Self-assembly and self-unlocking kinematic mechanism and method based on precision manufacturing

Abstract

The application relates to a self-assembly and self-unlocking movement mechanism and method based on precision manufacturing, which takes wing rib blocks, connecting rods and self-unlocking structures as main components and belongs to the technical field of aircraft structures. The application comprises fixed wing rib blocks (1), movable wing rib blocks and connecting rods; under the support of precision manufacturing technology, the connecting rod mechanism is combined with the weak connection relationship of the structure in a skillful manner, so that the connecting rod mechanism is in the hyperstatic state, and integrated manufacturing and self-assembly become possible; the self-unlocking structure is designed between the mechanism structures, the positioning precision between the movable wing rib blocks, the rotating shafts and the connecting rods is improved, and zero position calibration is facilitated; after unlocking, the self-unlocking structure plays the role of a bushing, can eliminate the gap and is beneficial to the movement of the mechanism. The application can realize the self-assembly and self-unlocking functions of the finger joint wing trailing edge movement mechanism, improves the production efficiency, reduces the structure weight, improves the assembly precision of the movement mechanism and is beneficial to zero position calibration.

Description

Technical Field

[0001] This invention relates to a self-assembly and self-unlocking motion mechanism and method based on precision manufacturing, with wing ribs, connecting rods, and self-unlocking structures as the main components, belonging to the field of aircraft structure technology. Background Technology

[0002] In aircraft structural design, the rational design and use of motion mechanisms enable aircraft to adapt to different mission requirements and meet various performance indicators. Currently, motion mechanism design is integrated into the structural design of components such as leading-edge flaps, control surfaces, landing gear, and speed brakes, significantly improving flight performance and stability, as well as flight efficiency and safety. In recent years, research and discussion on deformable structures, especially deformable wings, have been very active in the field of aircraft design. Designing wing components such as the leading edge, trailing edge, and winglets as deformable structures can greatly improve aerodynamic efficiency and fuel economy.

[0003] Currently, using motion mechanisms to achieve structural deformation is a relatively mature and reliable design approach for deformable structures. For variable-camber airfoil designs, motion mechanism-based designs not only have clear force transmission paths but also well-defined motion paths, facilitating structural design and optimization. Therefore, this approach boasts high feasibility and reliability. However, motion mechanisms also introduce problems such as increased component numbers, complex assembly, and increased overall weight. Precision manufacturing technology allows for integrated molding and automated assembly of the deformable motion mechanism, effectively improving assembly efficiency and reducing overall structural weight, thus largely resolving the new problems brought about by the introduction of motion mechanisms. Summary of the Invention

[0004] The purpose of this invention is to address the structural problems of existing knuckle-shaped wing trailing edge motion mechanisms, including large structural weight, numerous assembly steps, and cumbersome assembly processes. This invention proposes a self-assembly and self-unlocking motion mechanism design based on precision manufacturing, which solves the aforementioned problems and has significant application value in the field of motion mechanism design.

[0005] The idea behind this invention is to design a set of self-unlocking multi-link motion mechanisms based on precision manufacturing. This allows for the integrated molding and self-assembly of the motion mechanism. After molding, the motion mechanism is in a locked state and can be unlocked under driving load. The trailing edge of the wing can then deform and move.

[0006] The objective of this invention is achieved through the following technical solution:

[0007] A self-assembly and self-unlocking motion mechanism based on precision manufacturing includes a fixed wing rib 1, a movable wing rib, and connecting rods. The movable wing rib includes a first movable wing rib 2, a second movable wing rib 3, and a third movable wing rib 4. The connecting rod includes a first connecting rod 5 and a second connecting rod 6. The fixed wing rib 1 is connected to the rear wall of the wing. The first movable wing rib 2 is connected to the fixed wing rib 1. The second movable wing rib 3 is connected to the first movable wing 2. The third movable wing rib 4 is connected to the second movable wing 3. The second movable wing rib 3 is connected to the fixed wing rib 1 via the first connecting rod 5. The third movable wing 4 is connected to the first movable wing 2 via the second connecting rod 6. The connection points between the connecting rods and the fixed wing rib 1 and the movable wing rib are self-unlocking structures.

[0008] Furthermore, the self-unlocking structure includes a radial self-unlocking structure 8a and an axial self-unlocking structure 8b.

[0009] Furthermore, the self-unlocking structure is precisely manufactured laterally based on the integrated structural design, enabling self-assembly.

[0010] Furthermore, the self-unlocking motion structure establishes a weak connection radially in the shaft gap through a radial self-unlocking structure;

[0011] Furthermore, the self-unlocking motion structure establishes a weak connection along the axial direction in the lateral gap between the movable wing rib block and the connecting rod through the axial self-unlocking structure, thereby making the connecting rod mechanism a statically indeterminate structure in the initial state.

[0012] Furthermore, the radial self-unlocking structure 8a is composed of frustum-shaped connecting rods, distributed on the circumferential surface of the pivot hole, arranged between the pivot holes of adjacent movable wing ribs, in two rows, with no more than 12 in each row. Alternatively, it can be arranged between the pivot holes of the connecting rod and the fixed wing rib 1, in a single row, with 4 fixed in each row.

[0013] Furthermore, the frustum-shaped connecting rod has a height of no more than 1 mm, a minimum cross-sectional area radius of no more than 2 mm, and a maximum cross-sectional area radius of no more than 5 mm.

[0014] Furthermore, the axial self-unlocking structure 8b is arranged in the lateral gap between the rib block and the connecting rod, and is composed of a frustum-shaped connecting rod. There are four of them in a row on the outer circumference of the rotating shaft, with a fixed height of 1.5mm. Other parameters are the same as those of the radial self-unlocking structure.

[0015] The self-assembly and self-unlocking motion mechanism based on precision manufacturing allows for deformable motion of the wing trailing edge. This is achieved through powder-layout hot-melt technology, precision manufacturing along the transverse direction, and the integrated motion mechanism's self-unlocking structure, in a locked state and at zero position, undergoes heat treatment to remove excess struts on one side. It can then be installed onto the wing box section's rear wall. After installing the drive mechanism and motor, the single-set variable-camber wing trailing edge structure is assembled. Under 60% operating load (i.e., an input torque of not less than 2.04 Nm), the near-axis frustum-shaped connecting rod of the self-unlocking structure undergoes shear failure under the torque at point 7 on the drive shaft. The entire mechanism then releases its weak connection and enters the working motion state.

[0016] Beneficial effects of the invention

[0017] 1. With the support of precision manufacturing technology, the linkage mechanism and the weak connection relationship of the structure are cleverly combined, so that the linkage mechanism is in a state of superstatic indeterminateness, making integrated manufacturing and self-assembly possible, solving the problem of complex assembly of the original mechanism, and greatly improving production efficiency.

[0018] 2. Compared with the original structure, under the premise of unchanged strength and stiffness, the pin and rib block are combined, and the bushing and pin are eliminated, reducing a total of 12 parts and reducing weight by 21.92kg.

[0019] 3. By designing a self-unlocking structure between the mechanism components, the positioning accuracy between the movable wing rib block and the rotating shaft, and between the movable wing rib block and the connecting rod, is improved, and zero-position calibration is also facilitated.

[0020] 4. After unlocking, the self-unlocking structure acts as a bushing, which can eliminate gaps and facilitate the movement of the mechanism.

[0021] In summary, this invention enables the self-assembly and self-unlocking of the knuckle wing trailing edge motion mechanism, improving production efficiency, reducing structural weight, enhancing the assembly accuracy of the motion mechanism, and facilitating zero-position calibration. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of the present invention.

[0023] Wherein, 1 is the fixed wing rib, 2 is the first movable wing rib, 3 is the second movable wing rib, 4 is the third movable wing rib, 5 is the first connecting rod, 6 is the second connecting rod, and 7 is the drive shaft.

[0024] Figure 2 This is a schematic diagram of the self-unlocking structure of the present invention.

[0025] Among them, 8a is a radial self-unlocking structure and 8b is an axial self-unlocking structure. Detailed Implementation

[0026] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0027] like Figure 1 , Figure 2 As shown, a self-assembly and self-unlocking motion mechanism based on precision manufacturing includes a fixed wing rib 1, a movable wing rib, and connecting rods. The movable wing rib includes a first movable wing rib 2, a second movable wing rib 3, and a third movable wing rib 4. The connecting rod includes a first connecting rod 5 and a second connecting rod 6. The fixed wing rib 1 is connected to the rear wall of the wing. The first movable wing rib 2 is connected to the fixed wing rib 1. The second movable wing rib 3 is connected to the first movable wing rib 2. The third movable wing rib 4 is connected to the second movable wing rib 3. The second movable wing rib 3 is connected to the fixed wing rib 1 via the first connecting rod 5. The third movable wing rib 4 is connected to the first movable wing 2 via the second connecting rod 6. The connection points between the connecting rods and the fixed wing rib 1 and the movable wing ribs are self-unlocking structures. The self-unlocking structure includes a radial self-unlocking structure 8a and an axial self-unlocking structure 8b.

[0028] The self-unlocking structure is precision manufactured laterally based on an integrated structural design, enabling self-assembly. A radial self-unlocking structure establishes a weak connection in the radial direction of the shaft gap; an axial self-unlocking structure establishes a weak connection in the axial direction of the lateral gap between the movable wing rib and the connecting rod, thus making the linkage mechanism a statically indeterminate structure in its initial state.

[0029] The radial self-unlocking structure 8a is composed of frustum-shaped connecting rods, distributed on the circumferential surface of the pivot hole, arranged between the pivot holes of adjacent movable wing ribs in two rows, with no more than 12 rods in each row. Alternatively, it can be arranged between the pivot holes of the connecting rod and the fixed wing rib 1 in a single row, with 4 rods fixed in each row. The frustum-shaped connecting rod has a height not exceeding 1 mm, a minimum cross-sectional radius not exceeding 2 mm, and a maximum cross-sectional radius not exceeding 5 mm.

[0030] The axial self-unlocking structure 8b is arranged in the lateral gap between the rib block and the connecting rod. It is composed of a frustum-shaped connecting rod, with four rods arranged in a row on the outer circumference of the rotating shaft. The height is fixed at 1.5mm. Other parameters are the same as those of the radial self-unlocking structure.

[0031] The self-assembly and self-unlocking motion mechanism based on precision manufacturing allows for deformable motion of the wing trailing edge. This is achieved through powder-layout hot-melt technology, precision manufacturing along the transverse direction, and the integrated motion mechanism's self-unlocking structure, in a locked state and at zero position, undergoes heat treatment to remove excess struts on one side. It can then be installed onto the wing box section's rear wall. After installing the drive mechanism and motor, the single-set variable-camber wing trailing edge structure is assembled. Under 60% operating load (i.e., an input torque of not less than 2.04 Nm), the near-axis frustum-shaped connecting rod of the self-unlocking structure undergoes shear failure under the torque at point 7 on the drive shaft. The entire mechanism then releases its weak connection and enters the working motion state.

Claims

1. A self-assembly and self-unlocking motion mechanism based on precision manufacturing, characterized in that, It includes a fixed wing rib (1), a movable wing rib, and a connecting rod; the movable wing rib includes a first movable wing rib (2), a second movable wing rib (3), and a third movable wing rib (4); the connecting rod includes a first connecting rod (5) and a second connecting rod (6); the fixed wing rib (1) is connected to the rear wall of the wing; the first movable wing rib (2) is connected to the fixed wing rib (1); the second movable wing rib (3) is connected to the first movable wing rib (2); the third movable wing rib (4) is connected to the second movable wing rib (3); the second movable wing rib (3) is connected to the fixed wing rib (1) via the first connecting rod (5); the third movable wing rib (4) is connected to the first movable wing rib (2) via the second connecting rod (6); the connection between the connecting rod and the fixed wing rib (1) and the movable wing rib is a self-unlocking structure; The self-unlocking structure includes a radial self-unlocking structure (8a) and an axial self-unlocking structure (8b). Based on the integrated structural design, the self-unlocking structure is precision manufactured in the transverse direction to achieve self-assembly. The self-unlocking motion structure establishes a weak connection in the radial direction in the shaft gap through the radial self-unlocking structure. The self-unlocking motion structure establishes a weak connection in the axial direction in the lateral gap between the movable wing rib and the connecting rod through the axial self-unlocking structure, thereby making the connecting rod mechanism a statically indeterminate structure in the initial state. The radial self-unlocking structure (8a) is composed of a frustum-shaped connecting rod, distributed on the circumferential surface of the rotating shaft hole, arranged between the shaft holes of adjacent movable wing ribs, in two rows, with no more than 12 in each row, or arranged between the shaft holes of the connecting rod and the fixed wing rib (1), in a single row, with 4 fixed in each row. After unlocking, the self-unlocking structure acts as a bushing.

2. The self-assembly and self-unlocking motion mechanism based on precision manufacturing according to claim 1, characterized in that, The frustum-shaped connecting rod has a height of no more than 1 mm, a minimum cross-sectional radius of no more than 2 mm, and a maximum cross-sectional radius of no more than 5 mm.

3. The self-assembly and self-unlocking motion mechanism based on precision manufacturing according to claim 1, characterized in that, The axial self-unlocking structure (8b) is arranged in the lateral gap between the rib block and the connecting rod. It is composed of a frustum-shaped connecting rod, with four rods arranged in a row on the outer circumference of the rotating shaft. The height is fixed at 1.5mm. Other parameters are the same as those of the radial self-unlocking structure.

4. The self-assembly and self-unlocking method for a self-assembly and self-unlocking motion mechanism based on precision manufacturing according to claim 1, characterized in that, The deformable motion of the trailing edge of the wing is based on powder-spreading hot-melt technology. It is precisely manufactured in the transverse direction. The self-unlocking structure of the integrated motion mechanism is in a locked state and is located at zero position. After heat treatment, the excess struts on one side are removed, and it can be installed on the rear wall of the wing box section. After installing the drive mechanism and motor, the single-set variable camber wing trailing edge structure is assembled. Under 60% operating load, that is, the input torque is not less than 2.04 Nm, under the action of torque at the drive shaft (7), the near-axis frustum connecting rod of the self-unlocking structure is sheared and destroyed. The entire mechanism releases the weak connection relationship and enters the motion working state.

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