A composite general aviation aircraft anti-crash buffer energy absorption structure

Abstract

The present invention discloses a composite general aviation anti-crash buffer energy absorption structure, comprising: a piston cylinder seat, a piston outer cylinder, a piston inner cylinder, an air cavity, a floating piston, an annular flange, a tool fixing bolt, a cutting tool, a cutting tube, a piston, an oil cylinder, an oil cavity, an oil needle, an oil cylinder seat, an oil cylinder connecting bolt, an oil hole, a piston seal, and a floating piston seal. The piston seal and the floating piston seal are respectively installed on both sides of the corresponding components, and the components are assembled in an orderly manner to ensure the sealing of the oil cavity. This structure realizes multi-stroke buffer energy absorption and efficiently dissipates impact kinetic energy by combining cutting deformation of the cutting tube, friction between the oil and the oil hole, and air compression. During compression, the piston outer cylinder and the annular flange move axially along the cutting tube, improving the ability to resist lateral loads. The flow of oil carries away cutting heat, solving the problem of tool melting and reducing tool costs. The cutting tube can also be replaced by disassembling the oil cylinder seat to achieve reuse, reducing the cost of use, and achieving both good performance and economy.

Description

Technical Field

[0001] The present invention relates to the field of buffer mechanism design, and in particular to a composite general aircraft anti-crash buffer energy absorption structure. Background Art

[0002] Currently, independent oil-gas buffers, cutting-type energy-absorbing structures, and crushing-type energy-absorbing structures are commonly used for buffering and energy absorption. However, the connection between the inner and outer cylinders of the oil-gas buffer relies on the cooperation between the piston and the inner wall of the outer cylinder. The lateral stability of the structure is poor, and the effective working stroke does not exceed 50% of the total length of the structure, which limits the energy absorption effect of the structure. When the cutting force is large, the cutting-type energy-absorbing structure is prone to causing the tool to melt and deform. It has high requirements for the strength and thermal stability of the structural material, which limits the improvement of the total energy absorption of the structure. The crushing-type energy-absorbing structure occupies a part of the buffer stroke after the material is compacted, which has a significant impact on the total energy absorption of the buffer, and the stability of the structure itself is poor.

[0003] Therefore, it is necessary to develop a composite general aviation aircraft anti-crash buffer energy absorption structure to solve the above problems. Summary of the Invention

[0004] The purpose of the present invention is to provide a composite general aircraft anti-crash buffer energy absorption structure that realizes multi-stroke buffer energy absorption, effectively consumes impact kinetic energy, while improving the lateral stability of the structure, solving the problem of tool melting under large loads and reducing the cost of use.

[0005] In order to achieve the above object, the present invention provides the following technical solutions:

[0006] A composite general aircraft crash-resistant buffer energy-absorbing structure, comprising: a piston cylinder seat, a piston outer cylinder, a piston inner cylinder, an air cavity, a floating piston, an annular flange, a tool fixing bolt, a cutting tool, a cutting tube, a piston, an oil cylinder, an oil cavity, an oil needle, an oil cylinder seat, an oil cylinder connecting bolt, an oil hole, a piston seal ring, and a floating piston seal ring;

[0007] The piston sealing ring is installed on both sides of the piston, and the floating piston sealing ring is installed on both sides of the floating piston; then the piston is installed on the piston inner cylinder and the floating piston is installed on the bottom of the air cavity in turn; the oil needle is installed at the oil hole to ensure that it can adjust the size of the oil hole normally; the cutting tool is installed on the annular flange through the tool fixing bolt so that the cutting tool is evenly distributed along the ring; the annular flange is fixedly connected to the piston outer cylinder, and then the piston outer cylinder is connected to the piston cylinder seat; the oil cylinder and the oil cylinder seat are connected through the oil cylinder connecting bolts to ensure that the oil chamber is well sealed, and finally the cutting tube is installed on the outside of both sides of the oil chamber.

[0008] Specifically, during compression, the piston outer cylinder and the annular flange move axially along the cutting tube.

[0009] Specifically, the cutting contact point between the cutting tool and the cutting tube is always located in the upper layer of the oil.

[0010] Specifically, the oil cylinder seat can be disassembled and the cutting tube can be replaced through the oil cylinder connecting bolts.

[0011] The beneficial effects of the present invention are:

[0012] 1. The present invention realizes multi-stroke buffering energy absorption by combining cutting deformation of cutting tube, friction between oil and oil hole, and air compression, effectively consuming impact kinetic energy. The energy absorption effect is significantly better than the traditional single energy absorption device.

[0013] 2. When the structure is compressed, the outer cylinder of the piston and the annular flange move along the axial direction of the cutting tube, which greatly improves the ability to resist lateral loads, enhances the lateral stability of the device, and can adapt to more complex working conditions.

[0014] 3. The unique heat dissipation mechanism uses the flow of oil to take away the high temperature generated by cutting, solving the problem of tool melting under heavy loads, reducing the requirements for tool materials, and thus reducing tool costs.

[0015] 4. The cutting tube can be replaced by disassembling the oil cylinder seat, so that other structures can be reused, which reduces the overall cost of use and has good economic efficiency.

[0016] The above description is only an overview of the technical solution of the present invention. In order to more clearly understand the technical means of the present invention and implement it according to the contents of the specification, the following is a detailed description of the preferred embodiments of the present invention with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 The present invention is a schematic structural diagram of a composite general aircraft anti-crash buffer energy absorption structure.

[0018] Figure numerals: 1. Piston cylinder seat; 2. Piston outer cylinder; 3. Piston inner cylinder; 4. Air cavity; 5. Floating piston; 6. Annular flange; 7. Tool fixing bolt; 8. Cutting tool; 9. Cutting tube; 10. Piston; 11. Oil cylinder; 12. Oil cavity; 13. Oil needle; 14. Oil cylinder seat; 15. Oil cylinder connecting bolt; 16. Oil hole; 17. Piston sealing ring; 18. Floating piston sealing ring. DETAILED DESCRIPTION

[0019] The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. All other embodiments obtained by ordinary technicians in this field based on the embodiments of the present invention without making any creative efforts shall fall within the scope of protection of the present invention.

[0020] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate and simplify the description of the present invention. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation, and therefore should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0021] In the description of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed, detachable, or integral connections; mechanical or electrical connections; direct or indirect connections through an intermediate medium; and internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0022] In addition, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0023] See Figure 1 The composite general aircraft crash-resistant cushioning and energy-absorbing structure shown in this application includes: a piston cylinder seat 1, a piston outer cylinder 2, a piston inner cylinder 3, an air cavity 4, a floating piston 5, an annular flange 6, a tool fixing bolt 7, a cutting tool 8, a cutting tube 9, a piston 10, an oil cylinder 11, an oil cavity 12, an oil needle 13, an oil cylinder seat 14, an oil cylinder connecting bolt 15, an oil hole 16, a piston seal 17, and a floating piston seal 18;

[0024] The piston sealing ring 17 is installed on both sides of the piston 10, and the floating piston sealing ring 18 is installed on both sides of the floating piston 5; then the piston 10 is installed on the piston inner cylinder 3 and the floating piston 5 is installed on the bottom of the air cavity 4 in turn; the oil needle 13 is installed at the oil hole 16 to ensure that it can normally adjust the size of the oil hole 16; the cutting tool 8 is installed on the annular flange 6 through the tool fixing bolt 7 so that the cutting tool 8 is evenly distributed along the ring; the annular flange 6 is fixedly connected to the piston outer cylinder 2, and then the piston outer cylinder 2 is connected to the piston cylinder seat 1; the oil cylinder 11 and the oil cylinder seat 14 are connected through the oil cylinder connecting bolts 15 to ensure that the oil chamber 12 is well sealed, and finally the cutting tube 9 is installed on the outside of both sides of the oil chamber 12.

[0025] Specifically, during compression, the piston outer cylinder 2 and the annular flange 6 move axially along the cutting tube 9, which greatly improves the ability of the structure to resist lateral loads and enhances the lateral stability of the structure.

[0026] Specifically, the cutting contact point between the cutting tool 8 and the cutting tube 9 is always located in the upper layer of the oil, so the high temperature generated by cutting can be transferred to the oil and carried away by the flow of the upper oil, which has a good heat dissipation effect, solves the problem of melting the cutting tool 8 under large loads, and reduces the material requirements for the tool, thereby reducing the tool cost.

[0027] Specifically, the oil cylinder seat 14 can be disassembled through the oil cylinder connecting bolts 15, and the cutting tube 9 can be replaced, so that other structures can be reused and the use cost can be reduced.

[0028] How it works

[0029] Compression Stroke: During operation, piston cylinder seat 1 first drives piston outer cylinder 2 and piston inner cylinder 3 into axial compression. Piston outer cylinder 2 is fixedly connected to annular flange 6, which is connected to cutting tools 8 via tool fixing bolts 7. This facilitates tool replacement. The number of cutting tools 8 can be flexibly adjusted and evenly distributed around annular flange 6. During axial compression, cutting tools 8 cut into cutting tube 9, absorbing impact energy through cutting deformation.

[0030] The piston inner tube 3 is fixedly connected to the piston 10. During compression, the oil in the oil chamber 12 flows through the oil hole 16 to the other side, forcing the floating piston 5 to compress the gas in the air chamber 4. The oil needle 13 adjusts the size of the oil hole 16, absorbing the impact energy through friction between the oil and the oil hole 16. As the compression process progresses, the oil needle 13 gradually reduces the area of ​​the oil hole 16, gradually increasing the compression force. This air compression cushions the impact force and converts some of the impact kinetic energy into potential energy. Therefore, during the initial compression of the structure, the impact energy is absorbed simultaneously through the cutting deformation of the cutting tube 9 and the friction between the oil and the oil hole 16, improving energy absorption.

[0031] Extension Stroke: When the compression force reaches its maximum, the floating piston 5, driven by the potential energy of the gas, causes the piston 10, cutting tool 8, and their connected components to rebound, and the structure enters the extension stroke. During this period, the cutting tool 8 is inactive, and energy is absorbed solely through friction between the oil and the oil hole 16. After the extension stroke, the structure enters the compression stroke again. The cutting resistance between the cutting tool 8 and the cutting tube 9 is greatly reduced, but energy can still be absorbed through friction between them. This structure thus achieves multi-stroke energy absorption, gradually dissipating the impact kinetic energy.

[0032] The technical features of the above-mentioned embodiments can be combined arbitrarily. In order to make the description concise, not all possible combinations of the technical features in the above-mentioned embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0033] The above-described embodiments merely illustrate several implementations of the present invention, and while their descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the patent. It should be noted that a person skilled in the art would be able to make numerous variations and improvements without departing from the spirit of the present invention, all of which fall within the scope of protection of the present invention. Therefore, the scope of protection of the patent for this invention shall be determined by the appended claims.

Claims

1. A composite general aviation aircraft anti-crash buffer energy absorption structure, characterized in that: include: Piston cylinder seat, piston outer cylinder, piston inner cylinder, air cavity, floating piston, annular flange, tool fixing bolts, cutting tool, cutting tube, piston, oil cylinder, oil cavity, oil needle, oil cylinder seat, oil cylinder connecting bolts, oil hole, piston seal ring, floating piston seal ring; The piston sealing ring is installed on both sides of the piston, and the floating piston sealing ring is installed on both sides of the floating piston; the piston is installed on the piston inner cylinder in sequence, and the floating piston is installed at the bottom of the air cavity; the oil needle is installed at the oil hole; the cutting tool is installed on the annular flange through the tool fixing bolts, and the cutting tool is evenly distributed along the annular flange; the annular flange is fixedly connected to the piston outer cylinder, and the piston outer cylinder is connected to the piston cylinder seat; the oil cylinder and the oil cylinder seat are connected through the oil cylinder connecting bolts, and the cutting tube is installed on the outside of both sides of the oil cavity.

2. The composite general aircraft crash-resistant buffer energy-absorbing structure according to claim 1, characterized in that: When the structure is compressed, the piston outer cylinder and the annular flange move axially along the cutting tube.

3. The composite general aircraft crash-resistant buffer energy-absorbing structure according to claim 1, characterized in that: The cutting contact point between the cutting tool and the cutting tube is always located in the upper layer of the oil.

4. The composite general aircraft crash-resistant buffer energy-absorbing structure according to claim 1, characterized in that: The oil cylinder seat can be disassembled and the cutting tube can be replaced through the oil cylinder connecting bolts.

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