Force balance type low-impact cold air pushing and punching actuator

Abstract

The force balance type low-impact cold air pushing and impacting actuator comprises a base, an air box is fixedly installed in the base, four redundant electromagnetic control valves are fixedly installed in the base, and one end of each redundant electromagnetic control valve communicates with a communicating pipe; the opening degree of the redundant electromagnetic control valve can be intelligently adjusted through a control system externally connected with the arranged pushing and punching assembly, so that the air supply rate of the air box to the interior of the actuator cylinder is increased, the driving force of the piston plate and the piston rod in the actuator cylinder is adjusted, and the driving force is gradually increased; the dynamic adjustment process ensures the stability and controllability of the separation push disc when the separation push disc is pushed away from the ground and runs at a high speed, and meanwhile, the use efficiency of energy is optimized, so that takeoff assistance is realized, the smoothness and reliability of the separation action are improved, the whole system is more stable and durable when running in a complex environment, and the service life of the system is prolonged. Impact and vibration in the separation process are greatly reduced, and related assemblies are protected against damage.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace equipment, and in particular to a force-balanced low-impact cold air thrust actuator. Background Art

[0002] Takeoff technology for aircraft and spacecraft is one of the most critical technologies in modern aviation and aerospace. During takeoff, aircraft and spacecraft must rapidly accelerate from a stationary state to high-speed flight, a process that places extremely high demands on propulsion systems and structural design. During takeoff, aircraft and spacecraft must not only overcome Earth's gravity but also withstand the immense gravitational and centrifugal forces of the acceleration process, posing significant challenges to the design and stability of propulsion systems.

[0003] Traditional thrust-ram actuators often generate large impact forces during operation. During the rocket separation process, excessive impact forces may damage the rocket structure, affecting the overall strength and stability of the rocket. Traditional thrust-ram actuators experience large losses during energy conversion, resulting in low energy utilization efficiency. Some thrust-ram actuators use traditional mechanical or hydraulic drive methods. During the energy transmission and conversion process, a large amount of energy is wasted due to factors such as friction and leakage. This not only increases energy consumption but also limits the vehicle's endurance and payload. Summary of the Invention

[0004] The object of the present invention is to provide a force-balanced low-impact cold air thrust actuator to solve the problems raised in the above-mentioned background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a force-balanced low-impact cold air push actuator, comprising a base, an air box fixedly installed inside the base, four redundant electromagnetic control valves fixedly installed inside the base, one end of each of the four redundant electromagnetic control valves is connected to a connecting pipe, four rotating seats 2 are fixedly installed on the outside of the base, and rotating sleeves 2 are movably installed inside the four rotating seats 2, one end of each of the rotating sleeves 2 is fixedly installed with a support plate, the end of the support plate away from the rotating sleeve 2 is fixedly installed with a mounting plate, the bottom of the mounting plate is fixedly installed with a push assembly, and the top of the base is installed with a drive assembly.

[0006] Preferably, the push-punch assembly includes an actuator cylinder, an assembly seat is fixedly installed on the top of the actuator cylinder, a mounting flange is fixedly installed on the top of the assembly seat, an air connection hole is opened inside the mounting flange, a piston plate is slidably installed inside the actuator cylinder, a piston rod is fixedly installed on the bottom of the piston plate, a locking nut is fixedly installed on the bottom of the piston rod, and a separation push plate is fixedly installed on the bottom of the locking nut.

[0007] Preferably, the top of the mounting flange is fixedly connected to the bottom of the mounting plate, and the end of the redundant electromagnetic control valve away from the connecting pipe is connected to the outside of the air box, and the end of the connecting pipe away from the redundant electromagnetic control valve passes through the rotating sleeve 2, the support plate and the mounting plate and is connected to the air inlet hole at the top of the mounting flange.

[0008] Preferably, reinforcing ribs are fixedly installed on the outer side of the actuating cylinder, and there are four reinforcing ribs, which are symmetrically installed on the outer side of the actuating cylinder.

[0009] Preferably, a pressure sensor is fixedly mounted on the outer side of the actuating cylinder, and a rate sensor is fixedly mounted on the outer side of the actuating cylinder, and the positions of the pressure sensor and the rate sensor are symmetrical.

[0010] Preferably, the driving assembly includes a connecting tube, a wiring control box is fixedly installed inside the connecting tube, four rotating seats three are fixedly installed on the outside of the connecting tube, rotating sleeves three are rotatably installed on the outsides of the four rotating seats three, a driving cylinder is fixedly installed on one end of the rotating sleeve three, and a rotating sleeve one is fixedly installed on the output end of the driving cylinder.

[0011] Preferably, the connecting cylinder is fixedly mounted on the top of the base, and the output end of the wiring control box is connected to the four driving cylinders through wires.

[0012] Preferably, a rotating seat 1 is fixedly mounted on the top of each of the four support plates, and the rotating sleeve 1 is rotatably mounted on the outer side of the rotating seat 1.

[0013] Compared with the prior art, the beneficial effects of the present invention are as follows: the control system connected to the external push-pull assembly intelligently adjusts the opening and closing degree of the redundant electromagnetic control valve, thereby adjusting the rate at which the air box supplies air to the inside of the actuator cylinder, thereby adjusting the magnitude of the driving force of the piston plate and the piston rod inside the actuator cylinder, causing it to gradually increase. This dynamic adjustment process ensures the stability and controllability of the separation push plate when it is pushed off the ground at high speed, while also optimizing the efficiency of energy use, thereby achieving takeoff assistance. This design not only improves the smoothness and reliability of the separation action, but also makes the entire system more robust and durable when operating in complex environments. This feature greatly reduces the impact and vibration during the separation process, protecting related components from damage.

[0014] Through meticulous design of the internal structure of the actuator and optimization of its functions, we have successfully created a pushing device that can provide large acceleration in the initial stage, then intelligently adjust the driving force, and achieve efficient buffering during two-stage separation, thereby meeting the needs of various high-demand application scenarios. The driving coil of the redundant electromagnetic control valve adopts a dual-coil mode to improve reliability and has extremely high reliability. At the same time, through the reasonable design of the parallel three-redundant valve diversion path, it can be ensured that under general fault modes, the pushing performance of the separation device reaches more than 90% of the separation performance under normal circumstances. This high-reliability design enables the device to play an important role at critical moments and avoids mission failures caused by equipment failures. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the three-dimensional appearance structure of the present invention.

[0016] Figure 2 This is a schematic diagram of the three-dimensional appearance structure of the present invention from another perspective.

[0017] Figure 3 This is a schematic diagram of the three-dimensional appearance structure of the present invention from another perspective.

[0018] Figure 4 This is a schematic diagram of the three-dimensional structure of the present invention without the drive assembly.

[0019] Figure 5 It is a schematic diagram of the local three-dimensional structure of the present invention.

[0020] Figure 6 It is a schematic diagram of the three-dimensional structure of the push-punch assembly of the present invention.

[0021] Figure 7 This is an enlarged structural diagram of point A of the present invention.

[0022] Figure 8 It is a schematic cross-sectional structural diagram of the push-punch assembly of the present invention.

[0023] In the figure: 1. Base; 2. Support plate; 3. Connecting cylinder; 4. Actuating cylinder; 5. Mounting plate; 6. Separation push plate; 7. Rotating sleeve 1; 8. Rotating seat 1; 9. Rotating sleeve 2; 10. Driving cylinder; 11. Rotating seat 3; 12. Rotating sleeve 3; 13. Connecting rod; 14. Wiring control box; 15. Reinforcement rib; 16. Rate sensor; 17. Rotating seat 2; 18. Air box; 19. Redundant electromagnetic control valve; 20. Connecting pipe; 21. Mounting flange; 22. Piston plate; 23. Piston rod; 24. Locking nut; 25. Air hole; 26. Assembly seat; 27. Pressure sensor. DETAILED DESCRIPTION

[0024] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0025] See also Figures 1-8 The present invention provides a technical solution: a force-balanced low-impact cold air push-and-punch actuator, comprising a base 1, an air box 18 fixedly installed inside the base 1, four redundant electromagnetic control valves 19 fixedly installed inside the base 1, one end of the four redundant electromagnetic control valves 19 are connected to a connecting pipe 20, four rotating seats 2 17 fixedly installed on the outside of the base 1, a rotating sleeve 2 9 movably installed inside the four rotating seats 2 17, one end of the rotating sleeve 2 9 is fixedly installed with a support plate 2, the end of the support plate 2 away from the rotating sleeve 2 9 is fixedly installed with a mounting plate 5, the bottom of the mounting plate 5 is fixedly installed with a push-and-punch assembly, a driving assembly is installed on the top of the base 1, the push-and-punch assembly includes an actuator cylinder 4, an assembly seat 26 is fixedly installed on the top of the assembly seat 26, a mounting flange 21 is fixedly installed on the top of the assembly seat 26, an air receiving hole 25 is opened inside the mounting flange 21, and the actuator cylinder 4 is fixed with an assembly seat 26. A piston plate 22 is slidably installed inside, and a piston rod 23 is fixedly installed at the bottom of the piston plate 22. A locking nut 24 is fixedly installed at the bottom of the piston rod 23, and a separation push plate 6 is fixedly installed at the bottom of the locking nut 24. The top of the mounting flange 21 is fixedly connected to the bottom of the mounting plate 5. The end of the redundant electromagnetic control valve 19 away from the connecting pipe 20 is connected to the outside of the air box 18. The end of the connecting pipe 20 away from the redundant electromagnetic control valve 19 passes through the rotating sleeve 29, the support plate 2 and the mounting plate 5 and is connected to the air inlet 25 at the top of the mounting flange 21. A reinforcing rib 15 is fixedly installed on the outside of the actuator cylinder 4. There are four reinforcing ribs 15, and the four reinforcing ribs 15 are symmetrically installed on the outside of the actuator cylinder 4. A pressure sensor 27 is fixedly installed on the outside of the actuator cylinder 4. A rate sensor 16 is fixedly installed on the outside of the actuator cylinder 4, and the positions of the pressure sensor 27 and the rate sensor 16 are relatively symmetrical.

[0026] The working principle of the above technical solution: first, assemble the device with the external required equipment. During takeoff, the control system external to the thrust assembly will intelligently adjust the opening and closing degree of the redundant electromagnetic control valve 19, so that the air box 18 supplies air to the inside of the actuator cylinder 4 at a rate that adjusts the size of the driving force of the piston plate 22 and the piston rod 23 inside the actuator cylinder 4, making it gradually increase. This dynamic adjustment process ensures the stability and controllability of the separation push plate 6 when it is pushed off the ground at high speed, and also optimizes the efficiency of energy use, thereby achieving takeoff assistance. This design not only improves the smoothness and reliability of the separation action, but also makes the entire system more robust and durable when operating in a complex environment. This feature greatly reduces the impact and vibration during the separation process. movement, protecting related components from damage. Through meticulous design of the internal structure of the actuator 4 and functional optimization, a pushing device has been successfully created that can provide large acceleration in the initial stage, then intelligently adjust the driving force, and achieve efficient buffering during two-stage separation, thereby meeting the needs of various high-demand application scenarios. The driving coil of the redundant electromagnetic control valve 19 adopts a dual-coil mode to improve reliability, and has extremely high reliability. At the same time, through the reasonable design of the parallel three-redundancy valve diversion path, it can be ensured that under general fault mode, the pushing performance of the separation device reaches more than 90% of the separation performance under normal circumstances. This high-reliability design enables the device to play an important role at critical moments and avoids mission failures caused by equipment failures.

[0027] In another embodiment, Figures 1-8 As shown, the drive assembly includes a connecting tube 3, a wiring control box 14 is fixedly installed inside the connecting tube 3, four rotating seats 3 11 are fixedly installed on the outside of the connecting tube 3, and rotating sleeves 3 12 are rotatably installed on the outsides of the four rotating seats 3 11. One end of the rotating sleeve 3 12 is fixedly installed with a driving cylinder 10, and the output end of the driving cylinder 10 is fixedly installed with a rotating sleeve 7. The connecting tube 3 is fixedly installed on the top of the base 1, and the output end of the wiring control box 14 is connected to the four driving cylinders 10 through a wire. The top of the four support plates 2 is fixedly installed with a rotating seat 8, and the rotating sleeves 7 are rotatably installed on the outside of the rotating seat 8.

[0028] After the device takes off, the drive cylinder 10 can be started to retract through the wiring control box 14, thereby pulling the support plate 2 to move by rotating the sleeve 7 and the rotating seat 8, so that the support plate 2 is close to the connecting tube 3. As an important component of the device, the support plate 2 is originally in an expanded state, providing necessary support and stability for the take-off and initial flight of the device. However, during the flight, the expanded support plate will increase air resistance and affect the flight efficiency. Under the pull of the rotating seat 8, the support plate 2 begins to move slowly and gradually approaches the connecting tube 3. As the support plate 2 continues to approach the connecting tube 3, the overall shape of the device gradually becomes more compact, and the windward area originally increased due to the expansion of the support plate 2 is significantly reduced, which greatly reduces the resistance encountered during flight, making the flight smoother, while also reducing energy consumption and extending the endurance of the device.

[0029] Working principle: First, assemble the device with the external required equipment. During takeoff, the control system external to the thrust assembly will intelligently adjust the opening and closing degree of the redundant electromagnetic control valve 19, so that the air box 18 supplies air to the inside of the actuator 4 at a rate that adjusts the size of the driving force of the piston plate 22 and the piston rod 23 inside the actuator 4, making it gradually increase. This dynamic adjustment process ensures the stability and controllability of the separation push plate 6 when it is pushed off the ground at high speed, and also optimizes the energy utilization efficiency, thereby achieving takeoff assistance. This design not only improves the smoothness and reliability of the separation action, but also makes the entire system more robust and durable when operating in a complex environment. This feature greatly reduces the impact and vibration during the separation process and protects related components from damage. Through meticulous internal structural design and functional optimization of the actuator 4, a push-out device has been successfully created that can provide large acceleration in the initial stage, then intelligently adjust the driving force, and achieve efficient buffering during two-stage separation, thereby meeting the needs of various high-demand application scenarios. The drive coil of the redundant electromagnetic control valve 19 adopts a dual-coil mode to improve reliability and has extremely high reliability. At the same time, through the reasonable design of the parallel three-way redundant valve diversion path, it can be ensured that under normal failure modes, the release performance of the separation device reaches more than 90% of the separation performance under normal conditions. This high-reliability design enables the device to play an important role at critical moments and avoids mission failure due to equipment failure. After the device takes off, the drive cylinder 10 can be activated to retract through the wiring control box 14, thereby pulling the support plate 2 to move by rotating the sleeve 7 and rotating the seat 8, so that the support plate 2 is close to the connecting tube 3. As an important component of the device, the support plate 2 is originally in an expanded state, providing the necessary support and stability for the device's takeoff and initial flight. However, during flight, the expanded support plate increases air resistance and affects flight efficiency. Under the pull of the rotating seat 8, the support plate 2 begins to move slowly, gradually approaching the connecting tube 3. As the support plate 2 continues to approach the connecting tube 3, the overall shape of the device gradually becomes more compact. The windward area originally increased by the expansion of the support plate 2 is significantly reduced, greatly reducing the resistance encountered during flight, making the flight smoother, while also reducing energy consumption and extending the device's endurance.

[0030] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A force-balanced low-impact cold air push actuator, comprising a base (1), characterized in that: An air box (18) is fixedly installed inside the base (1), four redundant electromagnetic control valves (19) are fixedly installed inside the base (1), one end of each of the four redundant electromagnetic control valves (19) is connected to a connecting pipe (20), four rotating seats (17) are fixedly installed on the outside of the base (1), and a rotating sleeve (9) is movably installed inside each of the four rotating seats (17), one end of each of the rotating sleeves (9) is fixedly installed with a support plate (2), and one end of each of the support plates (2) away from the rotating sleeve (9) is fixedly installed with a mounting plate (5), the bottom of each of the mounting plates (5) is fixedly installed with a push assembly, and a driving assembly is installed on the top of the base (1).

2. A force-balanced low-impact cold air push actuator according to claim 1, characterized in that: The push-punch assembly includes an actuating cylinder (4), an assembly seat (26) is fixedly installed on the top of the actuating cylinder (4), a mounting flange (21) is fixedly installed on the top of the assembly seat (26), an air connection hole (25) is provided inside the mounting flange (21), a piston plate (22) is slidably installed inside the actuating cylinder (4), a piston rod (23) is fixedly installed on the bottom of the piston plate (22), a locking nut (24) is fixedly installed on the bottom of the piston rod (23), and a separation push plate (6) is fixedly installed on the bottom of the locking nut (24).

3. A force-balanced low-impact cold air thrust actuator according to claim 2, characterized in that: The top of the mounting flange (21) is fixedly connected to the bottom of the mounting plate (5), and the end of the redundant electromagnetic control valve (19) away from the connecting pipe (20) is connected to the outside of the air box (18). The end of the connecting pipe (20) away from the redundant electromagnetic control valve (19) passes through the rotating sleeve (9), the support plate (2) and the mounting plate (5) and is connected to the air connection hole (25) at the top of the mounting flange (21).

4. A force-balanced low-impact cold air thrust actuator according to claim 3, characterized in that: A reinforcing rib (15) is fixedly installed on the outer side of the actuating cylinder (4), and there are four reinforcing ribs (15), which are symmetrically installed on the outer side of the actuating cylinder (4).

5. The force-balanced low-impact cold air thrust actuator according to claim 4, characterized in that: A pressure sensor (27) is fixedly mounted on the outside of the actuating cylinder (4), and a rate sensor (16) is fixedly mounted on the outside of the actuating cylinder (4), and the positions of the pressure sensor (27) and the rate sensor (16) are symmetrical.

6. A force-balanced low-impact cold air thrust actuator according to claim 5, characterized in that: The driving assembly comprises a connecting cylinder (3), a wiring control box (14) is fixedly installed inside the connecting cylinder (3), four rotating seats (11) are fixedly installed on the outside of the connecting cylinder (3), a rotating sleeve (12) is rotatably installed on the outside of the four rotating seats (11), a driving cylinder (10) is fixedly installed on one end of the rotating sleeve (12), and a rotating sleeve (7) is fixedly installed on the output end of the driving cylinder (10).

7. The force-balanced low-impact cold air thrust actuator according to claim 6, characterized in that: The connecting cylinder (3) is fixedly mounted on the top of the base (1), and the output end of the wiring control box (14) is connected to the four driving cylinders (10) via wires.

8. The force-balanced low-impact cold air thrust actuator according to claim 7, characterized in that: A rotating seat (8) is fixedly mounted on the top of each of the four support plates (2), and the rotating sleeve (7) is rotatably mounted on the outer side of the rotating seat (8).

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