Emergency floating device for light airplane

Abstract

The utility model relates to the technical field of airplane emergency floating, in particular to an emergency floating device for a light airplane. The device comprises a shell, a stop cover and a cover, wing sliding rails are fixed to the two ends of the bottom of the shell, and the stop cover is fixed to one end of each wing sliding rail. According to the utility model, the cover can be quickly unfolded, the disassembly and assembly are very convenient, and the configuration can be quickly adjusted according to task requirements; the shell is installed at the root of a light aircraft wing or the two sides of a helicopter body, streamline design is adopted in the appearance, separation of local airflow is reduced, the installation process is simple and convenient, the internal structure of the aircraft does not need to be transformed, the installation time is greatly shortened, and the installation cost is greatly reduced; the inflation speed of the folding air bag can be obviously increased, the folding air bag can reach the needed pressure in a shorter time, and in addition, the situation that the whole system fails due to the fault of a single air cylinder is avoided.

Description

Technical Field

[0001] This utility model relates to the field of emergency flotation technology for aircraft, and in particular to an emergency flotation device for light aircraft. Background Technology

[0002] There are currently three types of emergency flotation devices:

[0003] Domestically produced emergency floatation devices are installed on both sides of the aircraft. These floatation devices are detachable and suitable for temporary missions, requiring installation before heading to sea. Their disadvantages include: their inability to be folded and stored, and their large size, which can affect the aircraft's flight. Furthermore, these devices cannot be permanently mounted on the aircraft, making it difficult to respond promptly to potential maritime accidents.

[0004] The second domestically produced emergency flotation device adopts a conformal design, with the airbag foldable and embedded inside the fuselage. In July 2016, the domestically produced AC313 conducted an in-flight emergency flotation device inflation test, achieving a breakthrough. This emergency airbag device, by modifying the fuselage structure, embeds the flotation device inside the fuselage, making it suitable for specially modified helicopters or aircraft. Its disadvantages are: installation requires modification of the aircraft's internal structure, a cumbersome process; and it cannot be easily disassembled, resulting in limited flexibility.

[0005] The third type of emergency flotation device developed domestically adopts an external design. The airbags are foldable and fixed to the landing gear, while the high-pressure gas cylinders are installed in the fuselage, inflating six airbags through a single gas source. This design has the advantage of easy disassembly and replacement, but its disadvantages are: it is only suitable for helicopters or aircraft equipped with landing gear. In addition, the large externally mounted high-pressure gas cylinders may interfere with the aerodynamic shape of the fuselage, thus affecting flight safety.

[0006] In summary, in view of the technical problems existing in the prior art, we propose an emergency flotation device for light aircraft. Utility Model Content

[0007] The purpose of this invention is to provide an emergency flotation device for light aircraft to solve the problems mentioned in the background art.

[0008] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0009] An emergency flotation device for a light aircraft includes a housing, a stop cover, and a cover. Both ends of the bottom of the housing are fixed with wing rails, which are fixed to the underside of the aircraft wing or the side of the helicopter fuselage. One end of each wing rail is fixed with a stop cover. The top of the housing is fitted with a cover. An unfolding mechanism is fitted between the housing and the cover for opening the cover.

[0010] Preferably, the unfolding mechanism includes a motor, a first gear, a second gear, and a transmission assembly. The motor is fixed at both ends of the bottom inner side of the housing. The first gear is fixed at the output end of the motor. The second gear is meshed with one side of the first gear. The transmission assembly is assembled between the second gear and the cover.

[0011] Preferably, the transmission assembly includes a positioning shaft, a first rocker arm, and a second rocker arm. The positioning shaft is fixed to the inner side of the second gear. One end of the positioning shaft is rotatably connected to the inner side of the housing. The first rocker arm is fixed to one end of the positioning shaft. One end of the first rocker arm is rotatably connected to the bottom of the cover. Both ends of the inner side of the housing are rotatably connected to a second rocker arm that is parallel to the first rocker arm. One end of each second rocker arm is rotatably connected to the cover.

[0012] Preferably, a folding airbag is fitted inside the housing, and an ejection mechanism is fitted between the housing and the folding airbag.

[0013] Preferably, the pop-out mechanism includes a third gear, a fourth gear, a first connecting rod, a second connecting rod, and a moving platform. The output end of the motor passes through the first gear and is fixed to the third gear. The outer side of the third gear is meshed with the fourth gear. One side of both the fourth gear and the third gear is fixed to the first connecting rod. One end of each of the first connecting rods is rotatably connected to a second connecting rod. One end of each of the multiple second connecting rods is rotatably connected to a moving platform, and the folding airbag is fixed on the moving platform.

[0014] Preferably, two gas cylinder fixing straps are fixed to the bottom of the inner side of the housing, and high-pressure gas cylinders are fixed to the inner side of each gas cylinder fixing strap. The output ends of the two high-pressure gas cylinders are connected to the input end of the folding airbag through a solenoid valve.

[0015] It is clear without a doubt that the technical solution described above in this application can solve the technical problem that this application aims to address.

[0016] At the same time, through the above technical solutions, this utility model has at least the following beneficial effects:

[0017] 1. Through the structural design of the unfolding mechanism, this utility model makes it easy to quickly unfold the cover, and the disassembly and assembly are very convenient, making maintenance and component replacement more efficient. At the same time, the configuration can be quickly adjusted according to task requirements.

[0018] 2. This utility model installs the shell at the wing root of a light aircraft or on both sides of the fuselage of a helicopter. The shell has a streamlined design that allows it to fit closely to the surface of the aircraft, reducing the separation of local airflow and thus reducing the impact on the aerodynamic performance of the aircraft. The installation process is simple and does not require modification of the internal structure of the aircraft, which greatly reduces installation time and cost.

[0019] 3. The folding airbag in this utility model is controlled by two small high-pressure gas cylinders. The dual-cylinder system can provide a larger gas reserve. At the same time, the two high-pressure gas cylinders supply gas simultaneously, which can significantly accelerate the inflation speed of the folding airbag, enabling the folding airbag to reach the required pressure in a shorter time. In addition, it avoids the failure of the entire system due to the failure of a single gas cylinder. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram showing the connection between the present invention and the wing;

[0022] Figure 2 This is a schematic diagram of the connection structure between the shell and the stop cover of this utility model;

[0023] Figure 3 This is a schematic diagram of the unfolded structure of the lid of this utility model;

[0024] Figure 4 This is a cross-sectional structural diagram of the shell and lid of this utility model;

[0025] Figure 5 This is a schematic diagram of the connection structure between the folding airbag and the mobile platform of this utility model;

[0026] Figure 6 This is a schematic diagram of the connection structure between the third and fourth gears of this utility model;

[0027] Figure 7 This is a flowchart illustrating the process of this utility model.

[0028] The attached diagram lists the components represented by each number as follows:

[0029] In the diagram: 1. Housing; 2. Stop cover; 3. Cover; 4. Motor; 5. First gear; 6. Second gear; 7. Positioning shaft; 8. First swing arm; 9. Second swing arm; 10. Folding airbag; 11. Third gear; 12. Fourth gear; 13. First connecting rod; 14. Second connecting rod; 15. Moving platform; 16. High-pressure gas cylinder; 17. Solenoid valve. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present utility model and are not intended to limit the present utility model.

[0031] Example 1

[0032] Reference Figure 1-7 An emergency flotation device for a light aircraft includes a housing 1, a stop cover 2, and a cover 3. Both ends of the bottom of the housing 1 are fixed with wing rails, which are fixed to the underside of the aircraft wing or the side of the helicopter fuselage. One end of each wing rail is fixed with a stop cover 2. The top of the housing 1 is fitted with a cover 3. An unfolding mechanism is fitted between the housing 1 and the cover 3 for opening the cover 3.

[0033] The unfolding mechanism includes a motor 4, a first gear 5, a second gear 6, and a transmission assembly. Motors 4 are fixed to both ends of the bottom inner side of the housing 1. The output ends of motors 4 are fixed to the first gear 5. The second gear 6 is meshed with one side of each first gear 5. A transmission assembly is assembled between the second gear 6 and the cover 3. The transmission assembly includes a positioning shaft 7, a first swing arm 8, and a second swing arm 9. A notch corresponding to the position of the second swing arm 9 is provided on one side of the housing 1 to prevent motion interference when the second swing arm 9 rotates. The positioning shaft 7 is fixed to the inner side of the second gear 6. One end of the positioning shaft 7 is rotatably connected to the inner side of the housing 1, and the first swing arm 8 is fixed to one end of the positioning shaft 7. One end of the first swing arm 8 is rotatably connected to the bottom of the cover 3. The second swing arm 9, parallel to the first swing arm 8, is rotatably connected to both ends of the inner side of the housing 1. One end of each second swing arm 9 is meshed with the cover. 3. Rotary connection: When the motor 4 starts, the output end of the motor 4 drives the first gear 5 to rotate, so that the first gear 5 meshes with the second gear 6 to rotate. Because the second gear 6 is fixed to the positioning shaft 7, and the positioning shaft 7 is fixed to the first swing rod 8, the first swing rod 8 and the second swing rod 9 are both rotatably connected to the cover 3. At the same time, the first swing rod 8 and the second swing rod 9 are arranged in parallel, so that when the positioning shaft 7 drives the first swing rod 8 to rotate, it can push the cover 3 to swing open from the top of the housing 1, so as to open the cover 3 and facilitate the subsequent deployment of the folding airbag 10.

[0034] A folding airbag 10 is mounted on the inner side of the housing 1, and an ejection mechanism is mounted between the housing 1 and the folding airbag 10. Two gas cylinder fixing straps are fixed to the bottom of the inner side of the housing 1, and high-pressure gas cylinders 16 are fixed to the inner side of each gas cylinder fixing strap. The output ends of the two high-pressure gas cylinders 16 are connected to the input end of the folding airbag 10 through a solenoid valve 17. Through the arrangement of the high-pressure gas cylinders 16 and the solenoid valve 17, the inflation function of the folding airbag 10 can be realized.

[0035] Example 2

[0036] Further optimizations to Example 1, specifically, such as... Figure 5-6 As shown, the ejection mechanism includes a third gear 11, a fourth gear 12, a first connecting rod 13, a second connecting rod 14, and a moving platform 15. The output end of the motor 4 passes through the first gear 5 and is fixed to the third gear 11. The fourth gear 12 is meshed with the outer side of the third gear 11. The first connecting rod 13 is fixed to one side of both the fourth gear 12 and the third gear 11. One end of each first connecting rod 13 is rotatably connected to a second connecting rod 14. One end of each of the multiple second connecting rods 14 is rotatably connected to a moving platform 15. The folding airbag 10 is fixed to the moving platform. On platform 15, when motor 4 starts, the output end of motor 4 drives the third gear 11 to mesh with the fourth gear 12 and rotate. Since the first link 13 is fixed to the third gear 11 and the fourth gear 12, and the first link 13 is rotatably connected to the second link 14, and the second link 14 is rotatably connected to the moving platform 15, the first link 13 can push the second link 14 when it rotates. Under the limit of the moving platform 15, the second link 14 rotates, thereby raising the moving platform 15 and realizing the deployment of the folding airbag 10.

[0037] This device is primarily suitable for light sport aircraft with a low-wing monoplane configuration and a plano-convex wing shape. For example... Figure 1 As shown, this device is installed below the wing root of the light aircraft. This location, close to the fuselage, helps the device avoid areas with high aerodynamic loads and reduces its interference with the ailerons and flaps. The housing 1 and the stop cover 2 allow the device to fit tightly against the lower surface of the light aircraft, reducing the separation of local airflow. In addition, it needs to be installed symmetrically on both sides of the fuselage to maintain the lateral balance of the fuselage.

[0038] In summary:

[0039] This utility model addresses the following technical problems: Domestic emergency float devices are installed on both sides of the aircraft. These float devices are detachable and suitable for temporary missions, requiring installation before heading to sea. Their disadvantages include: their inability to be folded and their large size can affect flight. Furthermore, these devices cannot be permanently mounted on the aircraft, making it difficult to respond to potential maritime accidents. A second domestic emergency float device employs a conformal design, with foldable airbags embedded internally in the fuselage. In July 2016, the domestically produced AC313 conducted an in-flight emergency float device inflation test, achieving a breakthrough. This emergency airbag device, by modifying the fuselage structure, embeds the float device internally, suitable for specially modified helicopters or aircraft. Its disadvantages include: requiring modification of the aircraft's internal structure for installation, a cumbersome process; and the inability to be easily disassembled, resulting in poor flexibility. A third domestically developed emergency float device adopts an external design, with foldable airbags fixed to the landing gear, while high-pressure gas cylinders are installed in the fuselage belly, inflating six airbags through a single gas source. This design has the advantage of easy disassembly and replacement, but its disadvantage is that it is only suitable for helicopters or aircraft equipped with landing gear. Furthermore, the externally mounted large high-pressure gas cylinder may interfere with the aerodynamic shape of the aircraft, thus affecting flight safety; therefore, the technical solutions described in the above embodiments are adopted. The implementation process of the above technical solutions is as follows:

[0040] All electrical components in this device are existing technologies, and their models are only one of them. Any electrical component that can achieve the purpose of this device can be used. Connect all electrical components in the device to their compatible power supply through wires. In addition, a suitable controller should be selected according to the actual situation to meet the control requirements. The specific connection and control sequence should refer to the working principle below, and the electrical connection between each electrical component should be completed in the order of operation. The detailed connection method is a well-known technology in this field. The following mainly introduces the working principle and process, and will not explain the electrical control.

[0041] When this device starts operating, two switches are needed to control the deployment and inflation of the folding airbag 10. Switch 1 is the preparation switch. After the driver presses the preparation switch in the cab, the control system controls the two motors 4 to drive the cover 3 and the moving platform 15 simultaneously, thus opening the cover 3 and deploying the folding airbag 10. After a 1-second interval, pressing the start switch will open the solenoid valve 17 of the high-pressure gas cylinder 16, and the folding airbag 10 will begin to inflate. The workflow is as follows: Figure 7 As shown.

[0042] The control system described above uses a PLC controller, which is a commonly used device and belongs to existing mature technology. Its electrical connection relationship and specific circuit structure will not be described in detail here.

[0043] With the above-mentioned settings, this application will certainly solve the above-mentioned technical problems, and at the same time achieve the following technical effects:

[0044] 1. Through the structural design of the unfolding mechanism, this utility model makes it easy to quickly unfold the cover 3, and the disassembly and assembly are very convenient, making maintenance and component replacement more efficient. At the same time, the configuration can be quickly adjusted according to task requirements.

[0045] 2. This utility model installs the shell 1 at the wing root of a light aircraft or on both sides of the fuselage of a helicopter. The shell 1 has a streamlined design and can fit closely to the surface of the aircraft, reducing the separation of local airflow and thus reducing the impact on the aerodynamic performance of the aircraft. The installation process is simple and does not require modification of the internal structure of the aircraft, which greatly reduces the installation time and cost.

[0046] 3. The folding airbag 10 in this utility model is controlled by two small high-pressure gas cylinders 16. The dual-cylinder system can provide a larger gas reserve. At the same time, the two high-pressure gas cylinders 16 supply gas simultaneously, which can significantly accelerate the inflation speed of the folding airbag 10, enabling the folding airbag 10 to reach the required pressure in a shorter time. In addition, it avoids the failure of the entire system due to the failure of a single gas cylinder.

[0047] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a connection that allows communication between them; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0048] Obviously, the embodiments described above are only some embodiments of this utility model, not all embodiments. The accompanying drawings show preferred embodiments of this utility model, but do not limit the patent scope of this utility model. This utility model can be implemented in many different forms; rather, the purpose of providing these embodiments is to provide a more thorough and comprehensive understanding of the disclosure of this utility model. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing specific embodiments, or make equivalent substitutions for some of the technical features. Any equivalent structures made using the content of this utility model specification and drawings, directly or indirectly applied to other related technical fields, are similarly within the patent protection scope of this utility model.

Claims

1. An emergency flotation device for light aircraft, characterized in that, The device includes a housing (1), a stop cover (2), and a cover (3). Both ends of the bottom of the housing (1) are fixed with wing rails. The wing rails are fixed to the underside of the aircraft wing or the side of the helicopter fuselage. One end of each wing rail is fixed with a stop cover (2). The top of the housing (1) is fitted with a cover (3). An unfolding mechanism is fitted between the housing (1) and the cover (3). The unfolding mechanism is used to open the cover (3).

2. The emergency flotation device for a light aircraft according to claim 1, characterized in that, The unfolding mechanism includes a motor (4), a first gear (5), a second gear (6), and a transmission assembly. The motor (4) is fixed at both ends of the bottom inner side of the housing (1). The first gear (5) is fixed at the output end of the motor (4). The second gear (6) is meshed with one side of the first gear (5). The transmission assembly is assembled between the second gear (6) and the cover (3).

3. The emergency flotation device for a light aircraft according to claim 2, characterized in that, The transmission assembly includes a positioning shaft (7), a first rocker arm (8), and a second rocker arm (9). The positioning shaft (7) is fixed to the inner side of the second gear (6). One end of the positioning shaft (7) is rotatably connected to the inner side of the housing (1). The first rocker arm (8) is fixed to one end of the positioning shaft (7). One end of the first rocker arm (8) is rotatably connected to the bottom of the cover (3). The two ends of the inner side of the housing (1) are rotatably connected to the second rocker arm (9) which is parallel to the first rocker arm (8). One end of the second rocker arm (9) is rotatably connected to the cover (3).

4. The emergency flotation device for a light aircraft according to claim 2, characterized in that, A folding airbag (10) is fitted inside the housing (1), and an ejection mechanism is fitted between the housing (1) and the folding airbag (10).

5. The emergency flotation device for a light aircraft according to claim 4, characterized in that, The ejection mechanism includes a third gear (11), a fourth gear (12), a first connecting rod (13), a second connecting rod (14), and a moving platform (15). The output end of the motor (4) passes through the first gear (5) and is fixed to the third gear (11). The outer side of the third gear (11) is meshed with the fourth gear (12). The first connecting rod (13) is fixed to one side of both the fourth gear (12) and the third gear (11). One end of the first connecting rod (13) is rotatably connected to the second connecting rod (14). One end of multiple second connecting rods (14) is rotatably connected to a moving platform (15). The folding airbag (10) is fixed on the moving platform (15).

6. The emergency flotation device for a light aircraft according to claim 5, characterized in that, Two gas cylinder fixing straps are fixed to the bottom of the inner side of the housing (1). High-pressure gas cylinders (16) are fixed to the inner side of each gas cylinder fixing strap. The output ends of the two high-pressure gas cylinders (16) are connected to the input end of the folding airbag (10) through a solenoid valve (17).

Images