Anti-crash buffering and energy-absorbing structure of combined type general aircraft

Abstract

The invention discloses an anti-crash buffering and energy-absorbing structure of a combined type general aircraft. The anti-crash buffering and energy-absorbing structure comprises a piston cylinder seat, a piston outer cylinder, a piston inner cylinder, an air cavity, a floating piston, an annular flange, a cutter fixing bolt, a cutting cutter, a cutting pipe, 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 sealing ring and a floating piston sealing ring. The piston sealing ring and the floating piston sealing ring are installed on the two sides of the corresponding parts respectively, and all the parts are assembled in order to ensure that an oil cavity is sealed. According to the structure, the modes of cutting deformation of the cutting pipe, friction between oil and the oil holes, air compression and the like are combined, multi-stroke buffering energy absorption is achieved, and impact kinetic energy is efficiently dissipated. And during compression, the piston outer cylinder and the annular flange axially move along the cutting pipe, so that the transverse load resistance is improved. The oil flows to take away cutting heat, the problem of tool fusing is solved, and the tool cost is reduced. In addition, the cutting pipe can be replaced by detaching the oil cylinder base, repeated utilization is achieved, the use cost is reduced, and good performance and economical efficiency are achieved.

Description

Technical Field

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

[0002] Currently, independent oil-gas buffers, cutting energy absorption structures, and crushing energy absorption structures are often used for buffer 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, resulting in poor lateral stability of the structure, 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 of the cutting energy absorption structure is large, it is easy to cause the tool to melt and deform, requiring high strength and thermal stability of the structural material, which limits the improvement of the total energy absorption of the structure. The crushing energy absorption structure occupies a part of the buffer stroke after the material is compacted, which has a great 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 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, improves the lateral stability of the structure, solves the problem of tool melting under large loads, and reduces the use cost.

[0005] To achieve the above object, the present invention provides the following technical solutions: A composite general aircraft anti-crash buffer energy absorption structure, comprising: a piston cylinder seat, a piston outer cylinder, a piston inner cylinder, an air chamber, a floating piston, an annular flange, a tool fixing bolt, a cutting tool, a cutting tube, a piston, an oil cylinder, an oil chamber, an oil needle, an oil cylinder seat, an oil cylinder connection bolt, an oil hole, a piston seal ring, and a floating piston seal ring; The piston seal rings are installed on both sides of the piston, and the floating piston seal rings are installed on both sides of the floating piston; then the piston is installed on the piston inner cylinder in sequence, and the floating piston is installed at the bottom of the air chamber; the oil needle is installed at the oil hole to ensure that it can normally adjust the size of the oil hole; the cutting tool is installed on the annular flange through the tool fixing bolt, so that the cutting tools are 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 connection bolt to ensure good sealing of the oil chamber, and finally the cutting tube is installed on the outer sides of both sides of the oil chamber.

[0006] Specifically, when compressed, the piston outer cylinder and the annular flange move axially along the cutting tube.

[0007] Specifically, the cutting contact point between the cutting tool and the cutting tube is always located above the oil layer.

[0008] Specifically, the oil cylinder seat can be disassembled and the cutting tube can be replaced through the oil cylinder connecting bolts.

[0009] The beneficial effects of the present invention are: 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 consumes impact kinetic energy, and the energy absorption effect is significantly better than the traditional single energy absorption device.

[0010] 2. When the structure is compressed, the piston outer cylinder 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.

[0011] 3. The unique heat dissipation mechanism uses the flow of oil to take away the high temperature generated by cutting, which solves the problem of tool melting under heavy loads, reduces the requirements for tool materials, and thus reduces tool costs.

[0012] 4. The cutting tube can be replaced by disassembling the oil cylinder seat, so that other structures can be reused, which reduces the overall use cost and has good economy.

[0013] 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 in conjunction with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 The present invention is a schematic structural diagram of a composite general aviation aircraft anti-crash buffer energy absorption structure.

[0015] 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

[0016] The technical solution of the present invention will be described clearly and completely below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of them. 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.

[0017] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention. In addition, the terms "first", "second", "third" are only used for descriptive purposes and cannot be construed as indicating or implying relative importance.

[0018] In the description of the present invention, it should be noted that unless otherwise clearly specified and defined, the terms "installation", "connection", "connection" should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be directly connected or indirectly connected through an intermediate medium, and it can be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0019] In addition, the technical features involved in different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0020] Please refer to Figure 1 , a composite general aircraft anti-crash buffer energy absorption structure shown in the present application includes: piston cylinder seat 1, piston outer cylinder 2, piston inner cylinder 3, air chamber 4, floating piston 5, annular flange 6, tool fixing bolt 7, cutting tool 8, cutting tube 9, piston 10, oil cylinder 11, oil chamber 12, oil needle 13, oil cylinder seat 14, oil cylinder connection bolt 15, oil hole 16, piston seal ring 17, floating piston seal ring 18; The piston seal ring 17 is installed on both sides of the piston 10, and the floating piston seal ring 18 is installed on both sides of the floating piston 5; then the piston 10 is installed on the piston inner cylinder 3 in sequence, and the floating piston 5 is installed at the bottom of the air chamber 4; 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 tools 8 are 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 connection bolt 15 to ensure that the oil chamber 12 is well sealed, and finally the cutting tube 9 is installed on the outer sides of both sides of the oil chamber 12.

[0021] Specifically, when compressed, the piston outer cylinder 2 and the annular flange 6 move axially along the cutting tube 9, greatly improving the ability of the structure to resist lateral loads and enhancing the lateral stability of the structure.

[0022] 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. Therefore, the high temperature generated by cutting can be transferred to the oil and carried away by the flow of the upper-layer oil, achieving a good heat dissipation effect, solving the problem of tool melting of the cutting tool 8 under large loads, and reducing the material requirements for the tool, thereby reducing the tool cost.

[0023] Specifically, the oil cylinder seat 14 can be disassembled through the oil cylinder connection bolt 15, and the cutting tube 9 can be replaced to realize the reuse of other structures and reduce the use cost.

[0024] Working principle Compression stroke: During operation, the piston cylinder seat 1 first drives the piston outer cylinder 2 and the piston inner cylinder 3 to compress axially. The piston outer cylinder 2 is fixedly connected to the annular flange 6, and the annular flange 6 is connected to the cutting tool 8 through the tool fixing bolt 7, which is convenient for tool replacement. The number of cutting tools 8 can be flexibly set and is evenly distributed along the ring on the annular flange 6. During axial compression, the cutting tool 8 cuts the cutting tube 9, and the impact energy is absorbed through cutting deformation.

[0025] The piston inner cylinder 3 is fixedly connected to the piston 10. During compression, the oil in the oil cavity 12 flows to the other side through the oil hole 16, forcing the floating piston 5 to compress the gas in the gas cavity 4. The oil needle 13 can adjust the size of the oil hole 16, and the impact energy is absorbed through the friction between the oil and the oil hole 16. As the compression process progresses, the oil needle 13 gradually reduces the passing area of the oil hole 16, and the compression force gradually increases. The impact force is buffered through the compression of the air, and a part of the impact kinetic energy is converted into the potential energy of the air. Therefore, during the initial compression of the structure, the impact energy can be absorbed simultaneously through the cutting deformation of the cutting tube 9 and the friction between the oil and the oil hole 16, improving the energy absorption effect.

[0026] Extension stroke: When the compression force reaches the maximum value, under the action of the gas potential energy, the floating piston 5 drives the piston 10, the cutting tool 8 and its connecting components to rebound, and the structure enters the extension stroke. At this time, the cutting tool 8 does not function, and only the friction between the oil and the oil hole 16 absorbs energy. After the extension stroke ends, the structure enters the compression stroke again. At this time, the cutting resistance between the cutting tool 8 and the cutting tube 9 is greatly reduced, but energy can still be absorbed based on the friction between the two. Therefore, this structure can achieve multi-stroke buffer energy absorption and gradually consume the impact kinetic energy.

[0027] The technical features of the above-described embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope described in this specification.

[0028] The above-described embodiments merely represent several implementation manners of the present invention. The description thereof is relatively specific and detailed, but it should not be construed as a limitation on the scope of the invention patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several modifications and improvements can still be made, and these all fall within the protection scope of the present invention. Therefore, the protection scope of the present invention patent shall be subject to the appended claims.

Claims

1. A crash-resistant buffering and energy-absorbing structure for a compound general aircraft, characterized in that, Comprising: Piston barrel seat, piston outer barrel, piston inner barrel, air chamber, floating piston, annular flange, tool fixing bolt, cutting tool, cutting tube, piston, oil barrel, oil chamber, oil needle, oil barrel seat, oil barrel connecting bolt, oil hole, piston seal ring, floating piston seal ring; The piston seal rings are installed on both sides of the piston, and the floating piston seal rings are installed on both sides of the floating piston; the piston is sequentially installed on the piston inner barrel, and the floating piston is installed at the bottom of the air chamber; the oil needle is installed at the oil hole; the cutting tool is installed on the annular flange through the tool fixing bolt, and the cutting tools are evenly distributed along the circumference of the annular flange; the annular flange is fixedly connected to the piston outer barrel and connects the piston outer barrel to the piston barrel seat; the oil barrel is connected to the oil barrel seat through the oil barrel connecting bolt, and the cutting tube is installed on the outer sides of both sides of the oil chamber.

2. The crashworthiness buffer energy absorption structure of a composite general aircraft according to claim 1, wherein, When compressed, the piston outer barrel and the annular flange move axially along the cutting tube.

3. A crash-resistant buffering and energy-absorbing structure for a compound general aircraft according to claim 1, characterized in that, The cutting contact point between the cutting tool and the cutting tube is always located above the oil layer.

4. A crash-resistant buffering and energy-absorbing structure for a composite general aircraft according to claim 1, characterized in that, The disassembly of the oil barrel seat and the replacement of the cutting tube can be achieved through the oil barrel connecting bolt.

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