Automatic separation mechanism of aircraft disengaging and inserting device

Abstract

The invention provides an automatic separating mechanism of an aircraft disengaging and inserting device, which comprises a connecting clamping opening, a rotating shaft, a telescopic rod, a rotating spring and a fixed seat, and is characterized in that the connecting clamping opening and the telescopic rod are connected together through the rotating shaft; the telescopic rod and the fixed seat are connected together through a rotary spring; and the fixed seat of the automatic separation mechanism is connected with the framework of the launching device. The mechanism actively prevents the plug-out head from colliding with the projectile body. And the releasing and inserting seat is arranged right above the projectile body, so that the operation is convenient, and the body structure of the target projectile is optimized. Depending on the deorbiting action of the target projectile, the separation of the deorbiting plug and the deorbiting socket in the deorbiting device is realized in a linkage manner, so that the deorbiting safety of the target projectile is ensured. The device has self-adaptability and can be suitable for box type or barrel type launching of various types of aircrafts, and the universality of the automatic separation mechanism of the disengaging and inserting device is achieved.

Description

Technical Field

[0001] This invention relates to the field of aircraft technology, and more specifically to an automatic separation mechanism for an aircraft decoupling device. Background Technology

[0002] In the field of aircraft, to test and calibrate the dynamic response data of various devices on a target missile in real time; similarly, before a target missile's flight, to test and analyze the relevant performance indicators of the test product, it is necessary to install a disengagement device on the target missile to transmit information data from the devices on the missile in real time. This allows for real-time monitoring of the data of various devices on the target missile, timely calibration of the command responses of the devices, ensuring that the target missile's control system remains within a controllable range, and guaranteeing the safety and reliability of the target missile throughout its flight lifecycle.

[0003] The disengagement device consists of a disengagement plug and a disengagement socket. Currently, aircraft, including target missiles, typically have installation windows machined on the missile bay, and the disengagement socket is installed on the lower side or bottom of the missile body via a threaded connection. As the target missile derails, the disengagement socket and the disengagement plug passively separate. The disengagement plug, along with the disengagement cable, remains beside the guide rail. The free movement of the disengagement plug may cause damage to the target missile body, thereby affecting the target missile's flight and producing unpredictable consequences.

[0004] The existing disengagement device has the disengagement socket installed on the side or bottom of the target projectile. The separation of the disengagement socket and the disengagement plug relies on the target projectile moving on the track, thus passively separating them. After the disengagement socket and the disengagement plug are separated, the disengagement plug is in a free-moving state. There is a hidden danger here: once the disengagement plug hits the projectile body, it will damage the surface of the projectile body, thereby affecting the local structural strength of the projectile body. If the surface of the projectile body is cracked by the impact, it will cause the target projectile to become unstable during flight, or even stall and lose control, resulting in irreversible consequences. Summary of the Invention

[0005] Based on the above-mentioned technical problems, the present invention proposes an automatic separation mechanism for aircraft disconnection devices to solve the problem that the free movement of the disconnector during the separation of the socket and the plug in traditional disconnection devices damages the surface of the aircraft, thereby affecting the flight safety of the aircraft.

[0006] To address the aforementioned technical problems, one objective of this invention is to provide an automatic separation mechanism for an aircraft disengagement device, comprising a connecting clamp 1, a rotating shaft 2, a telescopic rod 3, a rotating spring 4, and a fixing base 5. The connecting clamp 1 and the telescopic rod 3 are connected together by a rotary shaft 2; The telescopic rod 3 and the fixed base 5 are connected together by a rotary spring 4; The mounting base 5 of the automatic separation mechanism is connected to the frame of the launching device; During operation, before the target projectile is ignited, the front edge of the disengagement socket of the disengagement device has a front edge, and the connecting clamp 1 clamps the disengagement plug, which is locked in the disengagement socket by the front edge of the disengagement socket. After ignition, the target projectile begins to move linearly along the guide rail of the launching device. The projectile body moves relatively away from the automatic separation mechanism of the disengagement device, and the front edge of the disengagement socket no longer locks the connecting clamp 1 of the disengagement plug. Relying on the elastic deformation of the rotary spring 4, the telescopic rod 3 moves from a horizontal tilted downward state to a vertical state around the rotary spring 4, thereby ensuring that the connecting clamp 1 that clamps the disengagement plug can actively move away from the projectile body, ensuring the safety of the target projectile's derailment.

[0007] Furthermore, the rotary shaft 2 is connected to the connecting clamp 1 and the telescopic rod 3 by welding or threading.

[0008] Furthermore, the rotary spring 4 is connected to the telescopic rod 3 and the fixed seat 5 by welding or thread.

[0009] Furthermore, the mounting base 5 is connected to the frame of the launching device by welding or threading.

[0010] Furthermore, the connecting clamp 1 is made of aluminum alloy, plastic or new composite material to clamp the disconnecting plug of the disconnecting device.

[0011] Furthermore, the telescopic rod 3 is made of aluminum alloy, plastic or new composite material to ensure that the automatic separation mechanism has the ability to adaptively adjust the relative position between the connecting clamp 1 and the disconnect socket.

[0012] Furthermore, the fixing base 5 is made of steel pipe, square tube, I-beam or new composite material.

[0013] Furthermore, the upper surface of the fixing base 5 has a wire groove to facilitate the smooth wiring of the disconnected cable and prevent the cable from being damaged when the wire is threaded inside the fixing base. The disconnected cable is connected to the disconnect plug along the telescopic rod.

[0014] Furthermore, this automatic separation mechanism is applicable to the launch of box-type or tube-type launchers for aircraft, realizing the versatility of the automatic separation mechanism for the disengagement device.

[0015] The above-described one or more technical solutions of the present invention have at least one or more of the following technical effects: The automatic separation mechanism for the aircraft disengagement device provided by this invention actively avoids collisions between the disengagement plug and the projectile body. Furthermore, the disengagement socket is installed directly above the projectile body, facilitating operation and optimizing the target projectile's structure. Relying on the projectile's derailment action, the disengagement plug and socket are automatically separated in a coordinated manner, thus ensuring the projectile's derailment safety. Due to its adaptability, it is applicable to various types of box-type or tube-type launchers of aircraft, achieving versatility for the automatic separation mechanism of the disengagement device. Attached Figure Description

[0016] Figure 1 Schematic diagram of automatic separation mechanism; Figure 2 Schematic diagram of the automatic separation mechanism fixed to the launching device; Figure 3 Schematic diagram of the insertion / disconnection device; Figure 4 Working principle of automatic disengagement mechanism Figure 1 ; Figure 5 Working principle of automatic disengagement mechanism Figure 2 ; Among them: 1-connecting clamp, 2-rotating shaft, 3-telescopic rod, 4-rotating spring, 5-fixed base, 6-disconnect socket, 7-disconnect plug, 8-launch box frame, 9-projectile body, 10-disconnect socket front edge. Detailed Implementation Plan

[0017] This invention provides an automatic separation mechanism for an aircraft decoupling device. This mechanism is installed above the launch box, actively preventing contact and collision between the decoupling plug and the projectile body. Furthermore, the decoupling socket is installed directly above the projectile body, facilitating operation and optimizing the projectile's structure. The separation of the decoupling plug and socket is achieved in conjunction with the target projectile's derailment action, thus ensuring the target projectile's derailment safety. Moreover, this device is adaptive and applicable to various types of box-type or tube-type launchers of aircraft, achieving versatility for the automatic separation mechanism. The automatic separation mechanism for decoupling devices provided by this invention can be used for box-type or tube-type launchers of various types of aircraft.

[0018] The technical solutions of the present invention will be clearly and completely described below with reference to the embodiments and accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments obtained. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention are within the scope of protection of the present invention.

[0019] The automatic separation mechanism of this invention can adaptively realize the automatic separation of the plug and socket of the disconnection device. The connecting clamp 1 can be adjusted around the rotating shaft 2. The telescopic rod 3 can be adjusted in length to adapt to different specifications of launch boxes or launch tubes. The fixing base 5 can be selected from different shapes of steel pipes, square steel and other materials according to different usage occasions, thereby ensuring that the connecting clamp 1 can better clamp the plug. The mechanism proactively avoids collisions between the disconnector and the projectile body, and the disconnector socket is installed directly above the projectile body, facilitating operation and optimizing the projectile's structure. Relying on the projectile's derailment, the disconnector and disconnector socket in the disengagement device automatically separate, thus ensuring the projectile's safety during derailment.

[0020] Adding a disconnector front edge to the disconnector socket of the existing disconnector device ensures reliable connection and safe separation between the disconnector plug and the disconnector socket.

[0021] This mechanism is applicable to box-type or tube-type launchers of various types of aircraft, achieving the versatility of the automatic separation mechanism for the insertion / removal device.

[0022] like Figure 1 , Figure 2 As shown, the connecting clamp 1 and the telescopic rod 3 are connected together by a rotating shaft 2, and the connection method can be welding or threaded connection; the telescopic rod 3 and the fixed seat 5 are connected together by a rotating spring 4, and the connection method can be welding or threaded connection; the mechanism is connected to the frame of the launch box (or launch tube) through the fixed seat 5, and the connection method can be welding or threaded connection.

[0023] The connecting clamp 1 can be made of materials such as aluminum alloy or plastic that meet the structural strength requirements. This mechanism clamps the disconnect plug of the disconnect device through the connecting clamp 1.

[0024] The rotating shaft 2 ensures that the connecting clamp 1 can rotate relative to the telescopic rod 3 within a certain range.

[0025] The telescopic rod 3 can be made of materials such as aluminum alloy or plastic that meet the structural strength requirements. This ensures that the mechanism has the ability to adaptively adjust the relative position between the connecting clamp 1 and the disconnect socket, so that the connecting clamp 1 can be well adapted to the location of the disconnect plug.

[0026] The rotary spring 4 can be made of standard parts and other materials, and the fixing base 5 can be made of steel pipe, square tube, and I-beam. Taking square tube as an example, the upper surface of the square tube has a wire groove to facilitate the smooth wiring of the plug and unplug cable, and will not damage the cable due to the wire being threaded inside the square tube. The plug and unplug cable is connected to the plug along the telescopic rod.

[0027] Before the target missile is ignited and started, such as Figure 4 As shown, the front edge of the disconnect socket of the disconnect device has a front edge, the connecting clamp 1 clamps the disconnect plug 7, and the front edge 10 of the disconnect socket is fastened in the disconnect socket 6, which can also ensure a reliable connection between the disconnect plug and the disconnect socket.

[0028] After ignition, as Figure 5 As shown, the target projectile begins to move linearly along the guide rail of the launch box (or launch tube). The projectile body 9 moves relatively away from the automatic separation mechanism of the disengagement device. The front edge 10 of the disengagement socket no longer clamps the connecting jaw 1 of the disengagement plug 7. Relying on the elastic deformation of the rotary spring 4, the telescopic rod 3 moves around the rotary spring 4 from... Figure 4 Return to position Figure 5 Position. This ensures that the connecting jaw 1 of the clamping release plug 7 can actively move away from the projectile body 9, thus ensuring the safety of the target projectile's derailment.

[0029] The automatic separation mechanism for the aircraft disconnection device provided by this invention can adaptively realize the separation of the disconnection plug and the disconnection socket of the disconnection device; The automatic separation mechanism of the aircraft disengagement device provided by this invention actively avoids collision between the disengagement plug and the projectile body, and installs the disengagement socket directly above the projectile body, which facilitates operation and optimizes the structure of the target projectile. Relying on the projectile's derailment action, the automatic separation of the disengagement plug and socket in the disengagement device is achieved in a coordinated manner, thereby ensuring the safety of the target projectile's derailment. The automatic separation mechanism for aircraft disengagement devices provided by this invention is applicable to various types of box-type or tube-type launch aircraft, realizing the versatility of the automatic separation mechanism for disengagement devices.

[0030] This invention was applied to a target missile of a certain type in a box-type launch system. Prototype production and testing were completed, and the test results fully met the design requirements, verifying the feasibility, innovation, and reliability of the invention. Compared to existing traditional technologies, this invention not only optimizes the target missile's structure but also improves the reliability of the automatic separation of the plug and socket in its disengagement device, ensuring the target missile's safety after deorbiting. This provides an innovative and practical method and approach for the development of aircraft disengagement technology.

[0031] Obviously, those skilled in the art can make various modifications and variations to the embodiments of the present invention without departing from the spirit and scope of the embodiments of the present invention. Thus, if these modifications and variations to the embodiments of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention also intends to include these modifications and variations.

Claims

1. An automatic separation mechanism for an aircraft decoupling device, characterized in that: It includes a connecting clamp (1), a rotating shaft (2), a telescopic rod (3), a rotating spring (4), and a fixing seat (5). The connecting clamp (1) and the telescopic rod (3) are connected together by a rotating shaft (2); The telescopic rod (3) and the fixed base (5) are connected together by a rotary spring (4); The mounting base (5) of the automatic separation mechanism is connected to the frame of the launching device; During operation, before the target projectile is ignited, the front edge of the disengagement socket of the disengagement device has a front edge, and the connecting clamp (1) clamps the disengagement plug, which is locked in the disengagement socket by the front edge of the disengagement socket. After ignition, the target projectile begins to move linearly along the guide rail of the launching device. The projectile body moves relatively away from the automatic separation mechanism of the disengagement device, and the front edge of the disengagement socket no longer locks the connecting clamp (1) of the disengagement plug. Relying on the elastic deformation of the rotary spring (4), the telescopic rod (3) moves around the rotary spring (4) from a horizontal tilted downward state to a vertical state, thereby ensuring that the connecting clamp 1 that clamps the disengagement plug can actively move away from the projectile body, ensuring the safety of the target projectile's derailment.

2. The automatic separation mechanism of the aircraft decoupling device according to claim 1, characterized in that: The rotary shaft (2) is connected to the connecting clamp (1) and the telescopic rod (3) by welding or thread.

3. The automatic separation mechanism of the aircraft decoupling device according to claim 1, characterized in that: The rotary spring (4) is connected to the telescopic rod (3) and the fixed seat (5) by welding or thread.

4. The automatic separation mechanism of the aircraft decoupling device according to claim 1, characterized in that: The mounting base (5) is connected to the frame of the launching device by welding or threading.

5. The automatic separation mechanism of the aircraft decoupling device according to claim 1, characterized in that: The connecting clamp (1) is made of aluminum alloy, plastic or new composite material to clamp the plug of the disconnecting device.

6. The automatic separation mechanism of the aircraft decoupling device according to claim 1, characterized in that: The telescopic rod (3) is made of aluminum alloy, plastic or new composite material to ensure that the automatic separation mechanism has the ability to adaptively adjust the relative position between the connecting clamp (1) and the disconnect socket.

7. The automatic separation mechanism of the aircraft decoupling device according to claim 1, characterized in that: The fixing seat (5) is made of steel pipe, square tube, I-beam or new composite material.

8. The automatic separation mechanism of the aircraft decoupling device according to claim 7, characterized in that: The upper surface of the fixed base (5) has a wire groove to facilitate the smooth wiring of the plug and unplug cable, and to prevent the cable from being damaged by threading the wire inside the fixed base. The plug and unplug cable is connected to the plug along the telescopic rod.

9. The automatic separation mechanism of the aircraft decoupling device according to any one of claims 1-8, characterized in that: This automatic separation mechanism is applicable to the launch of box-type or tube-type launchers for aircraft, realizing the versatility of the automatic separation mechanism for the disengagement device.

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