A drilling fixture for an electric aircraft lift blade

Abstract

The utility model relates to electric airplane technical field especially electric airplane lift propeller blade's drilling frock, including positioning support plate, positioning column, positioning column sets up in positioning support plate, and positioning column is used for positioning the axial position degree of propeller blade, lateral limit component, lateral limit component sets up in positioning support plate, and lateral limit component is used for preventing propeller blade from happening rotation, the utility model structure passes through positioning support plate, positioning column, lateral limit component, mounting hole drilling template, positioning stop and C type clamp and constitutes drilling frock, and the structure design is simple, frock is easy to process, the guiding hole of drilling frok that is set up through mounting hole drilling template makes the hole, and the degree of dependence of operator reduces, avoids the unstable product quality of production, since it is the guiding hole of drilling frok that is set up through mounting hole drilling template makes the hole, makes the hole accuracy controllable and consistency high, and the composite material propeller blade body is not damaged in the hole making process.

Description

Technical Field

[0001] This utility model relates to the field of electric aircraft technology, and in particular to a drilling tool for electric aircraft lift rotor blades. Background Technology

[0002] eVTOL, or electric vertical takeoff and landing aircraft, is an aircraft that uses electric power and can take off and land vertically like a helicopter. Its core advantages are electrification and vertical takeoff and landing capabilities. Electric drive makes it more environmentally friendly, quieter, and has relatively lower maintenance costs; vertical takeoff and landing allows it to take off and land flexibly in space-constrained environments such as cities without the need for traditional runways, and vertical takeoff and landing rely entirely on lift blades mounted on the wings.

[0003] The main purpose of the lift blades of the compound-wing electric aircraft is for vertical lift: during vertical takeoff and landing and hovering, the lift blades are the main source of lift. Similar to multi-rotor drones, they generate downward airflow by rotating at high speed, thereby obtaining upward lift to counteract gravity. During this phase, they need to provide enough thrust to ensure that the aircraft can take off or descend vertically stably.

[0004] The connection between the propeller blades and the motor of an electric aircraft is a critical part of its design. Since the propeller blades are usually made of lightweight, high-strength composite materials, while the connectors and motors are metal, machining precise holes in the composite materials to ensure the reliability of the connection is a significant manufacturing challenge.

[0005] In the early stages of blade research and development and manufacturing, the manual drilling method adopted to save costs had some drawbacks, such as:

[0006] Poor precision and consistency: This is the most fatal drawback of manual machining. It is difficult to guarantee that the position, diameter and depth of each hole are completely consistent. For components such as blades that require precise dynamic balancing, any slight deviation may cause vibration, or even danger when rotating at high speed.

[0007] High risk of material damage: The properties of composite materials make them very fragile during drilling. When operating manually, the feed rate and pressure of the drill cannot be precisely controlled, which can easily lead to delamination, fiber fraying, or hole breakage. These damages will seriously weaken the structural strength of the blade and pose safety hazards during operation.

[0008] Highly dependent on operator skills: The results of manual processing largely depend on the operator's experience and skills, making it difficult to form standardized processes and guarantee the stability and reliability of the results. Utility Model Content

[0009] The purpose of this invention is to overcome the shortcomings of the prior art and provide a drilling fixture for electric aircraft lift blades, which has the advantages of controllable precision and high consistency, as well as reduced dependence on the operator.

[0010] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0011] A drilling fixture for electric aircraft lift blades, comprising:

[0012] Positioning support plate;

[0013] A positioning post is disposed on a positioning support plate and is used to position the axial position of the blade.

[0014] A lateral limiting component is disposed on a positioning support plate and is used to prevent the blade from rotating.

[0015] Install the hole drilling template. When drilling holes in the blade, place the hole drilling template on the positioning post and make it fit against the upper surface of the blade.

[0016] A positioning block, wherein the positioning block is used to ensure that the radial position of the mounting hole drill template meets the requirements;

[0017] The C-clamp is used to fix and install the hole drill template and the blade.

[0018] Preferably, the lateral limiting component includes a fixed positioning block disposed on the positioning support plate, the fixed positioning block being in contact with one side of the blade.

[0019] Preferably, the positioning column and the fixed positioning block are integrally formed with the positioning support plate by machining or by welding and then machining.

[0020] Furthermore, the lateral limiting component also includes a sliding positioning block disposed on the positioning support plate, the sliding positioning block being in contact with the other side of the blade.

[0021] Furthermore, the positioning support plate is provided with a guide groove that matches the sliding positioning block, and the sliding positioning block can slide linearly along the guide groove.

[0022] Furthermore, both the blade and the mounting hole drilling template have positioning holes in the middle that cooperate with the positioning posts.

[0023] Furthermore, the mounting hole drilling template has at least two guide holes.

[0024] Furthermore, there are two positioning blocks, both of which are T-shaped, and each positioning block has an upper mounting hole. The positioning support plate has two sets of lower mounting holes corresponding to the upper mounting holes. One set of lower mounting holes is vertically distributed on the positioning support plate, and the other set of lower mounting holes is horizontally distributed on the positioning support plate.

[0025] Furthermore, each set of lower mounting holes has two, one of which is a round hole and the other is an oblong hole.

[0026] Furthermore, there are two positioning blocks, which are installed on the upper surface of the positioning support plate and are vertically distributed.

[0027] The beneficial effects of this utility model are:

[0028] This utility model structure consists of a positioning support plate, a positioning column, a lateral limiting component, a mounting hole drilling template, a positioning block, and a C-clamp, forming a drilling fixture. The structure is simple and the fixture is easy to process.

[0029] The drilling process using a guide hole created by installing a drilling template reduces the dependence on the operator and avoids unstable product quality. Because the drilling is done using a guide hole created by installing a drilling template, the drilling accuracy is controllable and highly consistent, and the drilling process will not damage the composite material blade body. Attached Figure Description

[0030] 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.

[0031] Figure 1 This is a top view of the drilling fixture used to install the propeller blades on the electric aircraft lift propeller blades of this utility model.

[0032] Figure 2 This is a bottom view schematic diagram of the drilling fixture used to install the propeller blades on the electric aircraft lift propeller blades of this utility model.

[0033] Figure 3 This is a partial structural schematic diagram of the present invention;

[0034] Figure 4 This is a schematic diagram of the lateral limiting component of this utility model;

[0035] Figure 5 This is a partial structural schematic diagram of the present invention;

[0036] Figure 6 This is a partial structural schematic diagram of the present invention;

[0037] Figure 7 This is a top view of the positioning support plate of this utility model.

[0038] The markings in the diagram are as follows: 1. Positioning support plate; 2. Positioning column; 3. Paddle blade; 4. Lateral limiting component; 5. Mounting hole drill template; 6. Positioning stop block; 7. C-clamp; 101. Guide groove; 102. Lower mounting hole; 401. Fixed positioning block; 402. Sliding positioning block; 501. Guide hole; 701. Adjusting screw; 1021. Round hole; 1022. Oblong hole. Detailed Implementation

[0039] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those skilled in the art without creative effort are within the protection scope of the present utility model.

[0040] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0041] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the scope of the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0042] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0043] Example 1

[0044] Please see Figure 1-7As shown, a drilling fixture for an electric aircraft lift rotor blade includes a positioning support plate 1, a positioning post 2, a lateral limiting component 4, a mounting hole drilling template 5, a positioning block 6, and a C-clamp 7. The positioning post 2 is mounted on the positioning support plate 1 and is used to position the axial position of the rotor blade 3. The positioning post 2 and the positioning support plate 1 are preferably integrally formed by machining or by welding followed by machining to ensure positioning accuracy. The lateral limiting component 4 is mounted on the positioning support plate 1 and is used to prevent the rotor blade 3 from rotating. When drilling the rotor blade 3, the mounting hole drilling template 5 is fitted onto the positioning post 2 and fits against the upper surface of the rotor blade 3. The positioning block 6 ensures that the radial position of the mounting hole drilling template 5 meets the requirements. The C-clamp 7 is used to fix the mounting hole drilling template 5 and the rotor blade 3.

[0045] When drilling the blade 3, first, the blade 3 is fitted onto the positioning post 2, with the bottom of the blade 3 in contact with the upper surface of the positioning support plate 1. At this time, the positioning support plate 1 can support the blade 3, and the positioning post 2 can position the axial position of the blade 3. After the blade 3 is fitted onto the positioning post 2, the lateral limiting component 4 can prevent the blade 3 from rotating. Then, the positioning stop 6 is fixedly installed on the positioning support plate 1, and then the mounting hole drill template 5 is fitted onto the positioning post 2, and the mounting hole drill is then installed. The lower surface of template 5 contacts the upper surface of blade 3, and the mounting hole drilling template 5 contacts the positioning block 6. Then, the two ends of the C-clamp are clamped on the lower surface of the positioning support plate 1 and the upper surface of the mounting hole drilling template 5, respectively. At this time, with the cooperation of the positioning block 6 and the C-clamp 7, the mounting hole drilling template 5 can be pressed against the upper surface of blade 3, thereby fixing the mounting hole drilling template 5 and blade 3 and preventing the mounting hole drilling template 5 from rotating. Finally, the drill bit is used to drill a hole through the mounting hole drilling template 5 until the blade 3 is drilled.

[0046] The two ends of the C-clamp 7 are respectively clamped on the lower surface of the positioning support plate 1 and the upper surface of the mounting hole drilling template 5, and an adjusting screw 701 for fixing the mounting hole drilling template 5 is provided at one end of the C-clamp 7.

[0047] A threaded hole is provided at one end of the C-clamp 7 to cooperate with the adjusting screw 701. When the adjusting screw 701 is rotated clockwise, the threaded hole in the C-clamp 7 causes the adjusting screw 701 to move towards the mounting hole drill template 5 until the adjusting screw 701 and the mounting hole drill template 5 are tightly abutted together. This allows the mounting hole drill template 5 to be tightly abutted against the blade 3, thus fixing the mounting hole drill template 5 and preventing it from rotating. The tight abutment of the mounting hole drill template 5 against the blade 3 further fixes the blade 3.

[0048] The positioning pin 2 is used to position the axial position of the blade 3, and its outer diameter tolerance is controlled within + / -0.04.

[0049] The lateral limiting component 4 includes a fixed positioning block 401 disposed on the positioning support plate 1. The fixed positioning block 401 contacts one side of the blade 3. Preferably, the fixed positioning block 401 is integrally formed with the positioning support plate 1 by machining or by welding and then machining to ensure positioning accuracy. The fixed positioning block 401 fits against one side of the blade 3, ensuring that the radial position of the blade 3 is within the required range. Moreover, the profile tolerance of the side of the fixed positioning block 401 facing the blade 3 is 0.08. After the blade 3 is sleeved on the positioning post 2, it can rotate slightly around the positioning post 2 to adjust the radial position of the blade 3 until one side of the blade 3 contacts the fixed positioning block 401. The fixed positioning block 401 can constrain the blade 3, preventing the blade 3 from rotating.

[0050] Preferably, the lateral limiting component 4 further includes a sliding positioning block 402 disposed on the positioning support plate 1. The sliding positioning block 402 contacts the other side of the blade 3, further restricting the blade 3 from rotating. In this embodiment, the positioning support plate 1 has a guide groove 101 adapted to the sliding positioning block 402, and the sliding positioning block 402 can slide linearly along the guide groove 101 until it abuts against the other side of the blade 3. Since the blade 3 is tightly abutted against the mounting hole drill template 5, the blade 3 cannot rotate or move upward. The sliding positioning block 402 can be fixedly installed inside the guide groove 101 of the positioning support plate 1 or placed directly in the guide groove 101 of the positioning support plate 1.

[0051] Two positioning blocks 6 are provided, both of which are T-shaped, and each positioning block 6 has an upper mounting hole. The positioning support plate 1 has two sets of lower mounting holes 102 corresponding to the upper mounting holes. One set of lower mounting holes 102 is vertically distributed on the positioning support plate 1, and the other set of lower mounting holes 102 is horizontally distributed on the positioning support plate 1. In this embodiment, the two positioning blocks 6 are respectively installed on both sides of the upper surface of the positioning support plate 1, and the two positioning blocks 6 are vertically distributed.

[0052] Preferably, each set of lower mounting holes 102 includes a round hole 1021 and an oblong hole 1022. Two positioning blocks 6 are placed at the mounting positions of the positioning support plate 1, and screws are then passed through the upper mounting holes of the positioning blocks 6 and the round hole 1021 and oblong hole 1022 in the positioning support plate 1, so that the two positioning blocks 6 are mounted on the positioning support plate 1. The contour of the two surfaces of the positioning blocks 6 is then measured. The positions of the two positioning blocks 6 can be finely adjusted by gently tapping them, ensuring that their contours are controlled within + / -0.04.

[0053] Both the blade 3 and the mounting hole drilling template 5 have positioning holes in the middle that cooperate with the positioning post 2. The blade 3 is fitted onto the positioning post 2 through the positioning holes, and the mounting hole drilling template 5 is fitted onto the positioning post 2 through the positioning holes.

[0054] The mounting hole drilling template 5 has at least two guide holes 501. A drill bit is used to drill holes through the guide holes 501 of the mounting hole drilling template 5 until the blade 3 is drilled.

[0055] In summary, the structure of this utility model consists of a positioning support plate 1, a positioning column 2, a lateral limiting component 4, a mounting hole drilling template 5, a positioning stop block 6, and a C-clamp, forming a drilling fixture. The structure is simple and the fixture is easy to process.

[0056] The drilling process is achieved by using the guide hole 501 opened by the drilling template 5, which reduces the dependence on the operator and avoids unstable product quality. Since the drilling is done by the guide hole 501 opened by the drilling template 5, the drilling accuracy is controllable and consistent, and the drilling process will not damage the composite material blade 3 body.

[0057] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any person skilled in the art can easily conceive of various equivalent modifications or substitutions within the technical scope disclosed in this utility model, and these modifications or substitutions should all be covered within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the scope of the claims.

Claims

1. A drilling fixture for an electric aircraft lift rotor blade, characterized in that, include: Positioning support plate (1); Positioning column (2), the positioning column (2) is set on the positioning support plate (1), and the positioning column (2) is used to position the axial position of the blade (3); Lateral limiting component (4), which is disposed on the positioning support plate (1) and is used to prevent the blade (3) from rotating; Install the hole drilling template (5). When drilling holes in the blade (3), the installation hole drilling template (5) is placed on the positioning column (2) and fits against the upper surface of the blade (3). Positioning block (6), the positioning block (6) is used to ensure that the radial position of the mounting hole drill template (5) meets the requirements; C-clamp (7) is used to fix the hole drilling template (5) and the blade (3).

2. The drilling fixture for electric aircraft lift rotor blades according to claim 1, characterized in that, The lateral limiting component (4) includes a fixed positioning block (401) disposed on the positioning support plate (1), and the fixed positioning block (401) is in contact with one side of the blade (3).

3. The drilling fixture for electric aircraft lift rotor blades according to claim 2, characterized in that, The positioning column (2) and the fixed positioning block (401) are integrally formed with the positioning support plate (1) by machining or by welding and then machining.

4. The drilling fixture for electric aircraft lift rotor blades according to claim 1, characterized in that, The lateral limiting component (4) further includes a sliding positioning block (402) disposed on the positioning support plate (1), the sliding positioning block (402) being in contact with the other side of the blade (3).

5. The drilling fixture for electric aircraft lift rotor blades according to claim 4, characterized in that, The positioning support plate (1) is provided with a guide groove (101) that is compatible with the sliding positioning block (402), and the sliding positioning block (402) can slide linearly along the guide groove (101).

6. The drilling fixture for electric aircraft lift rotor blades according to claim 1, characterized in that, The blade (3) and the mounting hole drilling template (5) are both provided with positioning holes that cooperate with the positioning column (2) in the middle.

7. The drilling fixture for electric aircraft lift rotor blades according to claim 1, characterized in that, The mounting hole drilling template (5) has at least two guide holes (501).

8. The drilling fixture for electric aircraft lift rotor blades according to claim 1, characterized in that, There are two positioning blocks (6), both of which are T-shaped, and each positioning block (6) has an upper mounting hole. The positioning support plate (1) has two sets of lower mounting holes (102) corresponding to the upper mounting holes. One set of lower mounting holes (102) is vertically distributed on the positioning support plate (1), and the other set of lower mounting holes (102) is horizontally distributed on the positioning support plate (1).

9. The drilling fixture for electric aircraft lift rotor blades according to claim 8, characterized in that, Each set of lower mounting holes (102) is provided with two holes, one of which is a round hole (1021) and the other is an oblong hole (1022).

10. The drilling fixture for the electric aircraft lift rotor blade according to claim 1, characterized in that, There are two positioning blocks (6), which are installed on the upper surface of the positioning support plate (1) and are vertically distributed.

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