Delay separation aircraft adapter and separation method thereof

Abstract

According to the delayed separation aircraft adapter and the separation method thereof, the foam base body, the metal base, the adaptation layer, the filling foam and the anti-attrition layer are all formed through bonding, and the technological process is simplified. The explosive bolt is connected with the adapter to control the separation time of the adapter, so that the adapter is prevented from hitting ship-borne equipment after going out of the cylinder, and the launching safety is improved; the base body adopts low-density PMI foam as a main material of the supporting layer, so that the total weight of the adapter is reduced; the mode that the metal base with the horizontal wing plate is installed from the bottom of the adapter optimizes the force conduction mode, and the requirement for the bonding strength of the metal base and the foam base body is greatly lowered. A two-stage compression state is designed, so that the adapter has a buffering and damping function in the cylinder and has a function of being stably fixed on the surface of an aircraft when following the aircraft, and the contradiction between buffering and damping and flight following fixing is solved. Through the blanking cap, impact kinetic energy generated after the explosive bolt is exploded and unlocked acts on the adapter, and separation force in the radial direction of the aircraft is provided.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of adapters related to aircraft transportation, storage and launch, and in particular relates to a delayed separation aircraft adapter and a separation method thereof. BACKGROUND

[0002] The adapter is a filling ring type device between the storage and transportation launch cylinder and the aircraft, which is used for lateral support, shock absorption, delayed separation and gap adaptation of the aircraft. The adapter is launched out of the cylinder together with the aircraft, and is fixed on the aircraft for a period of time by explosive bolts, and is quickly separated from the aircraft after unlocking by explosive bolts.

[0003] The current mainstream adapter is a spring or leaf spring powered aircraft adapter that separates out of the cylinder, or a support block fixed on the aircraft that functions as a cylinder support.

[0004] For shipboard aircraft equipment, the aircraft adapter that separates out of the cylinder has some insurmountable shortcomings and risks in use.

[0005] First, the separation force is small. The spring or leaf spring powered out-of-cylinder separation adapter has a small radial separation force, which can only meet the requirements of adapter out-of-cylinder separation, and cannot meet the horizontal distance requirements of out-of-cylinder separation. The adapter may fall on the ship and damage the shipboard equipment after being launched out of the cylinder, or form excess material to hinder the normal use of other functional equipment.

[0006] Second, falling into the tail flame area causes launch risk. Since the direction and size of the aerodynamic force of the launch site are uncertain, the attitude of the adapter after separation out of the cylinder is unstable, and if the adapter separation distance is too close during the launch of the aircraft, the aircraft tail flame may wash onto the adapter, accelerating the impact on the adjacent cylinder cover and causing damage.

[0007] For example, the utility model patent with publication number CN219707324U discloses a mechanical delayed separation mechanism of an aircraft projectile adapter, which realizes separation from the aircraft after the rotating disc rotates a certain angle, but it has the defect that the adapter meets the separation condition when it leaves the launch cylinder, and cannot fly with the aircraft for a specified time.

[0008] If a support block fixed on the aircraft is used to support the cylinder, the support block will always be fixed on the aircraft, which will affect the aerodynamic performance and rudder efficiency of the aircraft, and the support block is generally made of hard material, which cannot provide shock absorption and damping function for the aircraft, and is very unfavorable for the structure of the projectile and its internal components under the cylinder transportation working condition.

[0009] Given that the adapter that separates immediately upon exiting the tube and the support block fixed to the aircraft cannot meet the usage requirements, there is an urgent need to invent a new type of time-delayed separation adapter to solve the above problems. Summary of the Invention

[0010] To address the shortcomings of existing technologies, the purpose of this invention is to provide a novel, lightweight adapter connected via explosive bolts. This adapter provides support, cushioning and shock absorption for the aircraft, allows for post-launch follow-the-air capability, and enables delayed separation.

[0011] According to the present invention, a time-delay separation aircraft adapter includes: a foam matrix 1, a metal base 2, an explosive bolt 3, an adapter layer 4, a plug 6, and a nut assembly 7. The metal base 2 is bonded to the bottom of the foam matrix 1, and its outer side is provided with horizontally extending wing plates to optimize the transmission of aerodynamic forces and constrain the foam matrix 1. The adapter layer 4 is bonded to the top of the foam matrix 1 and is used to contact the surface of the aircraft and provide support and cushioning. The explosive bolt 3 is connected to the metal base 2 via the nut assembly 7, which is used to realize the connection and delayed separation of the adapter and the aircraft. Its bolt rod passes through the metal base 2 and the foam matrix 1 in sequence. The plug 6 is installed at the front end of the foam matrix 1, directly opposite the end of the bolt shank of the explosive bolt 3, and is used to withstand the impact and provide separation force when the explosive bolt 3 is unlocked.

[0012] Preferably, it also includes a filling foam 5 and a friction-reducing layer 8; The filling foam 5 is bonded to the wing plate of the metal base 2 and inside the foam matrix 1 to reduce the thickness of the wing plate of the metal base 2. The friction-reducing layer 8 is bonded to the side of the foam matrix 1 and is used to contact the inner wall of the launch tube and reduce friction.

[0013] Preferably, the outer diameter of the bolt shank of the explosive bolt 3 is larger than the outer diameter of its threaded end portion to form a stepped surface; The inner diameter of the flat washer of the nut assembly 7 is larger than the outer diameter of the threaded portion at the end of the bolt shank and smaller than the outer diameter of the bolt shank. The metal base 2 is provided with a mounting hole for the bolt rod to pass through, and the mounting hole has an internal platform surface; The stepped surface of the bolt rod mates with the internal platform surface of the metal base 2, enabling the adaptation layer 4 to be compressed.

[0014] Preferably, the adapter layer 4 has two levels of compression: The nut assembly 7 makes the stepped surface of the bolt rod flush with the internal platform surface of the metal base 2, and the adapter layer 4 generates pre-compression to form primary compression. When the aircraft enters the launch tube, the adapter layer 4 is further compressed until the launch tube and the aircraft axis coincide. The bolt rod step extends downwards from the internal platform surface of the metal base 2 to form an adapter gap, thus forming a secondary compression.

[0015] Preferably, under the secondary compression state, the adapter gap enables the adapter layer 4 to provide cushioning and shock absorption during transportation. Under the constraint of primary compression, the adapter can be stably fixed during the follow-up flight phase after the aircraft exits the tube.

[0016] Preferably, the metal base 2 is installed from the bottom of the foam matrix 1 by embedding its wingplate into the foam matrix 1; this allows the aerodynamic force experienced by the adapter when flying with the aircraft to be transmitted to the metal base 2 through positive pressure, optimizing the force transmission method and reducing the requirement for the bonding strength between the metal base 2 and the foam matrix 1.

[0017] Preferably, the foam matrix 1 uses PMI foam as the main material of the support layer to reduce the total weight of the adapter.

[0018] Preferably, the adapters are arranged in pairs of four, symmetrically arranged vertically and horizontally on the aircraft.

[0019] Preferably, the nut assembly 7 adopts a double-nut anti-loosening structure.

[0020] A separation method for a time-delay separation aircraft adapter provided by the present invention includes the following steps: Step 1: Install the adapter onto the surface of the aircraft using the explosion bolts 3, and put the adapter layer 4 into a pre-compressed first-stage compression state; insert the aircraft into the launch tube, and further compress the adapter layer 4 into a second-stage compression state; Step 2: After the aircraft launches from the tube, under the constraint of primary compression, the adapter flies along with the aircraft; Step 3: After flying to the predetermined time or distance, the control system sends an unlock signal to detonate explosive bolt 3; Step 4: After the explosion, the bolt shank of the explosive bolt 3 breaks and impacts the plug 6 at high speed, generating an impact separation force along the radial direction of the aircraft. Under the combined action of this impact separation force and the aerodynamic force acting on the inclined surface at the front end of the foam matrix 1, the adapter and the aircraft quickly separate, completing the launch mission.

[0021] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention uses explosive bolts to connect the adapter. The explosive bolts achieve explosive unlocking through command and control signals and gunpowder, which can precisely control the separation time of the adapter and prevent the adapter from hitting the shipborne equipment after exiting the tube, thus improving launch safety.

[0022] 2. The present invention designs a metal base with horizontal wing plates and installs it from the bottom of the adapter. The superposition of the two allows the aerodynamic force on the adapter when it follows the aircraft to be transmitted to the metal base through positive pressure, which optimizes the force transmission method and greatly reduces the bonding strength requirements between the metal base and the foam matrix.

[0023] 3. This invention is designed with two-stage compression. Under the condition of transporting the cannonball, the adapter is in the second stage of compression. The explosive bolt can float up and down inside the adapter, so that the adapter has a buffer and shock absorption function for the aircraft. When flying with the aircraft, the adapter has the function of being stably fixed to the surface of the aircraft under the constraint of the first stage of compression.

[0024] 4. This invention uses low-density PMI foam as the main material of the support layer to reduce the total weight of the adapter; and uses filling foam to reduce the thickness of the metal base wing plate, further reducing the total weight of the adapter.

[0025] 5. The present invention uses a plug so that the impact kinetic energy of the bolt rod after the explosive bolt is detonated and unlocked acts on the adapter, providing a separation force along the radial direction of the aircraft.

[0026] 6. This invention uses double nuts to prevent loosening, has a simple assembly relationship, and is convenient for product inspection, disassembly and maintenance. It can effectively resist the vibration of the cartridge transport and the vibration of the adapter when it follows the aircraft.

[0027] 7. This invention provides an unlocking electrical signal via program instructions, enabling timed and precise control of the adapter's separation from the aircraft. This allows for adapter separation after the aircraft has been launched and is far from the naval formation or launch site, improving launch safety.

[0028] 8. The present invention uses only explosive bolts with small structural dimensions installed inside the aircraft, which reduces the space occupied inside the aircraft and further improves the space utilization rate inside the aircraft. Attached Figure Description

[0029] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Fig. 1 This is a schematic diagram of the cross-sectional structure of the present invention; Fig. 2 This is a schematic diagram of the cross-sectional structure of the present invention.

[0030] The diagram shows: Detailed Implementation

[0031] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0032] This invention provides a novel lightweight, time-delayed separation aircraft adapter for use in aircraft storage and launch tubes. The adapter supports the aircraft, provides shock absorption, allows the aircraft to follow the launch vehicle after launch, and enables time-delayed separation.

[0033] This invention designs a metal base 2 with horizontal wing plates, and the installation method from the bottom of the adapter optimizes the force transmission method, greatly reducing the bonding strength requirements between the metal base 2 and the foam matrix 1. Using low-density PMI foam as the main material of the support layer and employing filler foam to reduce the thickness of the wing plates of the metal base 2 reduces the overall weight of the adapter.

[0034] By using the explosive bolt 3 to connect the adapter, the timing of the adapter's separation can be precisely controlled, preventing the adapter from hitting shipboard equipment after exiting the launch tube and improving launch safety. The plug 6 allows the impact kinetic energy from the explosive bolt 3's detonation to act on the adapter, providing a separation force along the aircraft's radial direction.

[0035] The adapter layer 4 is designed with two-stage compression, which enables the adapter to have a buffer and shock absorption function inside the cylinder, and to be stably fixed to the surface of the aircraft when flying with the aircraft.

[0036] like Figs. 1-2 As shown, the time-delay separation adapter includes: a foam matrix 1, a metal base 2, an expansion bolt 3, an adapter layer 4, a filling foam 5, a plug 6, a nut assembly 7, and a friction-reducing layer 8. The foam matrix 1, metal base 2, adapter layer 4, filling foam 5, and friction-reducing layer 8 are all bonded together, simplifying the process. The friction-reducing layer 8 is a polytetrafluoroethylene rubber composite board.

[0037] To reduce the overall weight of the adapter, the main material in the metal base 2 is designed to be low-density PMI foam, thus reducing the overall weight of the adapter. Foam 5 is designed to fill the gaps and reduce the thickness of the wing plates of the metal base 2, further reducing the adapter's weight.

[0038] The use of explosive bolts 3 enables precise control of the adapter delay separation, improving launch safety and separation reliability.

[0039] The metal base 2 is bonded to the foam matrix 1 from the bottom of the adapter. When the adapter flies with the aircraft, the wing plate outside the cylinder of the metal base 2 constrains the foam matrix 1 to adhere to the surface of the projectile. Due to the bottom mounting and the presence of the wing plate constraint, the required bonding strength between the metal base 2 and the foam matrix 1 is greatly reduced.

[0040] The adapters are arranged in groups of four on the upper and lower parts of the aircraft, symmetrically arranged in all directions. The adapter layer 4 is subjected to the combined effects of the aircraft's gravity, the compressive force on the adapter when the launch tube is concentric with the aircraft's axis after entering the tube, and the elastic force of the upper adapter on the lower adapter, which plays a supporting and shock-absorbing role.

[0041] This invention is installed between the outer surface of the aircraft and the inner surface of the launch tube. Its specific functions are as follows: During the final assembly of the cannon-launched projectile, the explosive bolt 3 is pre-installed inside the projectile structure. The bolt shank of the explosive bolt 3 extends out of the projectile surface, and the outer diameter of the bolt shank is larger than the outer diameter of the threaded portion at the end of the bolt shank, forming a stepped surface. The inner diameter of the flat washer of the nut assembly 7 is larger than the outer diameter of the threaded portion at the end of the bolt shank, but smaller than the outer diameter of the bolt shank. With this design, when installing the adapter, the nut assembly 7 is first installed in place, so that the stepped surface of the explosive bolt shank and the inner platform surface of the metal base 2 are flush with the flat washer surface. At this time, the adapter layer 4 is pre-compressed to a certain extent as the first stage of compression. When the aircraft enters the cannon, the adapter layer 4 will be further compressed until the launch tube and the aircraft axis coincide, i.e., in a concentric state. This is the second stage of compression. At this time, the stepped surface of the bolt shank of the explosive bolt 3 extends downward out of the inner platform surface of the metal base 2, forming a certain adapter gap.

[0042] During storage, the cannonball is placed horizontally. The adapter layer 4 is subjected to the combined effects of the aircraft's gravity, the compressive force on the adapter when the launch tube is concentric with the aircraft's axis after entering the cannon, and the elastic force of the upper adapter on the lower adapter, and mainly serves to bear the weight.

[0043] In non-launching conditions such as transport and hoisting, if the adapter layer 4 is further compressed under secondary compression under overload, the adapter layer 4, with its elastic properties, can act as a buffer and shock absorber, increasing the gap between the stepped surface of the explosive bolt 3 and the internal platform surface of the metal base 2. If the adapter layer is released under secondary compression under the opposite overload, the design ensures that the adapter layer 4 will not be released beyond the primary compression state under the required overload. Thus, under overload, the elastic properties of the adapter layer 4 fully realize the buffer and adaptation function of the projectile structure. Through the two-stage compression design, the collision between the nut assembly 7 and the metal base 2 under the opposite overload is avoided, preventing damage to the adapter.

[0044] During launch, after the adapter leaves the launch tube with the aircraft, it follows the aircraft for a period of time. During this time, due to the fixing effect of the nut assembly 7 and the constraint of the first-stage compression state, the adapter will be stably fixed on the surface of the projectile. When the explosive bolt 3 explodes and unlocks, the broken bolt rod rushes towards the plug 6 at high speed, providing an impact force along the radial direction of the projectile. Under the combined action of the aerodynamic force along the radial direction of the projectile formed by the inclined surface at the front end of the foam matrix 1, the adapter and the projectile quickly separate, completing the launch mission.

[0045] In summary, the present invention can achieve corresponding functions such as support, buffering and vibration reduction, and time-delay separation during the transportation, storage, and launch of the projectile.

[0046] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They 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, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0047] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A time-delay separation aircraft adapter, characterized in that, include: Foam matrix (1), metal base (2), explosion bolt (3), adapter layer (4), plug (6) and nut assembly (7); The metal base (2) is bonded to the bottom of the foam matrix (1), and its outer side is provided with horizontally extending wing plates to optimize the transmission of aerodynamic forces and constrain the foam matrix (1). The adapter layer (4) is bonded to the top of the foam matrix (1) for contact with the surface of the aircraft and to provide support and cushioning; The explosive bolt (3) is connected to the metal base (2) through the nut assembly (7) to realize the connection and delayed separation of the adapter and the aircraft. Its bolt rod passes through the metal base (2) and the foam matrix (1) in sequence. The plug (6) is installed at the front end of the foam matrix (1), directly opposite the end of the bolt shank of the explosive bolt (3), and is used to withstand the impact and provide separation force when the explosive bolt (3) is unlocked.

2. The time-delay separation aircraft adapter according to claim 1, characterized in that, It also includes filling foam (5) and friction-reducing layer (8); The filling foam (5) is bonded to the wing plate of the metal base (2) and inside the foam matrix (1) to reduce the thickness of the wing plate of the metal base (2); The friction-reducing layer (8) is bonded to the side of the foam matrix (1) to contact the inner wall of the launch tube and reduce friction.

3. The time-delay separation aircraft adapter according to claim 1, characterized in that, The outer diameter of the bolt shank of the explosive bolt (3) is larger than the outer diameter of the threaded portion at its end to form a stepped surface; The inner diameter of the flat washer of the nut assembly (7) is greater than the outer diameter of the threaded portion at the end of the bolt rod and less than the outer diameter of the bolt rod. The metal base (2) is provided with a mounting hole for the bolt rod to pass through, and the mounting hole is provided with an internal platform surface; The stepped surface of the bolt rod cooperates with the internal platform surface of the metal base (2) to achieve the compression state of the adapter layer (4).

4. The time-delay separation aircraft adapter according to claim 3, characterized in that, The adapter layer (4) has two levels of compression: The nut assembly (7) makes the stepped surface of the bolt rod flush with the internal platform surface of the metal base (2), and the adapter layer (4) generates pre-compression to form primary compression; When the aircraft enters the launch tube, the adapter layer (4) is further compressed until the launch tube and the aircraft axis coincide. The bolt rod step extends downwards from the metal base (2) to form an adapter gap on the internal platform surface, thus forming a secondary compression.

5. The time-delay separation aircraft adapter according to claim 4, characterized in that, Under the secondary compression state, the adapter gap enables the adapter layer (4) to provide buffering and shock absorption during transportation. Under the constraint of primary compression, the adapter can be stably fixed during the follow-up flight phase after the aircraft exits the tube.

6. The time-delay separation aircraft adapter according to claim 1, characterized in that, The metal base (2) is installed from the bottom to the foam matrix (1) by embedding its wing plate into the foam matrix (1); so that the aerodynamic force received by the adapter when following the aircraft is transmitted to the metal base (2) through positive pressure, thereby optimizing the force transmission method and reducing the requirement for the bonding strength between the metal base (2) and the foam matrix (1).

7. The time-delay separation aircraft adapter according to claim 1, characterized in that, The foam matrix (1) uses PMI foam as the main material of the support layer to reduce the total weight of the adapter.

8. The time-delay separation aircraft adapter according to claim 1, characterized in that, The adapters are arranged in pairs of four, symmetrically positioned vertically and horizontally on the aircraft.

9. The time-delay separation aircraft adapter according to claim 1, characterized in that, The nut assembly (7) adopts a double nut anti-loosening structure.

10. A method for separation using a time-delay separation aircraft adapter as described in any one of claims 1 to 9, characterized in that, Includes the following steps: Step 1: Install the adapter onto the surface of the aircraft using the explosive bolts (3) and put the adapter layer (4) into a pre-compressed first-stage compression state; put the aircraft into the launch tube and further compress the adapter layer (4) to a second-stage compression state; Step 2: After the aircraft launches from the tube, under the constraint of primary compression, the adapter flies along with the aircraft; Step 3: After flying to the predetermined time or distance, the control system sends an unlock signal to detonate the explosive bolt (3). Step 4: The bolt rod of the explosive bolt (3) breaks after the explosion and impacts the plug (6) at high speed, generating an impact separation force along the radial direction of the aircraft. Under the combined action of this impact separation force and the aerodynamic force acting on the inclined surface at the front end of the foam matrix (1), the adapter and the aircraft quickly separate, completing the launch mission.

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