Land simulation device for equivalent acceleration of vertical entry of aircraft into water

Abstract

This invention relates to the field of equivalent acceleration simulation technology for vertical water entry of aircraft. To address the technical problem of existing water entry acceleration load measurement methods lacking a model and method for effectively simulating the acceleration of aircraft entering water on land, the present invention provides a technical solution: an equivalent impact environment model for aircraft entering water, comprising: an aircraft, with aircraft supports at both ends of the aircraft, the aircraft support at the head being mounted in a loading cylinder, and the aircraft support at the tail being mounted in a buffer cylinder; the buffer cylinder is used to provide a buffer for the aircraft when subjected to an impact load; and the loading cylinder is fixed to the loading hole of the acceleration load loading device. This invention can be applied to the performance evaluation of aircraft subjected to water entry impact.

Description

Technical Field

[0001] The invention relates to the technical field of acceleration equivalent simulation of a spacecraft entering water. Background Art

[0002] Cross-medium vehicles are essential tools for modern marine research and rescue operations. They play a vital role in improving maritime rescue efficiency, promoting marine scientific research, ensuring maritime safety, and responding to marine disasters. They are indispensable tools for modern marine activities. Cross-medium vehicles are typically launched into water via airdrop or boost. During water entry, their heads are often subjected to significant slamming acceleration loads, which can impact or even damage important equipment within the vehicle. Therefore, conducting water entry tests to investigate the accelerations experienced by the vehicle and its response is crucial.

[0003] Existing simulation tests for water entry processes are mainly divided into tank tests and sea trials. Tank tests are favored for their strong controllability and accurate data, but are restricted by the environment and have certain limitations in scale and cost. In contrast, the results of sea trials are more reliable and not limited by scale, but they are costly, require long preparation times, and present challenges in data collection. Given the high cost, long preparation times, and strict site requirements of tank and sea trials, developing a land-equivalent simulation method for the simulated water entry process of a vehicle has become a more convenient option, aiming to accurately, economically, conveniently, and quickly evaluate the loads and responses of the vehicle during water entry.

[0004] Currently, most land-based simulations of vehicle entry into water typically involve fixing the vehicle and applying a load to its nose. However, these existing methods struggle to simulate the acceleration loads and structural response during water entry. Therefore, designing a model and method that can effectively simulate vehicle acceleration on land remains a challenging technical challenge. This is crucial for improving the safety and reliability of vehicle design, particularly in civilian applications such as marine research and rescue operations. Summary of the Invention

[0005] To solve the technical problem in the prior art that there is no technology that can effectively simulate the water entry acceleration model and method of the vehicle on land in the existing water entry acceleration load measurement method, the present invention provides the following technical solutions:

[0006] A land-based simulation device for equivalent acceleration of a vertical entry of a vehicle into water, the model comprising:

[0007] A spacecraft, wherein both ends of the spacecraft are provided with a spacecraft support, the spacecraft support at the head of the spacecraft is arranged in a loading cylinder, and the spacecraft support at the tail of the spacecraft is arranged in a buffer cylinder;

[0008] When the aircraft is subjected to an acceleration load, the buffer cylinder is used to provide buffering for the aircraft;

[0009] The loading cylinder is fixed on the loading hole of the acceleration load loading device.

[0010] Furthermore, a preferred embodiment is provided, wherein the buffer cylinder is arranged on the top of the fixing frame, and the fixing frame is in a gate shape.

[0011] Furthermore, a preferred embodiment is provided, wherein the aircraft support comprises an aircraft cover and a piston, and the position of the aircraft relative to the aircraft support is fixed by the aircraft cover.

[0012] Furthermore, a preferred embodiment is provided in which a portion where the loading cylinder is connected to the acceleration load loading device is provided with a boss for stabilizing the connection between the loading cylinder and the loading hole.

[0013] Furthermore, a preferred embodiment is provided, wherein the buffer cylinder includes a shock-absorbing cylinder and a hollow conduit, the shock-absorbing cylinder is used to provide a buffering capacity, and the hollow conduit is used to limit the movement of the aircraft only along its own axis.

[0014] Furthermore, a preferred embodiment is provided, wherein the hollow conduit comprises two semi-cylindrical hollow curved plates, and the two semi-cylindrical hollow curved plates are respectively a part of a cylinder that can be sleeved on the aircraft.

[0015] Furthermore, a preferred embodiment is provided, wherein the shock absorbing tube is connected to the fixing frame via a slot, and the shock absorbing tube provides a buffering capacity via a spring and a piston.

[0016] Based on the same inventive concept, the present invention also provides a design method for the land-based simulation device for equivalent acceleration of a vertical entry of a vehicle into water, comprising:

[0017] Steps for collecting target water entry acceleration load parameters;

[0018] According to the parameters, a step of obtaining a load peak value and a pulse width required to be provided by the acceleration load loading device;

[0019] The step of obtaining the diameter of the aircraft support, the loading cylinder and the length of the loading cylinder according to the load peak value and the pulse width.

[0020] Based on the same inventive concept, the present invention also provides a computer storage medium for storing a computer program. When the computer program is read by a computer, the computer executes the method described above.

[0021] Based on the same inventive concept, the present invention also provides a computer, comprising a processor and a storage medium. When the processor reads the computer program stored in the storage medium, the computer executes the method described above.

[0022] Compared with the prior art, the technical solution provided by the present invention is beneficial in that:

[0023] The land-based simulation device for equivalent acceleration of vertical water entry of an aircraft provided by the present invention can greatly reduce the test cost and preparation time and improve the efficiency of the test compared to traditional water tank tests and sea tests.

[0024] The invention provides a land-based simulation device for equivalent acceleration of a vertical entry of a vehicle into water. The use of an acceleration load loading device for land-based testing can avoid potential safety risks in sea-based testing and ensure the safety of test personnel.

[0025] The equivalent acceleration land simulation device for vertical entry of an aircraft into water provided by the present invention solves the problem in the prior art that it is difficult to simulate the acceleration load of an aircraft entering water by using a land-based experimental device by simulating the acceleration load of an equivalent water entry impact.

[0026] The land-based simulation device for equivalent acceleration of vertical entry of an aircraft into water provided by the present invention has the advantages of low cost, short preparation time, and high safety compared to water tank tests and sea tests, and can better evaluate the performance of an aircraft under water impact.

[0027] The equivalent acceleration land simulation device for vertical entry of an aircraft into water provided by the present invention can be applied to the work of evaluating the impact of aircraft entering water. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] Figure 1 This is a three-dimensional schematic diagram of the land simulation device for the equivalent acceleration of a vertical entry into water of a spacecraft.

[0029] Figure 2 This is a schematic diagram of the installation of the vehicle model and the bow and stern supports in the land simulation device for the equivalent acceleration of the vehicle vertically entering water.

[0030] Figure 3 This is a schematic diagram of the installation and connection of the acceleration load loading device and the loading cylinder in the land simulation device for the equivalent acceleration of a vertical entry into water of a vehicle.

[0031] Figure 4 This is a cross-sectional view of the loading cylinder of the acceleration load loading device in the land simulation device for the equivalent acceleration of a vertical entry into water of a vehicle.

[0032] Figure 5Schematic diagram of the buffer cylinder structure of the equivalent acceleration load model of the aircraft in the equivalent acceleration land simulation device for vertical entry of the aircraft into water.

[0033] Figure 6 This is a perspective view of the buffer structure at the bottom of the buffer cylinder in the design method of the land simulation device for the equivalent acceleration of a vertical entry into water of a vehicle.

[0034] Figure 7 It is a simplified triangle curve of the target environment acceleration.

[0035] Figure 8 It is a simplified triangle load curve for the target environment.

[0036] Among them, 1 represents the aircraft, 2 represents the loading cylinder, 3 represents the aircraft support, 4 represents the acceleration load loading device, 5 represents the hollow conduit, 6 represents the buffer cylinder, 7 represents the fixing frame, 8 represents the aircraft cover, 9 represents the piston, 10 represents the loading hole, 11 represents the boss, 12 represents the semi-cylindrical hollow bent plate, 13 represents the semi-cylindrical hollow bent plate, 14 represents the spring, and 15 represents the piston. DETAILED DESCRIPTION

[0037] In order to make the advantages and benefits of the technical solution provided by the present invention more clearly reflected, the technical solution provided by the present invention is now further described in detail with reference to the accompanying drawings, specifically:

[0038] Embodiment 1: This embodiment provides a land simulation device for equivalent acceleration of a vertical entry of a vehicle into water, the model comprising:

[0039] A spacecraft, wherein both ends of the spacecraft are provided with a spacecraft support, the spacecraft support at the head of the spacecraft is arranged in a loading cylinder, and the spacecraft support at the tail of the spacecraft is arranged in a buffer cylinder;

[0040] When the aircraft is subjected to an acceleration load, the buffer cylinder is used to provide buffering for the aircraft;

[0041] The loading cylinder is fixed on the loading hole of the acceleration load loading device.

[0042] Implementation method 2: This implementation method further limits the land simulation device for equivalent acceleration of a vertical entry of a vehicle into water provided in implementation method 1. The buffer cylinder is arranged on the top of the fixing frame, and the fixing frame is in a gate shape.

[0043] Implementation method three: This implementation method further limits the land simulation device for equivalent acceleration of vertical entry of an aircraft into water provided in implementation method one. The aircraft support includes an aircraft cover and a piston, and the position of the aircraft relative to the aircraft support is fixed by the aircraft cover.

[0044] Implementation method 4. This implementation method further limits the land simulation device for equivalent acceleration of vertical entry of a vehicle into water provided in implementation method 1. The portion where the loading cylinder is connected to the acceleration load loading device is provided with a boss for stabilizing the connection between the loading cylinder and the loading hole.

[0045] Implementation method five. This implementation method further limits the land simulation device for the equivalent acceleration of a vertical entry of an aircraft into water provided in implementation method two. The buffer cylinder includes a slamming shock-absorbing cylinder and a hollow duct. The slamming shock-absorbing cylinder is used to provide a buffering capacity, and the hollow duct is used to limit the aircraft to move only along its own axis.

[0046] Implementation method six. This implementation method further limits the land simulation device for equivalent acceleration of vertical entry of an aircraft into water provided in implementation method five. The hollow conduit includes two semi-cylindrical hollow bent plates, and the two semi-cylindrical hollow bent plates are respectively: a part of a cylinder that can be sleeved on the aircraft.

[0047] Implementation method seven. This implementation method further limits the land simulation device for equivalent acceleration of vertical entry of a vehicle into water provided in implementation method five. The impact shock absorber is connected to the fixing frame through a slot, and the shock absorber provides buffering capacity through a spring and a piston.

[0048] Embodiment 8: This embodiment provides a design method for a land-based simulation device for a vertical entry of a vehicle into water equivalent acceleration, as provided in Embodiment 1, including:

[0049] Steps for collecting target water entry acceleration load parameters;

[0050] According to the parameters, a step of obtaining a load peak value and a pulse width required to be provided by the acceleration load loading device;

[0051] The step of obtaining the diameter of the aircraft support, the loading cylinder and the length of the loading cylinder according to the load peak value and the pulse width.

[0052] Implementation method 9: This implementation method provides a computer storage medium for storing a computer program. When the computer program is read by a computer, the computer executes the method provided in implementation method 8.

[0053] Implementation 10: This implementation provides a computer, including a processor and a storage medium. When the processor reads the computer program stored in the storage medium, the computer executes the method provided in Implementation 8.

[0054] Implementation Method 11: Combination Figure 1-8 This embodiment further describes the technical solution provided above through specific examples, specifically:

[0055] See also Figure 1 , this embodiment provides an equivalent acceleration load model of the acceleration of a vehicle entering water under an acceleration load, the equivalent acceleration load model includes a vehicle 1, a loading cylinder 2, a vehicle support 3, an acceleration load loading device 4, a buffer cylinder 6 and a fixing frame 7, the vehicle support 3 is arranged at both ends of the vehicle 1 for supporting the vehicle, wherein the vehicle support 3 at the head of the vehicle 1 is arranged in the loading cylinder 2, wherein the vehicle support 3 at the tail of the vehicle 1 is arranged in the buffer cylinder 6, the loading cylinder 2 is arranged on the loading hole of the acceleration load loading device 4 and is fixed by a flange, the buffer cylinder 6 is arranged on the top of the fixing frame 7 and is used to receive the vehicle 1 that jumps up due to the acceleration load, and the acceleration load loading device 4 is arranged at the bottom of the fixing frame 7 and is welded and fixed thereto.

[0056] The aircraft 1 is a rotating body aircraft, and the aircraft support 3 is provided at both the head and the tail of the aircraft, wherein the aircraft support 3 at the head of the aircraft 1 is provided in the loading cylinder 2, wherein the aircraft support 3 at the tail of the aircraft 1 is provided in the buffer cylinder 6, wherein the loading cylinder 2 is provided on the loading hole of the acceleration load loading device 4 and is fixed by a flange, and the diameter of the loading cylinder 2 can be designed and adjusted according to the diameter of the aircraft. The buffer cylinder 6 is provided on the top of the fixing frame 7 and is used to receive the aircraft 1 that is jumped by the acceleration load. In order to prevent the acceleration load loading device from jumping under the action of the acceleration load, the acceleration load loading device 4 is provided at the bottom of the fixing frame 7 and is fixed by welding.

[0057] See also Figure 2 This embodiment further limits the equivalent acceleration land simulation device for vertical entry of an aircraft into water under acceleration load described in embodiment 1. An aircraft support 3 is provided at the bow and tail ends of the aircraft 1, and the aircraft support 3 is composed of an aircraft cover 8 and a piston 9.

[0058] See also Figure 3 and 4 This embodiment further defines the equivalent acceleration land simulation device for vertical entry of an aircraft into water under acceleration load described in the first embodiment. A loading hole 10 is provided directly above the acceleration load loading device 4. The loading cylinder 2 is mounted above the acceleration load loading device at the loading hole position and secured by a flange. Furthermore, the diameter of the circular portion below the loading cylinder connected to the loading hole is larger than the diameter of the inner wall of the loading cylinder. In this manner, a boss 11 is designed to provide support before loading, allowing the aircraft to stand inside the loading cylinder. Furthermore, after loading, the aircraft jumps to its highest position, impacts the buffer in the buffer cylinder, and then falls to protect the aircraft, preventing it from falling into the acceleration load loading device.

[0059] See also Figure 5This embodiment further defines the equivalent acceleration land simulation device for a vertical entry of an aircraft into water under acceleration load described in Embodiment 1. The buffer cylinder 6 comprises a hollow conduit and a shock-absorbing cylinder. The hollow conduit is composed of a semi-cylindrical hollow curved plate 12 on one side and a semi-cylindrical hollow curved plate 13 on the other side, which are secured by external bolts and flanged to the shock-absorbing cylinder. During installation, the semi-cylindrical hollow curved plate is first installed. The aircraft, with the aircraft holder installed, is then placed within the loading cylinder with the other end contacting the inner wall of the semi-cylindrical hollow curved plate. Finally, the other semi-cylindrical hollow curved plate is installed via the flange structure on the side of the semi-cylindrical hollow curved plate.

[0060] See also Figure 6 One end of the shock-absorbing tube is fixed to the hollow conduit 5 via a flange, while the other end is designed with a slot for connection and fixation with the mounting bracket 7. A buffer is installed inside the buffer tube. The buffer mainly consists of two parts: a spring 14 and a piston 15. The two ends of the buffer spring are connected to the bottom of the buffer tube and the piston respectively. The buffer can reduce vibration and protect the aircraft when it jumps under acceleration load, and facilitate the recovery of the aircraft.

[0061] The mounting frame 7 is constructed from square steel tubes, I-beams, and toggle plates. In this embodiment, the beams of the mounting frame are made of square steel. To prevent the acceleration load-applying device from jumping during loading, it is welded to the horizontal steel at the bottom of the mounting frame. A buffer cylinder is welded to the center of the top beam of the mounting frame.

[0062] This embodiment also provides a method for designing a land simulation device for equivalent acceleration of a vertical entry of a vehicle into water, the method comprising the following steps:

[0063] S1. Arrange sensors on components or target locations within the vehicle body;

[0064] S2. Design the peak load and pulse width required by the acceleration load loading device based on the target acceleration;

[0065] S3. Design the diameter of the aircraft support and the loading tube, as well as the length of the loading tube, according to the aircraft model;

[0066] S4, fixing the loading cylinder described in S3 above the loading hole of the acceleration load loading device via a flange connection;

[0067] S5. Connect the two ends of the aircraft model obtained in S4 to the aircraft support through side threads;

[0068] S6. Place the tail end of the assembled spacecraft obtained in S5 into the loading cylinder described in S2, and connect the other end to the semi-cylindrical hollow elbow, and then install the semi-cylindrical hollow elbow on the other side;

[0069] S7. Apply acceleration load and complete the test.

[0070] It is generally believed that the acceleration load on the aircraft in the water entry problem is a triangular load. The acceleration curve of the aircraft is similar to the load curve. The acceleration curve of the aircraft is simplified to a triangular acceleration, such as Figure 7 shown.

[0071] According to the target acceleration, design the appropriate load peak and pulse width, and use the acceleration load loading device to provide the load. According to the formula:

[0072] F=P s ·S effective ,

[0073]

[0074] The peak load P can be derived s for:

[0075]

[0076] Where, P s is the peak load, F is the loading force, S effective is the effective loading area on the piston force surface, a is the target acceleration of the spacecraft, G is the gravity acting on the spacecraft, and m is the mass of the spacecraft.

[0077] It can be seen that the peak pressure of the triangular acceleration load is calculated. During the acceleration load loading process, when the spacecraft reaches a certain height after jumping, the acceleration drops to 0 at time t0. At this time, the acceleration load P0 is equal to the spacecraft's own gravity G. According to the similarity of the triangle, the load pulse width τ can be derived according to the following formula:

[0078]

[0079] The triangular acceleration load curve is as follows Figure 8 shown.

[0080] The time t0 is the moment when the load is equal to the gravity.

[0081] The diameter of the loading cylinder (S3) is determined based on the diameter of the vehicle. It needs to be larger than the vehicle's main diameter, with a margin to ensure frictional resistance between the vehicle support and the loading cylinder wall. The diameter of the boss 11 is larger than the inner diameter of the loading cylinder. This provides support before loading, allowing the vehicle to stand within the loading cylinder. It also protects the vehicle from falling after it reaches its highest point and impacts the buffer inside the buffer cylinder, preventing it from falling into the acceleration load loading device.

[0082] Since the first-stage shock wave load lasts for τ, the length of the loading tube needs to be designed so that the vehicle can travel a full distance inside the loading tube to fully receive the target load. The length of the loading tube in S2 can be changed through design or by adding additional loading tubes connected by flanges. Since the shock wave load is a triangular load, considering the influence of gravity, the loading tube length l should satisfy the following formula:

[0083] l>h piston ,

[0084]

[0085] Where, v t Refers to the speed of the spacecraft at time t, h piston It is the thickness of the aircraft's tailstock piston.

[0086] S6: The aircraft, after the aircraft support is installed, is placed in the loading cylinder. First, the semi-cylindrical hollow curved tube on one side is installed. After the aircraft, equipped with the aircraft support, is aligned with the inner wall of the semi-cylindrical hollow curved plate on one side, the semi-cylindrical hollow curved tube on the other side is installed. The inner wall of the hollow tube is evenly coated with lubricating oil to reduce frictional resistance between the aircraft support and the aircraft at the rear of the aircraft. The hollow tube can restrain the lateral displacement and rotation angle of the aircraft. The inner wall of the hollow tube is evenly coated with lubricating oil to reduce frictional resistance between the aircraft support and the aircraft at the rear of the aircraft. The hollow tube can restrain the lateral displacement and rotation angle of the aircraft.

[0087] In S7, the acceleration load is loaded, and the vehicle jumps up under the action of the acceleration load. When the vehicle moves to the top of the hollow conduit, the buffer is used to achieve shock absorption and protection.

[0088] The following is a specific example to further illustrate the equivalent acceleration land simulation device and design method for a vertical entry of a vehicle into water under acceleration loads proposed in the present invention. It is generally believed that the acceleration load on a vehicle entering water is a triangular load.

[0089] Table 1 shows the target characteristic parameters of a known spacecraft and the size parameters of the existing acceleration load loading device. Assuming that the target acceleration needs to provide an initial acceleration of 50g and the acceleration pulse width is 2.998×10 -4 s.

[0090] Table 1 Target characteristic parameters of a known spacecraft and dimensional parameters of the existing acceleration load loading device

[0091] Aircraft length / mm Aircraft weight / kg Aircraft diameter D / mm 1177.62 231 200

[0092] Step S1: Arrange sensors on components or target locations within the vehicle body;

[0093] Step S2: Based on the 50g initial acceleration provided by the target acceleration, the acceleration load loading device provides the required load pressure peak and the required pulse width; since the target acceleration a is 50g, the acceleration load loading device needs to provide Peak load. Required load pulse width The load is a triangular load.

[0094] Step S3: Based on the diameter of the aircraft model obtained in S2 being 200 mm, the diameters of the aircraft support and the loading cylinder are designed. The loading cylinder diameter should be greater than 212 mm, and the designed loading cylinder diameter is 220 mm. The relevant parameters are shown in Table 2.

[0095] Table 2 Some structural parameters obtained based on calculation

[0096] Loading cylinder diameter / mm Buffer tube diameter / mm Hollow tube diameter / mm Piston diameter / mm 220 220 220 220

[0097] The loading cylinder and the acceleration load loading device are connected to the loading hole through a flange. The parameters of the relevant components are obtained based on the design diameter of the loading cylinder of 220mm. The diameter of the boss at the bottom of the loading cylinder should be smaller than the diameter of the loading cylinder of 220mm. The designed boss diameter is 180mm, so the effective loading area S effective is 2.5434×10 -2 m 2 At this point, the required acceleration load peak value and pulse width can be calculated. According to the above calculation, the peak load P s is 4539348.8N; the pulse width is 3×10 -4 s. The length of the loading cylinder that meets all conditions should be greater than 60mm. For the convenience of processing, the length of the loading cylinder is designed to be 200mm;

[0098] Step S4: Fix the loading cylinder described in S3 above the loading hole of the acceleration load loading device via a flange connection;

[0099] Step S5: Bolt the two ends of the aircraft model to the aircraft support through the threaded holes on the side;

[0100] Step S6: Place the tail end of the assembled vehicle from S5 into the loading cylinder described in S3. Connect the head end to a single semi-cylindrical hollow elbow. Then, install the other semi-cylindrical hollow elbow and secure it with a flange. Based on the existing parameters, a designed hollow pipe length of 1520 mm satisfies the requirements. See Table 3 for the relevant parameters.

[0101] Table 3 Remaining structural parameters obtained according to calculation

[0102] Hollow tube length / mm 1520 Diameter of boss at the bottom of loading cylinder / mm 180 <![CDATA[Piston thickness h piston / mm]]> 40 Buffer tube length / mm 300

[0103] Step S7: Complete the load loading and record the data obtained by the statistical sensor.

[0104] The above further describes the technical solution provided by the present invention in detail through several specific embodiments in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the several specific embodiments described above are not intended to limit the present invention. Any reasonable modification and improvement of the present invention, combination of embodiments and equivalent replacement based on the spirit and principles of the present invention should be included in the scope of protection of the present invention.

[0105] The descriptions in this specification refer only to preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Furthermore, reference to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples" implies that a specific feature, structure, material, or characteristic described in conjunction with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative descriptions of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or N embodiments or examples. Furthermore, those skilled in the art may combine and integrate the different embodiments or examples described in this specification, as well as features from different embodiments or examples, unless otherwise specified. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed to indicate or imply relative importance or to implicitly specify the number of the technical features indicated. Therefore, features designated "first" or "second" may explicitly or implicitly include at least one of these features. In the description of the present invention, "N" means at least two, for example, two, three, etc., unless otherwise specifically defined. Any process or method description in a flowchart or otherwise described herein can be understood to represent a module, segment, or portion of code comprising one or more executable instructions for implementing a custom logic function or process, and the scope of the preferred embodiments of the present invention includes alternative implementations in which functions may be performed in a different order than shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as will be understood by those skilled in the art to which the embodiments of the present invention pertain. The logic and / or steps represented in a flowchart or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing a logic function, can be embodied in any computer-readable medium for use by an instruction execution system, apparatus, or device (e.g., a computer-based system, a system including a processor, or other system that can fetch and execute instructions from an instruction execution system, apparatus, or device), or in conjunction with such instruction execution systems, apparatuses, or devices. For purposes of this specification, a "computer-readable medium" can be any device that can contain, store, communicate, propagate, or transmit a program for use by an instruction execution system, apparatus, or device, or in conjunction with such instruction execution systems, apparatuses, or devices. More specific examples (a non-exhaustive list) of computer-readable media include the following: an electrical connection having one or N wirings (electronic devices), a portable computer disk cartridge (magnetic devices), random access memory (RAM), read-only memory (ROM), erasable and programmable read-only memory (EPROM or flash memory), fiber optic devices, and portable compact disc read-only memory (CDROM).In addition, the computer-readable medium may even be paper or other suitable medium on which the program can be printed, because the program can be obtained electronically, for example, by optically scanning the paper or other medium, then editing, interpreting, or processing in other suitable ways as necessary, and then storing it in a computer memory. It should be understood that the various parts of the present invention can be implemented with hardware, software, firmware, or a combination thereof. In the above embodiment, the N steps or methods can be implemented with software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented with hardware, as in another embodiment, any one of the following technologies known in the art or their combination can be used to implement: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0106] Those skilled in the art will appreciate that all or part of the steps carried out in the above-mentioned embodiment method can be completed by instructing the relevant hardware through a program, and the program can be stored in a computer-readable storage medium, which, when executed, includes one or a combination of the steps of the method embodiment. In addition, the functional units in the various embodiments of the present invention can be integrated into a processing module, or each unit can exist physically alone, or two or more units can be integrated into one module. The above-mentioned integrated module can be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

Claims

1. The equivalent impact environment model of a spacecraft entering water is characterized by: The model includes: A spacecraft, wherein both ends of the spacecraft are provided with a spacecraft support, the spacecraft support at the head of the spacecraft is arranged in a loading cylinder, and the spacecraft support at the tail of the spacecraft is arranged in a buffer cylinder; When the aircraft is subjected to an impact load, the buffer cylinder is used to provide buffering for the aircraft; The loading cylinder is fixed on the loading hole of the impact load loading device; in, The aircraft support at the head of the aircraft is arranged in the loading cylinder, and the aircraft support at the tail of the aircraft is arranged in the buffer cylinder. The loading cylinder is arranged on the loading hole of the impact load loading device and fixed by a flange. The buffer cylinder is arranged on the top of the fixing frame and is used to receive the aircraft that jumps up due to the impact load. The buffer cylinder is composed of a hollow conduit and an impact shock-absorbing cylinder. A buffer is arranged in the buffer cylinder. The buffer is composed of a spring and a piston. The two ends of the buffer spring are respectively connected to the bottom of the buffer cylinder and the piston. The buffer plays a vibration reduction role for the aircraft that jumps up under the impact load. The hollow conduit is used to limit the movement of the aircraft only along its own axis. The hollow conduit includes two semi-cylindrical hollow bent plates. The two semi-cylindrical hollow bent plates are respectively: a part of a cylinder that can be sleeved on the aircraft; The diameter of the circle below the loading cylinder connected to the loading hole is larger than the diameter of the inner wall of the loading cylinder. It serves as a boss to provide support before loading so that the aircraft can stand inside the loading cylinder.

2. The equivalent impact environment model for a vehicle entering water according to claim 1, characterized in that: The buffer cylinder is arranged on the top of the fixing frame, and the fixing frame is in a gate shape.

3. The equivalent impact environment model of a vehicle entering water according to claim 1, characterized in that: The aircraft holder includes an aircraft cover and a piston, and the position of the aircraft relative to the aircraft holder is fixed by the aircraft cover.

4. The equivalent impact environment model for a vehicle entering water according to claim 1, characterized in that: The shock absorbing tube is connected to the fixing frame through a slot, and the shock absorbing tube provides a buffering capacity through a spring and a piston.

5. The design method of the equivalent impact environment model of a vehicle entering water according to claim 1 is characterized in that: include: Steps for collecting target impact environment parameters; According to the parameters, a step of obtaining a load peak value and a pulse width required to be provided by an impact load loading device; The step of obtaining the diameter of the aircraft support, the loading cylinder and the length of the loading cylinder according to the load peak value and the pulse width.

6. A computer storage medium for storing a computer program, characterized in that When the computer program is read by a computer, the computer executes the method according to claim 5 .

7. A computer comprising a processor and a storage medium, characterized in that When the processor reads the computer program stored in the storage medium, the computer executes the method according to claim 5 .

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