Two-stage redundancy high-reliability landing buffer device

Abstract

The two-stage redundant high-reliability landing buffer device comprises a buffer assembly and a gas cylinder, the buffer assembly comprises an actuator cylinder, a piston plate is slidably and hermetically mounted in the actuator cylinder, and a piston rod is fixedly mounted on one side of the piston plate; by means of the well-designed buffer device structure and function layout, the rocket can have strong driving force in the initial stage when landing, a remarkable acceleration is provided for the separation process, it is ensured that the separation action is rapid and powerful, and the landing speed is gradually increased; a control system externally connected with the buffer assembly can intelligently adjust the opening degree of the redundant electromagnetic control valve, so that the gas supply rate of the gas cylinder to the interior of the actuator cylinder is adjusted, and the driving force of the piston plate and the piston rod in the actuator cylinder is adjusted to be gradually reduced; the dynamic adjustment process ensures the stability and controllability of the push-out device externally connected with the separation push disc during high-speed operation, and meanwhile, the use efficiency of energy is also optimized.

Description

Technical Field

[0001] The present invention relates to the technical field of rocket landing, and in particular to a two-stage redundant high-reliability landing buffer device. Background Art

[0002] During the landing process, aircraft, spacecraft or heavy transport vehicles experience a sharp transition from high-speed flight to a stationary state. This process not only requires extremely high precision and stability, but also faces huge impact challenges.

[0003] Traditional landing cushioning systems have long relied on several relatively simple cushioning mechanisms to cope with the huge impact during landing. These mechanisms include but are not limited to airbags, hydraulic shock absorbers, and spring systems. The airbag system is popular for its good energy absorption capacity and light weight, but under extreme environmental conditions, such as high or low temperatures, the performance of the airbag material may be affected, resulting in a significant reduction in its cushioning effect. Hydraulic shock absorbers dissipate energy through the flow of liquid. Although the effect is significant, the complex hydraulic system has high requirements for sealing and maintenance. Once a failure occurs, it is difficult to repair. The spring system is widely used because of its simplicity and reliability, but in the face of extremely large impacts, the deformation of the spring may exceed the design limit, resulting in permanent deformation or breakage, which in turn affects its subsequent use.

[0004] Although these traditional landing cushioning systems can effectively absorb the impact energy during landing and protect the landing body from serious damage to a certain extent, their reliability and redundancy are insufficient when facing extreme environments or system failures. Extreme environmental conditions, such as extreme temperatures, strong winds, and sandstorms, may affect the normal operation of the cushioning system, resulting in poor cushioning effect. System failures, such as leakage, breakage, or electronic control failure, may directly lead to serious consequences such as landing failure or equipment damage. Therefore, in order to improve the safety and stability during landing, it is urgent to develop a new type of landing cushioning device with high redundancy and high reliability. Summary of the invention

[0005] The object of the present invention is to provide a two-level redundant high-reliability landing buffer device to solve the problems raised in the above background technology.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a two-stage redundant high-reliability landing buffer device, including a buffer assembly and a gas cylinder, the buffer assembly including an actuator cylinder, the internal sliding seal of the actuator cylinder is installed with a piston plate, a piston rod is fixedly installed on one side of the piston plate, a separation push plate is installed on the end of the piston rod away from the piston plate, an assembly seat is fixedly installed on one end of the actuator cylinder, a mounting flange is installed on the side of the assembly seat away from the actuator cylinder, an air connection hole is opened in the mounting flange, one end of the gas cylinder is connected to a connecting pipe, and a redundant electromagnetic control valve is fixedly connected to the middle part of the connecting pipe.

[0007] Preferably, one end of the connecting pipe away from the gas cylinder is sealed and inserted into the inner side of the gas connecting hole.

[0008] Preferably, the internal thread connection of the assembly seat is provided with a plurality of assembly bolts, and the assembly seat and the mounting flange are sealed and connected via the plurality of assembly bolts.

[0009] Preferably, the internal threads of the mounting flange are connected with a plurality of mounting bolts.

[0010] Preferably, four reinforcing ribs are fixedly mounted on the outer side of the actuating cylinder, and a pressure sensor and a rate sensor are respectively fixedly mounted inside one end of two of the reinforcing ribs.

[0011] Preferably, a locking nut is sleeved and installed on the outer side of the connection between the piston rod and the separation push plate.

[0012] Preferably, a pressure gauge is connected to the outside of the gas cylinder.

[0013] Preferably, the outer side of the connecting pipe is connected to a pressure relief pipe, and the middle part of the pressure relief pipe is fixedly connected to an electromagnetic relief valve.

[0014] Compared with the prior art, the beneficial effects of the present invention are as follows: through the carefully designed buffer device structure and functional layout, a strong driving force can be provided in the initial stage when the rocket is landing, providing a significant acceleration for the separation process, ensuring that the separation action is rapid and powerful. As the landing speed gradually increases, the control system external to the buffer assembly will intelligently adjust the opening and closing degree of the redundant electromagnetic control valve, thereby adjusting the rate at which the gas cylinder supplies gas to the inside of the actuator, thereby adjusting the size of the driving force of the piston plate and the piston rod inside the actuator to gradually reduce it. This dynamic adjustment process ensures the stability and controllability of the ejection device external to the separation push plate when running at high speed, and also optimizes the energy efficiency.

[0015] In addition, at the critical moment of two-stage separation, the design of the buffer component further demonstrates its exquisiteness. At this time, the buffer effect can be easily achieved by only dissipating the kinetic energy of the piston plate and the piston rod inside the actuator. This feature greatly reduces the impact and vibration during the separation process and protects related components from damage. 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. Through meticulous internal structural design and functional optimization of the actuator, 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;

[0016] In addition, the driving coil of the redundant electromagnetic control valve and the electromagnetic switch 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-redundancy valve shunt path, it can be ensured that under a single fault mode, the separation device's ejection performance can reach more than 90% of the separation performance under normal circumstances. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic diagram of the three-dimensional appearance structure of the present invention.

[0018] Figure 2 It is a schematic diagram of the three-dimensional structure of the present invention when viewed from above.

[0019] Figure 3 It is a schematic diagram of the three-dimensional structure of the buffer assembly of the present invention.

[0020] Figure 4 For the present invention Figure 3 Enlarged structural diagram at A in the middle.

[0021] Figure 5 It is a schematic diagram of the local three-dimensional structure of the present invention.

[0022] Figure 6 It is a schematic diagram of the cross-sectional structure of the buffer assembly of the present invention.

[0023] In the figure: 1. Actuator; 2. Gas cylinder; 3. Reinforcement rib; 4. Mounting flange; 5. Pressure sensor; 6. Piston rod; 7. Locking nut; 8. Separation push plate; 9. Connecting pipe; 10. Redundant electromagnetic control valve; 11. Pressure relief pipe; 12. Electromagnetic relief valve; 13. Pressure gauge; 14. Assembly seat; 15. Assembly bolts; 16. Mounting bolts; 17. Piston plate; 18. Air connection hole; 19. Rate sensor. DETAILED DESCRIPTION

[0024] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

[0025] See also Figure 1-Figure 6 The present invention provides a technical solution: a two-stage redundant high-reliability landing buffer device, comprising a buffer assembly and a gas cylinder 2, the buffer assembly comprising an actuator 1, a piston plate 17 is installed in the internal sliding seal of the actuator 1, a piston rod 6 is fixedly installed on one side of the piston plate 17, a separation push plate 8 is installed on the end of the piston rod 6 away from the piston plate 17, an assembly seat 14 is fixedly installed on one end of the actuator 1, a mounting flange 4 is installed on the side of the assembly seat 14 away from the actuator 1, an air connection hole 18 is opened inside the mounting flange 4, one end of the gas cylinder 2 is connected with a connecting pipe 9, a middle part of the connecting pipe 9 is fixedly connected with a redundant electromagnetic control valve 10, four reinforcing ribs 3 are fixedly installed on the outside of the actuator 1, wherein a pressure sensor 5 and a rate sensor 19 are fixedly installed inside one end of two reinforcing ribs 3 respectively, a locking nut 7 is sleeved on the outer side of the connection between the piston rod 6 and the separation push plate 8, and a pressure gauge 13 is connected to the outside of the gas cylinder 2.

[0026] The working principle of the above technical solution: through the carefully designed buffer device structure and functional layout, it can be made to have a strong driving force in the initial stage when the rocket is landing, providing a significant acceleration for the separation process, ensuring that the separation action is quick and powerful. As the landing speed gradually increases, the control system external to the buffer component will intelligently adjust the opening and closing degree of the redundant electromagnetic control valve 10, thereby adjusting the rate at which the gas cylinder 2 supplies air to the inside of the actuator cylinder 1, thereby adjusting the size of the driving force of the piston plate 17 and the piston rod 6 inside the actuator cylinder 1, making it gradually reduce. This dynamic adjustment process ensures the stability and controllability of the ejection device external to the separation push plate 8 when running at high speed, and also optimizes the energy utilization efficiency. At the critical moment of reaching the two-stage separation, the design of the buffer component further demonstrates its exquisiteness. At this time, it is only necessary to dissipate the piston plate 17 and the piston rod 6 in the actuator cylinder 1. This feature greatly reduces the impact and vibration during the separation process and protects related components from damage. 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. Through meticulous internal structure design and function optimization of the actuator 1, a push-out device is 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 10 electromagnetic switch 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-redundancy valve shunt path, it can be guaranteed that under a single-fault mode, the push-out performance of the separation device reaches more than 90% of the separation performance under normal circumstances.

[0027] In another embodiment, Figure 1-Figure 6 As shown, the internal thread of the assembly seat 14 is connected with a plurality of assembly bolts 15 , and the assembly seat 14 and the mounting flange 4 are sealedly connected via the plurality of assembly bolts 15 , and the internal thread of the mounting flange 4 is connected with a plurality of mounting bolts 16 .

[0028] The assembly seat 14 and the mounting flange 4 can be assembled by means of the provided assembly bolts 15 , and the mounting flange 4 can be installed at a desired position by means of the provided mounting bolts 16 .

[0029] In another embodiment, Figure 1-Figure 6 As shown, the outer side of the connecting pipe 9 is connected to a pressure relief pipe 11 , and the middle part of the pressure relief pipe 11 is fixedly connected to an electromagnetic relief valve 12 .

[0030] The pressure relief pipe 11 and the pressure gauge 13 are provided to facilitate pressure relief of the entire device.

[0031] Working principle: Through the carefully designed structure and functional layout of the buffer device, a strong driving force can be provided in the initial stage when the rocket is landing, providing a significant acceleration for the separation process, ensuring that the separation action is rapid and powerful. As the landing speed gradually increases, the control system external to the buffer component will intelligently adjust the opening and closing degree of the redundant electromagnetic control valve 10, thereby adjusting the rate at which the gas cylinder 2 supplies air to the inside of the actuator 1, thereby adjusting the size of the driving force of the piston plate 17 and the piston rod 6 inside the actuator 1, causing it to gradually decrease. This dynamic adjustment process ensures the stability and controllability of the ejection device external to the separation push plate 8 when running at high speed, and also optimizes the energy efficiency. At the critical moment of reaching the two-stage separation, the design of the buffer component further demonstrates its exquisiteness. At this time, it only needs to dissipate the kinetic energy of the piston plate 17 and the piston rod 6 inside the actuator 1 to easily achieve the buffering effect. This feature greatly reduces the impact and vibration during the separation process and protects related components from damage. This design not only improves the smoothness and reliability of the separation action. , and also makes the entire system more robust and durable when operating in a complex environment. Through meticulous internal structural design and functional optimization of the actuator 1, a push-out device that can provide large acceleration in the initial stage, then intelligently adjust the driving force, and achieve efficient buffering during two-stage separation has been successfully created, thereby meeting the needs of various high-demand application scenarios. The redundant electromagnetic control valve 10 electromagnetic switch valve drive coil adopts a double-coil mode to improve reliability and has extremely high reliability. At the same time, through the reasonable design of the parallel three-redundancy valve shunt path, it can be ensured that under a single-fault mode, the push-out performance of the separation device reaches more than 90% of the separation performance under normal circumstances. The assembly seat 14 and the mounting flange 4 can be assembled by the set assembly bolts 15, and the mounting flange 4 can be installed in the desired position by the set mounting bolts 16. The pressure relief pipe 11 and the pressure gauge 13 are convenient for depressurizing the entire device. The redundant design scheme is adopted in the design, which can improve the reliability of the scheme on the one hand, and reduce the difficulty of designing the peak flow and response time of the valve on the other hand.

[0032] Although 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 the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A two-level redundant high-reliability landing cushioning device, comprising a cushioning assembly and a gas cylinder (2), characterized in that: The buffer assembly comprises an actuator cylinder (1), a piston plate (17) is installed in an internal sliding seal of the actuator cylinder (1), a piston rod (6) is fixedly installed on one side of the piston plate (17), a separation push plate (8) is installed on the end of the piston rod (6) away from the piston plate (17), an assembly seat (14) is fixedly installed on one end of the actuator cylinder (1), a mounting flange (4) is installed on the side of the assembly seat (14) away from the actuator cylinder (1), an air connection hole (18) is opened inside the mounting flange (4), one end of the gas cylinder (2) is connected to a connecting pipe (9), and a redundant electromagnetic control valve (10) is fixedly connected to the middle part of the connecting pipe (9).

2. A two-level redundant high-reliability landing cushioning device according to claim 1, characterized in that: One end of the connecting pipe (9) away from the gas cylinder (2) is sealed and inserted into the inner side of the gas receiving hole (18).

3. The two-level redundant high-reliability landing cushioning device according to claim 2, characterized in that: The internal threads of the assembly seat (14) are connected with a plurality of assembly bolts (15), and the assembly seat (14) and the mounting flange (4) are sealedly connected via the plurality of assembly bolts (15).

4. The two-level redundant high-reliability landing buffer device according to claim 3, characterized in that: The internal threads of the mounting flange (4) are connected with a plurality of mounting bolts (16).

5. The two-level redundant high-reliability landing cushioning device according to claim 4, characterized in that: Four reinforcing ribs (3) are fixedly mounted on the outer side of the actuator cylinder (1), wherein a pressure sensor (5) and a speed sensor (19) are respectively fixedly mounted inside one end of two of the reinforcing ribs (3).

6. A two-level redundant high-reliability landing cushioning device according to claim 5, characterized in that: A locking nut (7) is sleeved and installed on the outer side of the connection between the piston rod (6) and the separation push plate (8).

7. A two-level redundant high-reliability landing cushioning device according to claim 6, characterized in that: The outer side of the gas cylinder (2) is connected to a pressure gauge (13).

8. The two-level redundant high-reliability landing buffer device according to claim 7, characterized in that: The outer side of the connecting pipe (9) is connected to a pressure relief pipe (11), and the middle part of the pressure relief pipe (11) is fixedly connected to an electromagnetic relief valve (12).

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