Foldable rotor arm structure of manned aircraft

Abstract

The utility model discloses a foldable rotor arm structure of a manned aircraft, and relates to the field of aircrafts. The device comprises four groups of rotor arms, connecting rod assemblies are arranged in the rotor arms, each connecting rod assembly comprises a power sliding block, a double-shaft hinge block, two groups of first connecting rods, an adjustable connecting block and a second connecting rod, the double-shaft hinge block is fixedly connected to one end of the power sliding block, and the two groups of first connecting rods are hinged to the two ends of the double-shaft hinge block; the adjustable connecting block is hinged to the end, away from the double-shaft hinge block, of the first connecting rod and fixedly connected to the second connecting rod, and the two ends of the second connecting rod are hinged to the two sets of rotor arms. According to the device, the connecting rod assemblies are arranged in the four sets of rotor arms for unified control, power is conveyed to the connecting rod assemblies through the independent power pieces, the weight of the aircraft can be reduced, the cost of a power mechanism can be reduced, and the angles of the rotor arms can be finely adjusted through the adjustable connecting blocks.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, specifically to a foldable rotor arm structure for manned aircraft. Background Technology

[0002] With the development of urban air mobility and vertical takeoff and landing (VTOL) aircraft, compact and structurally optimized aircraft designs have become a key research focus. The application of foldable rotor arm structures in manned aircraft is gradually expanding. As technology advances and costs decrease, more and more manned aircraft are adopting this design. Especially in urban air mobility, emergency rescue, and personal flight, foldable rotor arm structures have broad application prospects. These aircraft typically need to take off and land within limited space, while also requiring high portability and flexibility.

[0003] However, the foldable rotor arm structure, due to its folding mechanism, not only results in a complex structure but also requires a power mechanism on each foldable rotor arm. This increases manufacturing and maintenance costs, adds to the aircraft's weight, and further complicates the operating system and operational procedures, reducing ease of use. To address these issues, this invention provides a foldable rotor arm structure for a manned aircraft. Utility Model Content

[0004] To address the shortcomings of existing technologies, this utility model provides a foldable rotor arm structure for manned aircraft. This solves the problems caused by the foldable rotor arm structure, which requires a folding structure, resulting in a complex mechanism and the need to set a power mechanism on each foldable rotor arm. This increases the manufacturing and maintenance costs and the weight of the aircraft. In addition, the additional power mechanisms make the operating system more complex and the operation process more cumbersome, reducing the convenience of actual use.

[0005] To achieve the above objectives, this utility model provides the following technical solution: a foldable rotor arm structure for a manned aircraft, comprising four sets of rotor arms. Each rotor arm contains a connecting rod assembly, which includes a power slider, a dual-axis hinge block, a first connecting rod, an adjustable connecting block, and a second connecting rod. The power slider drives the connecting rod assembly to move. The dual-axis hinge block is fixedly connected to one end of the power slider. Two sets of the first connecting rod are hinged to both ends of the dual-axis hinge block. The adjustable connecting block is hinged to the end of the first connecting rod furthest from the dual-axis hinge block. The adjustable connecting block is fixedly connected to the second connecting rod, whose two ends are hinged to two sets of rotor arms. The adjustable connecting block can change its fixed position on the second connecting rod.

[0006] Preferably, the four sets of rotor arms are provided in two pairs, front and rear, and the bottom end of each rotor arm is fixedly connected to a sliding rod. The two ends of the second connecting rod are respectively hinged to the front and rear sets of rotor arms.

[0007] Preferably, a power component is installed at one end of the power slider. The power component includes a power cylinder and an electronic valve. The power slider is fixedly connected to the power output end of the power cylinder. The electronic valve is installed on the power cylinder and is used to drive the power cylinder.

[0008] Preferably, a support member is provided at the bottom end of the rotor arm and connecting rod assembly, the support member being used to support and fix the rotor arm, connecting rod assembly and power component.

[0009] Preferably, the support includes a rear rotor arm rotating block, and the two sets of rear rotor arms are rotatably connected within the rear rotor arm rotating block.

[0010] Preferably, the support further includes a limiting slide rail, and the slide rod is slidably connected in the limiting slide rail. The limiting slide rail is used to limit the two sets of rear rotor arms.

[0011] Preferably, the support further includes a front rotor arm, and the two sets of front rotor arms are rotatably connected in the front rotor arm. A limiting groove is formed in the front rotor arm, and the slide rod is slidably connected in the limiting groove. The limiting groove is used to limit the two sets of front rotor arms.

[0012] Preferably, the support further includes a support slide rail, and the dual-axis hinge block is slidably connected within the support slide rail, which is used to limit the movement of the dual-axis hinge block.

[0013] This utility model discloses a foldable rotor arm structure for a manned aircraft, which has the following beneficial effects: The foldable rotor arm structure of this manned aircraft, by setting up linkage assemblies in four sets of rotor arms for unified control, and by transmitting power to the linkage assemblies through separate power components, can not only reduce the weight of the aircraft and the cost of the power mechanism, but also fine-tune the rotor arm angle through adjustable connecting blocks. Attached Figure Description

[0014] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0015] Figure 1 This is a schematic diagram of the overall front structure of this utility model;

[0016] Figure 2 This is a schematic diagram of the overall side structure of this utility model;

[0017] Figure 3 This is a schematic diagram of the overall structure of the connecting rod assembly of this utility model;

[0018] Figure 4 This is a schematic diagram showing the detailed structure of the connecting rod assembly of this utility model.

[0019] In the diagram: 1. Rotor arm; 11. Slide bar; 2. Support component; 21. Rear rotor arm rotating block; 22. Limiting slide rail; 23. Front rotor arm; 231. Limiting slide groove; 24. Supporting slide rail; 3. Linkage assembly; 31. Power slider; 32. Dual-axis hinge block; 33. First link; 34. Adjustable connecting block; 35. Second link; 4. Power component; 41. Power cylinder; 42. Electronic valve. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions in the embodiments of this utility model are described clearly and completely. Obviously, the described embodiments are only some embodiments of this utility model, not all embodiments. Based on the embodiments of this utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of this utility model.

[0021] This application provides a foldable rotor arm structure for manned aircraft, which solves the problem that the foldable rotor arm structure is not only complex due to the need for a folding structure, but also requires a power mechanism on each foldable rotor arm, which increases the manufacturing and maintenance costs and the weight of the aircraft. In addition, the more power mechanisms make the operating system more complex and the operation process more cumbersome, reducing the convenience of actual use.

[0022] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0023] This utility model discloses a foldable rotor arm structure for a manned aircraft.

[0024] Example 1

[0025] According to the appendix Figure 1-4 As shown,

[0026] The system includes four sets of rotor arms 1. Each rotor arm 1 contains a connecting rod assembly 3, which includes a power slider 31, a dual-axis hinge block 32, a first connecting rod 33, an adjustable connecting block 34, and a second connecting rod 35. The power slider 31 drives the connecting rod assembly 3 to move. The dual-axis hinge block 32 is fixedly connected to one end of the power slider 31. Two sets of the first connecting rod 33 are hinged to both ends of the dual-axis hinge block 32. The adjustable connecting block 34 is hinged to the end of the first connecting rod 33 away from the dual-axis hinge block 32. The adjustable connecting block 34 is fixedly connected to the second connecting rod 35, whose two ends are hinged to the two sets of rotor arms 1. The adjustable connecting block 34 can change its fixed position on the second connecting rod 35.

[0027] The four sets of rotor arms 1 are provided in two pairs, front and rear. The bottom end of the rotor arm 1 is fixedly connected to the slide rod 11, and the two ends of the second connecting rod 35 are respectively hinged to the front and rear sets of rotor arms 1.

[0028] One end of the power slider 31 is equipped with a power component 4, which includes a power cylinder 41 and an electronic valve 42. The power slider 31 is fixedly connected to the power output end of the power cylinder 41, and the electronic valve 42 is installed on the power cylinder 41. The electronic valve 42 is used to drive the power cylinder 41.

[0029] By setting the linkage assembly 3, the four sets of rotor arms 1 can be driven by the power cylinder 41, the power slider 31 drives the double-axis hinge block 32, the double-axis hinge block 32 drives the first link 33 to rotate, the first link 33 drives the second link 35 to move, and finally the second link 35 drives the rotor arms 1 at both ends to rotate, retract or unfold simultaneously, so that one set of power mechanism can drive folding, and at the same time, the position can be moved by releasing the adjustable connecting block 34, thereby adjusting the angle.

[0030] Example 2

[0031] Based on Example 1, according to Appendix Figure 1-4 As shown,

[0032] The rotor arm 1 and the connecting rod assembly 3 are provided with a support member 2 at their bottom ends. The support member 2 is used to support and fix the rotor arm 1, the connecting rod assembly 3 and the power unit 4.

[0033] The support member 2 includes a rear swing arm rotating block 21, and two sets of rear rotor arms 1 are rotatably connected in the rear swing arm rotating block 21.

[0034] The support component 2 also includes a limiting slide rail 22, in which the slide rod 11 is slidably connected. The limiting slide rail 22 is used to limit the two sets of rear rotor arms 1.

[0035] The support member 2 also includes a front rotor arm 23, and two sets of front rotor arms 1 are rotatably connected in the front rotor arm 23. A limiting groove 231 is provided in the front rotor arm 23, and the slide rod 11 is slidably connected in the limiting groove 231. The limiting groove 231 is used to limit the two sets of front rotor arms 1.

[0036] The support member 2 also includes a support slide rail 24, and the dual-axis hinge block 32 is slidably connected in the support slide rail 24. The support slide rail 24 is used to limit the position of the dual-axis hinge block 32.

[0037] Both the limiting slide groove 231 and the limiting slide rail 22 serve to limit and fix the rotor arm 1.

[0038] The foregoing has shown and described the basic principles, main features, and advantages of this utility model. Those skilled in the art should understand that this utility model is not limited to the above embodiments. The embodiments and descriptions in the specification are merely illustrative of the principles of this utility model. Various changes and modifications can be made to this utility model without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claims. The scope of protection of this utility model is defined by the appended claims and their equivalents.

Claims

1. A foldable rotor arm structure for a manned aircraft, comprising a rotor arm (1), characterized in that, The rotor arm (1) is provided with four sets, and the rotor arm (1) is provided with a connecting rod assembly (3), the connecting rod assembly (3) including: A power slider (31) is used to drive the connecting rod assembly (3) to move; A dual-axis hinge block (32) is fixedly connected to one end of a power slider (31); The first link (33) is provided in two sets, and the two sets of the first link (33) are hinged to both ends of the double-axis hinge block (32); An adjustable connecting block (34) is hinged to the end of the first link (33) away from the biaxial hinge block (32); The second link (35) is fixedly connected to the adjustable connecting block (34). The two ends of the second link (35) are hinged to two sets of rotor arms (1). The adjustable connecting block (34) can change the fixed position on the second link (35).

2. The foldable rotor arm structure of the manned aircraft according to claim 1, characterized in that: The four sets of rotor arms (1) are provided in two pairs, front and rear. The bottom end of each rotor arm (1) is fixedly connected to a slide rod (11). The two ends of the second connecting rod (35) are respectively hinged to the front and rear sets of rotor arms (1).

3. The foldable rotor arm structure of the manned aircraft according to claim 2, characterized in that: A power component (4) is installed at one end of the power slider (31), and the power component (4) includes: The power cylinder (41) has a power slider (31) fixedly connected to the power output end of the power cylinder (41); An electronic air valve (42) is mounted on a power cylinder (41) and is used to drive the power cylinder (41).

4. The foldable rotor arm structure of the manned aircraft according to claim 3, characterized in that: The rotor arm (1) and the connecting rod assembly (3) are provided with a support member (2) at their bottom ends. The support member (2) is used to support and fix the rotor arm (1), the connecting rod assembly (3) and the power unit (4).

5. The foldable rotor arm structure of a manned aircraft according to claim 4, characterized in that: The support member (2) includes a rear rotor rotating block (21), and the two sets of rear rotor arms (1) are rotatably connected in the rear rotor rotating block (21).

6. The foldable rotor arm structure of a manned aircraft according to claim 4, characterized in that: The support member (2) also includes a limiting slide rail (22), and the slide rod (11) is slidably connected in the limiting slide rail (22). The limiting slide rail (22) is used to limit the two sets of rear rotor arms (1).

7. The foldable rotor arm structure of a manned aircraft according to claim 4, characterized in that: The support member (2) also includes a front rotor arm (23), and two sets of front rotor arms (1) are rotatably connected in the front rotor arm (23). A limiting groove (231) is provided in the front rotor arm (23), and the slide rod (11) is slidably connected in the limiting groove (231). The limiting groove (231) is used to limit the two sets of front rotor arms (1).

8. The foldable rotor arm structure of a manned aircraft according to claim 4, characterized in that: The support member (2) also includes a support slide rail (24), and the dual-axis hinge block (32) is slidably connected in the support slide rail (24). The support slide rail (24) is used to limit the position of the dual-axis hinge block (32).

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