An extreme impact load loading device

Abstract

The application discloses an extreme impact load loading device, which comprises a gas sealing latch body, a charge structure, a gas chamber, a pushing force generating device and a load loading connector, wherein the gas sealing latch body is arranged at the bottom of the gas chamber, the charge structure is arranged in the gas chamber and adjacent to the gas sealing latch body, the pushing force generating device is used for generating an extreme impact load with transient action under the action of high-pressure gas, and the load loading connector is arranged in the gas chamber and connected with a force receiving device to be tested, so that the extreme impact load is transmitted to the tested device in a required load loading direction.

Description

Technical Field

[0001] This invention belongs to the field of artillery firing impact load technology, specifically an extreme impact load loading device. Background Technology

[0002] During artillery firing, the propellant gases act on the projectile, propelling it at high speed. Simultaneously, the reaction force from the barrel acts on the gun body, generating a massive impact load. The process and characteristics of this extreme impact load are crucial to the structural design of the artillery's cradle, recoil mechanism, carriage, and other components, and are key factors determining the artillery's firing stability, reliability, and safety. Therefore, researching rapidly constructable test methods and devices for testing the impact load during artillery firing with low experimental requirements is an important means to support the efficient design and verification of artillery.

[0003] Traditional methods for testing artillery impact loads primarily involve actual artillery firing for verification. This method can realistically and accurately verify the process of extreme artillery impact and its impact on the structure. However, because it requires the construction of a complete artillery firing device for the corresponding testing and verification, the construction cycle is long and the cost is high. Furthermore, it requires the firing of projectiles, resulting in complex testing conditions, demanding testing site requirements, and safety risks. This makes it difficult to meet the requirements for preliminary principle verification, and in particular, it cannot provide testing and verification conditions for preliminary design, thus restricting the optimal design of the artillery.

[0004] The hydraulic manual recoil test system is a device for simulating the recoil test of artillery. This system mounts a hydraulic cylinder to the front of the recoil mechanism, using high-pressure hydraulic fluid to push a piston-driven recoil rod within the mechanism backward, causing the artillery to recoil. Once the artillery has recoiled to a predetermined position, the hydraulic system quickly unloads, and the gun barrel automatically begins its return to its original position under the pressure of compressed gas within the recoil mechanism. While this method can make the artillery recoil and simulate the return process, because it uses hydraulic loading, it cannot simulate the impact loads during artillery firing and can only be used for design verification of the recoil mechanism. Summary of the Invention

[0005] This invention proposes an extreme impact load loading device. Utilizing the working principle of a muzzle brake, a reverse-mounted muzzle brake is used. The combined force of the high-pressure propellant gas and the reverse muzzle brake simulates the gun barrel force during artillery firing and is applied to the artillery structure to achieve dynamic loading of extreme loads.

[0006] The technical solution to achieve the purpose of this invention is as follows: an extreme impact load loading device, comprising: a gas-sealed latch, a charge structure, a gas chamber, a thrust generating device, and a load loading connector. The gas-sealed latch is disposed at the bottom of the gas chamber, and the charge structure is disposed within the gas chamber and adjacent to the gas-sealed latch. The thrust generating device is used to generate a transient extreme impact load under the action of high-pressure gas. The load loading connector is disposed in the gas chamber and is connected to the force-bearing device under test through the load loading connector to transfer the extreme impact load to the device under test in the required load loading direction.

[0007] Preferably, the propulsion generating device adopts an impact-type or reaction-type muzzle brake structure, and the central bullet hole of the muzzle brake is closed by a front end baffle, leaving only side holes for generating transient extreme impact loads under the action of high-pressure gas.

[0008] Preferably, the propellant loading structure includes a cartridge, a solid propellant charge, and a pressure relief port. The cartridge is disposed inside the gas combustion chamber and adjacent to the gas sealing latch. The solid propellant charge is disposed inside the cartridge, and the pressure relief port is disposed at the end of the cartridge away from the sealing latch.

[0009] Preferably, the desired loading force curve is formed by adjusting the solid propellant and the pressure relief orifice.

[0010] Preferably, the specific method for forming the desired loading force curve by adjusting the solid propellant and pressure relief orifice is as follows:

[0011] Calculate the relationship between propellant combustion ratio and generated pressure based on the propellant combustion equation.

[0012]

[0013] Where Ψ is the percentage of gunpowder already burned, χ, λ, and μ are the shape characteristics of the gunpowder, Z is the relative thickness of the gunpowder already burned, t is time, u1 is the burning rate constant, p is the gas pressure, n is the burning rate index, and e1 is half the initial thickness of the gunpowder.

[0014] The gas pressure is controlled by controlling the propellant type and the flow rate of the pressure relief orifice. The gas pressure acts on the front baffle of the propellant gas in the propellant generating device and the working surface of the recoil device structure, generating a corresponding force.

[0015] Let S be the area of ​​the total working surface of the front baffle and the recoil brake structure that is equivalent to the area in the axial direction of the gas chamber. Then the resulting impact load is F(t) = p a (t)S, where p a F(t) represents the change in pressure at the inlet of the force generating device over time, and F(t) represents the change in impact load over time, i.e., the loading force curve.

[0016] Compared with the prior art, the significant advantages of this invention are:

[0017] The extreme impact load loading device provided by this invention can achieve impact load loading that is consistent with the actual process of artillery projectile firing. Compared with the actual artillery firing test, no projectile is fired. Since there is no high-speed projectile flying out of the artillery barrel, there are no complex requirements for the test site such as target track, projectile impact point control, and shelter. This greatly reduces the difficulty of test organization, improves test safety, and increases test efficiency.

[0018] The propellant loading structure with a pressure relief hole on the cartridge case used in this invention can realize the control of the propellant combustion process and its pressure regulation. By adjusting the amount of propellant and the size of the pressure relief hole, different extreme impact load curves can be loaded. Compared with the traditional hydraulic manual recoil test system or static loading test method, it can realize dynamic load loading that matches the artillery firing process, with higher loading realism and stronger adjustability.

[0019] The thrust generating device provided by this invention has a front end baffle, which can directly interact with the high-pressure gas ejected from the barrel, greatly increasing the area of ​​high-pressure gas interaction and generating a larger reverse impact force. Compared with the traditional brake force, the force is greatly increased, which can solve the problem that it is difficult to increase the peak value of simulated loading under extreme impact loads.

[0020] The load-loading connector provided by this invention can be connected to different devices as needed. Compared with real shooting test or hydraulic manual recoil test system, it has the advantages of higher flexibility and wider applicability. It can be extended to simulate the high thrust load in different stages of the launch process of rockets, missiles, etc.

[0021] The present invention will now be described in further detail with reference to the accompanying drawings. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of an extreme load loading device provided in an embodiment of the present invention.

[0023] Figure 2 This is a schematic diagram of an extreme impact load test of an artillery recoil device provided in an embodiment of the present invention.

[0024] Figure 3 The curve of extreme impact load force versus time for an artillery recoil device provided in an embodiment of the present invention. Detailed Implementation

[0025] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0026] The present invention is conceived as follows: an extreme impact load loading device, comprising a gas-sealed latch, a cartridge, a solid propellant charge, a pressure relief port, a gas chamber, a thrust generating device, and a load loading connector.

[0027] The sealing latch is located at the bottom of the gas chamber. When open, it is used for loading the propellant charge; when closed, it seals the high-pressure gas. The cartridge case, solid propellant charge, and pressure relief hole constitute the propellant structure for generating high-pressure gas. After firing, the solid propellant charge burns to generate high-pressure gas, which enters the gas chamber through the pressure relief hole with controlled flow. The gas chamber is the space for the high-pressure gas to expand and flow out. The thrust generating device operates on the same principle as the muzzle brake of an artillery piece. It can adopt an impact-type or reaction-type muzzle brake structure, and the central bullet hole of the muzzle brake is closed by a front baffle, leaving only side holes for generating transient extreme impact loads under the action of high-pressure gas. The load loading connector is used to connect to the force-bearing device under test, transferring the extreme impact load to the device under test in the required load loading direction. The direction of the force is the same as the direction of the high-pressure gas outlet.

[0028] The propellant structure, consisting of a cartridge, solid propellant, and pressure relief holes, uses the propellant as an energy source. After firing, the propellant burns to generate high-pressure gas. In order to ensure that the high-pressure gas acts on the thrust generating device at an appropriate pressure and flow rate, a set of pressure relief holes is designed at the front end of the cartridge to control the gas flow rate and achieve controllable gas chamber pressure.

[0029] When high-pressure gas enters the propulsion generating device through the gas chamber, the gas expands rapidly because the cross-section of the device is larger than that of the gas chamber connection, and there are guide holes on its side. Part of the gas flows forward and acts on the front baffle, generating a force that propels the device, while the other part changes its flow direction and enters the side hole, exiting through the guide surface, also generating a force that propels the device. The combination of these two forces generates an extreme impact load.

[0030] The characteristics of extreme impact loads can be adjusted by modifying the solid propellant and pressure relief orifice to achieve the desired loading force curve. The relationship between the propellant combustion ratio and the generated pressure can be calculated based on the propellant combustion equation.

[0031]

[0032] Where Ψ is the percentage of gunpowder already burned, χ, λ, and μ are the characteristic quantities of gunpowder shape, Z is the relative thickness of the gunpowder already burned, t is time, u1 is the burning rate constant, p is the gas pressure, n is the burning rate exponent, and e1 is half the initial thickness of the gunpowder. The gas pressure can be controlled by the propellant type and the flow rate through the pressure relief orifice. The gas pressure acts on the working surfaces of the propellant gas front-end baffle and the recoil mechanism of the propellant-generating device, generating a corresponding force. Assuming the total area of ​​the working surfaces of the front-end baffle and the recoil mechanism is equivalent to the area S in the axial direction of the gas chamber, the resulting impact load is F(t) = p a (t)S, where p a F(t) represents the change in pressure at the inlet of the force generating device over time, and F(t) represents the change in impact load over time, i.e., the loading force curve.

[0033] The load-loading connector is used to connect to the force-bearing device. The direction of the high-pressure gas flow in the gas chamber is the direction of the force. When connecting, the load-bearing direction of the force-bearing device should be kept parallel to the axis of the gas chamber. After tightening the connection, the load test can be carried out.

[0034] The working principle of this invention is to use a multi-stage parallel rocket engine as power, and to simulate the combined force in the barrel of a cannon during firing by controlling the thrust of the rocket engine, which is then applied to the cannon structure to provide verification conditions for cannon structure design.

[0035] Example

[0036] An extreme impact load loading device, the device comprising as follows Figure 1 As shown, the device includes a gas-sealed latch 1, a cartridge 2, a solid propellant charge 3, a pressure relief port 4, a gas chamber 5, a thrust generating device 6, and a load loading connector 7. The gas-sealed latch 1 is located at the bottom of the gas chamber 5; when open, it is used for loading the propellant charge; when closed, it seals the high-pressure gas. The cartridge 2 is disposed inside the gas chamber 5, and the solid propellant charge 3 is disposed inside the gas chamber 5. The pressure relief port 4 is located at the end of the cartridge 2 furthest from the gas-sealed latch 1. The thrust generating device 6 is used to generate a transient extreme impact load under the action of high-pressure gas. The load loading connector 7 is disposed in the gas chamber 5 and connects to the tested device to transfer the extreme impact load to the tested device in the required load loading direction. The direction of the extreme impact load is the same as the direction of the high-pressure gas outlet.

[0037] Furthermore, the cartridge 2, solid propellant 3, and pressure relief hole 4 constitute a propellant structure for generating high-pressure gas. After firing, the solid propellant 3 burns to generate high-pressure gas, and the high-pressure gas enters the gas chamber 5 through the pressure relief hole 4 with controlled flow. The gas chamber 5 is the space for the high-pressure gas to expand and flow out. The principle of the thrust generating device 6 is the same as that of the muzzle brake of an artillery gun. It can adopt an impact type or reaction type muzzle brake structure, and the central bullet hole of the muzzle brake is closed by the front end baffle, leaving only the side holes, which are used to generate transient extreme impact loads under the action of high-pressure gas.

[0038] This embodiment provides an example of the use of an extreme impact load loading device in testing artillery recoil mechanisms, such as... Figure 2 As shown. The cannon is firmly constrained to the ground by the fixed bracket 10, and the load loading connector 7 is tightly clamped to the front end of the cannon barrel 8. The extreme impact load is transmitted to the recoil device 9 through the barrel and its supporting structure for test loading. In order to ensure the stability of the barrel during the test, a support device 11 can be installed at the front end of the barrel.

[0039] During the test loading, the charge structure consisting of cartridge 2, solid propellant 3, and pressure relief hole 4 is used as the energy source. The charge structure is then filled into the rear end of the gas chamber 5, the sealing latch 1 is closed, and then the solid propellant 3 is fired. The solid propellant 3 burns to generate high-pressure gas. In order to make the high-pressure gas act on the thrust generating device 6 with appropriate pressure and flow rate, a set of pressure relief holes 4 are designed at the front end of cartridge 2 to control the gas flow rate so as to achieve the purpose of controllable gas chamber pressure.

[0040] When high-pressure gas enters the propulsion generating device 6 through the gas chamber 5, the gas expands rapidly because the cross-section of the device is larger than that of the gas chamber connection and it has guide holes on its side. Part of the gas flows forward and acts on the front baffle, generating a force that propels the device, while the other part changes its flow direction and enters the side hole, then is discharged through the guide surface, also generating a force that propels the device. The combination of these two forces generates an extreme impact load.

[0041] The characteristics of extreme impact loads can be adjusted through solid propellant and pressure relief orifices, forming a pattern such as... Figure 3 The loading force curve shown.

[0042] The above provides a detailed description of an extreme impact load loading device provided by the present invention. Specific examples have been used to illustrate the principle and implementation of the present invention. The description of the above embodiments is only for the purpose of helping to understand the method and core idea of ​​the present invention. At the same time, for those skilled in the art, there will be changes in the specific implementation and application scope based on the idea of ​​the present invention. Therefore, the content of this specification should not be construed as a limitation of the present invention.

Claims

1. An extreme impact load loading device, characterized in that, include: The device comprises a gas-sealed latch, a propellant charge structure, a gas combustion chamber, a thrust generating device, and a load loading connector. The gas-sealed latch is located at the bottom of the gas combustion chamber. The propellant charge structure is located inside the gas combustion chamber and adjacent to the gas-sealed latch. The thrust generating device is used to generate transient extreme impact loads under high-pressure gas. The load loading connector is located in the gas combustion chamber and is connected to the tested force-bearing device to transfer the extreme impact load to the tested device in the required load loading direction. The thrust generating device adopts an impact-type or reaction-type muzzle brake structure, and the central bullet hole of the muzzle brake is closed by a front end baffle, leaving only side holes for generating transient extreme impact loads under high-pressure gas.

2. The extreme impact load loading device according to claim 1, characterized in that, The charge structure includes a cartridge, a solid propellant charge, and a pressure relief port. The cartridge is located inside the gas chamber and adjacent to the gas sealing latch. The solid propellant charge is located inside the cartridge, and the pressure relief port is located at the end of the cartridge away from the sealing latch.

3. The extreme impact load loading device according to claim 1, characterized in that, The desired loading force curve is formed by adjusting the solid propellant and pressure relief orifice.

4. The extreme impact load loading device according to claim 1, characterized in that, The specific method for forming the desired loading force curve by adjusting the solid propellant and pressure relief orifice is as follows: Calculate the relationship between propellant combustion ratio and generated pressure based on the propellant combustion equation. ； in, This represents the percentage of gunpowder already burned. For the characteristic quantity of gunpowder shape, The relative thickness of the burned gunpowder. For time, Where is the burning rate constant. For gas pressure, The burn rate index, It is 1 / 2 the initial thickness of the gunpowder; The gas pressure is controlled by controlling the propellant type and the flow rate of the pressure relief orifice. The gas pressure acts on the front baffle of the propellant gas in the propellant generating device and the working surface of the recoil device structure, generating a corresponding force. Let S be the area of ​​the total working surface of the front baffle and the recoil brake structure that is equivalent to the area along the axial direction of the gas chamber. Then the resulting impact load is: ,in This represents the change in pressure at the inlet of the force-generating device over time. This represents the change of impact load over time, i.e., the applied force curve.

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