Guide rail type missile launching variable thrust propelling device

Abstract

The invention relates to the technical field of missile launching ground simulation, and discloses a guide rail type missile launching variable-thrust propelling device which comprises a foundation mounting plate, a force bearing seat is fixedly connected to the upper side of the foundation mounting plate, a cylinder barrel front seat is fixedly mounted on the left side of the force bearing seat, and a servo locking assembly is arranged on the left side of the cylinder barrel front seat; the right side of the cylinder barrel front seat is connected with a cylinder barrel through a bolt, a propelling cavity is formed in the cylinder barrel, the right side of the cylinder barrel is connected with an electric straight-through flange ball valve through a flange, the right side of the electric straight-through flange ball valve is fixedly communicated with a high-pressure gas tank, and a square piston rod is arranged in the cylinder barrel. High-pressure gas is used as a power source, a servo hydraulic cylinder is used for generating transient variable braking force, the thrust of the system is obtained by subtracting the braking force from the thrust of the air cylinder, and due to the fact that high-response servo braking is adopted, rapidly-changed thrust or any acceleration waveform can be generated.

Description

Technical Field

[0001] This invention relates to the field of missile launch ground simulation technology, specifically to a rail-guided missile launch variable thrust propulsion device. Background Technology

[0002] The phase from engine ignition to separation from the launch pad is a crucial part of the missile's flight. This phase involves complex dynamic processes, requiring performance parameter testing, reliability and stability experiments on the rail-launched system. These include the coupling between the missile and the rail, the service life of the launch pad, maintaining the missile's exit attitude, and the unlocking and disengagement of the electrical connections between the missile and the airborne systems. Therefore, simulated launch verification of rail-launched devices in ground laboratories is essential. To ensure the accuracy of parameter testing, it is necessary to accurately simulate engine thrust, ensuring that the exit velocity and duration of the rail are consistent with actual engine ignition and launch. However, existing simulation devices and technologies still have many shortcomings in accurately simulating the launch process of rail-launched missiles.

[0003] In the field of rail-guided missile launch simulation technology, current techniques employ pneumatic or hydraulic propulsion, neglecting changes in missile engine thrust and only requiring the missile's derailment velocity to be achieved. Because these techniques cannot simulate the missile's actual engine thrust and acceleration, nor accurately reflect the dynamic characteristics of the missile-rail contact and the wear condition of the rail and launch pad, the tests are inaccurate.

[0004] Therefore, there is an urgent need for a new type of rail-mounted missile launch simulation device that can accurately simulate engine thrust and reflect the real state of rail-mounted launch, providing a more efficient and economical ground testing method for the design and verification of missile rail-mounted pylons.

[0005] In addition, the variable thrust propulsion device is used to generate acceleration that varies with time. It can also be used for automobile crash tests, especially small acceleration trolleys. The thrust is between 300kN and 1000kN, which can realize the acceleration waveform of automobile crash regulations for components such as child seats and airbags. Summary of the Invention

[0006] To address the shortcomings of existing technologies, this invention provides a rail-guided missile launch variable thrust propulsion device, which solves the problem that existing ground test devices cannot accurately simulate the variable thrust characteristics of missile engines and the real launch dynamics process, thus leading to inaccurate simulation test data.

[0007] To achieve the above objectives, the present invention provides the following technical solution: a rail-mounted missile launch variable thrust propulsion device, comprising a ground mounting plate, a support seat fixedly connected to the upper side of the ground mounting plate, a cylinder front seat fixedly mounted on the left side of the support seat, a servo locking assembly disposed on the left side of the cylinder front seat, a cylinder bolted to the right side of the cylinder front seat, a propulsion chamber formed inside the cylinder, an electrically operated straight-through flange ball valve connected to the right side of the cylinder via a flange, and a high-pressure gas tank fixedly connected to the right side of the electrically operated straight-through flange ball valve. The cylinder has a square piston rod inside, and a buffer chamber and a propulsion chamber inside. The buffer chamber is located on the right side of the propulsion chamber. The servo locking assembly includes a servo seat, which is fixedly connected to the foundation mounting plate. An integrated valve block is fixedly connected to the upper side of the servo seat, and a servo valve is fixedly connected to the upper side of the integrated valve block. A pressure sensor is fixedly installed on the right side of the servo valve. A servo cylinder assembly is located on the lower side of the integrated valve block. A servo locking plate is fixedly connected to the inner wall of the servo seat, and three brake pads are fixedly installed on the servo locking plate.

[0008] Preferably, the servo cylinder assembly includes a servo cylinder seat, which is disposed on the lower side of the integrated valve block. A piston is disposed inside the servo cylinder seat, and a servo cylinder cover is threadedly connected to the upper side of the piston. A pressure plate is disposed inside the servo cylinder cover, and the pressure plate is disposed on the upper side of the servo cylinder cover.

[0009] Preferably, the piston is used to drive the pressure plate under hydraulic pressure and transmit positive pressure to the brake pad so that the brake pad comes into contact with the surface of the square piston rod.

[0010] Preferably, one piston end of the square piston rod divides the interior of the cylinder into the propulsion chamber and the buffer chamber.

[0011] Preferably, the integrated valve block is provided with a hydraulic oil source, and the servo valve is connected to the hydraulic oil source.

[0012] Preferably, the brake pads are made of ceramic matrix composite material, and the brake pads contact the square piston rod to form six friction surfaces.

[0013] Preferably, the square piston rod has a hollow structure.

[0014] Preferably, the pressure sensor is used to monitor the hydraulic pressure applied to the servo cylinder assembly in real time, and the servo valve is used to adjust the hydraulic flow and pressure entering the servo cylinder assembly according to external control commands.

[0015] Preferably, the high-pressure gas tank is used to provide high-pressure gas to the propulsion chamber to drive the square piston rod to generate the main thrust for axial movement.

[0016] Preferably, the brake pad is located on the movement path of the square piston rod.

[0017] This invention provides a rail-guided missile launch variable thrust propulsion device. It has the following beneficial effects:

[0018] 1. This invention uses high-pressure gas as a power source and a servo hydraulic cylinder to generate transiently variable braking force. The cylinder thrust minus the braking force equals the system thrust. Due to the use of a high-response servo brake, it can generate rapidly changing thrust or arbitrary acceleration waveforms. Employing servo closed-loop control, the acceleration control accuracy is high; across the entire acceleration range, the RMS control accuracy can reach below 2%, and the repeatability error can reach within 1%.

[0019] 2. Braking force is generated by braking piston rod, which is simple in structure. The propulsion piston and servo seat are mounted on a base plate. Only the base plate bears the dynamic inertial force, and the foundation installation area required during equipment installation is small.

[0020] 3. Simple installation and easy debugging; no complex adjustments or settings are required for different acceleration parameters. Attached Figure Description

[0021] Figure 1 This is a perspective view of the present invention;

[0022] Figure 2 This is a schematic diagram of the propulsion system structure of the present invention;

[0023] Figure 3 This is a schematic diagram of the servo locking assembly structure of the present invention;

[0024] Figure 4 This is a schematic diagram of the servo locking assembly structure of the present invention;

[0025] Figure 5 This is a schematic diagram of the servo cylinder assembly structure of the present invention.

[0026] The components include: 1. Foundation mounting plate; 2. Servo locking assembly; 21. Pressure sensor; 22. Servo seat; 23. Integrated valve block; 24. Brake pad; 25. Servo cylinder assembly; 251. Servo cylinder seat; 252. Piston; 253. Servo cylinder head; 254. Pressure plate; 26. Servo valve; 27. Servo locking plate; 3. Cylinder front seat; 4. Buffer chamber; 5. Bearing seat; 6. Square piston rod; 7. Propulsion chamber; 8. Hydraulic oil source; 9. Electric straight-through flange ball valve; 10. High-pressure air tank; 11. Cylinder. Detailed Implementation

[0027] The technical solutions in 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. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0028] Please see the appendix Figure 1 - Appendix Figure 2 This invention provides a rail-mounted missile launch variable thrust propulsion device, including a base mounting plate 1. A support seat 5 is fixedly connected to the upper side of the base mounting plate 1. A cylinder front seat 3 is fixedly installed on the left side of the support seat 5. A servo locking assembly 2 is provided on the left side of the cylinder front seat 3. A cylinder 11 is bolted to the right side of the cylinder front seat 3. A propulsion chamber 7 is opened inside the cylinder 11. An electric straight-through flange ball valve 9 is connected to the right side of the cylinder 11 through a flange. A high-pressure gas tank 10 is fixedly connected to the right side of the electric straight-through flange ball valve 9. The high-pressure gas tank 10 is used to provide high-pressure gas to the propulsion chamber 7 to drive a square piston rod 6 to generate the main thrust for axial movement. A square piston rod 6 is provided inside the cylinder 11. The square piston rod 6 adopts a hollow structure. One piston end of the square piston rod 6 divides the inside of the cylinder 11 into a propulsion chamber 7 and a buffer chamber 4. The buffer chamber 4 is located on the right side of the propulsion chamber 7.

[0029] Specifically, the propulsion system consists of the cylinder front seat 3, buffer chamber 4, load-bearing seat 5, square piston rod 6, and propulsion chamber 7. The load-bearing seat 5, as a key structural component connecting the foundation and the main body of the launching device, provides a high-rigidity installation reference for the entire system. The square piston rod 6, as the core moving component, has a square cross-section design that effectively resists torsional loads during movement, ensuring attitude stability. At the same time, its hollow internal design significantly reduces the inertial mass of the piston rod itself, which is crucial for improving the dynamic response characteristics of the entire system and achieving rapid acceleration changes. To ensure that the square piston rod 6 moves smoothly and accurately within the cylinder 11, copper sleeve guide structures are also provided on its upper and lower sides, reducing motion friction and preventing unnecessary radial runout. The presence of the buffer chamber 4 provides an important safety barrier for the system. In extreme conditions where the servo locking assembly 2 completely fails or an accident occurs, when the piston rod moves to the end of its stroke, the gas in the buffer chamber 4 will be compressed to form a non-linear buffer cushion, effectively absorbing the huge kinetic energy of the piston rod, thereby avoiding rigid impacts that could damage the main structure of the equipment and greatly improving the reliability and safety of the system.

[0030] Please see the appendix Figure 2 - Appendix Figure 3The servo locking assembly 2 includes a servo seat 22, which is fixedly connected to the foundation mounting plate 1. An integrated valve block 23 is fixedly connected to the upper side of the servo seat 22, and a servo valve 26 is fixedly connected to the upper side of the integrated valve block 23. A hydraulic oil source 8 is provided on the integrated valve block 23, and the servo valve 26 is connected to the hydraulic oil source 8. A pressure sensor 21 is fixedly installed on the right side of the servo valve 26. The pressure sensor 21 is used to monitor the hydraulic pressure applied to the servo cylinder assembly 25 in real time. The servo valve 26 is used to adjust the hydraulic flow and pressure entering the servo cylinder assembly 25 according to external control commands. A servo locking plate 27 is fixedly connected to the inner wall of the servo seat 22. Three brake pads 24 are fixedly installed on the servo locking plate 27. The brake pads 24 are made of ceramic matrix composite material, and the brake pads 24 contact the square piston rod 6 to form six friction surfaces. The brake pads 24 are located on the movement path of the square piston rod 6.

[0031] Specifically, the servo locking assembly 2 is designed as a highly integrated module. Its servo base 22 has extremely high structural rigidity, ensuring that its deformation is minimal (no more than 0.05mm) under the action of a huge hydraulic cylinder. The integrated valve block 23, as the core of hydraulic control, integrates the oil circuit, three high-response direct-acting servo valves 26, and pressure sensor 21 into one unit. This not only makes the structure compact but also greatly shortens the length of the hydraulic pipeline, reduces the elastic deformation and flow delay of the hydraulic oil, thereby improving the response bandwidth of the control system. The brake pads 24 are made of high-performance ceramic matrix composite material, which is designed to maintain a stable coefficient of friction under high-speed and heavy-load friction conditions, and to have excellent high-temperature resistance and wear resistance, thus ensuring the high repeatability and long service life of the device. The servo valve 26 and the pressure sensor 21 together form a closed-loop servo system for precise control of friction force. The pressure sensor 21 feeds back the hydraulic cylinder pressure signal monitored in real time to the external servo controller. The controller adjusts the control signal output to the servo valve 26 in real time by comparing the deviation between the actual pressure and the target pressure curve, so as to achieve accurate and dynamic tracking of friction force.

[0032] Please see the appendix Figure 3 - Appendix Figure 5 A servo cylinder assembly 25 is provided on the lower side of the integrated valve block 23. The servo cylinder assembly 25 includes a servo cylinder seat 251, which is located on the lower side of the integrated valve block 23. A piston 252 is provided inside the servo cylinder seat 251. A servo cylinder cover 253 is threadedly connected to the upper side of the piston 252. A pressure plate 254 is provided inside the servo cylinder cover 253, which is located on the upper side of the servo cylinder cover 253. The piston 252 is used to drive the pressure plate 254 under hydraulic action and transmit positive pressure to the brake pad 24 so that the brake pad 24 contacts and rubs against the surface of the square piston rod 6.

[0033] Specifically, the variable thrust process of this device begins with a launch command. The electrically operated straight-through flange ball valve 9 opens, and high-pressure gas rushes into the propulsion chamber 7, generating main thrust and driving the square piston rod 6 to begin accelerating. Simultaneously, the servo controller, based on a preset thrust or acceleration curve, regulates the hydraulic oil entering the servo cylinder assembly 25 from the hydraulic oil source 8 via the servo valve 26. The high-pressure oil acts on the piston 252, and this force is transmitted through the pressure plate 254 to the brake pad 24 mounted on the servo locking plate 27, causing it to press against the piston at high speed with precise and controllable positive pressure. The friction surface of the moving square piston rod 6 generates a friction braking force that is opposite in direction to the main thrust. Its magnitude is proportional to the hydraulic pressure set by the servo system. Ultimately, the net driving force acting on the square piston rod 6 is equal to the vector sum of the pneumatic main thrust and the servo hydraulic friction braking force. By continuously adjusting the friction force at the millisecond level through a servo closed-loop system with high dynamic response, real-time and precise control of the net output thrust can be achieved. This allows the square piston rod 6 to move strictly according to any preset variable acceleration curve, ultimately achieving the predetermined goal of variable thrust launch.

[0034] Working principle: When using this device, the propulsion chamber 7 is used to generate propulsion force. During operation, high-pressure air drives the propulsion piston device, which in turn drives the square piston rod 6 to move. A pressure sensor 21 is installed in the front and rear chambers of the integrated valve block 23, respectively. The pressure of the hydraulic servo cylinder is calculated and fed back through the pressure sensors 21 in the two chambers. Three servo valves 26 are installed on the upper end of the integrated valve block 23. The servo controller adjusts the flow rate of the servo valves according to the required pressure, thereby controlling the positive pressure output by the square piston rod 6. The piston 252 drives the pressure plate 254 to press the servo locking plate 27. The brake pad 24 fixed on the servo locking plate 27 rubs against the moving square piston rod 6 to generate friction. By adjusting the magnitude of the positive pressure output by the piston 252, the servo locking assembly 2 generates a reverse friction force. The resultant force acting on the square piston rod 6 causes the square piston rod 6 to output a variable thrust to generate a variable acceleration.

[0035] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A rail-guided missile launch variable thrust propulsion device, comprising a ground-mounted plate (1), characterized in that, A bearing seat (5) is fixedly connected to the upper side of the foundation mounting plate (1). A cylinder front seat (3) is fixedly installed on the left side of the bearing seat (5). A servo locking assembly (2) is provided on the left side of the cylinder front seat (3). A cylinder (11) is connected to the right side of the cylinder front seat (3) by bolts. A propulsion chamber (7) is opened inside the cylinder (11). An electric straight-through flange ball valve (9) is connected to the right side of the cylinder (11) by a flange. A high-pressure gas tank (10) is fixedly connected to the right side of the electric straight-through flange ball valve (9). A square piston rod (6) is provided inside the cylinder (11). A buffer chamber (4) and a propulsion chamber (7) are provided inside the cylinder (11). The buffer chamber (4) is located on the right side of the propulsion chamber (7). The servo locking assembly (2) includes a servo base (22), which is fixedly connected to the foundation mounting plate (1). An integrated valve block (23) is fixedly connected to the upper side of the servo base (22), and a servo valve (26) is fixedly connected to the upper side of the integrated valve block (23). A pressure sensor (21) is fixedly installed on the right side of the servo valve (26). A servo cylinder assembly (25) is provided on the lower side of the integrated valve block (23). A servo locking plate (27) is fixedly connected to the inner wall of the servo base (22), and three brake pads (24) are fixedly installed on the servo locking plate (27).

2. The rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, The servo cylinder assembly (25) includes a servo cylinder seat (251), which is located on the lower side of the integrated valve block (23). A piston (252) is provided inside the servo cylinder seat (251), and a servo cylinder cover (253) is threadedly connected to the upper side of the piston (252). A pressure plate (254) is provided inside the servo cylinder cover (253), and the pressure plate (254) is located on the upper side of the servo cylinder cover (253).

3. The rail-guided missile launch variable thrust propulsion device according to claim 2, characterized in that, The piston (252) is used to drive the pressure plate (254) under hydraulic action and transmit positive pressure to the brake pad (24) so ​​that the brake pad (24) comes into contact with the surface of the square piston rod (6) for friction.

4. The rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, One piston end of the square piston rod (6) divides the interior of the cylinder (11) into the propulsion chamber (7) and the buffer chamber (4).

5. The rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, The integrated valve block (23) is provided with a hydraulic oil source (8), and the servo valve (26) is connected to the hydraulic oil source (8).

6. The rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, The brake pad (24) is made of ceramic matrix composite material, and the brake pad (24) contacts the square piston rod (6) to form six friction surfaces.

7. A rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, The square piston rod (6) adopts a hollow structure.

8. A rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, The pressure sensor (21) is used to monitor the hydraulic pressure applied to the servo cylinder assembly (25) in real time, and the servo valve (26) is used to adjust the hydraulic flow and pressure entering the servo cylinder assembly (25) according to external control commands.

9. A rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, The high-pressure gas tank (10) is used to supply high-pressure gas to the propulsion chamber (7) to drive the square piston rod (6) to generate the main thrust for axial movement.

10. A rail-guided missile launch variable thrust propulsion device according to claim 1, characterized in that, The brake pad (24) is located on the movement path of the square piston rod (6).

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