Aircraft tail protection device

Abstract

The application discloses an aircraft tail protection device and relates to the technical field of aircraft tail protection.The aircraft tail protection device comprises a shell assembly and a tail cover assembly.The shell assembly is sleeved between an aircraft engine and an engine nozzle in a circumferential direction.The tail cover assembly is sleeved outside the engine nozzle and is in sliding connection with the engine nozzle.The tail cover assembly is also detachably connected with the shell assembly.When the aircraft is ejected from a barrel, the tail cover assembly is connected with the shell assembly and the engine nozzle.When the aircraft is ejected from the barrel, the gas ejected from the engine nozzle pushes the tail cover assembly to slide along the length direction of the engine nozzle and separate from the shell assembly.The tail cover assembly protects the engine nozzle when the aircraft is ejected from the barrel, thereby avoiding damage of the high-temperature and high-pressure gas to the engine nozzle.The tail cover assembly automatically falls off after the aircraft is ejected from the barrel, so that an ejection bottom plate in the barrel is not needed, space is saved, and the mass and cost of the barrel and the aircraft are reduced.

Description

Technical Field

[0001] This invention relates to the field of aircraft tail protection technology, and in particular to an aircraft tail protection device. Background Technology

[0002] During the ejection process, the aircraft is propelled by the gas generated by the power unit at the bottom of the launch tube. In order to avoid damage to the tail engine, nozzle and other equipment of the aircraft by the high temperature and high pressure gas generated during ejection, the ejection base plate is usually used to bear the huge airflow impact force generated by the gas.

[0003] In existing technologies, most catapult-launched aircraft use a catapult base plate inside the launch tube to withstand the enormous airflow impact force generated by the combustion gases. However, the catapult base plate occupies a significant amount of space in the launch tube, increasing the weight and cost of both the launch tube and the aircraft. Summary of the Invention

[0004] This invention provides a tail protection device for aircraft to solve the technical problem that the existing ejection base plate used for aircraft protection occupies a large space in the launch tube, increasing the weight and cost of the launch tube and the aircraft.

[0005] This invention provides a tail protection device for an aircraft, comprising: A housing assembly, which is circumferentially fitted between the aircraft engine and the engine nozzle; A tail cover assembly, which is sleeved on the outside of the engine nozzle and slidably connected thereto, and is also detachably connected to the housing assembly; When the aircraft is ejected from the tube, the tail cone assembly is connected to the shell assembly and the engine nozzle; After the aircraft is ejected from the ejection tube, the exhaust gas ejected from the engine nozzle pushes the tail cover assembly to slide along the length of the engine nozzle and separate from the housing assembly.

[0006] In some embodiments, the housing assembly includes: The housing has its front end positioned circumferentially on the aircraft engine, and its rear end extends to the edge of the engine nozzle. A connecting block is provided on the outside of the housing along the circumferential direction, and the tail end of the connecting block and the housing has a stepped structure.

[0007] In some embodiments, the tailgate assembly includes: A circular cover plate is fitted over the outside of the engine nozzle, and the edge of the circular cover plate abuts against the connecting block and is detachably connected to the tail end of the housing. A first guide ring is disposed on the inner side of the circular cover plate along the circumferential direction, and the first guide ring is slidably connected to the outer side of the engine nozzle.

[0008] In some embodiments, the edge of the circular cover plate and the connecting block are inclined structures that fit together.

[0009] In some embodiments, the connection between the circular cover plate and the housing is further provided with a weakening groove.

[0010] In some embodiments, the circular cover plate is a planar structure or a unidirectional convex structure.

[0011] In some embodiments, the edge of the circular cover plate is provided with at least one sealing groove along the circumferential direction, and a sealing ring is provided in the sealing groove, the sealing ring being sealed to the tail end of the housing.

[0012] In some embodiments, the tailgate assembly further includes: The second guide ring is disposed circumferentially between the first guide ring and the outer side of the engine nozzle.

[0013] In some embodiments, the circular cover plate, the housing, and the connecting block are also provided with exhaust holes.

[0014] In some embodiments, the aircraft tail protection device further includes: A heat shield is fitted around the outside of the engine nozzle in a circumferential direction. One end of the heat shield is connected to the tail end of the housing, and the other end of the heat shield is connected to the outside of the engine nozzle.

[0015] The beneficial effects of the technical solution provided by this invention include: This invention provides a tail protection device for an aircraft, comprising: a shell assembly and a tail cover assembly. The shell assembly is circumferentially fitted between the aircraft engine and the engine nozzle. The tail cover assembly is fitted outside the engine nozzle and slidably connected to it. The tail cover assembly is also detachably connected to the shell assembly. When the aircraft is ejected from the launch tube, the tail cover assembly is connected to the shell assembly and the engine nozzle. After the aircraft is ejected from the launch tube, the exhaust gas ejected from the engine nozzle pushes the tail cover assembly to slide along the length of the engine nozzle and separate from the shell assembly. The tail cover assembly protects the engine nozzle when the aircraft is ejected from the launch tube, bearing the huge airflow impact force generated by the exhaust gas and preventing high-temperature and high-pressure exhaust gas from damaging the engine nozzle. After the aircraft is ejected from the launch tube, the tail cover assembly separates from the engine nozzle along with the exhaust gas and automatically detaches. This eliminates the need for an ejection base plate inside the launch tube, saving space and reducing the weight and cost of the launch tube and the aircraft. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 This is a schematic diagram of the first embodiment of an aircraft tail protection device provided by the present invention; Figure 2 This is a schematic diagram of the structure of a separated tail protection device for an aircraft, provided by an embodiment of the present invention. Figure 3 This is a schematic diagram of a second embodiment of an aircraft tail protection device provided by the present invention; Figure 4 A schematic diagram of a third embodiment of an aircraft tail protection device provided by the present invention; Figure 5 This is a schematic diagram of the fourth embodiment of an aircraft tail protection device provided by the present invention; Figure label: 1. Housing assembly; 11. Housing; 12. Connecting block; 2. Tail cover assembly; 21. Circular cover plate; 211. Weakening groove; 212. Sealing groove; 213. Sealing ring; 22. First guide ring; 23. Guide ring; 231. Stop end; 3. Aircraft engine; 4. Engine nozzle; 5. Vent; 6. Heat shield; 7. Gaskets. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0019] This invention provides a tail protection device for aircraft, which solves the technical problem in the related art that the internal ejection base plate used for aircraft protection occupies a large space in the launch tube, increasing the weight and cost of the launch tube and the aircraft.

[0020] Figure 1 This invention provides a tail protection device for an aircraft, comprising: a housing assembly 1 and a tail cover assembly 2. The housing assembly 1 is sleeved circumferentially between the aircraft engine 3 and the engine nozzle 4. The tail cover assembly 2 is sleeved outside the engine nozzle 4 and slidably connected to it. The tail cover assembly 2 is also detachably connected to the housing assembly 1. When the aircraft is ejected from the ejection tube, the tail cover assembly 2 is connected to the housing assembly 1 and the engine nozzle 4. After the aircraft is ejected from the ejection tube, the exhaust gas ejected from the engine nozzle 4 pushes the tail cover assembly 2 to slide along the length of the engine nozzle 4 and separate it from the housing assembly 1.

[0021] The tail protection device for an aircraft provided in this invention includes a shell assembly and a tail cover assembly. The shell assembly is circumferentially fitted between the aircraft engine and the engine nozzle. The tail cover assembly is fitted outside the engine nozzle and slidably connected to it. The tail cover assembly is also detachably connected to the shell assembly. When the aircraft is ejected from the launch tube, the tail cover assembly is connected to the shell assembly and the engine nozzle, forming a protective barrier outside the engine nozzle to withstand the huge airflow impact force generated by the launch exhaust and prevent the high-temperature and high-pressure exhaust from damaging the engine nozzle. After the aircraft is ejected from the launch tube, the exhaust gas ejected from the engine nozzle pushes the tail cover assembly to slide along the length of the engine nozzle and separate from the shell assembly. The exhaust gas ejected from the engine nozzle from front to back pushes the tail cover assembly to move towards the rear of the engine nozzle until it separates from the shell assembly and falls off. This eliminates the need for an ejection base plate inside the launch tube, saving space and reducing the weight and cost of the launch tube and the aircraft. Furthermore, the tail cover assembly has a simple structure, is lightweight, and the separation operation is convenient and quick.

[0022] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 2As shown, the housing assembly 1 includes a housing 11 and a connecting block 12. The front end of the housing 11 is circumferentially mounted on the aircraft engine 3, and the rear end of the housing 11 extends to the edge of the engine nozzle 4. The connecting block 12 is circumferentially located outside the housing 11. The connecting block 12 and the rear end of the housing 11 have a stepped structure. The housing 11 is a cylindrical structure fitted onto the aircraft engine 3. The rear end of the engine nozzle 4 is located at the opening of the housing 11, and the diameter of the engine nozzle 4 is smaller than the diameter of the opening of the housing 11. The connecting block 12 is an annular structure circumferentially located outside the housing 11. A reinforcing structure is formed on the outer side. The stepped structure formed by the connecting block 12 and the tail end of the housing 11 creates a stepped transition at the connection, realizing the functional connection of the connecting block 12, the housing 11 and the tail cover assembly 2, providing a clear assembly benchmark, preventing the connecting block 12, the housing 11 and the tail cover assembly 2 from shifting or rotating during connection, and also increasing the contact area, dispersing local stress and improving the load-bearing capacity at the connection. In addition, the connecting block 12 and the housing 11 are connected by screwing, riveting, gluing or other methods. The connecting block 12 and the housing 11 are also made of heat-insulating composite materials such as fiberglass or heat-resistant metal materials to improve their heat resistance and deformation resistance.

[0023] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 2 As shown, the tail cover assembly 2 includes a circular cover plate 21 and a first guide ring 22. The circular cover plate 21 is fitted onto the outside of the engine nozzle 4. The edge of the circular cover plate 21 abuts against the connecting block 12 and is detachably connected to the tail end of the housing 11. The first guide ring 22 is disposed circumferentially on the inner side of the circular cover plate 21 and is slidably connected to the outer side of the engine nozzle 4. The first guide ring 22 fits the circular cover plate 21 onto the tail of the engine nozzle 4, so that the circular cover plate 21 forms protection at the tail of the engine nozzle 4, and also provides stable guidance during the rearward movement of the circular cover plate 21. See also... Figure 5 As shown, it can also be configured such that the first guide ring 22 is slidably connected to the inner side of the engine nozzle 4.

[0024] Specifically, the diameter of the circular cover plate 21 matches the inner ring diameter of the connecting block 12. The edge of the circular cover plate 21 fits into the stepped structure formed by the connecting block 12 and the housing 11. The circular cover plate 21 and the housing 11 are detachably connected by a weakening screw. When the aircraft is ejected from the tube, high-temperature and high-pressure gas builds up high external pressure and impact load at the tail of the aircraft. The circular cover plate 21 forms protection at the tail of the engine nozzle 4 to prevent high-temperature and high-pressure gas from damaging the engine nozzle 4. The external pressure acts on the circular cover plate 21 and is transmitted to the housing 11 and the connecting block 12. After the aircraft is ejected from the tube, the engine nozzle 4 ejects gas from front to back. The circular cover plate 21 bears the gas pressure. Under the action of gas thrust, the first guide ring 22 slides along the outside of the engine nozzle 4 to the rear until the weakening screw is broken. The circular cover plate 21 is released from axial constraint and separates from the housing 11 until it falls off.

[0025] Furthermore, the circular cover plate 21 can be made of lightweight materials such as plastic, foam, honeycomb, and composite materials, which can reduce impact damage after detachment. It can also be cushioned by using soft materials such as metal-coated rubber.

[0026] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 2 As shown, the edge of the circular cover plate 21 and the connecting block 12 are inclined structures that fit together. The inclined structure forms an inclined transition at the connection between the circular cover plate 21 and the connecting block 12, achieving a smooth transition, avoiding mutual obstruction during the separation process of the circular cover plate 21, reducing stress concentration at the right angle transition, reducing the risk of cracking or fatigue, and extending the service life. The inclined structure can also guide the circular cover plate 21 to fit or align quickly, reducing assembly difficulty. In addition, the edge of the circular cover plate 21 and the connecting block 12 can also be set as an overlapping or butt joint structure. The fitting inclined structure, overlapping or butt joint can be selected according to the usage scenario and requirements.

[0027] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 As shown, the connection between the circular cover plate 21 and the housing 11 is also provided with a weakening groove 211. The weakening groove 211 can replace the weakening screw or serve as a separation redundancy structure. The weakening groove 211 can preset the initiation and propagation path of the crack to control the fracture location and direction. When the aircraft is ejected from the tube, the circular cover plate 21 is subjected to the gas pressure and slides along the outside of the engine nozzle 4 to the rear under the action of gas thrust until the circular cover plate 21 breaks along the weakening groove 211 and separates and falls off from the housing 11.

[0028] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 3 As shown, the circular cover plate 21 has a planar structure or a one-way convex structure. When the circular cover plate 21 has a planar structure, the ejection gas impact force when the aircraft ejects from the tube acts perpendicularly on the plane of the circular cover plate 21, and the stress is highly concentrated near the impact point. The circular cover plate 21 can effectively protect the engine nozzle 4. When the circular cover plate 21 has a one-way convex structure, the circular cover plate 21 forms a rearward convex arc-shaped cover plate at the tail of the engine nozzle 4. The convex arc-shaped structure will disperse the ejection gas impact force to a wider area, and the impact force will be transmitted to all sides along the arc, which significantly reduces the local stress of the circular cover plate 21, the stress distribution is more uniform, stress concentration is avoided, and the impact resistance of the circular cover plate 21 is greatly improved.

[0029] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 2 As shown, the circular cover plate 21 has at least one sealing groove 212 along its circumferential direction. A sealing ring 213 is provided in the sealing groove 212. The sealing ring 213 is sealed to the tail end of the shell 11. When the aircraft is ejected from the tube, the ejection gas flows from the rear to the front of the aircraft and establishes high external pressure. The edge of the circular cover plate 21 fits against the stepped structure formed by the connecting block 12 and the shell 11, forming a flow-through step and forming the first sealing protection to prevent the gas flowing from the rear to the front of the aircraft from entering between the circular cover plate 21, the connecting block 12, and the shell 11. At the same time, the sealing ring 213 forms the second sealing protection to further prevent gas from entering. In addition, the sealing groove 212 can be set in two at intervals, and the sealing ring 213 is provided in both sealing grooves 212 to improve the sealing performance of the circular cover plate 21.

[0030] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 2 and Figure 4 As shown, the tail cover assembly 2 further includes a second guide ring 23. The second guide ring 23 is disposed circumferentially between the first guide ring 22 and the outer side of the engine nozzle 4. The first guide ring 22 is sleeved on the outer side of the second guide ring 23 and forms a sealed piston structure with it. The second guide ring 23 provides flexible guidance between the contact surfaces of the first guide ring 22 and the engine nozzle 4, reducing the frictional resistance of the contact surfaces and reducing friction and wear. The second guide ring 23 can be supported by self-lubricating materials with different temperature resistance grades such as PTFE, copper, and graphite, which can reduce the resistance to sliding and separating of the first guide ring 22.

[0031] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 4 As shown, a stop end 231 is provided on one side of the second guide ring 23, and the front end of the first guide ring 22 abuts against the stop end 231 of the second guide ring 23 to withstand additional axial force during ejection. A gasket 7 can also be provided between the circular cover plate 21 and the tail of the engine nozzle 4. The gasket 7 is made of flexible materials such as high-temperature resistant rubber or quartz gasket or metal gasket to fill the tiny gaps between the connecting parts and ensure the sealing and reliability of the connection.

[0032] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 As shown, the circular cover plate 21, the housing 11, and the connecting block 12 are also provided with exhaust holes 5. The exhaust holes 5 are used to release internal pressure during the flight of the aircraft to ensure the balance of the aircraft system and its safety and normal function under various operating conditions.

[0033] As an optional implementation, in one embodiment of the invention, see [link to relevant documentation]. Figure 1 and Figure 2 As shown, the tail protection device of the aircraft also includes a heat shield 6, which is circumferentially fitted around the outside of the engine nozzle 4. One end of the heat shield 6 is connected to the tail end of the housing 11, and the other end of the heat shield 6 is connected to the outside of the engine nozzle 4. The heat shield 6 forms a third layer of sealing protection between the edge of the circular cover plate 21 and the housing 11 and the connecting block 12, preventing the exhaust gas flowing from the rear to the front of the aircraft from entering the space between the circular cover plate 21 and the connecting block 12 and the housing 11, thus providing redundant sealing and heat insulation. The heat shield 6 is made of flexible materials such as adaptable cloth and high-temperature resistant rubber. When the aircraft ejects from the tube, the circular cover plate 21 separates from the housing 11 and falls off. The radial constraint of the engine nozzle 4 is released. When the engine nozzle 4 swings, the heat shield 6 deforms along with the swing of the engine nozzle 4 to adapt to the swing of the engine nozzle 4 and forms a sealing protection between the tail of the engine nozzle 4 and the housing 11.

[0034] In the description of this invention, it should be noted that the terms "upper," "lower," etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Unless otherwise expressly specified and limited, the terms "installed," "connected," and "linked" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication between two elements. For those skilled in the art, the specific meaning of the above terms in this invention can be understood according to the specific circumstances.

[0035] It should be noted that in this invention, relational terms such as "first" and "second" are used merely to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0036] The above description is merely a specific embodiment of the present invention, enabling those skilled in the art to understand or implement the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the present invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features of the invention herein.

Claims

1. A tail protection device for an aircraft, characterized in that, include: The housing assembly (1) is sleeved between the aircraft engine (3) and the engine nozzle (4) in a circumferential direction; Tail cover assembly (2), which is sleeved on the outside of the engine nozzle (4) and slidably connected thereto, and is also detachably connected to the housing assembly (1); When the aircraft is ejected from the tube, the tail cover assembly (2) is connected to the shell assembly (1) and the engine nozzle (4); After the aircraft is ejected from the tube, the exhaust gas ejected from the engine nozzle (4) pushes the tail cover assembly (2) to slide along the length of the engine nozzle (4) and separate from the housing assembly (1); The housing assembly (1) includes: The housing (11) has its front end located on the aircraft engine (3) along the circumferential direction, and its tail end extends to the edge of the engine nozzle (4). Connecting block (12), the connecting block (12) is disposed on the outside of the shell (11) along the circumferential direction, and the tail end of the connecting block (12) and the shell (11) is a stepped structure; The tailgate assembly (2) includes: A circular cover plate (21) is fitted outside the engine nozzle (4), and the edge of the circular cover plate (21) abuts against the connecting block (12) and is detachably connected to the tail end of the housing (11). The first guide ring (22) is disposed on the inner side of the circular cover plate (21) along the circumferential direction, and the first guide ring (22) is slidably connected to the outer side of the engine nozzle (4).

2. The aircraft tail protection device according to claim 1, characterized in that: The edge of the circular cover plate (21) and the connecting block (12) are inclined structures that fit together.

3. The aircraft tail protection device according to claim 1, characterized in that: The connection between the circular cover plate (21) and the shell (11) is further provided with a weakening groove (211).

4. The aircraft tail protection device according to claim 1, characterized in that: The circular cover plate (21) is a planar structure or a unidirectional protruding structure.

5. The aircraft tail protection device according to claim 1, characterized in that: The edge of the circular cover plate (21) is provided with at least one sealing groove (212) along the circumferential direction. A sealing ring (213) is provided in the sealing groove (212), and the sealing ring (213) is sealed to the tail end of the housing (11).

6. The aircraft tail protection device according to claim 1, characterized in that, The tailgate assembly (2) also includes: The second guide ring (23) is disposed circumferentially between the first guide ring (22) and the outer side of the engine nozzle (4).

7. The aircraft tail protection device according to claim 1, characterized in that: The circular cover plate (21), the housing (11), and the connecting block (12) are also provided with exhaust holes (5).

8. The aircraft tail protection device according to claim 1, characterized in that, Also includes: A heat shield (6) is fitted around the outside of the engine nozzle (4) along the circumferential direction. One end of the heat shield (6) is connected to the tail end of the housing (11), and the other end of the heat shield (6) is connected to the outside of the engine nozzle (4).

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