High-speed release device for low-altitude aircraft forced landing parachute

Abstract

The invention relates to the technical field of aircraft safety protection, in particular to a high-speed release device for a low-altitude aircraft forced landing parachute, which comprises a top cover, a shell, a launching cabin, a traction rocket, an ejection plate and a gas generator, an accommodating space is formed in the shell; the ejection plate divides the accommodating space into an upper part and a lower part which are not communicated with each other; the launching bin is installed in the shell, and a through hole is formed in the bottom wall of the launching bin. The traction rocket is arranged in the launching cabin; the gas generator is communicated with the lower part of the accommodating space; when the ejection plate moves upwards, the parachute located on the ejection plate is driven to move upwards, the parachute bursts the top cover by means of the acting force of the parachute, and opening of the top cover is completed. After the ejection plate continuously moving upwards reaches the position of the through hole, the lower portion of the containing space communicates with the launching bin, high-pressure gas enters the launching bin, the traction rocket is pushed to rush out of the shell in the axial direction, and the parachute is pulled to be unfolded.

Description

Technical Field

[0001] This application relates to the field of aircraft safety protection technology, and in particular to a high-speed release device for a parachute used for emergency landing of low-altitude aircraft. Background Technology

[0002] With the rapid development of aircraft technology, its applications are becoming increasingly widespread. Accidents during flight can easily cause unpredictable property damage and safety risks to the aircraft itself, ground structures, and personnel. To mitigate these risks, equipping aircraft with emergency landing parachutes to slow their impact velocity and provide safety protection has become one of the mainstream solutions.

[0003] In existing technologies, the vast majority of aircraft emergency landing parachutes employ a passive deployment structure. This structure relies on the air resistance generated by the free fall of the aircraft to pull out the parachute, resulting in a slow deployment response. Furthermore, it requires high-altitude initiation to ensure successful parachute deployment, making it unsuitable for the emergency landing needs of low-altitude aircraft.

[0004] Currently, there are also some active parachute deployment methods. Active parachute deployment technology adopts a towing parachute deployment scheme, in which a towing rocket pushes open the outer shell, and then the towing parachute opens. In this type of technology, there is energy loss during the process of the towing rocket pushing open the parachute, which slows down its launch speed and is not conducive to towing the parachute. In addition, there are technical problems such as complex mechanism design, high failure rate, and inability to be repeatedly opened and closed, which limit its popularization and application. Summary of the Invention

[0005] The purpose of this application is to overcome the above-mentioned defects of the prior art and provide a high-speed release device for a low-altitude aircraft emergency landing parachute, so as to achieve the technical effects of rapid parachute opening, simplified structure and reusability.

[0006] To solve the above-mentioned technical problems, the technical solution of this application provides a high-speed release device for a low-altitude aircraft forced landing parachute, including a top cover 1, an outer shell 2, a launch chamber 3, a traction rocket 4, an ejection plate 5, and a gas generator 6. The outer shell 2 forms an accommodating space; The ejection plate 5 is located within the receiving space and divides the receiving space into an upper part and a lower part that are not connected to each other; the top of the ejection plate 5 is used to place the parachute 7; The top cover 1 is connected to the top of the outer shell 2, together forming a shell; The launch chamber 3 is installed inside the outer shell 2, and its bottom wall is provided with a through hole 8 for communicating with the lower part of the accommodating space; The traction rocket 4 is placed inside the launch chamber 3 and connected to the parachute 7 via a traction rope; The gas generator 6 is connected to the lower part of the accommodating space and is used to generate high-pressure gas when triggered, pushing the catapult plate 5 to move upward along the axis; When the ejection plate 5 moves upward, it drives the parachute 7 located on it to move upward. The parachute 7 uses its own force to break through the top cover 1, completing the opening of the top cover 1. After the ejection plate 5 continues to move upward and reaches the position of the through hole 8, the lower part of the accommodating space is connected to the launch chamber 3. High-pressure gas enters the launch chamber 3, pushing the traction rocket 4 to rush out of the outer shell 2 along the axis, and pulling the parachute 7 to unfold.

[0007] As an improvement to the above-mentioned device, the outer casing 2 has an opening at the top and includes a side wall and a bottom wall, the bottom wall having a protrusion 21 extending inward; a first gap is formed between the side wall of the protrusion 21 and the side wall of the outer casing 2; the launch chamber 3 includes a side wall and a bottom wall, the bottom wall of the launch chamber 3 is fixedly connected to the top of the protrusion 21, and a second gap is formed between the side wall of the launch chamber 3 and the side wall of the outer casing 2; the accommodating space is composed of the first gap and the second gap.

[0008] As an improvement to the above-mentioned device, the outer shell 2, the protrusion 21 and the launch chamber 3 are all cylindrical, and the first gap and the second gap are both annular gaps.

[0009] As an improvement to the above-mentioned device, the top cover 1 is provided with a weak part 11, which is a groove structure and has a thickness less than the thickness of other parts of the top cover 1, so that the parachute 7 can break through and open it.

[0010] As an improvement to the above-mentioned device, the device further includes a sealing ring 9; wherein the side wall of the ejection plate 5 is sealed and fitted with the side wall of the accommodating space by the sealing ring 9; the bottom side wall of the traction rocket 4 is sealed and fitted with the side wall of the launch chamber 3 by the sealing ring 9.

[0011] As an improvement to the above-mentioned device, the parachute 7 is placed in the upper part of the receiving space. In the initial position, the axial distance between the top of the parachute 7 and the top cover 1 is less than the axial distance between the ejection plate 5 and the through hole 8, so as to ensure that after the parachute 7 breaks through the top cover 1, the ejection plate 5 communicates with the through hole 8.

[0012] As an improvement to the above-mentioned device, the device also includes a limiting part located inside the outer shell 2, which is used to limit the upward movement of the ejector plate 5 and prevent the ejector plate 5 from falling out of the outer shell 2.

[0013] As an improvement to the above-mentioned device, the limiting part is in the shape of a notch and is disposed on the outside of the side wall of the launch chamber 3.

[0014] As an improvement to the aforementioned device, the device further includes: a detection and control component; wherein the detection and control component includes an attitude sensor for detecting the aircraft's attitude, a barometer for monitoring the aircraft's flight altitude, and a controller; wherein the controller is electrically connected to the gas generator 6, the attitude sensor, and the barometer respectively; the controller has a manual control mode and an automatic control mode; wherein, in the manual control mode, the controller triggers the gas generator 6 to generate gas based on manual commands; in the automatic control mode, the controller collects monitoring data from the attitude sensor and the barometer, and automatically triggers the gas generator 6 to generate gas when it determines that the aircraft's tilt angle exceeds a preset first safety threshold and the aircraft's descent speed exceeds a preset second safety threshold.

[0015] As an improvement to the above-mentioned device, the device also includes a lower cover plate 10, which is connected to the bottom outer side of the housing 2 and forms an installation space between the lower cover plate 10 and the bottom outer side of the housing 2.

[0016] The advantages of this application are: 1. Improved parachute deployment process: When the parachute is deployed, the folded parachute 7 is pushed upward by the ejection plate 5. The parachute 7 opens the pre-set weak part 11 of the top cover 1 through its own force, which replaces the traditional method of the towing rocket 4 opening the top cover 1. This ensures that the parachute 7 is smoothly discharged from the cabin and avoids the risk of jamming.

[0017] 2. The parachute opening process is faster: After the parachute 7 is completely discharged from the cabin, the traction rocket 4 carries the parachute 7 out in the air and opens it as it is pulled upwards. This causes the parachute 7 to rapidly increase its frontal area during the aircraft's descent, which helps the parachute 7 to open faster. Attached Figure Description

[0018] Figure 1 This is a first schematic diagram showing the initial state of the release device in an embodiment of this application; Figure 2 This is a second schematic diagram showing the initial state of the release device in an embodiment of this application; Figure 3 This is a third schematic diagram showing the initial state of the release device in an embodiment of this application; Figure 4 This is a first schematic diagram of the parachute 7 breaking through the top cover 1 in an embodiment of this application; Figure 5 This is a second schematic diagram of the parachute 7 breaking through the top cover 1 in an embodiment of this application; Figure 6 This is a first schematic diagram of the traction rocket 4 after it has launched in the embodiment of this application; Figure 7 This is a second schematic diagram of the traction rocket 4 after it has launched in an embodiment of this application; Figure 8 This is a partial structural diagram of the top cover 1 in an embodiment of this application. Detailed Implementation

[0019] The technical solutions provided in this application are further illustrated below with reference to the embodiments.

[0020] This application proposes a high-speed release device for a low-altitude aircraft emergency landing parachute. The parachute is rapidly deployed through a distributed air duct structure. With a simplified structure, the parachute can be quickly ejected and deployed by means of a fast-response gas-driven mechanism, effectively shortening the parachute deployment time and providing favorable conditions for low-altitude parachute deployment of aircraft.

[0021] As attached Figure 1-8 As shown, the release device includes a top cover 1, an outer shell 2, a launch chamber 3, a traction rocket 4, a launch plate 5, a gas generator 6, and a sealing ring 9. The connections and structural features of each component are as follows: Outer shell 2: Open at the top, with side walls and bottom walls, and a protrusion 21 extending inward at the bottom. The protrusion 21 and the outer shell 2 are preferably integrally formed, both being cylindrical; the protrusion 21 has at least a top wall and a side wall, the bottom of its side wall is fixedly connected to the bottom of the outer shell 2, and a first gap is formed between the side wall of the protrusion 21 and the side wall of the outer shell 2.

[0022] Top cover 1: Covers the top of the outer shell 2 and is detachably fixed to the outer shell 2 by bolts, together forming a closed shell. The top cover 1 has a weak part 11. In this embodiment, the weak part 11 is a groove structure. The thickness of the top cover 1 at the weak part 11 is less than the thickness at other positions, which makes it easier for the parachute 7 to break through and open.

[0023] Launch chamber 3: Located inside the shell, it is cylindrical with an open top and side walls and a bottom wall. The bottom wall of launch chamber 3 is fixedly connected to the top wall of protrusion 21 by welding or bolts, and a second gap is formed between its side wall and the side wall of the outer shell 2. The bottom wall of launch chamber 3 is provided with a cross-shaped through hole 8, the axis of which is perpendicular to the side wall of launch chamber 3, so that launch chamber 3 communicates with the interior of the shell through the through hole 8.

[0024] Traction rocket 4: It is placed inside the launch chamber 3, and its bottom side wall is sealed to the side wall of the launch chamber 3 by a sealing ring 9 to ensure pressure stability during gas propulsion.

[0025] The accommodation space is formed by the first gap between the protrusion 21 and the outer shell 2 and the second gap between the launch chamber 3 and the outer shell 2, and is used to accommodate the parachute 7 and the ejection plate 5.

[0026] Ejector plate 5: Placed within the receiving space, dividing the receiving space into an upper and lower part that are not connected to each other. The ejector plate 5 is sealed to the side wall of the receiving space by a sealing ring 9 to ensure efficient air pressure transmission.

[0027] Gas generator 6: Installed on the outer casing 2, located in the lower part of the containment space, it is used to generate high-pressure gas. The high-pressure gas can push the catapult plate 5 upward. When the catapult plate 5 slides past the through hole 8, the launch chamber 3 is connected to the lower part of the containment space through the through hole 8, and the gas then pushes the traction rocket 4 upward.

[0028] Parachute 7: Located in the upper part of the containment space and above the ejection plate 5, it is connected to the towing rocket 4 via a towing rope. The axial distance between the top of the parachute 7 and the top cover 1 is less than the axial distance from the initial position of the ejection plate 5 to the through hole 8, ensuring that when the ejection plate 5 pushes the parachute 7 upward, it can first break through the top cover 1, and then the lower part of the containment space will connect with the launch chamber 3.

[0029] Limiting part: It is located on the outside of the side wall of the launch chamber 3 and has a notch structure. It is used to limit the stroke length of the ejection plate 5 and ensure that the ejection plate 5 is always inside the shell to prevent it from falling out.

[0030] The detection and control components include an attitude sensor for detecting the aircraft's attitude, a barometer for monitoring the aircraft's altitude, and a controller. The controller is electrically connected to the attitude sensor, barometer, and gas generator 6, and has manual and automatic control modes. In manual mode, the gas generator 6 is controlled by manual commands to produce gas. In automatic mode, the controller collects data on the aircraft's tilt angle (the angle between the aircraft's plane and the ground plane) detected by the attitude sensor and the descent speed data detected by the barometer. When the tilt angle exceeds a preset first safety threshold and the descent speed exceeds a preset second safety threshold, the gas generator 6 is automatically triggered to produce gas.

[0031] The lower cover plate 10 is detachably and fixedly connected to the bottom outer side of the outer casing 2 by bolts. The gap between the two forms an installation space for assembling control components such as circuit boards.

[0032] The working process of the release device in this embodiment is as follows: Initial state ( Figure 1-3 ): Gas generator 6 is not activated, ejection plate 5 is located near the bottom of the containment space, parachute 7 is folded and placed above ejection plate 5, and top cover 1 remains intact and closed.

[0033] Top cover 1 opening stage ( Figure 4-5 When the gas generator 6 is triggered, it generates high-pressure gas, which pushes the ejection plate 5 upward, thereby causing the parachute 7 to squeeze the top cover 1. Due to the structural design of the weak part 11, the parachute 7 can successfully break through the top cover 1; after the top cover 1 breaks, the ejection plate 5 continues to move upward until it is blocked by the limiting part. At this time, the lower part of the accommodating space is connected to the launch chamber 3 through the through hole 8.

[0034] Parachute deployment phase 7 ( Figure 6-7 High-pressure gas enters the launch chamber 3 through the through-hole 8, propelling the traction rocket 4 upwards out of the casing. The traction rocket 4 pulls the top of the parachute 7 via a traction rope, pulling the parachute 7 to a high altitude and deploying it, thus achieving deceleration and forced landing of the aircraft.

[0035] This application utilizes the linkage structure of the ejection plate 5, launch chamber 3, and top cover 1 to ensure that the parachute 7 breaks through the top cover 1 before being pulled out and deployed by the traction rocket 4, thereby reducing the energy loss of the traction rocket 4 and improving the parachute deployment response speed.

[0036] This release device is reusable. When reusing it, simply fold the parachute 7 and reload it into the containment space, and replenish the gas generator 6 with the gas-generating medium to complete the reassembly.

[0037] The aircraft described in this application includes, but is not limited to, small flying devices such as drones, and its release device achieves advantageous effects through the following technological improvements: 1. The method of opening the top cover 1 by parachute 7 is adopted to avoid the speed loss caused by the traditional traction rocket 4 opening the top cover 1, ensuring that there is no upward obstruction when the traction rocket 4 starts, and improving the traction speed.

[0038] 2. In conventional techniques, speed is lost when the tractor rocket 4 punctures the top cover 1. On the other hand, simply pulling the parachute 7 upward by the tractor rocket 4 also results in speed loss. In this application, the parachute 7 is moved upward by the ejection plate 5 and punctures the top cover 1. After the top cover 1 breaks, the tractor rocket 4 rushes upward directly, maintaining a higher speed and reducing energy loss.

[0039] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to the embodiments, those skilled in the art should understand that modifications or equivalent substitutions to the technical solutions of the present invention do not depart from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A high-speed release device for a parachute used in a low-altitude aircraft forced landing, characterized in that, It includes a top cover (1), outer shell (2), launch compartment (3), traction rocket (4), ejection plate (5) and gas generator (6); The outer shell (2) forms an internal accommodating space; The ejection plate (5) is located within the receiving space and divides the receiving space into an upper part and a lower part that are not connected to each other; the top of the ejection plate (5) is used to place the parachute (7). The top cover (1) is connected to the top of the outer shell (2) to form a shell together; The launch chamber (3) is installed inside the outer shell (2), and its bottom wall is provided with a through hole (8) for communicating with the lower part of the accommodating space; The traction rocket (4) is placed inside the launch chamber (3) and connected to the parachute (7) by a traction rope; The gas generator (6) is connected to the lower part of the accommodating space and is used to generate high-pressure gas when triggered, pushing the catapult plate (5) to move upward along the axis; When the ejection plate (5) moves upward, it drives the parachute (7) located on it to move upward. The parachute (7) breaks through the top cover (1) with its own force, and the top cover (1) is opened. After the ejection plate (5) continues to move upward and reaches the position of the through hole (8), the lower part of the accommodating space is connected to the launch chamber (3). High-pressure gas enters the launch chamber (3) and pushes the traction rocket (4) to rush out of the outer shell (2) along the axis, and pulls the parachute (7) to unfold.

2. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 1, characterized in that, The outer casing (2) has an opening at the top and includes a side wall and a bottom wall, the bottom wall having an inwardly extending protrusion (21). A first gap is formed between the sidewall of the protrusion (21) and the sidewall of the outer shell (2); The launch chamber (3) includes a side wall and a bottom wall. The bottom wall of the launch chamber (3) is fixedly connected to the top of the protrusion (21). A second gap is formed between the side wall of the launch chamber (3) and the side wall of the outer shell (2). The accommodating space is composed of a first gap and a second gap.

3. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 2, characterized in that, The outer shell (2), the protrusion (21) and the launch chamber (3) are all cylindrical, and the first gap and the second gap are both annular gaps.

4. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 1, characterized in that, The top cover (1) has a weak part (11), which is a groove structure with a thickness less than the thickness of other parts of the top cover (1) so that the parachute (7) can break through and open.

5. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 1, characterized in that, It also includes a sealing ring (9); wherein the side wall of the ejection plate (5) is sealed to the side wall of the accommodating space by the sealing ring (9); the bottom side wall of the traction rocket (4) is sealed to the side wall of the launch chamber (3) by the sealing ring (9).

6. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 1, characterized in that, The parachute (7) is placed in the upper part of the accommodating space. In the initial position, the axial distance between the top of the parachute (7) and the top cover (1) is less than the axial distance between the ejection plate (5) and the through hole (8) to ensure that the ejection plate (5) communicates with the through hole (8) after the parachute (7) breaks through the top cover (1).

7. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 1, characterized in that, It also includes a limiting part located inside the outer shell (2) to limit the upward movement of the ejector plate (5) and prevent the ejector plate (5) from falling out of the outer shell (2).

8. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 7, characterized in that, The limiting part is in the shape of a notch and is located on the outside of the side wall of the launch chamber (3).

9. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 1, characterized in that, Also includes: A detection and control component; wherein the detection and control component includes an attitude sensor for detecting the aircraft's attitude, a barometer for monitoring the aircraft's flight altitude, and a controller; wherein the controller is electrically connected to a gas generator (6), the attitude sensor, and the barometer; the controller has a manual control mode and an automatic control mode; wherein, In the manual control mode, the controller triggers the gas generator (6) to generate gas based on manual commands; In the automatic control mode, the controller collects monitoring data from the attitude sensor and barometer. When it is determined that the tilt angle of the aircraft exceeds the preset first safety threshold and the descent speed of the aircraft exceeds the preset second safety threshold, the gas generator (6) is automatically triggered to generate gas.

10. The high-speed release device for a low-altitude aircraft forced landing parachute according to claim 1, characterized in that, It also includes a lower cover plate (10), which is connected to the bottom outer side of the housing (2) and forms an installation space between the lower cover plate (10) and the bottom outer side of the housing (2).

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