Flexible adapter tail pusher launcher for composite material launch canister

Abstract

The application provides a flexible adaptive tail push ejector suitable for a composite material launching tube, which comprises a tail seat, a supporting ring, a missile fixing mechanism, a rear cover and a gas generator, the aircraft is arranged in the launching tube, the rear cover is tightly and fixedly installed at the tail of the launching tube, and the gas generator is installed in the rear cover; the tail of the aircraft is sequentially provided with the tail seat and the supporting ring, and the three are tightly connected through the missile fixing mechanism, the outer ring of the supporting ring is tightly connected with the launching tube, the outer periphery of the tail seat is not in contact with the inner wall of the launching tube, and the outer periphery of the tail seat is provided with a sealing ring. Through the dynamic sealing between the metal tail seat and the composite material launching tube, the high-temperature and high-pressure gas flow generated by the gas generator in the launching process is blocked to ablate the aircraft, and the aircraft is effectively isolated and protected; meanwhile, the radial gap deviation of the tail seat and the launching tube is flexibly adapted, and the contact between the tail seat and the cylinder in the aircraft launching process is avoided to cause scratching or damage.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft launching, and in particular to a flexible adaptable tail-thrust catapult suitable for a composite material launching tube. Background Art

[0002] Tail-push catapults are a common form of cold launch for aircraft. However, this technology requires a strong dynamic seal between the low-pressure chamber formed by the catapult and the launch tube, placing high demands on the dimensional accuracy of the fit between the catapult and the launch tube. The launch tube body is typically manufactured from metal materials such as aluminum alloy and stainless steel using processes such as cold drawing and crimping welding. After initial forming, the inner surface of the body requires polishing, grinding, and cleaning to ensure roundness, straightness, and roughness. Furthermore, the structural dimensional accuracy of the mating surfaces between the catapult and the body must be strictly controlled. With the rapid advancement of aircraft launch technology, the demand for lightweight launch tubes has become more stringent, leading to the widespread use of lightweight composite materials in launch tube production. Glass fiber or carbon fiber reinforced composite materials are typically used for winding the launch tube body. However, since the inner surface roundness, straightness, and roughness of composite materials cannot be further processed after demolding, the accuracy required for tail-push launch conditions is insufficient.

[0003] The existing Chinese patent with publication number CN116447922A discloses a flexible tail thrust system for a launch tube and a launch tube, including: a tube body, a missile 1, a flexible tail seat 10, and a gas generator 5; the missile 1 is located inside the tube body; the missile 1 is located in front of the flexible tail seat 10, and the tail of the missile 1 is axially constrained by the flexible tail seat 10; the gas generator 5 is located in the initial cavity on the rear side of the flexible tail seat 10.

[0004] However, there are still many problems when applying the tail-push catapult technology in the existing technology to composite launch tubes. In view of the structural characteristics of the composite launch tube, such as the low roundness, straightness and roughness of the inner surface, and the problem that the catapult easily scratches the inner surface of the composite launch tube during the aircraft launch, the present invention proposes a flexible adaptive tail-push catapult suitable for the composite launch tube, which can not only adapt to the fact that the structural dimensional accuracy of the composite launch tube is not as high as that of the metal launch tube, but also protect the composite launch tube. Summary of the Invention

[0005] In view of the defects in the prior art, the purpose of the present invention is to provide a flexible adaptive tail-thrust catapult suitable for composite material launch tubes.

[0006] According to the present invention, a flexible adaptable tail-push catapult suitable for a composite launch tube includes: a tail seat, a support ring, a bullet fixing mechanism, a rear cover, and a gas generator. The aircraft is arranged inside the launch tube, the rear cover is fastened to the tail of the launch tube, and the gas generator is installed inside the rear cover.

[0007] The tail of the aircraft is provided with the tail stock and the support ring in sequence. The aircraft, the tail stock and the support ring are fastened together by the bullet fixing mechanism. The outer ring of the support ring is fastened together with the launch tube. The outer periphery of the tail stock does not contact the inner wall of the launch tube. A sealing ring is installed on the outer periphery of the tail stock, and the sealing ring fills the gap between the tail stock and the launch tube.

[0008] Preferably, the launch tube, the aircraft, the tail seat, the support ring and the gas generator are coaxially arranged.

[0009] Preferably, the tailstock comprises an inner raised portion and an outer ring mounting portion, and the shape of the raised portion comprises an arched spherical structure.

[0010] Preferably, the elastic fixing mechanism passes through the support ring and the mounting portion and extends into the aircraft, and the mounting portion is arranged in close contact with the aircraft.

[0011] Preferably, it further comprises a control device, which is connected to the fixed bullet mechanism and the gas generator respectively.

[0012] Preferably, the sealing ring is fastened to the tail stock by a pressure plate and connecting screws, and the sealing ring between the tail stock and the launching tube is in a compressed state.

[0013] Preferably, the cross-sectional shape of the sealing ring is an outward-flashed L-shaped ring, and the pressure plate is an annular thin sheet structure.

[0014] Preferably, the support ring is provided at the tail of the launching tube, and the rear cover is fastened to the launching tube via the support ring.

[0015] Preferably, the tailstock comprises a metal tailstock.

[0016] Preferably, the sealing ring comprises a rubber ring.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. The present invention uses a dynamic seal between the metal tailstock and the composite launch tube to prevent the high-temperature and high-pressure gas flow generated by the gas generator from eroding the aircraft during launch, effectively isolating and protecting the aircraft and improving launch safety. At the same time, the invention flexibly adapts to the radial gap deviation between the tailstock and the launch tube, avoiding scratches or damage caused by contact between the tailstock and the tube during the aircraft ejection process, thereby improving the security of the equipment.

[0019] 2. The present invention achieves the purpose of flexible adaptation and dynamic sealing by using a sealing ring made of compressible rubber instead of direct contact between the tailstock and the composite material launch tube, thus avoiding the extrusion, friction and scratching of the composite material launch tube by the metal tailstock.

[0020] 3. The present invention is installed in the support ring through the fixed bullet mechanism and connected to the tail end of the aircraft, so as to fix the aircraft, tail seat and support ring in series along the axial direction, thereby limiting the other degrees of freedom of the aircraft in the launch tube except yaw, and playing the role of locking the aircraft; that is, the axial position of the aircraft is limited during transportation, and the axial degrees of freedom of the aircraft can be unlocked during launch. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0022] Figure 1 This is a cross-sectional view of a flexible adaptable tail-thrust catapult applicable to a composite material launch tube, which is mainly embodied in the present invention;

[0023] Figure 2 This is a schematic diagram of the installation of the sealing ring mainly embodied in the present invention.

[0024] Shown in the figure: aircraft 1; tail seat 2; launch tube 3; sealing ring 4; support ring 5; bullet fixing mechanism 6; rear cover 7; gas generator 8; pressure plate 9; connecting screw 10. DETAILED DESCRIPTION

[0025] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0026] like Figure 1 and 2As shown, according to the present invention, a flexible adaptive tail-thrust catapult suitable for a composite launch tube includes: a tail seat 2, a support ring 5, a bullet fixing mechanism 6, a rear cover 7 and a gas generator 8. The aircraft 1 is arranged inside the launch tube 3, the rear cover 7 is fastened to the tail of the launch tube 3, and the gas generator 8 is installed inside the rear cover 7; the tail of the aircraft 1 is sequentially provided with a tail seat 2 and a support ring 5, the aircraft 1, the tail seat 2 and the support ring 5 are fastened together by the bullet fixing mechanism 6, the outer ring of the support ring 5 is fastened to the launch tube 3, the outer periphery of the tail seat 2 does not contact the inner wall of the launch tube 3, and a sealing ring 4 is installed on the outer periphery of the tail seat 2, and the sealing ring 4 fills the gap between the tail seat 2 and the launch tube 3.

[0027] The present application is applicable to a launch tube 3 formed of composite materials, which enables the composite launch tube 3 to adopt tail-push catapult technology to launch the aircraft 1, solves the problem of difficulty in dynamic sealing matching caused by the low dimensional accuracy of the composite launch tube 3, and at the same time changes the traditional radial seal of the tail-push catapult to an end face seal, avoiding the risk of the inner surface of the launch tube 3 being scratched by the catapult during the launch process.

[0028] The launch tube 3 is made of carbon fiber / glass fiber reinforced composite material using a wet or dry winding molding method. After demolding, its inner surface is no longer machined. It is used to provide a low-pressure chamber and a guide channel for the aircraft 1 to leave the tube when the aircraft 1 is launched.

[0029] The launch tube 3, the aircraft 1, the tail seat 2, the support ring 5 and the gas generator 8 are coaxially arranged.

[0030] Tailstock 2 rests on a support ring 5, which is mounted at the rear of launch tube 3 and provides support for aircraft 1. Tailstock 2 comprises a metal tailstock, which is well-suited to withstand the high-pressure loads generated by gas generator 8 during ejection. Tailstock 2 radially avoids contact with the inner wall of launch tube 3, preventing scratches on the composite inner wall of launch tube 3 during launch of aircraft 1. Tailstock 2 includes an internal raised portion and an outer ring mounting portion. The raised portion is shaped like an arched spherical structure, providing excellent pressure-bearing properties.

[0031] When the aircraft 1 is launched, the tail seat 2 pushes the aircraft 1 out of the tube under the action of the gas pressure generated by the gas generator 8, thereby achieving physical isolation between the gas and the aircraft 1; its shape is an arched spherical structure, which can well withstand the high-pressure load generated by the gas generator 8 during ejection.

[0032] The support ring 5 is provided at the end surface of the tail of the launch tube 3 for mounting the tailstock 2 and the bullet fixing mechanism 6, serving as a support and bearing structure for the aircraft 1 in the launch tube 3. The rear cover 7 is fastened to the launch tube 3 via the support ring 5.

[0033] The ammunition securing mechanism 6 extends through the support ring 5 and the mounting portion of the tailstock 2 into the interior of the aircraft 1. The mounting portion of the tailstock 2 is positioned flush against the aircraft 1, meaning that the tail end of the aircraft 1 directly rests on the tailstock 2. During launch, the tailstock 2 propels the aircraft 1. The ammunition securing mechanism 6 is installed within the support ring 5 and connected to the tail end of the aircraft 1. This secures the aircraft 1, the tailstock 2, and the support ring 5 in a series axial arrangement, restricting all degrees of freedom of the aircraft 1 in the launch tube 3 except for yaw, effectively locking the aircraft. This ensures axial restraint of the aircraft 1 during transport and unlocks the axial degrees of freedom during launch.

[0034] The sealing ring 4 includes a rubber ring and has compressible properties. The cross-sectional shape of the sealing ring 4 before being installed in the launch tube 3 is an outward-flared L-shaped ring. During the assembly process, affected by the cooperation between the tailstock 2 and the launch tube 3, the skirt is retracted inward, and the cross-sectional shape is changed from an obtuse angle to a right angle. The internal force generated by the deformation makes the contact between the tailstock 2, the sealing ring 4 and the launch tube 3 more reliable, thereby achieving a sealing effect. The pressure plate 9 is an annular thin sheet structure. The sealing ring 4 has certain compressible elastic characteristics and can adapt to the diameter deviation and low straightness of the inner surface of the composite launch tube 2; at the same time, the hardness of the rubber sealing ring 4 is lower than that of the composite launch tube 3, which avoids scratches on the inner surface of the launch tube 3 during the launch process.

[0035] Before being installed into the launch tube 3, the sealing ring 4 is fastened to the tail seat 2 by the pressure plate 9 and the connecting screws 10. After being installed into the launch tube 3, the skirt of the sealing ring 4 is constrained by the inner wall of the launch tube 3. The sealing ring 4 between the tail seat 2 and the launch tube 3 is in a compressed state to eliminate the gap between the cylinder body of the launch tube 3 and the tail seat 2, thereby achieving a sealing effect and forming a pressure chamber. At the same time, the isolation between the fuel gas and the aircraft 1 is realized, thereby avoiding the ablation of the aircraft 1 by the fuel gas.

[0036] When the aircraft is launched, the tailstock 2 and the composite launch tube 3 are not in direct contact, but are transitioned through a sealing ring 4 made of compressible rubber material, thereby achieving the purpose of flexible adaptation and dynamic sealing, and avoiding the extrusion, friction and scratching of the composite launch tube 3 by the metal tailstock 2.

[0037] The present application also includes a control device, which is connected to the fixed bomb mechanism 6 and the gas generator 8. When the aircraft is ejected, the fixed bomb mechanism 6 is unlocked, and the gas generator 8 serves as the power source for launching the aircraft 1. During launch, it can generate a high-pressure gas flow. When a certain pressure is established in the sealed pressure chamber formed by the launch tube 3, the tail seat 2, and the rear cover 7, the control device overcomes the effect of gravity and propels the aircraft 1 out of the tube.

[0038] Furthermore, under the action of the high-pressure gas flow, the sealing ring 4 contacts and tightly adheres to the inner wall of the launch tube 3, forming a sealing pair and providing a radial seal between the tailstock 2 and the launch tube 3. An airtight low-pressure chamber is formed between the tailstock 2, the tube body, and the rear cover 7. The gas expands within this chamber, generating work that propels the tailstock 2 and drives the aircraft 1 upward. The rubber sealing ring 4 forms a dynamic seal between the tailstock 2 and the launch tube 3. A large radial gap is left between the tailstock 2 and the launch tube 3 to prevent scratches on the inner surface of the launch tube 3 during launch.

[0039] This application implements the technology of using a tail thruster to launch an aircraft in a composite launch tube 3, achieving the goal of lightweighting weapon equipment. This application achieves a dynamic seal between the metal tailstock 2 and the composite launch tube 3, preventing the high-temperature, high-pressure gas flow generated by the gas generator 8 from ablating the aircraft 1 during launch, effectively isolating and protecting the aircraft 1 and improving launch safety. At the same time, the application flexibly adapts to the radial gap deviation between the tailstock 2 and the launch tube 3, avoiding scratches or damage caused by contact between the tailstock 2 and the tube during the aircraft ejection process, thereby improving the equipment's security.

[0040] In the description of this application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0041] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. A flexible adaptable tail-thrust catapult suitable for composite material launch tubes, characterized in that: include: A tail seat (2), a support ring (5), a bullet fixing mechanism (6), a rear cover (7) and a gas generator (8), wherein the aircraft (1) is arranged inside a launch tube (3), the rear cover (7) is fixedly mounted on the tail of the launch tube (3), and the gas generator (8) is mounted inside the rear cover (7); The tail portion of the aircraft (1) is provided with the tail seat (2) and the support ring (5) in sequence. The aircraft (1), the tail seat (2) and the support ring (5) are fastened together by the bullet fixing mechanism (6). The outer ring of the support ring (5) is fastened together with the launch tube (3). The outer periphery of the tail seat (2) does not contact the inner wall of the launch tube (3). A sealing ring (4) is installed on the outer periphery of the tail seat (2), and the sealing ring (4) fills the gap between the tail seat (2) and the launch tube (3). The tailstock (2) comprises an inner raised portion and an outer ring mounting portion, wherein the raised portion has an arched spherical structure; The elastic fixing mechanism (6) passes through the support ring (5), and the mounting portion extends into the aircraft (1), and the mounting portion is arranged in close contact with the aircraft (1).

2. The flexible adaptable tail-thrust catapult suitable for a composite material launch tube according to claim 1, characterized in that: The launch tube (3), the aircraft (1), the tail seat (2), the support ring (5), and the gas generator (8) are coaxially arranged.

3. The flexible adaptable tail-thrust catapult suitable for a composite material launch tube according to claim 1, characterized in that: It also includes a control device, which is connected to the fixed bullet mechanism (6) and the gas generator (8) respectively.

4. The flexible adaptable tail-thrust catapult suitable for a composite material launch tube according to claim 1, characterized in that: The sealing ring (4) is fastened to the tailstock (2) via a pressure plate (9) and a connecting screw (10), and the sealing ring (4) between the tailstock (2) and the launching tube (3) is in a compressed state.

5. The flexible adaptable tail-thrust catapult suitable for a composite material launch tube according to claim 4, characterized in that: The cross-sectional shape of the sealing ring (4) is an outward-expanded L-shaped ring, and the pressing plate (9) is an annular thin sheet structure.

6. The flexible adaptable tail-thrust catapult suitable for a composite material launch tube according to claim 1, characterized in that: The support ring (5) is arranged at the tail of the launch tube (3), and the rear cover (7) is fastened to the launch tube (3) via the support ring (5).

7. The flexible adaptable tail-thrust catapult suitable for a composite material launch tube according to claim 1, characterized in that: The tailstock (2) comprises a metal tailstock.

8. The flexible adaptable tail-thrust catapult suitable for a composite material launch tube according to claim 1, characterized in that: The sealing ring (4) comprises a rubber ring.

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