An adapter suitable for aircraft catapulting process

Abstract

The application provides an adapter suitable for aircraft ejection process, which is composed of multiple fixing members, compared with the traditional single adapter, the weight of the single fixing member is obviously reduced, and the impact caused by the collision with the object during the scattering process is small; the adapters of the fixing members have the same shape, and are combined by using the unified shape, the adaptability is strong, the aerodynamic shape is consistent, the scattering trajectory and the expected landing point can be predicted by the program; the separation mechanism of the adapter is designed by using the pre-compression spring structure, which can provide a buffer for the material deformation, when the material deforms, the separation mechanism of the adapter can quickly compensate a certain amount, keep the attitude of the aircraft stable and unchanged, and avoid the structural failure of the adapter caused by the material deformation.

Description

Technical Field

[0001] This invention belongs to the field of catapult technology, specifically relating to an adapter suitable for the catapult process of aircraft. Background Technology

[0002] When using catapult technology for aircraft, an adapter is typically used as an elastic gasket between the aircraft and the catapult mechanism. As a crucial component of the aircraft catapult system, the adapter provides support, vibration damping, guidance, and initial disturbance control during storage, transportation, erection, and launch, preventing damage to the aircraft due to external environmental interference. The adapter, assembled inside the catapult, is generally in an interference fit with the catapult mechanism. During launch, the adapter also acts as a seal, ensuring the aircraft is not subjected to the impact and ablation of the propellant, thus improving the efficiency of the propellant's work. The adapter structure solves the support and sealing problems during launch, provides vibration damping, and offers initial guidance. Its structural design has a significant impact on the aircraft catapult system and is one of the most important design aspects of the system.

[0003] However, current technology presents the following problems: the adapter is typically heavy and complex in structure, and its separation process is affected by various external factors, making its scattering process and distribution unpredictable. During separation, the adapter is prone to secondary collisions with the aircraft surface, and its weight after impact may pose a threat to the catapult platform and ground personnel. Typically, the adapter is made from a single type of material in a single molding process, resulting in poor adaptability. Manufacturing errors, thermal expansion and contraction of materials, and plastic deformation can lead to either an excessively loose or excessively tight fit between the adapter and the catapult device. An excessively tight fit causes a surge in friction, preventing the aircraft from reaching its intended separation speed due to energy dissipation during the catapult process. An excessively loose fit creates gaps, causing vibrations during catapult launch and reducing the overall structural seal, potentially affecting the aircraft's flight attitude or causing damage due to the impact of the catapult propellant. Summary of the Invention

[0004] In view of this, the purpose of the present invention is to provide an adapter suitable for the aircraft ejection process, which can ensure the stability of the aircraft's flight attitude after ejection and at the same time reduce the probability of collision accidents.

[0005] An adapter suitable for aircraft catapult launch process includes a rhomboid fixing part (3), an upper triangular fixing part (1), a lower triangular fixing part (4) and an elastic part (2); multiple rhomboid fixing parts (3), upper triangular fixing parts (1) and lower triangular fixing parts (4) are arranged in a spatial topology and connected to form a ring structure; a limiting groove (5) is opened in the middle of the rhomboid fixing part (3), upper triangular fixing part (1) and lower triangular fixing part (4), and the elastic part (2) is embedded in the limiting groove (5).

[0006] Preferably, the rhomboid fastener (3) is rhomboid in shape, the upper triangular fastener (1) and the lower triangular fastener (4) are triangular in shape, the outer surfaces of the three are arc surfaces, multiple rhomboid fasteners (3) are arranged along the circumference of the ring, the triangular gap formed at the top of the two rhomboid fasteners (3) is filled by the upper triangular fastener (1), and the triangular gap formed at the bottom is filled by the lower triangular fastener (4).

[0007] Preferably, the upper part of the inner surface of the rhomboid fastener (3) and the upper triangular fastener (1) is machined with an inward angle from bottom to top.

[0008] Preferably, the elastic element (2) includes a housing (23), a spring (24), a pressure cap (22), and a pin (21); the housing (23) is a disc-shaped structure with an annular countersunk hole at the center of one side, and a cylindrical protrusion is machined at the center of the countersunk hole, on which the spring (24) is fitted; the pressure cap (22) is a disc-shaped structure with a circular protrusion machined at its lower end, which can be embedded in the annular countersunk hole of the housing, and the edge of the pressure cap (22) overlaps and is fixed to the housing (23) on the outer side of the countersunk hole; The cover (22) has a central through hole, and the cylindrical protrusion structure at the center of the countersunk hole passes through the central through hole of the cover (22); the upper end of the pin (21) is a cylinder, and the center of the lower surface is machined with a central countersunk hole. A ring of protrusions is provided on the outside of the countersunk hole to form a cylindrical cavity. The cylindrical cavity passes through the central through hole on the cover (22), and the cylindrical protrusion structure of the shell (23) enters the cylindrical cavity of the pin (21); the lower outer side of the cylindrical cavity is machined with a protrusion that is stuck in the central through hole of the cover (22).

[0009] Preferably, a compensation layer (25) is also provided on the inner side of the housing (23) of the elastic element (2).

[0010] Preferably, the diamond-shaped fastener (3), the upper triangular fastener (1), and the lower triangular fastener (4) sequentially include a compensation layer (44), a body layer (43), a rubber layer (42), and a lubrication layer (41) from the inside to the outside.

[0011] Preferably, the compensation layer (44) is made of sponge material, such as EVA foam or EPE pearl cotton.

[0012] Preferably, the body layer (43) is a polyurethane foam layer; the rubber layer (42) is made of polyurethane foam material.

[0013] Preferably, the lubricating layer (41) is made of polytetrafluoroethylene, perfluoroethylene propylene resin, polyphenylene sulfide, epoxy resin, polyimide or polyether ether ketone.

[0014] Preferably, the diamond-shaped fastener (3), the upper triangular fastener (1), and the lower triangular fastener (4) are connected by at least one of splicing, slotting, and extrusion.

[0015] The present invention has the following beneficial effects:

[0016] This invention provides an adapter suitable for the ejection process of an aircraft. The adapter is constructed by combining multiple fasteners. Compared with the traditional single-molded adapter, the weight of each fastener is significantly reduced, and the impact is minimal even if it collides with an object during the scattering process.

[0017] The adapters of each fixed component have the same shape and are assembled using a uniform shape. They are highly applicable and consistent with the aerodynamic shape. Their scattering trajectory and expected landing point can be predicted by the program.

[0018] The adapter's separation mechanism is designed with a spring structure for pre-compression, which provides a buffer for overall material deformation. When material deformation occurs, the adapter's separation mechanism can quickly provide a certain amount of compensation, keeping the aircraft's attitude stable and preventing adapter structure failure due to material deformation.

[0019] The adapter is constructed from a multi-layered composite material, ensuring that the connection and fit between the adapter and the catapult remain stable and possess a degree of self-adaptability. Compared to a single material, it is less affected by environmental factors, enhancing the adapter's resistance to external disturbances and ensuring a stable flight attitude for the launched aircraft. Attached Figure Description

[0020] Figure 1 This is a schematic diagram of an adapter suitable for the catapult launch process of an aircraft according to the present invention;

[0021] Figure 2 Here is a structural diagram of the lower triangular fastener;

[0022] Figure 3 This is a structural diagram of the upper triangular fastener;

[0023] Figure 4 This is a structural diagram of a rhomboid fastener;

[0024] Figure 5 This is a structural diagram of the elastic element;

[0025] Figure 6 This is a cross-sectional view of the elastic component structure;

[0026] Among them, 1-upper triangular fastener, 2-elastic component, 3-diamond-shaped fastener, 4-lower triangular fastener, 5-limiting groove, 11-pneumatic chamfer, 21-pin body, 22-pressure cap, 23-shell, 24-spring, 25-compensation layer, 31-pneumatic chamfer, 41-lubricating layer, 42-rubber layer, 43-body layer, 44-compensation layer. Detailed Implementation

[0027] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0028] This invention provides an adapter suitable for the catapult process of aircraft. In order to solve the problem of the large mass of the adapter itself, this invention optimizes the adapter structure by reducing the volume of a single adapter piece and reducing the mass by using composite materials.

[0029] To address the issue of adapters failing due to environmental factors, this invention optimizes the adapter's composition by altering its material distribution and employing a composite of multiple materials. This prevents a single material from being affected by the environment, thus avoiding adapter failure.

[0030] To address the difficulty in predicting the uniform trajectory of adapters, the adapters in this structure have similar aerodynamic characteristics and simple shapes, making it easy to predict their landing point distribution.

[0031] This adapter ensures that all technical requirements of the adapter are met during the ejection process, meets the performance requirements of the adapter, and complies with the requirements of economy, manufacturability, practicality, and operability.

[0032] like Figure 1 As shown, the adapter of the present invention, applicable to the catapult process of an aircraft, mainly comprises four parts: a rhomboid fixing member 3, an upper triangular fixing member 1, a lower triangular fixing member 4, and an elastic member 2. The components are spliced ​​together, and multiple rhomboid fixing members 3, upper triangular fixing members 1, and lower triangular fixing members 4 are arranged in a spatial topology to form a ring structure. Limiting grooves 5 are opened in the middle of the rhomboid fixing members 3, upper triangular fixing members 1, and lower triangular fixing members 4. The elastic member 2 is embedded in the limiting grooves 5, which can ensure that the aircraft is in a uniform force state in the catapult mechanism and avoid eccentric torque caused by uneven force, which would affect the trajectory of the catapult process.

[0033] like Figure 2 , 3As shown in Figure 4, the rhomboid fastener 3 is rhomboid in shape, the upper triangular fastener 1 and the lower triangular fastener 4 are both triangular in shape, and the outer surfaces of the three are arc surfaces. Multiple rhomboid fasteners 3 are arranged along the circumference of the ring. The triangular gap formed by the upper part of the two rhomboid fasteners 3 is filled by the upper triangular fastener 1, and the triangular gap formed by the lower part is filled by the lower triangular fastener 4.

[0034] like Figure 5 and 6 As shown, the elastic element 2 includes a housing 23, a spring 24, a pressure cap 22, and a pin 21. The housing 23 has a disc-shaped structure with an annular countersunk hole at the center of one side. A cylindrical protrusion is machined at the center of the countersunk hole, on which the spring 24 is fitted. The pressure cap 22 has a disc-shaped structure with a circular protrusion at its lower end, which can be embedded in the annular countersunk hole of the housing. The edge of the pressure cap 22 overlaps and is fixed to the housing 23 on the outer side of the countersunk hole. The pressure cap 22 has a central through hole, through which the cylindrical protrusion at the center of the countersunk hole passes. The pin 21 has a cylinder at its upper end and a central countersunk hole at the center of its lower surface. A ring of protrusions is provided on the outer side of the countersunk hole, forming a cylindrical cavity. The cylindrical cavity passes through the central through hole on the pressure cap 22, and the cylindrical protrusion of the housing 23 enters the cylindrical cavity of the pin 21. To prevent the pin 21 from detaching from the housing 23, a protruding edge is machined on the lower outer side of the cylindrical cavity, which can be locked in the central through hole of the pressure cap 22.

[0035] The inner side of the shell 23 of the elastic element 2 is also provided with a compensation layer 25, which is generally made of sponge. The sponge layer is attached to the side of the shell 23 that contacts the aircraft surface. The sponge layer acts as an elastic element and contacts the aircraft surface. The deformation of the sponge layer reduces the impact of the adapter on the aircraft, avoiding damage to the aircraft caused by rigid contact between the two. At the same time, it also avoids the elastic mechanism 2 from being squeezed and deformed by material deformation, which would affect the aircraft. Before ejection, the elastic element 2 in the adapter is pressed into the limiting groove 5 of the fixing part and is in a pre-tightened state. After the aircraft leaves the ejection mechanism, the elastic potential energy of the spring 24 is converted into kinetic energy to eject the fixing part of the adapter outward. Because the adapter is relatively light, it will move away from the aircraft under the action of the elastic element 2, avoiding secondary collision with the aircraft.

[0036] The rhomboid fixing component 3, the upper triangular fixing component 1, and the lower triangular fixing component 4 are all composed of four layers: from the inside out, a compensation layer 44, a body layer 43, a rubber layer 42, and a lubrication layer 41. The compensation layer 44 uses sponge as a compensation mechanism. When the adapter material deforms due to processing errors or thermal expansion and contraction and comes into contact with the adapter on the aircraft surface, the sponge layer deforms to ensure that the fit between the adapter and the catapult mechanism does not affect the catapult process or the aircraft. The body layer 43 is made of polyurethane foam, reducing the adapter's weight while also being less susceptible to deformation due to external environmental influences. The rubber layer 42 is made of rubber to absorb and reduce the vibration and impact of external conditions on the aircraft, ensuring the stability of the aircraft within the catapult device. The lubrication layer 41 is made of polytetrafluoroethylene (PTFE) to reduce the friction between the adapter and the catapult mechanism during catapult launch, improving the work conversion efficiency of the catapult mechanism.

[0037] The upper part of the inner surface of the rhomboid fastener 3 and the upper triangular fastener 1 is machined with a 60° inclination angle to form an aerodynamic chamfer, which is used to ensure that the adapter can be smoothly separated from the aircraft during the separation process.

[0038] In this invention, the connection between the components is currently achieved by splicing, but it can also be achieved by using slots, compression connections, or other methods.

[0039] The compensation layer 44 can be made of not only sponge material, but also foamed materials such as EVA foam and EPE pearl cotton.

[0040] The body layer 43 is made of polyurethane foam and rubber, but other polyurethane foam materials can also be used as substitutes, such as polyisocyanates, polyether polyols, polyester polyols, etc.

[0041] The lubrication layer 41 uses polytetrafluoroethylene (PTFE) as the connecting layer for lubrication, and can also use perfluoroethylene propylene (FEP) resin, polyphenylene sulfide (PPS), epoxy resin, polyimide (PI), polyether ether ketone (PEEK), etc.

[0042] In summary, the above are merely preferred embodiments of the present invention and are not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An adapter suitable for use in an aircraft launch process, the adapter comprising: The device comprises rhombic fixing members (3), upper triangular fixing members (1), lower triangular fixing members (4) and elastic members (2); the rhombic fixing members (3), the upper triangular fixing members (1) and the lower triangular fixing members (4) are arranged in space topology and connected to form a circular ring structure; the middle part of each of the rhombic fixing members (3), the upper triangular fixing members (1) and the lower triangular fixing members (4) is provided with a limiting groove (5), and the elastic member (2) is embedded in the limiting groove (5); The elastic member (2) comprises a shell (23), a spring (24), a gland (22) and a pin body (21); the shell (23) is in a discoid structure, one side of which is provided with an annular counterbore, the center of the counterbore is provided with a cylindrical protruding structure, and the spring (24) is sleeved on the cylindrical protruding structure; the gland (22) is in a discoid structure, the lower end of which is provided with a circular protrusion which can be embedded in the annular counterbore of the shell, and the edge of the gland (22) is overlapped and fixed on the shell (23) outside the edge of the counterbore; the gland (22) is provided with a central through hole, and the cylindrical protruding structure in the center of the counterbore passes through the central through hole of the gland (22); the pin body (21) is in a cylindrical shape at the upper end, the center of the lower surface is provided with a central counterbore, and a ring of protrusions is arranged outside the central counterbore to form a cylindrical cavity, the cylindrical cavity passes through the central through hole of the gland (22), and the cylindrical protruding structure of the shell (23) enters the cylindrical cavity of the pin body (21); a protruding edge is arranged outside the lower part of the cylindrical cavity and clamped in the central through hole of the gland (22).

2. An adapter suitable for use in an aircraft launch process as in claim 1, wherein, The rhombic fixing members (3) are in a rhombic shape as a whole, the upper triangular fixing members (1) and the lower triangular fixing members (4) are in a triangular shape as a whole, and the outer surfaces of the three are in a circular arc surface; a plurality of rhombic fixing members (3) are arranged along the circumference of the circular ring, the triangular gap formed at the upper part of two rhombic fixing members (3) is filled by the upper triangular fixing member (1), and the triangular gap formed at the lower part is filled by the lower triangular fixing member (4).

3. An adapter suitable for use in an aircraft launch process as in claim 2, wherein, The upper part of the inner side surface of the rhombic fixing member (3) and the upper triangular fixing member (1) is processed with an inwardly inclined angle from bottom to top.

4. An adapter suitable for use in an aircraft launch process as in claim 3, wherein, The inner side of the shell (23) of the elastic member (2) is further provided with a first compensation layer (25).

5. An adapter for use in the aircraft launch process as defined in claim 1, 2 or 3, wherein, The rhombic fixing member (3), the upper triangular fixing member (1) and the lower triangular fixing member (4) sequentially comprise a second compensation layer (44), a body layer (43), a rubber layer (42) and a lubricating layer (41) from inside to outside.

6. An adapter suitable for use in an aircraft launch process as in claim 5, wherein, The second compensation layer (44) is made of sponge material, EVA foam or EPE pearl wool material.

7. An adapter suitable for use in an aircraft launch process as in claim 5, wherein, The body layer (43) is made of polyurethane foam layer; the rubber layer (42) is made of polyurethane foam material.

8. An adapter suitable for use in an aircraft launch process as in claim 5, wherein, The lubricating layer (41) is made of polytetrafluoroethylene, polyperfluoroethylene resin, polyphenylene sulfide, epoxy resin, polyimide or polyether ether ketone.

9. An adapter for use in the aircraft launch process as defined in claim 1, 2 or 3, wherein, The rhombic fixing member (3), the upper triangular fixing member (1) and the lower triangular fixing member (4) are connected by at least one of splicing, clamping groove and extrusion.

Images