A folding wing deployment device

Abstract

The application discloses a folding wing unfolding device and relates to the technical field of flight equipment. The device comprises a fixed shaft, a steel ball assembly fixedly connected to the fixed shaft, a lower piston rotating assembly and an upper piston rotating assembly rotatably connected to the side wall of the fixed shaft, the upper piston rotating assembly and the lower piston rotating assembly are in plug-in cooperation and form a working cavity, the steel ball assembly is located in the working cavity, and the bottom end of the lower piston rotating assembly is connected to an ignition driving assembly. The upper piston rotating assembly comprises an upper piston, the upper piston is provided with an upper spiral slide rail, the lower piston rotating assembly comprises a lower piston, the lower piston is provided with a lower spiral slide rail, the rotation directions of the upper spiral slide rail and the lower spiral slide rail are opposite, the upper piston and the lower piston are both sleeved on the fixed shaft, and the upper piston and the lower piston are both movably connected to the steel ball assembly. The folding wing unfolding device of the application has the advantages of reducing impact overload without affecting the storage life and being more practical.

Description

Technical Field

[0001] This invention relates to the field of flight equipment technology, and more specifically to a folding wing deployment device. Background Technology

[0002] The main drive types for folding wing deployment mechanisms include spring-driven, hydraulic-driven, electric motor-driven, shape memory alloy-driven, and pyrotechnic-driven. Small folding-wing UAVs or aircraft possess advantages in maneuverability and long range. However, due to their small size and light weight, these devices cannot accommodate hydraulically or electrically driven folding wing deployment mechanisms. Furthermore, the elastic potential energy of spring-driven folding wing deployment mechanisms decreases during long-term storage, reducing equipment reliability; while shape memory alloy-driven mechanisms are prone to accidental triggering in harsh environments, leading to premature wing deployment. Compared to the above drive methods, pyrotechnic-driven folding wing deployment mechanisms utilize propellant gases to complete the action. They offer strong environmental adaptability, fast response, small size, and a storage life of over ten years, showing great promise in small folding-wing aircraft applications. However, their impact overload can significantly affect flight attitude, leading to mission failure.

[0003] Therefore, it is necessary to provide a folding wing deployment device that reduces the impact overload of the folding wing deployment device without affecting its storage life. Summary of the Invention

[0004] The main objective of this invention is to provide a folding wing deployment device to solve the problems existing in the prior art.

[0005] To solve the above-mentioned technical problems, the present invention adopts the following technical solution: A folding wing deployment device includes a fixed shaft, on which a steel ball assembly is fixedly connected. A lower piston rotating assembly and an upper piston rotating assembly are rotatably connected to the side wall of the fixed shaft. The upper piston rotating assembly and the lower piston rotating assembly are inserted and fitted together to form a working chamber. The steel ball assembly is located in the working chamber. An ignition drive assembly is connected to the bottom end of the lower piston rotating assembly. The upper piston rotating assembly includes an upper piston with an upper helical slide rail. The lower piston rotating assembly includes a lower piston with a lower helical slide rail. The upper and lower helical slide rails rotate in opposite directions. Both the upper and lower pistons are sleeved on the fixed shaft. The upper and lower pistons are movably connected to the steel ball assembly.

[0006] Furthermore, the steel ball assembly includes a bushing, which is fixedly sleeved on the outer wall of the fixed shaft. Two steel ball sleeves are provided on the inner wall of the bushing, and the two steel ball sleeves are arranged at a 180° angle relative to each other along the circumference of the bushing. Both steel ball sleeves are provided with steel balls. The upper steel ball sleeve is connected to the upper spiral slide rail of the upper piston through the steel balls, and the lower steel ball sleeve is connected to the lower spiral slide rail of the lower piston through the steel balls.

[0007] Furthermore, a stepped mounting portion is provided at the bottom end of the fixed shaft, the lower piston rotating assembly is rotatably connected to the upper side of the stepped mounting portion, a sealing ring is provided between the lower piston rotating assembly and the fixed shaft, the upper piston rotating assembly is inserted into the upper end of the lower piston rotating assembly, and the upper piston rotating assembly is rotatably sleeved on the fixed shaft, and a nut is connected to the top end of the fixed shaft, the nut being used to restrict the upper piston rotating assembly from sliding out of the fixed shaft.

[0008] Furthermore, the lower piston rotating assembly also includes a lower rotating shaft, on which a lug groove is provided, and on which a lug is provided, the lower piston is fixedly connected to the lug groove on the lower rotating shaft through the lug, the lower rotating shaft is rotatably connected to the fixed shaft, and the sealing ring is provided between the lower rotating shaft and the fixed shaft.

[0009] Furthermore, the upper piston rotating assembly also includes an upper rotating shaft with a lug groove and an upper piston with a lug. The upper piston is fixedly connected to the lug groove on the upper rotating shaft via the lug. The upper rotating shaft is rotatably connected to the fixed shaft. The lower rotating shaft has a pin and the upper rotating shaft has a slot. The pin is inserted into the slot to connect the upper rotating shaft and the lower rotating shaft.

[0010] Furthermore, both the upper rotating shaft and the lower rotating shaft are provided with shear pin holes, and shear pins are provided in the shear pin holes. The shear pins are provided with narrow diameter portions, which facilitate breakage and stop limiting when the upper rotating shaft and the lower rotating shaft rotate relative to each other.

[0011] Furthermore, the upper rotating shaft is provided with a locking pin hole, and a locking pin is provided in the locking pin hole. The lower rotating shaft is provided with a limiting insertion hole that cooperates with the locking pin. The limiting insertion hole and the locking pin cooperate to limit each other when the upper rotating shaft and the lower rotating shaft rotate to their respective positions.

[0012] Furthermore, the ignition drive assembly includes an ignition control module and an electric detonator. The ignition control module is electrically connected to the electric detonator. Both the ignition control module and the electric detonator are fixedly connected to the bottom end of the lower piston rotation assembly. The electric detonator is used to generate high-pressure gas to directly drive the lower piston rotation assembly to rotate and rise. The lower piston rotation assembly synchronously drives the upper piston rotation assembly to move.

[0013] Furthermore, an end cap is fixedly connected to the lower piston rotating assembly, and the end cap is located between the lower piston rotating assembly and the fixed shaft.

[0014] Furthermore, both the upper piston rotating assembly and the lower piston rotating assembly have folding wings connected to their outer sides via splines.

[0015] Compared with the prior art, the present invention has the following beneficial effects: (1) The folding wing deployment device does not use torsion springs, which can effectively prevent the elastic potential energy of the spring-driven folding wing deployment device from decreasing due to long-term storage, and the storage life can reach more than ten years.

[0016] (2) This device changes the working mode of the traditional pyrotechnic folding wing unfolding device, eliminates the actuator, adopts a sliding piston, and drives the piston to rotate by the continuous pressure of the gunpowder gas. The impact load during the movement does not exceed 10kN. The impact overload of the device can be further reduced by selecting gunpowder with a lower burning rate.

[0017] (3) The device only needs to be supplied with rated current when it is working, the power supply requirement is low, the size is small, the working time is less than 0.3s, the structure is intact after working, and no pollutants such as flying pieces are generated.

[0018] (4) The device has an external spline design on the outer periphery of the rotating shaft, which allows for quick loading and unloading with the wing and can be applied to a variety of aircraft. Attached Figure Description

[0019] Figure 1 This is a three-dimensional schematic diagram of a folding wing deployment device according to the present invention.

[0020] Figure 2 This is a cross-sectional view of a folding wing deployment device according to the present invention.

[0021] Figure 3 This is a schematic diagram of the upper and lower piston structures of a folding wing deployment device according to the present invention.

[0022] Among them, 1-fixed shaft; 2-ball assembly; 21-shaft sleeve; 22-ball sleeve; 23-ball; 3-upper piston; 31-upper spiral slide rail; 4-lower piston; 41-lower spiral slide rail; 5-step mounting part; 6-sealing ring; 7-nut; 8-lower rotating shaft; 9-upper rotating shaft; 10-shearing pin; 11-locking pin; 12-ignition control module; 13-electric detonator; 14-end cover; 15-spline. Detailed Implementation

[0023] The technical solution of the present invention will be further described below with reference to the accompanying drawings and embodiments.

[0024] Example 1

[0025] Combination Figures 1-3 This invention provides a folding wing deployment device, including a fixed shaft 1, on which a steel ball assembly 2 is fixedly connected. A lower piston rotating assembly and an upper piston rotating assembly are rotatably connected to the side wall of the fixed shaft 1. The upper piston rotating assembly and the lower piston rotating assembly are inserted and fitted together to form a working cavity. The steel ball assembly 2 is located in the working cavity. An ignition drive assembly is connected to the bottom end of the lower piston rotating assembly. The upper piston rotating assembly includes an upper piston 3, on which an upper helical slide rail 31 is provided. The lower piston rotating assembly includes a lower piston 4, on which a lower helical slide rail 41 is provided. The rotation directions of the upper helical slide rail 31 and the lower helical slide rail 41 are opposite. The upper piston 3 and the lower piston 4 are both sleeved on the fixed shaft 1. The upper piston 3 and the lower piston 4 are respectively movably connected to the steel ball assembly 2.

[0026] The folding wing deployment device can be connected to a drone or aircraft via a fixed shaft 1.

[0027] The steel ball assembly 2 includes a bushing 21, which is fixedly sleeved on the outer side wall of the fixed shaft 1. Two steel ball sleeves 22 are provided on the inner wall of the bushing 21. The two steel ball sleeves 22 are arranged at a 180° angle relative to each other along the circumference of the bushing 21. Each of the two steel ball sleeves 22 is provided with a steel ball 23. The upper steel ball sleeve 22 is connected to the upper spiral slide rail 31 of the upper piston 3 through the steel ball 23, and the lower steel ball sleeve 22 is connected to the lower spiral slide rail 41 of the lower piston 4 through the steel ball 23.

[0028] The bottom end of the fixed shaft 1 is provided with a stepped mounting part 5. The lower piston rotating assembly is rotatably connected to the upper side of the stepped mounting part 5. A sealing ring 6 is provided between the lower piston rotating assembly and the fixed shaft 1. The upper piston rotating assembly is inserted into the upper end of the lower piston rotating assembly and is rotatably sleeved on the fixed shaft 1. The top end of the fixed shaft 1 is connected with a nut 7, which is used to restrict the upper piston rotating assembly from sliding out of the fixed shaft 1.

[0029] The lower piston rotation assembly also includes a lower rotating shaft 8, on which a lug groove is provided, and on which a lug is provided, the lower piston 4 is fixedly connected to the lug groove on the lower rotating shaft 8 through the lug. The lower rotating shaft 8 is rotatably connected to the fixed shaft 1, and the sealing ring 6 is provided between the lower rotating shaft 8 and the fixed shaft 1.

[0030] The upper piston rotating assembly also includes an upper rotating shaft 9, on which a lug groove is provided. The upper piston 3 is provided with a lug. The upper piston 3 is fixedly connected to the lug groove on the upper rotating shaft 9 through the lug. The upper rotating shaft 9 is rotatably connected to the fixed shaft 1. The lower rotating shaft 8 is provided with a pin. The upper rotating shaft 9 is provided with a slot. The pin is inserted into the slot to connect the upper rotating shaft 9 and the lower rotating shaft 8.

[0031] Both the upper rotating shaft 9 and the lower rotating shaft 8 are provided with shear pin holes, and shear pins 10 are provided in the shear pin holes. The shear pins 10 are provided with narrow diameter portions, which facilitate breakage and stop limiting when the upper rotating shaft 9 and the lower rotating shaft 8 rotate relative to each other.

[0032] The upper rotating shaft 9 is provided with a locking pin hole, and a locking pin 11 is provided in the locking pin hole. The lower rotating shaft 8 is provided with a limiting insertion hole that cooperates with the locking pin 11. The limiting insertion hole and the locking pin 11 cooperate to limit each other when the upper rotating shaft 9 and the lower rotating shaft 8 are rotated into position.

[0033] The ignition drive assembly includes an ignition control module 12 and an electric detonator 13. The ignition control module 12 is electrically connected to the electric detonator 13. Both the ignition control module 12 and the electric detonator 13 are fixedly connected to the bottom end of the lower piston rotation assembly. The electric detonator 13 is used to generate high-pressure gas to directly drive the lower piston rotation assembly to rotate and rise. The lower piston rotation assembly synchronously drives the upper piston rotation assembly to move.

[0034] An end cap 14 is fixedly connected to the lower piston rotating assembly, and the end cap 14 is located between the lower piston rotating assembly and the fixed shaft 1.

[0035] Both the upper piston rotating assembly and the lower piston rotating assembly have folding wings connected to their outer sides via splines 15, enabling quick loading and unloading of the wings.

[0036] The working principle of the device is as follows: This device eliminates the actuator cylinder and uses pneumatic rotation to open the folding wing. The core component is the piston, with helical slide rails rotating in opposite directions around the upper and lower pistons. These slide rails engage with the steel ball assembly. The steel ball assembly is fixedly connected to a fixed shaft, and the piston, under the pressure of the combustion gas, drives the shaft to rotate.

[0037] During operation, the ignition control module 12 receives the ignition command and outputs a constant current, and the charge in the electric detonator 13 begins to burn. The propellant gas rapidly accumulates in the expansion chamber at the bottom of the lower piston 4. When the starting pressure is reached, the shear pin breaks, the limit is released, and the upper and lower pistons drive the upper and lower rotating shafts to start rotating clockwise and counterclockwise, respectively. When both the upper and lower pistons have rotated 90°, the internal sliding pin in the upper rotating shaft 9 pops out, fixing the upper rotating shaft 9 and the lower rotating shaft 8 relative to each other, preventing the folding wings from rebounding after unfolding.

[0038] Specifically, the locking pin includes a pin housing and an inner sliding pin. The inner sliding pin is slidably connected inside the pin housing. A spring is provided between the pin housing and the inner sliding pin. A limiting insertion hole that cooperates with the locking pin is provided on the lower rotating shaft. The spring can push the inner sliding pin into the limiting insertion hole.

[0039] This device addresses the issues of short storage life and high impact overload in folding wing deployment devices for small UAVs or aircraft. Instead of using conventional power sources such as torsion springs or gas-operated cylinders, this device features a helical slide rail around the piston. The piston is driven to rotate and open the folding wing by the pressure of propellant gas. Compared to conventionally powered folding wing deployment devices, this device experiences an impact load of no more than 10kN during operation, has an operating time of less than 0.3s, a storage life of over ten years, maintains structural integrity after actuation, and produces no fly debris or other contaminants. Furthermore, the device exhibits strong environmental adaptability, rapid response, and small size, making it a promising candidate for applications in small folding wing aircraft.

[0040] The above description is merely a preferred embodiment of the present invention and does not constitute any limitation on the technical scope of the present invention. Therefore, any minor modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. A folding wing deployment device, characterized in that, Includes a fixed shaft (1), on which a steel ball assembly (2) is fixedly connected, and a lower piston rotating assembly and an upper piston rotating assembly are rotatably connected to the side wall of the fixed shaft (1). The upper piston rotating assembly and the lower piston rotating assembly are inserted and fitted together to form a working cavity. The steel ball assembly (2) is located in the working cavity. The bottom end of the lower piston rotating assembly is connected to an ignition drive assembly. The upper piston rotating assembly includes an upper piston (3) with an upper spiral slide rail (31) on it. The lower piston rotating assembly includes a lower piston (4) with a lower spiral slide rail (41) on it. The upper spiral slide rail (31) and the lower spiral slide rail (41) rotate in opposite directions. The upper piston (3) and the lower piston (4) are both sleeved on the fixed shaft (1). The upper piston (3) and the lower piston (4) are respectively movably connected to the steel ball assembly (2).

2. The folding wing deployment device as described in claim 1, characterized in that, The ball assembly (2) includes a bushing (21), which is fixedly sleeved on the outer side wall of the fixed shaft (1). Two ball sleeves (22) are provided on the inner wall of the bushing (21). The two ball sleeves (22) are arranged at a 180° angle relative to each other along the circumference of the bushing (21). Each ball sleeve (22) is provided with a ball (23). The upper ball sleeve (22) is connected to the upper spiral slide rail (31) of the upper piston (3) through the ball (23), and the lower ball sleeve (22) is connected to the lower spiral slide rail (41) of the lower piston (4) through the ball (23).

3. The folding wing deployment device as described in claim 2, characterized in that, The bottom end of the fixed shaft (1) is provided with a stepped mounting part (5). The lower piston rotating assembly is rotatably connected to the upper side of the stepped mounting part (5). A sealing ring (6) is provided between the lower piston rotating assembly and the fixed shaft (1). The upper piston rotating assembly is inserted into the upper end of the lower piston rotating assembly and is rotatably sleeved on the fixed shaft (1). The top end of the fixed shaft (1) is connected with a nut (7). The nut (7) is used to restrict the upper piston rotating assembly from sliding out of the fixed shaft (1).

4. A folding wing deployment device as described in claim 3, characterized in that, The lower piston rotating assembly also includes a lower rotating shaft (8), on which a lug groove is provided, and on which a lug is provided, and the lower piston (4) is fixedly connected to the lug groove on the lower rotating shaft (8) through the lug. The lower rotating shaft (8) is rotatably connected to the fixed shaft (1), and the sealing ring (6) is provided between the lower rotating shaft (8) and the fixed shaft (1).

5. A folding wing deployment device as described in claim 4, characterized in that, The upper piston rotating assembly also includes an upper rotating shaft (9), on which a lug groove is provided, and on which an upper piston (3) is provided, and the upper piston (3) is fixedly connected to the lug groove on the upper rotating shaft (9) through the lug. The upper rotating shaft (9) is rotatably connected to the fixed shaft (1), and on which a pin is provided on the lower rotating shaft (8). On which a slot is provided on the upper rotating shaft (9), the pin is inserted into the slot to realize the connection between the upper rotating shaft (9) and the lower rotating shaft (8).

6. A folding wing deployment device as described in claim 5, characterized in that, Both the upper rotating shaft (9) and the lower rotating shaft (8) are provided with shear pin holes, and shear pins (10) are provided in the shear pin holes. The shear pins (10) are provided with narrow diameter portions, which facilitate breakage and stop limiting when the upper rotating shaft (9) and the lower rotating shaft (8) rotate relative to each other.

7. A folding wing deployment device as described in claim 5, characterized in that, The upper rotating shaft (9) is provided with a locking pin hole, and a locking pin (11) is provided in the locking pin hole. The lower rotating shaft (8) is provided with a limiting insertion hole that cooperates with the locking pin (11). The limiting insertion hole and the locking pin (11) cooperate to limit each other when the upper rotating shaft (9) and the lower rotating shaft (8) are rotated into position.

8. A folding wing deployment device as described in claim 1, characterized in that, The ignition drive assembly includes an ignition control module (12) and an electric detonator (13). The ignition control module (12) is electrically connected to the electric detonator (13). Both the ignition control module (12) and the electric detonator (13) are fixedly connected to the bottom end of the lower piston rotation assembly. The electric detonator (13) is used to generate high-pressure gas to directly drive the lower piston rotation assembly to rotate and rise. The lower piston rotation assembly synchronously drives the upper piston rotation assembly to move.

9. A folding wing deployment device as described in claim 1, characterized in that, An end cap (14) is fixedly connected to the lower piston rotating assembly, and the end cap (14) is located between the lower piston rotating assembly and the fixed shaft (1).

10. A folding wing deployment device as described in claim 1, characterized in that, The outer sides of both the upper piston rotating assembly and the lower piston rotating assembly are connected to folding wings via splines (15).

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