribution curve, determine the damage area of ​​each layer structure caused by the debris cloud, and determine whether the back plate in the layer structure is perforated.

[0064] After obtaining the load distribution curve, the critical failure load density ρ of each thin plate is calculated. In_critical By comparing, we can determine the number of layers of the satellite's internal plate structure that are effectively damaged by the kinetic debris, and obtain the damage area of ​​each plate. In addition, we can confirm whether the satellite backplane will be perforated based on the load density distribution on the satellite backplane, thereby evaluating whether the debris will penetrate the satellite.

[0065] Specifically, when the load reflected by the load distribution curve exceeds the critical failure load density, the surface will be damaged and perforated, otherwise no damage perforation will occur. In addition, according to the load conditions at each position of the load distribution curve, the damage area of ​​the laminate structure can also be obtained.

[0066] The model in this embodiment quickly obtains the damage condition of the laminate structure by automatic calculation, which reduces the cost and improves the efficiency of determining the damage caused by space debris impacting the satellite structure compared with the high-speed impact test.

[0067] Figure 2 It is a schematic diagram of the space debris impacting the satellite structure provided by this embodiment.

[0068] like Figure 2 As shown, the satellite structure is multi-layered, including the front plate, n thin plates and the back plate. The kinetic warhead refers to space debris. The debris cloud generated by the debris hitting the front plate is defined as the primary debris cloud. The mass of the entire primary debris cloud is the sum of the mass of the debris and the mass of the perforated part of the front plate (1):

[0069] m1=m p +m b1 (1)

[0070] Where m1 represents the mass of the primary debris cloud; m pIndicates the mass of the fragment; m b1 It indicates the mass of the perforated part of the front plate, which can be calculated according to the perforation formula.

[0071] The perforation formula of the front plate is:

[0072]

[0073] Among them, D b Indicates the front plate perforation diameter, d p represents the fragment diameter, v p represents the fragmentation velocity, t b represents the thickness of the front plate. The mass m of the perforated part of the front plate can be calculated by formula (2): b1 .

[0074] According to the conservation of momentum and energy, we can obtain (3) and (4):

[0075] m p v p =m p v c1 +m b1 v c1 (3)

[0076]

[0077] Among them, v c1 represents the velocity of the center of mass of a debris cloud, v r1 represents the radial expansion speed of the debris cloud, E f1 is the energy absorbed by the fragments and the front plate material, E i1 It is the internal energy increment of the fragments and front plate material during the impact process.

[0078] According to Grady's crushing theory, the crushing energy of the fragments and the front plate can be calculated, that is, the energy absorbed by the crushing of the fragments and the front plate material (5):

[0079]

[0080] Among them, K c represents the fracture toughness of the material, ρ P represents the density of the debris material, ρ b Indicates the density of the buffer screen material, c p , c p Represents the speed of sound in a material. Represents the strain rate and can be obtained based on the radial expansion velocity.

[0081] The internal energy increment of the fragments and the front plate material during the impact process is divided into the internal energy increment caused by the shock wave loading and the internal energy increment caused by the plastic work, as shown in (6):

[0082] E i1 =(m p +m b1 )(e s +e p ) (6)

[0083] Among them, e s represents the increment of internal energy per unit mass of material caused by shock wave loading, e p It represents the increment of internal energy per unit mass of material caused by plastic work and can be calculated by the following formula:

[0084]

[0085] e p =β∫σdε (8)

[0086] Among them, P H 、V H To represent the shock wave pressure and the specific volume under this pressure, β is the work-heat conversion coefficient, which is generally taken as 0.8 to 0.9. V0 represents the initial specific volume of the material, P represents the pressure, σ represents the material stress, and ε represents the strain.

[0087] By combining equations (1), (3), and (4), and substituting the energy parameters calculated according to equations (5), (6), (7), and (8), we can find the characteristic velocity of the primary debris cloud, that is, the center of mass moving velocity and radial expansion velocity of the primary debris cloud.

[0088] like Figure 2 As shown, the debris cloud (secondary debris cloud) generated by the collision of the first debris cloud with the second thin plate is a sphere, and the debris and the second thin plate fragments are evenly distributed on the sphere. Since the perforation area of ​​the second thin plate is equal to the area of ​​the debris in the first debris cloud that hits the second thin plate, we have (9):

[0089]

[0090] Where S1 is the distance between the front plate and the second thin plate, m b2 Indicates the perforation quality of the second layer of thin plate, t b2 is the thickness of the second thin plate, v c2 represents the moving speed of the center of mass of the secondary debris cloud, v r2 represents the radial expansion velocity of the secondary debris cloud, ρ b Indicates the density of the buffer screen material.

[0091] The fragments in the secondary debris cloud and the thin plate fragments have the same center of mass moving speed and radial expansion speed, so the energy and momentum conservation equations (10)(11) are:

[0092]

[0093] m p v c1 =m p v c2 +m b2 v c2 (11)

[0094] Among them, E f2 is the energy absorbed by the fragments and the second sheet material, E i2 It is the internal energy increment of the fragments and the second layer of thin plate material during the impact process.

[0095] By analogy, the relationship between the perforation mass of the nth thin plate of the n-layer structure of the satellite, that is, the perforation mass of each layer structure and the mass movement speed and radial expansion speed of the debris cloud is (12):

[0096]

[0097] Among them, m bn Indicates the perforation quality of the nth layer of board, t bn represents the thickness of the nth layer, ρ b Indicates the density of the buffer screen material, S n Indicates the distance between the nth layer and the n-1th layer, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v r(n-1) represents the radial expansion speed of the n-1th debris cloud.

[0098] For the n-th layer of thin plate, the relationship between the kinetic energy of each layer structure and the velocity of the center of mass moving and the radial expansion velocity of the debris cloud is as follows (13); the relationship between the momentum of each layer structure and the velocity of the center of mass moving and the radial expansion velocity of the debris cloud is as follows (14):

[0099]

[0100] m p v c(n-1) =m p v cn +m bn v cn (14)

[0101] Among them, m p represents the mass of the fragment, m bn Indicates the perforation quality of the nth layer of board, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v r(n-1) represents the radial expansion velocity of the n-1th debris cloud, v cn represents the velocity of the center of mass of the nth debris cloud, v rnrepresents the radial expansion speed of the nth debris cloud, E in represents the internal energy increment of the nth fragment and the n-1th plate during the impact process, E fn It represents the energy absorbed by the crushing of the nth fragment and the n-1th plate.

[0102] By combining equations (12), (13) and (14), we can calculate the characteristic velocity of the n-th debris cloud impacting n thin plates. Based on the characteristic velocity of the n-th debris cloud, we can establish the load distribution model of the debris cloud on the satellite backplane.

[0103] Figure 3 It is a schematic diagram of the load distribution of the debris cloud on each layer of the plate structure provided in this embodiment.

[0104] like Figure 3 As shown in Fig. 1, the annular microelement on the sphere of the debris cloud at an angle θ to the axis moves forward and expands radially at the same time. The speeds of the annular microelement in the X and Y directions can be expressed as (15) and (16):

[0105] v x1 =v c1 +v r1 cosθ (15)

[0106] v y1 =v r1 sinθ (16)

[0107] The area of ​​the annular element when it is about to hit the second thin plate can be calculated as (17):

[0108] ds1=(r1sinθ)·2π·r1dθ (17)

[0109] Among them, r1 is the radius of the first debris cloud when it hits the second thin plate.

[0110] Then we have the mass and impulse of the annular element, as (18) and (19):

[0111]

[0112] The distance R1 between the primary debris cloud ring element and the impact center on the second thin plate can be expressed as (20):

[0113]

[0114] The mass density of the annular element of the first-order debris cloud on the second thin plate can be obtained as (21):

[0115]

[0116] Then, the impulse density of the annular element of the first debris cloud on the second thin plate can be obtained, as shown in (22):

[0117]

[0118] The characteristic velocity of the primary debris cloud is obtained according to equations (1), (3) and (4). Substituting them into equations (20) and (22), the impact radius of the primary debris cloud on the second thin plate and the load density distribution of the primary debris cloud on the second thin plate can be calculated.

[0119] Similarly, the load density distribution of the n-1th debris cloud on the nth thin plate can be obtained. For a satellite with n+1 thin plates (including the front plate and the back plate), the distance between the position of the annular element of the nth debris cloud on the back plate and the impact center can be expressed as (23):

[0120]

[0121] Among them, R n S represents the distance between the position of the annular element of the nth debris cloud on the backplane and the impact center. n Indicates the distance between the nth layer and the n-1th layer, v cn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, and θ represents the angle between the debris cloud and the axis on the sphere.

[0122] Through formula (23), the distance between the position of the annular microelement of each debris cloud on the backplane and the impact center can be determined. Based on the distance between the position of the annular microelement of each debris cloud on the backplane and the impact center, and the centroid moving speed and radial expansion speed of each debris cloud, the impulse density of the annular microelement of each debris cloud on the backplane is determined as (24):

[0123]

[0124] Among them, ρ In represents the impulse density of the annular microelement of the nth debris cloud on the backplane, m n represents the mass of the nth debris cloud, v cn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, θ represents the angle between the debris cloud and the axis on the sphere, R n Represents the distance between the position of the annular element of the nth debris cloud on the backplane and the impact center.

[0125] The characteristic speed of the n-th fragment cloud, i.e., the mass center moving speed and the radial expansion speed, can be obtained by combining equations (12), (13), and (14). The characteristic speed of the n-th fragment cloud can be substituted into equations (23) and (24) to obtain the load distribution of the fragment cloud on the back layer of thin plate, and then the damage area of ​​each layer of thin plate can be obtained. Finally, the load distribution of the fragment cloud on the back plate can be calculated to determine whether the back plate will be perforated.

[0126] The critical failure load density ρ of each thin plate In_critical By comparing, we can determine the number of layers of thin plate structure inside the satellite that are effectively damaged by kinetic debris, and obtain the damage area of ​​each thin plate. In addition, we can confirm whether the satellite backplane will be perforated based on the load density distribution on the satellite backplane, and thus evaluate whether the debris will penetrate the satellite.

[0127] Compared with the hypervelocity impact test, the method of this embodiment can reduce the number of tests, shorten the test time, save a lot of manpower and material costs, and provide a basis for the design of satellite protection structures.

[0128] In order to verify the effectiveness of this method, the following parameters are designed for simulation tests. The satellite structure is a 5-layer plate structure, each thin plate is an aluminum alloy plate with a thickness of 2 mm, the spacing between each layer of plates is 10 cm, the size of each layer of plates is: 40 cm × 40 cm, and the size of the satellite structure is 40 cm × 40 cm × 40 cm. The kinetic fragments are cylindrical, with a diameter of 1 cm and a length of 1 cm.

[0129] Taking the impact velocity of 5 km / s as an example, the characteristic velocity of the debris cloud generated by each layer of thin plates is first calculated according to equations (12), (13), and (14). The characteristic velocity is substituted into equations (23) and (24) to calculate the load distribution curve on each layer of the plate, as shown in the following figure: Figure 4 As shown. Figure 4 It can be concluded that the diameter of the damaged area of ​​the second thin plate is 12.3 cm, the diameter of the damaged area of ​​the third thin plate is 18.3 cm, the diameter of the damaged area of ​​the third thin plate is 24.7 cm, and the diameter of the damaged area of ​​the back plate is 40 cm. In_critical =50Pa·s, so the back plate will not be penetrated by fragments.

[0130] Through simulation tests, it can be concluded that the method of the present invention can quickly and efficiently perform damage assessment, effectively improve work efficiency, and provide data reference for the design of satellite structures.

[0131] Based on the same general inventive concept, the present invention also protects a device for determining damage to a satellite structure caused by space debris impacting the structure. The device for determining damage to a satellite structure caused by space debris impacting the structure provided by the present invention is described below. The device for determining damage to a satellite structure caused by space debris impacting the structure described below and the method for determining damage to a satellite structure caused by space debris impacting the structure described above can be referenced to each other.

[0132] Figure 5 It is a schematic diagram of the structure of the device for determining damage to a satellite structure caused by space debris impacting the satellite structure provided in this embodiment.

[0133] like Figure 5 As shown, this embodiment provides a device for determining damage caused by space debris impacting a satellite structure, comprising:

[0134] A first determination module 501 is used to determine the number of layer structures of the satellite structure;

[0135] The second determination module 502 is used to determine the mass center moving speed and radial expansion speed of the debris cloud after the debris cloud impacts each layer plate structure by using a pre-built debris cloud theoretical model of the debris impacting the multi-layer plate structure;

[0136] Output module 503, used to input each mass center moving speed and radial expansion speed into a pre-built load distribution model of multiple debris clouds impacting the satellite backplane, and output a load distribution curve on each layer structure;

[0137] The third determination module 504 is used to determine the damage area of ​​each layer structure caused by the debris cloud based on the load distribution curve, and determine whether the back plate in the layer structure is perforated.

[0138] Figure 6 It is a schematic diagram of the structure of the electronic device provided in this embodiment.

[0139] like Figure 6As shown, the electronic device may include: a processor 610, a communication interface 620, a memory 630 and a communication bus 640, wherein the processor 610, the communication interface 620 and the memory 630 communicate with each other through the communication bus 640. The processor 610 may call the logic instructions in the memory 630 to execute the damage determination method of the space debris impacting the satellite structure, the method comprising: determining the number of the layer plate structure of the satellite structure; determining the mass center moving speed and radial expansion speed of the debris cloud after the debris cloud impacts each of the layer plate structures through a pre-constructed debris cloud theoretical model of the debris impacting the multi-layer plate structure; inputting each of the mass center moving speed and the radial expansion speed into the pre-constructed load distribution model of multiple debris clouds impacting the satellite back plate, and outputting the load distribution curve on each of the layer plate structures; determining the damage area of ​​each layer plate structure caused by the debris cloud based on the load distribution curve, and determining whether the back plate in the layer plate structure is perforated.

[0140] In addition, the logic instructions in the above-mentioned memory 630 can be implemented in the form of a software functional unit and can be stored in a computer-readable storage medium when it is sold or used as an independent product. Based on such an understanding, the technical solution of the present invention can be essentially or partly embodied in the form of a software product that contributes to the prior art. The computer software product is stored in a storage medium, including several instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to perform all or part of the steps of the method described in each embodiment of the present invention. The aforementioned storage medium includes: U disk, mobile hard disk, read-only memory (ROM, Read-Only Memory), random access memory (RAM, Random Access Memory), disk or optical disk, etc. Various media that can store program codes.

[0141] On the other hand, the present invention also provides a computer program product, which includes a computer program, which can be stored on a non-transitory computer-readable storage medium. When the computer program is executed by a processor, the computer can execute the damage determination method for space debris impacting a satellite structure provided by the above-mentioned methods, which method includes: determining the number of layer structures of the satellite structure; determining the center of mass movement speed and radial expansion speed of the debris cloud after the debris cloud impacts each of the layer structures through a pre-constructed debris cloud theoretical model of debris impacting a multi-layer plate structure; inputting each of the center of mass movement speeds and radial expansion speeds into a pre-constructed load distribution model of multiple debris clouds impacting a satellite backplane, and outputting a load distribution curve on each of the layer structures; based on the load distribution curve, determining the damage area of ​​each layer structure caused by the debris cloud, and determining whether the backplane in the layer structure is perforated.

[0142] On the other hand, the present invention also provides a non-transitory computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, is implemented to execute the damage determination method for space debris impacting a satellite structure provided by the above-mentioned methods, the method comprising: determining the number of layer structures of the satellite structure; determining the center of mass movement speed and radial expansion speed of the debris cloud after the debris cloud impacts each of the layer structures through a pre-constructed debris cloud theoretical model of debris impacting a multi-layer plate structure; inputting each of the center of mass movement speeds and the radial expansion speeds into a pre-constructed load distribution model of multiple debris clouds impacting a satellite backplate, and outputting a load distribution curve on each of the layer structures; based on the load distribution curve, determining the damage area of ​​each layer structure caused by the debris cloud, and determining whether the backplate in the layer structure is perforated.

[0143] The device embodiments described above are merely illustrative, wherein the units described as separate components may or may not be physically separated, and the components displayed as units may or may not be physical units, that is, they may be located in one place, or they may be distributed on multiple network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the scheme of this embodiment. Ordinary technicians in this field can understand and implement it without paying creative labor.

[0144] Through the description of the above implementation methods, those skilled in the art can clearly understand that each implementation method can be implemented by means of software plus a necessary general hardware platform, and of course, it can also be implemented by hardware. Based on this understanding, the above technical solution is essentially or the part that contributes to the prior art can be embodied in the form of a software product, and the computer software product can be stored in a computer-readable storage medium, such as ROM / RAM, a disk, an optical disk, etc., including a number of instructions for a computer device (which can be a personal computer, a server, or a network device, etc.) to execute the methods described in each embodiment or some parts of the embodiments.

[0145] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A method for determining damage caused by space debris impacting a satellite structure, characterized in that: include: Determine the number of laminate structures of the satellite structure; Determine the mass center movement speed and radial expansion speed of the debris cloud after the debris cloud impacts each of the layered plate structures by using a pre-constructed debris cloud theoretical model of the debris cloud impacting the multi-layered plate structure; Input each of the mass center moving speeds and the radial expansion speeds into a pre-constructed load distribution model of multiple debris clouds impacting a satellite backplane, and output a load distribution curve on each of the layer structures; Based on the load distribution curve, the damage area of ​​each layer structure caused by the debris cloud is determined, and it is determined whether a back plate in the layer structure is perforated.

2. The method for determining damage caused by space debris impacting a satellite structure according to claim 1, characterized in that: Before determining the number of the satellite structure's laminate structures, the method further includes: Determining the mass relationship between the perforation mass of each of the layer structures and the mass center movement speed and radial expansion speed of the debris cloud; determining a kinetic energy relationship between the kinetic energy of each of the layer structures and the velocity of movement of the center of mass and the velocity of radial expansion of the debris cloud; determining a momentum relationship between the momentum of each of the layer structures and the velocity of movement of the center of mass and the velocity of radial expansion of the debris cloud; A theoretical model of a debris cloud of debris impacting a multilayer plate structure is constructed based on the mass relationship, the kinetic energy relationship and the momentum relationship.

3. The method for determining damage caused by space debris impacting a satellite structure according to claim 2, characterized in that: The quality relationship is: Among them, m bn Indicates the perforation quality of the nth layer of board, t bn represents the thickness of the nth layer, ρ b Indicates the density of the buffer screen material, S n Indicates the distance between the nth layer and the n-1th layer, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v r(n-1) represents the radial expansion speed of the n-1th debris cloud.

4. The method for determining damage caused by space debris impacting a satellite structure according to claim 2, characterized in that: The kinetic energy relationship is: Among them, m p represents the mass of the fragment, m bn Indicates the perforation quality of the nth layer of board, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v r(n-1) represents the radial expansion speed of the n-1th debris cloud, E in represents the internal energy increment of the nth fragment and the n-1th plate during the impact process, E fn It represents the energy absorbed by the crushing of the nth fragment and the n-1th plate.

5. The method for determining damage caused by space debris impacting a satellite structure according to claim 2, characterized in that: The momentum relationship is: m p in c(n-1) =m p in cn +m bn in cn ; Among them, m p represents the fragment mass, v c(n-1) represents the velocity of the center of mass of the n-1th debris cloud, v cn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, m bn Indicates the perforation quality of the nth layer of board.

6. The method for determining damage caused by space debris impacting a satellite structure according to any one of claims 1 to 5, characterized in that: Before determining the number of the satellite structure's laminate structures, the method further includes: Determine the distance between the position of the annular microelement of each debris cloud on the backplane and the impact center; Determine the impulse density of the annular microelement of each debris cloud on the backboard based on the distance between the position of the annular microelement of each debris cloud on the backboard and the impact center, and the moving speed of the center of mass of each debris cloud and the radial expansion speed; Based on the impulse density of the annular microelement of each debris cloud on the backplate, a load distribution model of multiple debris clouds impacting the satellite backplate is constructed.

7. The method for determining damage caused by space debris impacting a satellite structure according to claim 6, characterized in that: The distance between the position of the annular microelement of each debris cloud on the backplane and the impact center is: Among them, R n S represents the distance between the position of the annular element of the nth debris cloud on the backplane and the impact center. n Indicates the distance between the nth layer and the n-1th layer, v cn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, and θ represents the angle between the debris cloud and the axis on the sphere.

8. The method for determining damage caused by space debris impacting a satellite structure according to claim 7, characterized in that: The impulse density of the annular microelement of each debris cloud on the backplane is: Among them, ρ In represents the impulse density of the annular microelement of the nth debris cloud on the backplane, m n represents the mass of the nth debris cloud, v cn represents the velocity of the center of mass of the nth debris cloud, v rn represents the radial expansion speed of the nth debris cloud, θ represents the angle between the debris cloud and the axis on the sphere, R n Represents the distance between the position of the annular element of the nth debris cloud on the backplane and the impact center.

9. The method for determining damage caused by space debris impacting a satellite structure according to any one of claims 1 to 5, characterized in that: The method of determining the damage area of ​​each layer structure caused by the debris cloud based on the load distribution curve and determining whether a back plate in the layer structure is perforated comprises: Based on the load distribution curve on each layer of the plate, the load distribution curve is compared with the critical failure load density of each layer of the plate to determine the number of effectively destroyed layers and obtain the damage area of ​​each layer of the plate; Based on the load distribution curve of the back plate, a comparison is made with the critical failure load density of the back plate. If the load distribution curve is greater than the critical failure load density of the back plate, it is determined that the back plate is perforated, otherwise, there is no perforation.

10. A device for determining damage caused by space debris impacting a satellite structure, characterized in that: include: A first determination module is used to determine the number of laminate structures of the satellite structure; A second determination module is used to determine the mass center movement speed and radial expansion speed of the debris cloud after the debris cloud impacts each of the layer plate structures by using a pre-constructed debris cloud theoretical model of the debris impacting the multi-layer plate structure; An output module, used for inputting each of the mass center moving speeds and the radial expansion speeds into a pre-built load distribution model of multiple debris clouds impacting a satellite back panel, and outputting a load distribution curve on each of the layer plate structures; The third determination module is used to determine the damage area of ​​each layer plate structure caused by the debris cloud based on the load distribution curve, and determine whether the back plate in the layer plate structure is perforated.

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