Impact isolation method for spacecraft return capsule

Abstract

The embodiment of the application provides a spacecraft return cabin impact isolation method, comprising: establishing a geometric model of a spacecraft return system, and the impact isolation device of the spacecraft return cabin is a pyramid type dot matrix structure; adding constraint conditions in the geometric model and applying simulated explosion separation impact loads to perform finite element discretization, dynamic modeling and analysis on the spacecraft return system, simulate the impact process of the spacecraft return cabin caused by the explosion of the explosive in the parachute operation of the parachute, and perform impact spectrum characteristic analysis and stress wave theory analysis on the impact process, and verify and correct the geometric model. The method provided by the embodiment of the application improves the impact isolation device of the spacecraft return cabin into a pyramid type dot matrix structure, and corrects the geometric model of the spacecraft return system, so that the spacecraft return system can better isolate the impact caused by high-frequency excitation.

Description

Technical Field

[0001] The embodiments of the present invention relate to the technical field of aerospace equipment, and in particular to a shock isolation method for a spacecraft re-entry capsule. Background Art

[0002] During the return journey, a spacecraft's reentry capsule often requires parachutes to slow down. This is typically done by exploding explosives. However, explosive detonations generate high-frequency excitation, which can significantly impact the spacecraft's reentry capsule, severely impacting the astronauts and equipment inside.

[0003] In order to reduce the impact of high-frequency excitation generated during parachute operations on astronauts and instruments in the spacecraft's return capsule, related technologies often focus more on improvements to the parachute ropes, while there are fewer improvements to the impact isolation devices of the spacecraft's return capsule. Summary of the Invention

[0004] To overcome at least one aspect of the above-mentioned problems, an embodiment of the present invention provides a method for shock isolation of a spacecraft return capsule, comprising: establishing a geometric model of a spacecraft return system, the spacecraft return system comprising a return capsule, a parachute separation mechanism cabin and a shock isolation device, the parachute separation mechanism cabin being connected to the top of the return capsule, and the shock isolation device being arranged between the return capsule and the parachute separation mechanism cabin; wherein the shock isolation device is a pyramid-shaped lattice structure; adding constraints to the geometric model and applying simulated explosion separation shock loads to perform finite element discretization and dynamic modeling and analysis on the spacecraft return system, simulating the impact process of the explosive explosion on the return capsule during the parachute operation; performing shock spectrum characteristic analysis and stress wave theory analysis on the impact process to verify whether the geometric model meets the predetermined impact requirements; when the geometric model meets the predetermined impact requirements, obtaining a spacecraft return system with a shock isolation device; when the geometric model does not meet the predetermined impact requirements, correcting the geometric model until the geometric model meets the predetermined impact requirements.

[0005] The method provided in an embodiment of the present invention improves the impact isolation device of the spacecraft return capsule into a pyramid-shaped lattice structure, and modifies and optimizes the structure of the impact isolation device, so that the spacecraft return system can better isolate the impact caused by the high-frequency excitation generated by the explosion of explosives during parachute operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0006] Other objects and advantages of the present invention will become apparent from the following description of the embodiments of the present invention with reference to the accompanying drawings, which will help to provide a comprehensive understanding of the present invention.

[0007] Figure 1 is a schematic flow chart of a shock isolation method according to an embodiment of the present invention;

[0008] Figure 2 is a schematic diagram of a spacecraft return system according to one embodiment of the present invention;

[0009] Figure 3 is a schematic diagram of a geometric model of a spacecraft return system according to one embodiment of the present invention;

[0010] Figure 4 is a schematic diagram of a geometric model of an original spacecraft return system according to one embodiment of the present invention;

[0011] Figure 5 is a schematic diagram of sampling points for impact characteristic analysis of a spacecraft return system according to one embodiment of the present invention;

[0012] Figure 6 is a schematic diagram of sampling points for shock characteristic analysis of an original spacecraft return system according to one embodiment of the present invention;

[0013] Figure 7 is a schematic diagram of a shock response spectrum of an original spacecraft return system according to one embodiment of the present invention;

[0014] Figure 8 Schematic diagram of a shock response spectrum of a spacecraft return system according to an embodiment of the present invention.

[0015] It should be noted that the drawings are not necessarily drawn to scale, but are merely shown in a schematic manner that does not affect the reader's understanding. DETAILED DESCRIPTION

[0016] To make the purpose, technical solutions, and advantages of this application more clear, the technical solutions of this application will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of this application. Obviously, the described embodiment is only one embodiment of this application, not all embodiments. Based on the described embodiments of this application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0017] It should be noted that the technical terms or scientific terms used in the present application should be understood as the general meaning understood by those skilled in the art to which the present application belongs, unless otherwise defined. If the description of "first", "second", etc. is involved throughout the text, the "first", "second", etc. is only used to distinguish similar objects, and cannot be understood as indicating or implying the relative importance, the order of precedence or implicitly indicating the number of the indicated technical features. It should be understood that the data of "first", "second", etc. can be interchanged under appropriate circumstances. If "and / or" appears throughout the text, it means that three parallel schemes are included, for example, "A and / or B" includes A scheme, or B scheme, or A and B scheme. In addition, in order to facilitate description, spatial relative terms such as "above", "below", "top", "bottom" and the like can be used here, which are only used to describe the spatial position relationship of one device or feature with other devices or features as shown in the figure. It should be understood to include different orientations in use or operation in addition to the orientation shown in the figure.

[0018] Embodiments of the present application provide a shock isolation method for a spacecraft return capsule. Figure 1 A flowchart of a shock isolation method according to an embodiment of the present application is shown. As shown in Figure 1 The shock isolation method in the embodiment includes the following steps:

[0019] Step 1, a geometric model of a spacecraft return system is established, the spacecraft return system including a return capsule, a parachute separation mechanism cabin and a shock isolation device, the parachute separation mechanism cabin being connected to the top end of the return capsule, and the shock isolation device being arranged between the return capsule and the parachute separation mechanism cabin; wherein the shock isolation device is a pyramid type dot matrix structure;

[0020] Step 2, constraint conditions are added in the geometric model and simulated explosion separation shock loads are applied to perform finite element discretization and dynamic modeling and analysis on the spacecraft return system, to simulate the shock process of the return capsule in the explosion of the parachute operation of the parachute;

[0021] Step 3, shock spectrum characteristic analysis and stress wave theory analysis are performed on the shock process to verify whether the geometric model meets the predetermined shock requirements;

[0022] Step 4, when the geometric model meets the predetermined shock requirements, a spacecraft return system with the shock isolation device is obtained;

[0023] Step 5, when the geometric model does not meet the predetermined shock requirements, the geometric model is corrected until the geometric model meets the predetermined shock requirements.

[0024] The method provided in an embodiment of the present invention improves the impact isolation device of the spacecraft return capsule into a pyramid-shaped lattice structure, and corrects and optimizes the impact isolation device of the spacecraft return system, so that the impact isolation device of the spacecraft return system can better isolate the impact of high-frequency excitation generated by the explosion of explosives during parachute operation on the return capsule.

[0025] Figure 2 Schematic diagram of a spacecraft return system provided by an embodiment of the present invention. Figure 2 As shown, the spacecraft return system in the embodiment of the present invention includes a parachute separation mechanism module 10, a return capsule 20, and a shock isolation device 30. The parachute separation mechanism module 10 is connected to the top of the return capsule 20, and the shock isolation device 30 is disposed between the return capsule 20 and the parachute separation mechanism module 10.

[0026] In this embodiment, a parachute is disposed within the parachute separation mechanism compartment 10. The parachute is ejected from the compartment 10, thereby allowing the return capsule 20 to land safely. A shock isolation device 30 may be connected to the bottom end of the parachute separation mechanism compartment 10, such that the shock isolation device 30 is disposed between the return capsule 20 and the parachute separation mechanism compartment 10.

[0027] During a parachute ejection operation, the explosives in the parachute separation mechanism compartment 10 explode, generating a radiating impact force that can eject the parachute. Simultaneously, the impact force generated by the explosives explosion is transmitted downward to the return capsule 20. In this embodiment of the present invention, a shock isolation device 30 is provided between the return capsule 20 and the parachute separation mechanism compartment 10. The shock isolation device 30 transmits the impact force generated by the explosives explosion during the parachute ejection operation to the return capsule 20 via the shock isolation device 30. The unique structure of the shock isolation device 30 hinders the propagation of the impact force during the parachute ejection operation, thereby reducing the impact of high-frequency excitation on the return capsule 20, preventing the impact from significantly affecting the astronauts and instruments within the return capsule 20, and providing effective protection for the return capsule 20.

[0028] Specifically, the impact isolation device 30 is a pyramid-shaped lattice structure. Figure 2 As shown, in some embodiments, the pyramid-shaped lattice structure may include a pyramid-shaped lattice core 31 and connecting plates 32 connected to both ends of the pyramid-shaped lattice core 31. In some embodiments, the pyramid-shaped lattice core 31 includes multiple rods, which are obliquely arranged between two connecting plates 32. The multiple rods are interconnected to form the pyramid-shaped structure. The connecting plates 32 and the rods may be made of steel or aluminum alloy.

[0029] The pyramid-shaped lattice structure has a complex stress wave transmission path, which is conducive to hindering the propagation of stress waves. At the same time, the pyramid-shaped lattice structure has excellent specific strength and specific stiffness, and is lighter than other materials. In addition, the pyramid-shaped lattice structure is resistant to high temperatures and has stable structural performance, which meets the material requirements of the spacecraft return capsule. In the embodiment of the present invention, by providing an impact isolation device with a pyramid-shaped lattice structure, the stress wave impedance of the parachute separation mechanism cabin interface is increased, the reflectivity of the stress wave is increased, and the impact of high-frequency excitation on the return capsule is reduced, thereby achieving impact isolation during the parachute launch operation.

[0030] In some embodiments, in order to determine the specific structural parameters of the pyramid-shaped lattice structure and achieve better impact isolation effect, in an embodiment of the present invention, the specific structural parameters of the pyramid-shaped lattice structure are analyzed and determined by constructing a model and performing finite element discretization and dynamic modeling on the model.

[0031] In some embodiments, when constructing the model, the spacecraft return system can be parametrically modeled, with the dimensional parameters of the spacecraft return system set as variables to achieve dimensional parameterization. Furthermore, the dimensions of the impact isolation device 30 must match the dimensions of the interface between the parachute separation mechanism compartment 10, so that the impact isolation device 30 can fully isolate the return capsule 20 from the parachute separation mechanism compartment 10.

[0032] In step 2, when performing finite element discretization and dynamic modeling on the spacecraft return system, the geometric model of the spacecraft return system can be constructed first, such as Figure 3 As shown, the geometric model is then meshed and constraints are added to the geometric model to obtain a finite element model of the spacecraft return system for finite element discretization and dynamic modeling and analysis.

[0033] Specifically, a geometric model of a spacecraft re-entry system containing a pyramidal lattice structure can be established. Constraints can be added to the geometric model, and simulated explosive separation impact loads can be applied to simulate the high-frequency excitation generated by the explosion. Furthermore, a transient dynamic analysis of the spacecraft re-entry system can be performed to simulate the impact of explosive detonations on the re-entry capsule during parachute deployment.

[0034] In some embodiments, adding constraints to the geometric model includes: adding a triangular wave excitation to the explosive explosion location of the parachute in the geometric model. After adding the triangular wave excitation, the triangular wave excitation can work together with the simulated explosion separation impact load, so that the impact load on the impact isolation device is a positive triangular wave force, rather than a constant force. In addition, the positive triangular wave force has a short action time and will gradually decay and disappear, while the constant force continues, which will cause the simulation program to be unable to end in subsequent simulations. By adding a triangular wave excitation, this embodiment can simulate the actual situation of the impact force generated by the explosion of explosives pushing the parachute upward and simultaneously impacting the return capsule downward, so as to restore the actual working conditions during the parachute operation as much as possible. For example, the triangular wave excitation can have a period of 400us, and the peak value of the triangular wave excitation can be 2KN.

[0035] In some embodiments, adding constraints to the geometric model further includes: adding Rayleigh damping to the pyramid lattice structure. By adding Rayleigh damping, the damping of real shock-absorbing materials can be simulated, making the simulation of the impact process more accurate. The damping matrix of Rayleigh damping is a combination of the stiffness matrix and the mass matrix. When adding Rayleigh damping, the coefficient α of the stiffness matrix can be 0.001, and the coefficient β of the mass matrix can be 3.15×10 -7 .

[0036] Furthermore, after finite element modeling of the spacecraft re-entry system, the transient dynamics of the impact process can be analyzed, and the geometric model can be verified based on the analysis results to determine whether the geometric model is correct and whether the geometric model needs to be modified.

[0037] In some embodiments, the impact process can be analyzed through shock spectrum characteristics and stress wave theory to verify whether the geometric model meets the predetermined impact requirements. If the geometric model meets the predetermined impact requirements, a spacecraft reentry capsule structure with a shock isolation device is obtained. If the geometric model does not meet the predetermined impact requirements, the geometric model is modified and subjected to finite element discretization, dynamic modeling, and analysis until the geometric model meets the predetermined impact requirements. Based on the geometric model that meets the predetermined impact requirements, the specific structural parameters of the pyramid lattice structure can be determined, and a shock isolation device that meets the impact requirements can be obtained.

[0038] In some embodiments, the modified geometric model may include at least one of the following: dimensional parameters of the modified geometric model, constraints, and simulated explosive separation impact loads. In some embodiments, the dimensional parameters of the geometric model may include at least one of the following: a pitch angle, a cross-sectional shape, a rod length, and a wall thickness of the pyramidal lattice structure.

[0039] In some embodiments, a parachute impact simulation experiment can be conducted on the original spacecraft return system to obtain the actual impact response value and allowable impact response value of the explosive explosion on the return capsule 20 during the parachute operation. Figure 4 As shown, the original spacecraft return system includes a return capsule 20 and a parachute separation mechanism module 10 connected to the top of the return capsule 20.

[0040] The original spacecraft return system is the unmodified spacecraft return capsule. Figure 4 As shown, the original spacecraft return system may include a return capsule 20 and a parachute separation mechanism module 10 connected to the top of the return capsule 20. A partition 40 is connected between the parachute separation mechanism module 10 and the top of the return capsule 20. The partition 40 can serve as a shock isolation device in the original spacecraft return system, providing a certain degree of shock isolation. By conducting parachute impact simulation experiments on the original spacecraft return system, the actual shock response value and allowable shock response value of the return capsule 20 caused by the explosive explosion during the parachute operation can be obtained.

[0041] The actual shock response values ​​and the allowable shock response values ​​can be used to determine the specific structural parameters of the pyramidal lattice structure during model construction and verification. In some embodiments, the simulated explosive separation shock load applied to the geometric model can be determined based on the actual shock response values. For example, the simulated explosive separation shock load determined based on the actual shock response values ​​can be 10 kN. The allowable shock response values ​​can serve as a reference for determining predetermined shock requirements when verifying whether the geometric model in the spacecraft re-entry system meets predetermined shock requirements.

[0042] In order to verify whether the geometric model meets the predetermined impact requirements, the impact process can be subjected to shock spectrum characteristic analysis and stress wave theory analysis.

[0043] In some embodiments, shock spectrum analysis of the impact process includes extracting the acceleration transient response of the parachute explosive explosion point and the top end surface of the reentry capsule in the geometric model; processing the acceleration transient response data to obtain a shock response spectrum; and verifying whether the geometric model meets preset shock requirements based on the shock response spectrum. The shock response spectrum can also be used to verify whether the stress attenuation meets the requirements.

[0044] Specifically, when verifying whether the geometric model meets the preset impact requirements based on the impact response spectrum, the attenuation degree of the stress wave generated by the explosion separation shock from the explosion point of the parachute explosive to the top of the re-entry capsule can be determined based on the impact response spectrum; verify whether the attenuation degree meets the preset attenuation value; when the attenuation degree meets the preset attenuation value, the geometric model meets the preset impact requirements.

[0045] like Figure 5As shown, when performing shock spectrum characteristic analysis, sampling points (as shown by the arrows in the figure) can be set on the upper surface of the shock isolation device 30 to obtain the shock response at the shock isolation device 30, and sampling points can be set on the upper surface of the return capsule 20 to obtain the shock response at the return capsule 20 to determine the attenuation degree of the stress wave generated by the explosive separation shock from the explosion point of the parachute explosive to the top of the return capsule, thereby determining the isolation effect of the shock isolation device 30 on the impact force.

[0046] Specifically, the shock response spectrum at the sampling points can be obtained, and the degree of stress wave attenuation can be determined based on the relative coefficients in the shock response spectrum at the two sampling points. The relative coefficients of the shock response spectrum include the maximum value Er and the average value Mr of the shock acceleration.

[0047] In this embodiment, the acceleration transient response at the sampling point in the geometric model may be obtained and data processed to obtain an impulse response time domain diagram and an impulse response spectrum.

[0048] In some embodiments, since the original spacecraft return system is equipped with a partition, it can also attenuate stress and produce a certain degree of impact isolation. Therefore, when performing shock spectrum characteristic analysis on the impact process of the improved spacecraft return system, if the stress wave generated by the explosion separation shock does not attenuate or attenuates very little, it can be considered that there is an error in the established finite element model, and it is necessary to readjust the constraints such as the triangular wave excitation or the simulated explosion separation shock load.

[0049] Specifically, the same finite element discretization and dynamic modeling and analysis can be performed on the original spacecraft return system to determine the attenuation effect of the partition in the original spacecraft return system on the impact force during the parachute operation. Figure 4 As shown, the original spacecraft return system is geometrically modeled to obtain the geometric model of the original spacecraft return system, and constraints are imposed on it and transient dynamics analysis is performed.

[0050] Specifically, the shock spectrum characteristics of the impact process during the parachute operation can be analyzed to obtain the attenuation degree of the stress wave generated by the explosion separation shock in the original spacecraft return system from the explosion point of the parachute explosive to the top of the return capsule. Figure 6 As shown, when performing shock spectrum characteristic analysis, sampling points can be set on the upper surface of the partition 40 to obtain the shock response at the partition 40, and sampling points can be set on the upper surface of the return capsule 20 to obtain the shock response at the return capsule 20, so as to determine the attenuation degree of the stress wave generated by the explosive separation shock from the explosion point of the parachute explosive to the top of the return capsule.

[0051] If the stress wave generated by the explosion in the improved spacecraft re-entry system is attenuated no more than the original spacecraft re-entry system after passing through the shock isolation device, the geometric model of the spacecraft re-entry system needs to be revised. If the stress wave generated by the explosion in the improved spacecraft re-entry system is attenuated more than the original spacecraft re-entry system after passing through the shock isolation device, the geometric model of the spacecraft re-entry system is correct.

[0052] When the geometric model is correct, further verification can be performed to determine whether the geometric model meets predetermined impact requirements. In some embodiments, when the impact response at the reentry capsule 20 does not exceed the allowable impact response, the geometric model of the spacecraft reentry system meets the predetermined impact requirements. If the geometric model does not meet the predetermined impact requirements, the impact response of the reentry capsule 20 can be adjusted to meet the requirements by adjusting the dimensional parameters of the pyramidal lattice structure in the impact isolation device 30, such as the pitch angle, cross-sectional shape, rod length, and wall thickness.

[0053] In some embodiments, when performing stress wave theory analysis on the impact process, the transmittance and reflectance of the impact isolation device can be calculated based on the size of the impact isolation device. Based on the transmittance and reflectance of the impact isolation device, it can be verified whether the geometric model meets the preset impact requirements. In some embodiments, the size of the impact isolation device can include the area of ​​the connecting plate 32 and the contact area between the pyramid-shaped lattice sandwich 31 and the connecting plate 32. The transmittance and reflectance of the impact isolation device can be calculated using the following formula (1).

[0054]

[0055] In formula (1), σT / σI is the transmittance of the shock isolation device; σR / σI is the reflectivity of the shock isolation device; where σI is the stress of the incident wave, σT is the stress of the transmitted wave, and σR is the stress of the reflected wave; R A is the area ratio, R A =A2 / A1, wherein A1 is the area of ​​the connecting plate 32, and A2 is the contact area between the pyramid-shaped lattice core 31 and the connecting plate 32.

[0056] In some embodiments, when the transmittance of the impact isolation device is less than a transmittance threshold and the reflectance is greater than a reflectance threshold, the geometric model meets the preset impact requirement.

[0057] Figure 7 Shown is a shock response spectrum of an original spacecraft re-entry system according to one embodiment of the present invention. Figure 8 FIG. 4 shows a shock response spectrum of a spacecraft return system according to an embodiment of the present invention.

[0058] like Figure 7 and Figure 8 As shown, in the original spacecraft re-entry system, the relative coefficients Er and Mr in the shock response spectrum decay as the stress wave generated by the shock propagates from the explosion-side upper surface of the bulkhead 40 to the non-explosion-side upper surface of the re-entry capsule. The average interface attenuation from the upper surface of the bulkhead 40 to the upper surface of the re-entry capsule is 26.79%, with a maximum of 25.27%. In the improved spacecraft re-entry system, namely the one equipped with a pyramid-shaped lattice structure, the average interface attenuation from the upper surface of the shock isolation device 30 to the upper surface of the re-entry capsule is 77.88%, with a maximum of 80.65%, meeting the shock isolation requirements of actual parachute missions.

[0059] The analysis results show that after adding the pyramid lattice structure, the stress wave generated by the explosion shock during the parachute operation was significantly reflected, the shock response was fully suppressed, and the spacecraft return system was able to effectively achieve shock isolation.

[0060] The embodiments of the present invention employ a pyramidal lattice structure as a shock isolation device between the reentry capsule and the parachute separation mechanism compartment. This structure utilizes the pyramidal lattice structure's complex transmission path to increase the stress wave impedance at the parachute separation mechanism compartment interface, enhancing stress wave reflectivity and reducing shock response. This achieves shock isolation during parachute deployment and provides more effective protection for the reentry capsule. Furthermore, the pyramidal lattice structure boasts excellent specific strength and stiffness, making it lighter than other structures, achieving ideal shock isolation with minimal weight gain.

[0061] Regarding the embodiments of the present invention, it should also be noted that, in the absence of conflict, the embodiments of the present invention and the features therein may be combined with each other to obtain new embodiments.

[0062] The above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. The protection scope of the present invention shall be based on the protection scope of the claims.

Claims

1. A method for isolating a spacecraft return capsule from shock, characterized in that: include: Establish a geometric model of a spacecraft re-entry system, comprising a re-entry capsule, a parachute separation mechanism capsule, and a shock isolation device, wherein the parachute separation mechanism capsule is connected to the top of the re-entry capsule, and the shock isolation device is disposed between the re-entry capsule and the parachute separation mechanism capsule; wherein the shock isolation device has a pyramidal lattice structure; Adding constraints to the geometric model and applying simulated explosion separation impact loads to perform finite element discretization and dynamic modeling and analysis on the spacecraft re-entry system, simulating the impact process of explosive explosion on the re-entry capsule during the parachute operation; Performing shock spectrum characteristic analysis and stress wave theory analysis on the shock process to verify whether the geometric model meets the predetermined shock requirements; When the geometric model meets a predetermined impact requirement, obtaining a spacecraft return system with a shock isolation device; When the geometric model does not meet the predetermined impact requirement, the geometric model is modified until the geometric model meets the predetermined impact requirement.

2. The shock isolation method according to claim 1, characterized in that: Add constraints to the geometric model, including: In the geometric model, a triangular wave excitation is added to the explosive explosion location of the parachute.

3. The shock isolation method according to claim 2, characterized in that: Adding constraints to the geometric model also includes: Rayleigh damping is added to the pyramid lattice structure.

4. The shock isolation method according to claim 1, characterized in that: Also includes: A parachute impact simulation experiment was conducted on the original spacecraft return system to obtain the actual impact response value and allowable impact response value of the explosive explosion on the return capsule during the parachute operation; wherein, The original spacecraft return system includes the return capsule and the parachute separation mechanism cabin connected to the top of the return capsule.

5. The shock isolation method according to claim 4, characterized in that: The simulated explosion separation impact load applied to the geometric model is determined according to the actual impact response value.

6. The shock isolation method according to claim 1, characterized in that: Performing shock spectrum characteristic analysis on the shock process, including: Extracting the acceleration transient response of the parachute explosive explosion point and the top end surface of the reentry capsule in the geometric model; performing data processing on the acceleration transient response to obtain an impact response spectrum; According to the shock response spectrum, it is verified whether the geometric model meets the preset shock requirements.

7. The shock isolation method according to claim 6, characterized in that: Verifying whether the geometric model meets preset impact requirements according to the impact response spectrum includes: determining, based on the shock response spectrum, the attenuation degree of the stress wave generated by the explosive separation shock from the explosion point of the parachute explosive to the top of the reentry capsule; Verifying whether the attenuation degree meets a preset attenuation value; When the attenuation degree meets the preset attenuation value, the geometric model meets the preset impact requirement.

8. The shock isolation method according to claim 1, characterized in that: The impact process is subjected to stress wave theory analysis, including: Calculating the transmittance and reflectance of the impact isolation device according to the size of the impact isolation device; According to the transmittance and reflectivity of the impact isolation device, it is verified whether the geometric model meets the preset impact requirements.

9. The shock isolation method according to claim 8, characterized in that: When the transmittance of the impact isolation device is less than a transmittance threshold and the reflectance is greater than a reflectance threshold, the geometric model meets the preset impact requirement.

10. The shock isolation method according to claim 8, characterized in that: The impact isolation device includes a pyramid-shaped lattice sandwich core and connecting plates connected to both ends of the pyramid-shaped lattice sandwich core; The dimensions of the impact isolation device include: the area of ​​the connecting plate and the contact area between the pyramid-shaped lattice core and the connecting plate.

11. The shock isolation method according to claim 10, characterized in that: Modifying the geometric model includes at least one of the following: The dimension parameters of the geometric model, the constraint conditions and the simulated explosion separation impact load are modified.

12. The shock isolation method according to claim 11, characterized in that: The pyramid-shaped lattice sandwich includes a plurality of rods, and the plurality of rods are obliquely arranged between the two connecting plates; The size parameters of the geometric model include at least one of the following: a pitch angle, a cross-sectional shape, a length and a wall thickness of the pyramid-shaped lattice structure.

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