A hatch breaching device and aircraft

Abstract

The utility model discloses a cabin cover breaking device and aircraft, including cabin support frame, the overlap of at least two cabin cover assembly of cabin support frame top, cabin cover assembly includes the cabin cover framework fixedly connected with cabin support frame, the detonation subassembly that is along the cabin cover framework top opening place surrounds and set, the cabin cover subassembly that overlaps in the cabin cover framework top and is connected with detonation subassembly, and set in the rear hinged mechanism of cabin cover subassembly rear end for connecting cabin cover framework, through the ignition of detonation device output end point and implement the trigger of energy -accumulating cutting cable, and make the cabin cover lift after energy -accumulating cutting cable cut -off by aircraft wind resistance, in the process, make it along its track rapid overturn by rear hinged mechanism, at the same time, rocket push injector starts, and strictly restricts cabin cover throw and releases trajectory, ensures that cabin cover does not occur lateral tilt, and when cabin cover enters free flow field, forms resultant force with rocket push injector, makes cabin cover accelerate after throw along rear hinged mechanism axis 45 DEG inclination.

Description

Technical Field

[0001] This utility model relates to the field of aircraft escape technology, and in particular to a hatch breaking device and an aircraft. Background Technology

[0002] With the rapid development of my country's aviation industry, the strength of the Chinese Air Force has been greatly enhanced, and the performance of various aircraft, such as fighter jets and bombers, has improved by leaps and bounds. However, further development is still needed in the field of aviation life-saving.

[0003] During flight missions, aircraft may encounter various emergencies, such as mechanical failures or enemy attacks. When these situations occur, pilots need to quickly evacuate the aircraft to save their lives. While the canopy, as an important component of the aircraft, protects the pilots during normal flight, it can become an obstacle during emergency escape.

[0004] Currently, among the escape methods after an aircraft malfunction, opening the canopy may be impossible due to the aircraft malfunction causing the canopy to lock and become unusable, or the canopy-breaking escape method may be used. However, breaking the canopy glass may cause impact or cuts to the pilot. In particular, breaking the canopy may cause spinal injuries in non-directional glass or canopies thicker than 10mm, posing a significant operational risk. Utility Model Content

[0005] Based on this, the purpose of this utility model is to provide a canopy breaking device and aircraft, which aims to solve the problem that there are significant operational risks in the current methods of escaping by opening the canopy or breaking the cockpit after an aircraft malfunction.

[0006] The present invention provides a hatch cover breaking device, which includes a cabin support frame and at least two hatch cover assemblies that are attached above the cabin support frame. The hatch assembly includes a hatch frame fixedly connected to the cabin support frame, a detonation assembly enclosing the top opening of the hatch frame, a hatch assembly overlapping the top of the hatch frame and connected to the detonation assembly, and a rear hinge mechanism disposed at the rear end of the hatch assembly for connecting to the hatch frame. Specifically, by triggering the detonation assembly, the hatch assembly, which is attached to the top of the hatch frame, is axially rotated and separated along the rear hinge mechanism.

[0007] The above-mentioned method triggers the shaped charge cutting cable by outputting the detonation device. After the shaped charge cutting cable is cut, the canopy is lifted due to the wind resistance of the aircraft. During the process, the rear hinge mechanism causes it to flip up rapidly along its trajectory. At the same time, the rocket propellant is activated and strictly constrains the canopy's trajectory to ensure that the canopy does not tilt. When the canopy enters the free flow field, it forms a combined force with the rocket propellant, causing the canopy to be accelerated backward at a 45° tilt angle along the axis of the rear hinge mechanism. Finally, the ejection function of the aircraft seat is triggered, effectively avoiding the situation where the pilot collidees with the canopy during ejection when the canopy enters the free flow field. This solves the problem that the current method of escaping by opening the canopy or breaking the cockpit after an aircraft failure has a high operational risk.

[0008] In addition, the hatch opening device proposed according to the embodiments of this utility model may also have the following additional technical features: Furthermore, a cabin cover plate is fixedly installed on the top of the cabin support frame, and the cabin cover plate is fixedly connected to the cabin cover frame.

[0009] Furthermore, a cabin side cover plate is fixedly installed at the side perimeter of the cabin support frame.

[0010] Furthermore, the detonation assembly includes a plurality of detonation devices arranged along the inner wall of the hatch frame, and a shaped charge cutting cable disposed at the output end of the detonation device.

[0011] Furthermore, the canopy assembly includes a canopy adapted to the opening at the top of the canopy frame, and a rocket injector fixedly disposed at the bottom of the canopy and on the side away from the rear hinge mechanism.

[0012] Furthermore, the energy-concentrating cutting cable is disposed between the hatch cover and the hatch cover frame to close the top opening edge of the hatch cover and the hatch cover frame.

[0013] In addition, this utility model also proposes an aircraft, including the canopy breaking device, which is installed on the aircraft. Attached Figure Description

[0014] Figure 1 This is a schematic diagram of the structure of a hatch opening device proposed in an embodiment of this utility model; Figure 2 This is a schematic diagram of the other side of a hatch opening device proposed in an embodiment of this utility model; Figure 3 This is a partial structural diagram of the hatch assembly in a hatch demolition device proposed in this utility model embodiment.

[0015] Explanation of key component symbols:

[0016] The following detailed description, in conjunction with the accompanying drawings, will further illustrate this utility model. Detailed Implementation

[0017] To facilitate understanding of this utility model, a more complete description will be given below with reference to the accompanying drawings. Several embodiments of this utility model are shown in the drawings. However, this utility model can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided so that the disclosure of this utility model will be more thorough and complete.

[0018] It should be noted that when a component is said to be "fixed to" another component, it can be directly on the other component or there may be an intervening component. When a component is said to be "connected to" another component, it can be directly connected to the other component or there may be an intervening component. The terms "vertical," "horizontal," "left," "right," and similar expressions used in this document are for illustrative purposes only.

[0019] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of the invention. The term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0020] Please see Figures 1 to 3 The image shows a hatch removal device according to an embodiment of the present invention, including a cabin support frame 4 and at least two hatch assemblies 3 that overlap the cabin support frame 4. Each hatch assembly 3 includes a hatch frame 31 fixedly connected to the cabin support frame 4, a detonation assembly arranged around the top opening of the hatch frame 31, a hatch assembly that overlaps the top of the hatch frame 31 and is connected to the detonation assembly, and a rear hinge mechanism 35 provided at the rear end of the hatch assembly for connecting the hatch frame 31. By triggering the detonation assembly, the hatch assembly that overlaps the top of the hatch frame 31 is axially rotated and separated along the rear hinge mechanism 35.

[0021] Furthermore, a cabin top cover plate 1 is fixedly installed on the top of the cabin support frame 4. The cabin top cover plate 1 is fixedly connected to the hatch frame 31. A cabin side cover plate 2 is fixedly installed on the side edge of the cabin support frame 4. The detonation assembly includes multiple detonation devices 32 arranged along the inner wall of the hatch frame 31, and a shaped charge cutting cable 36 installed at the output end of the detonation device 32. The hatch assembly includes a hatch 34 adapted to the top opening of the hatch frame 31, and a rocket injector 33 fixedly installed at the bottom of the hatch 34 and away from the rear hinge mechanism 35. The shaped charge cutting cable 36 is installed between the hatch 34 and the hatch frame 31 to close the top opening edge of the hatch 34 and the hatch frame 31.

[0022] In practice, depending on the aircraft model, the cabin support frame 4 is erected using aluminum rods. Then, the cabin top cover 1 and cabin side cover 2 are placed over the erected cabin support frame 4. It should be noted that both the cabin top cover 1 and cabin side cover 2 are made of skin material. Skin is a thin shell material covering the exterior of the aircraft structure (such as wing spars, stringers, fuselage frames, etc.). It is a key component that constitutes the aircraft's aerodynamic shape, bears flight loads, and protects internal systems. Like the aircraft's "skin," it must meet aerodynamic requirements and possess sufficient strength and durability. The installation method is as follows: When the aluminum rod is placed horizontally, T-nuts are pre-installed in the grooved track of the main structure. The skin is placed to the predetermined position, and M6 hexagonal bolts are screwed into the pre-drilled holes in the skin to secure it. A 2mm thick shim is placed between the bolt head and the skin for protection and cushioning. When the aluminum rod is placed vertically or at an angle, the T-nut will slide within the track. The operating steps are as follows: First, place the steel skin plate in the predetermined position, aligning the pre-drilled hole with the grooved track; then, place the washer on the bolt and screw the T-nut in slightly; finally, insert it into the groove and tighten it. The key to the success of this connection method is that the diameter of the pre-drilled hole in the skin is larger than the length of the T-nut, facilitating insertion. The washer not only increases the contact area but, more importantly, provides a supporting surface for the nut. This connection method is simple and quick to operate, and from a mechanical perspective, the reasonable selection of connector specifications and materials ensures the strength of the connection, enabling stable operation under complex working conditions and providing a guarantee for structural safety and reliability.

[0023] Next, after covering the surface of the cabin support frame 4 with the cabin top cover plate 1 and the cabin side cover plate 2, the hatch frame 31 can be assembled on the top of the cabin support frame 4. The assembly of the cabin frame 31 can also be completed between the cabin support frame 4 and the cabin top cover plate 1 and the cabin side cover plate 2 using the same installation method. Then, the operator can install the detonation device 32 along the inner edge of the hatch frame 31 by welding or screwing. The rear hinge mechanism 35 is installed behind the hatch frame 31, and the hatch 34 is fixedly installed on the other side of the rear hinge mechanism 35. The rear hinge mechanism 35 is a key mechanism for connecting the hatch frame 31 and the hatch 34, and is mainly used to realize the opening and closing of the hatch 34 and maintain airtightness and structural strength during flight. Furthermore, the rear hinge mechanism 35 is particularly important in fighter jets and some high-performance aircraft, as these aircraft are typically equipped with ejection escape systems. During ejection in such aircraft, the rear hinge mechanism must ensure that the canopy is thrown along a predetermined trajectory to avoid collision with the fuselage structure, allowing the canopy 34 to rotate axially along the rear hinge mechanism 35. A rocket injector 33 is installed on the bottom of the canopy 34 away from the rear hinge mechanism 35. After the canopy 34 and the canopy frame 31 are closed, a partial edge gap will remain. It should be noted that this gap corresponds to the output end of the detonator 32, and a shaped charge cutting cable 36 is added based on this gap to seal the edges of the canopy 36 and the canopy frame 31. In some optional embodiments of this utility model, the point of the rocket injector 33 is... The ignition point can be connected to the output end of the detonation device 32, so that the detonation device 32 can cut the shaped charge cutting cable 36 and trigger the rocket injector 33 simultaneously after being triggered. During operation, the pilot can trigger the detonation device 32, and the trigger key can be set at any convenient emergency triggering position in the cockpit of the aircraft. The shaped charge cutting cable 36 is triggered by ignition at the output end of the detonation device 32. The shaped charge cutting cable 36 can be understood as a "powder tube". In this application, shaped charge cutting is an important cutting technology that uses a high-speed metal jet to penetrate and destroy the target. Its principle is to convert the energy generated by the explosion of the explosive into the kinetic energy of the shaped charge liner. The metal jet formed by the liner under the action of the explosive achieves penetration of the target. Compared to conventional mechanical cutting techniques, this special cutting method is high-speed, efficient, easy to operate, and unrestricted by the environment, offering significant advantages. It has crucial applications in pipe cutting, clearing aircraft ejection escape routes, and separating vehicle pylons. After the shaped charge cutting cable 36 cuts, the aircraft's wind resistance causes the hatch 34 to lift. During this process, the rear hinge mechanism 35 rapidly flips it along its trajectory. Simultaneously, the rocket propellant 33 activates, employing solid fuel pulse injection technology to generate a thrust vector of 800-1200N within 0.2 seconds, driving the hatch to flip outwards. Throughout this process, the rear hinge mechanism 35, through its structural design, strictly constrains the hatch's trajectory, ensuring that the hatch does not tilt.Once the canopy 34 enters the free flow field, aerodynamic effects begin to dominate the trajectory: the low-pressure vortex region formed by the washout airflow on the fuselage will apply a normal aerodynamic load, which, together with the rocket booster, will create a combined force, causing the canopy 34 to accelerate backward along the axis of the rear hinge mechanism 35 at a 45° angle. Finally, the ejection function of the aircraft seat will be triggered, effectively preventing the pilot from colliding with the canopy 34 during ejection when the canopy 34 enters the free flow field.

[0024] In summary, the shaped charge cutting cable 36 is triggered by the output ignition of the detonator 32. After the shaped charge cutting cable 36 is cut, the canopy 34 is lifted due to the wind resistance of the aircraft. During this process, the rear hinge mechanism 35 causes it to flip up rapidly along its trajectory. At the same time, the rocket injector 33 is activated and strictly constrains the canopy's trajectory to ensure that the canopy does not tilt. When the canopy 34 enters the free flow field, it forms a combined force with the rocket injector 33, causing the canopy 34 to be accelerated and thrown backward at a 45° tilt angle along the axis of the rear hinge mechanism 35. Finally, the ejection function of the aircraft seat is triggered, effectively avoiding the collision between the pilot and the canopy 34 during the ejection process when the canopy 34 enters the free flow field. This solves the problem that the current method of escaping by opening the canopy or breaking the cockpit after an aircraft failure has a high operational risk.

[0025] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0026] The above embodiments only illustrate several implementation methods of this utility model, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of this utility model patent. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this utility model, and these all fall within the protection scope of this utility model. Therefore, the protection scope of this utility model patent should be determined by the appended claims.

Claims

1. A hatch cover breaking device, characterized in that, Includes a cabin support frame and at least two hatch assemblies that overlap the cabin support frame; The hatch assembly includes a hatch frame fixedly connected to the cabin support frame, a detonation assembly enclosing the top opening of the hatch frame, a hatch assembly overlapping the top of the hatch frame and connected to the detonation assembly, and a rear hinge mechanism disposed at the rear end of the hatch assembly for connecting to the hatch frame. Specifically, by triggering the detonation assembly, the hatch assembly, which is attached to the top of the hatch frame, is axially rotated and separated along the rear hinge mechanism.

2. The hatch cover breaking device according to claim 1, characterized in that, The top of the cabin support frame is also fixedly installed with a cabin cover plate, which is fixedly connected to the cabin cover frame.

3. The hatch cover breaking device according to claim 2, characterized in that, A cabin side cover plate is fixedly installed at the side edge of the cabin support frame.

4. The hatch cover breaking device according to claim 1, characterized in that, The detonation assembly includes a plurality of detonation devices arranged along the inner wall of the hatch frame, and a shaped charge cutting cable disposed at the output end of the detonation device.

5. The hatch cover breaking device according to claim 4, characterized in that, The canopy assembly includes a canopy adapted to the opening at the top of the canopy frame, and a rocket injector fixedly disposed at the bottom of the canopy on the side away from the rear hinge mechanism.

6. The hatch cover breaking device according to claim 5, characterized in that, The energy-concentrating cutting cable is disposed between the hatch cover and the hatch cover frame to close the top opening edge of the hatch cover and the hatch cover frame.

7. An aircraft, characterized in that, Includes the hatch breaking device according to any one of claims 1-6, wherein the hatch breaking device is disposed on the aircraft.

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