An aircraft assembly jig
By designing a multi-degree-of-freedom adjustment and locking mechanism for aircraft assembly jigs, the problems of difficult centering adjustment and precision assurance during the assembly of electric vertical take-off and landing aircraft were solved, achieving efficient and safe assembly results.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-06-30
- Publication Date
- 2026-07-28
AI Technical Summary
During the assembly of electric vertical takeoff and landing aircraft, the airframe structure is complex and the assembly precision requirements are high. Existing technologies rely on lifting equipment for hoisting and positioning, which makes centering adjustment difficult, assembly efficiency low and precision hard to guarantee. Furthermore, large tooling components are difficult to support stably and lock in real time during hoisting, posing a risk of positioning slippage.
An aircraft assembly jig was designed, including fuselage positioning components, wing positioning components, tail positioning components, inner motor arm positioning components, and outer motor arm positioning components. It adopts a multi-degree-of-freedom adjustment and locking mechanism, combined with a lead screw lifting mechanism, a multi-directional displacement module, and a common hinge guide module, to achieve high-precision multi-dimensional adjustment and locking of the wings and tail, ensuring assembly accuracy and safety.
The multi-degree-of-freedom adjustment and locking mechanism improves assembly accuracy and operational safety, reduces reliance on lifting equipment, enhances overall assembly efficiency and quality, and solves the problems of centering difficulties and precision assurance in traditional hoisting methods.
Smart Images
Figure CN122464078A_ABST
Abstract
Description
Technical Field
[0001] This invention relates to the field of electric vertical takeoff and landing aircraft manufacturing technology, specifically to an aircraft assembly jig. Background Technology
[0002] In the assembly process of electric vertical takeoff and landing (EVTOL) aircraft, the airframe structure is complex and the assembly precision requirements are extremely high, especially in the wing-body docking and tail assembly stages, which typically require high-precision splicing within a limited space. In existing technologies, segment docking mostly relies on lifting equipment for hoisting and positioning. Due to the lack of sophisticated multi-dimensional adjustment and locking mechanisms, alignment is extremely difficult, requiring extensive manual adjustments on-site, resulting in low assembly efficiency and difficulty in consistently maintaining accuracy. Furthermore, large tooling components are difficult to stably support and lock in real-time during hoisting, posing a risk of positioning slippage. The balance between ease of assembly operation and safety assurance urgently needs to be addressed. Summary of the Invention
[0003] In view of this, the present invention proposes an aircraft assembly jig that enables high-precision multi-degree-of-freedom adjustment and positioning of the wings and tail, reducing reliance on lifting equipment and improving the overall assembly efficiency and safety. The present invention provides the following technical solution: An aircraft assembly jig includes a fuselage positioning assembly, a wing positioning assembly, a tail fin positioning assembly, an inner motor arm positioning assembly, and an outer motor arm positioning assembly. The fuselage positioning components are arranged along the length of the fuselage; The wing positioning components are two in number, symmetrically arranged on both sides of the fuselage positioning components, including a first lifting adjustment module, a multi-directional displacement module provided on the first lifting adjustment module, and a wing mounting module for connecting the wing movably disposed on the multi-directional displacement module. The tail fin positioning components are two in number, symmetrically arranged on both sides of the rear of the fuselage positioning components, including a second lifting adjustment module, on which a tail fin mounting module for clamping the tail fin is provided; There are two internal motor arm positioning components, which are symmetrically arranged on both sides of the body positioning component; The external motor arm positioning components are in two sets, symmetrically arranged on both sides of the body positioning components; The internal motor arm positioning assembly, wing positioning assembly, and tail wing positioning assembly are arranged sequentially from front to back along the length of the fuselage positioning assembly.
[0004] Optionally, the first lifting adjustment module is a lead screw lifting mechanism; The multi-directional displacement module includes a base plate and a mounting base plate, and the base plate is connected to the lifting end of the lead screw lifting mechanism. Multiple ball bearings are movably disposed on the base plate, and the mounting base plate rolls against the ball bearings; The wing mounting module is detachably connected to the mounting base plate.
[0005] Optionally, the wing mounting module includes a first mounting bracket and a second mounting bracket; The second mounting bracket is provided with at least two first tapered pins; A limiting hole is provided on the mounting base plate corresponding to the position of the first tapered pin, and the first tapered pin is inserted into the limiting hole; The first end of the first mounting bracket is hinged to the first end of the second mounting bracket by a lockable fixing pin. The second end of the second mounting bracket is provided with a connecting plate, and a set screw is threaded onto the connecting plate. The end of the set screw abuts against the second end of the first mounting bracket, so as to adjust the pitch angle of the first mounting bracket by screwing in or out the set screw.
[0006] Optionally, the wing mounting module further includes a wing support base, on which a first slide rail is provided, and a mounting slider is slidably disposed on the first slide rail, and the first lifting adjustment module is disposed on the mounting slider; The sliding direction of the mounting slider is perpendicular to the lifting direction of the lead screw lifting mechanism.
[0007] Optionally, the fuselage positioning assembly includes a connecting block and a mounting base, wherein the connecting block includes a positioning part and a second tapered pin; The mounting base is provided with a guide hole, and the second tapered pin is inserted into the mounting base through the guide hole; The second tapered pin has a first vent groove on its side, and the mounting base has a second vent groove that penetrates the guide hole.
[0008] Optionally, the tail fin positioning assembly further includes a common hinge guide module, which includes a front guide block and a rear guide block. A first drill sleeve is provided on the front guide block, and a second drill sleeve is provided on the rear guide block. The first drill bushing and the second drill bushing are spaced apart along the length of the machine body, and the axes of the first drill bushing and the second drill bushing are collinear.
[0009] Optionally, it also includes a shared hinge tool, which includes a cutting section, a leading section and a trailing section arranged coaxially; The inner diameter of the first drill sleeve is adapted to the outer diameter of the leading section, and the inner diameter of the second drill sleeve is adapted to the outer diameter of the rear leading section. The common reamer is configured to feed along the second drill bushing toward the first drill bushing, so that the leading section and the trailing section pass through the first drill bushing and the second drill bushing respectively, thereby limiting and guiding the common reamer during the hole reaming process.
[0010] Optionally, the fuselage positioning assembly further includes a front fuselage inspection module and a rear fuselage inspection module; The front fuselage inspection module and the rear fuselage inspection module are respectively located at the front end and rear end of the fuselage positioning component; Both the front inspection module and the rear inspection module of the fuselage are provided with inspection positioning holes, which are adapted to the positioning holes on the fuselage.
[0011] Optionally, the inner motor arm positioning assembly includes an inner motor support frame and an inner motor positioning plate disposed on the top of the inner motor support frame. The inner motor positioning plate has a ring structure, and a crossbeam is provided across the inner motor positioning plate. The crossbeam and / or the inner motor positioning plate are provided with multiple locking elements for fixing and positioning the inner motor.
[0012] Optionally, the external motor arm positioning assembly includes an external motor support frame and an external motor positioning plate disposed on the top of the external motor support frame. The external motor positioning plate has a ring structure, and a crossbeam is provided across the external motor positioning plate. The crossbeam and / or the external motor positioning plate are provided with multiple locking components for fixing and positioning the external motor.
[0013] This invention further discloses an aircraft assembly method, applied to the aforementioned aircraft assembly jig, comprising the following steps: The fuselage is hoisted to the fuselage positioning assembly. The connecting block fixed to the fuselage is quickly positioned by inserting into the guide hole through the guiding action of the second conical pin. The air between the mating surfaces is discharged through the first and second exhaust grooves to prevent vacuum adsorption. After the fuselage is positioned, the fuselage position is inspected through the front inspection module and the rear inspection module. The wing is hoisted onto the wing positioning assembly, connected to the first mounting bracket, and quickly guided and positioned using the first tapered pin and the limiting hole. The wing is then finely adjusted in multiple degrees of freedom using the first lifting adjustment module, the multi-directional displacement module, and the pitch adjustment mechanism to mate with the fuselage. After mateting and installation, the first mounting bracket is separated from the wing, and the mounting slider is pushed along the slide rail to the non-mateting installation position. The inner motor is hoisted to the inner motor arm positioning assembly, and the inner motor is positioned and supported by the inner motor positioning plate, so as to position the connecting joint of the inner motor arm to the target installation position. The tail fin is clamped onto the tail fin mounting module, and the tail fin height is adjusted using the second lifting adjustment module. The common reaming tool is fed from the second drill sleeve toward the first drill sleeve, and the first and second drill sleeves are used to synchronously limit and guide the front and rear guide sections. The common reaming is performed on the connection joint between the tail fin and the inner motor arm.
[0014] According to the technical solution of the present invention, a multi-degree-of-freedom decoupled adjustment and locking mechanism is constructed by connecting the first lifting adjustment module, the multi-directional displacement module, and the wing mounting module in the wing positioning assembly. This enables the wing to achieve independent fine-tuning and real-time locking in multiple dimensions such as lifting, translation, rotation, and pitch during assembly, effectively solving the problems of difficult alignment and inability to guarantee accuracy in traditional hoisting methods, and significantly improving assembly accuracy and operational safety. Simultaneously, the tail wing positioning assembly, through the cooperation structure of the double drill sleeve and the front and rear guide sections of the tool in the common hinge guide module, transforms the process method into a purely hardware guiding and limiting feature, ensuring tool stability and hole concentricity during coaxial machining of cross-components, further improving the overall assembly quality. Furthermore, the fuselage positioning assembly adopts a tapered pin and exhaust groove cooperation structure, realizing rapid fuselage positioning and anti-adsorption removal from the frame. Combined with the symmetrical layout of each positioning assembly based on the fuselage positioning assembly, the overall coordination and operational efficiency of the assembly jig are improved. Attached Figure Description
[0015] For illustrative and not limiting purposes, the present invention will now be described in conjunction with embodiments and accompanying drawings, wherein: Figure 1 This is a schematic diagram of the planar layout structure of the aircraft assembly jig according to an embodiment of this application; Figure 2 This is a cross-sectional view of the fuselage positioning component according to an embodiment of this application; Figure 3 This is a schematic diagram of the installation structure of the connecting block and the mounting base according to an embodiment of this application. Figure 4 This is a schematic diagram of the structure of the fuselage front inspection module according to an embodiment of this application; Figure 5 This is a schematic diagram of the rear inspection module of the fuselage according to an embodiment of this application; Figure 6 This is a schematic diagram of the wing positioning component structure according to an embodiment of this application; Figure 7 This is a schematic diagram of the structure of the first lifting module and the multi-directional displacement module according to an embodiment of this application; Figure 8 This is a schematic diagram of the tail fin positioning component structure according to an embodiment of this application; Figure 9 This is a schematic diagram of the conjoined hinge guide module structure according to an embodiment of this application; Figure 10 yes Figure 7Enlarged diagram of section A in the middle; Figure 11 This is a schematic diagram of the internal motor arm positioning component structure according to an embodiment of this application; Figure 12 This is a schematic diagram of the external motor arm positioning assembly structure according to an embodiment of this application; Figure 13 This is a schematic diagram of the structure of the conjoined tool according to an embodiment of this application.
[0016] Reference numerals: 1-Fuselage positioning assembly, 101-Fuselage positioning module, 102-Positioning support frame, 2-Front fuselage inspection module, 202-First inspection positioning hole, 3-Rear fuselage inspection module, 301-Second inspection positioning hole, 4-Inner motor arm positioning assembly, 41-Inner motor support frame, 42-Inner motor positioning plate, 43-Locking component, 6-Outer motor arm positioning assembly, 61-Outer motor support frame, 62-Outer motor positioning plate, 7-Positioning part, 8-Wing positioning assembly, 9-Tail fin positioning assembly, 10-Connecting block, 11-Mounting base, 111-Guide hole, 12-Second tapered pin, 13-First exhaust groove, 14-Second exhaust groove, 15-First lifting adjustment module, 16-Multi-directional displacement module, 17-Wing mounting module, 18-First mounting bracket, 181-Connector head. 19-Second mounting bracket, 191-First fixing pin, 192-Connecting plate, 193-Second fixing pin, 20-First tapered pin, 201-Limiting hole, 21-Top screw, 22-Ball bearing, 23-Base plate, 24-Mounting base plate, 241-Cover plate, 242-First slide rail, 243-Third fixing pin, 244-Mounting slider, 245-Wing support seat, 25-Second lifting adjustment module, 26-Tail wing mounting module, 261-Tail wing support seat, 262-Upper clamping plate, 263-Lower clamping plate, 264-Assembly slider, 27-Common hinge guide module, 271-Second slide rail, 28-Front guide block, 29-Rear guide block, 30-First drill sleeve, 31-Second drill sleeve, 32-Common hinge tool, 321-Front guide section, 322-Rear guide section, 323-Cutting part, 50-Reference positioning rod. Detailed Implementation
[0017] To enable those skilled in the art to better understand the present invention, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.
[0018] It should be noted that the terms "first," "second," etc., in the specification and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be used interchangeably where appropriate for the embodiments of the invention described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.
[0019] In this invention, the terms "upper," "lower," "left," "right," "front," "rear," "top," "bottom," "inner," "outer," "middle," "vertical," "horizontal," "lateral," and "longitudinal" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. These terms are primarily for the purpose of better describing this invention and its embodiments, and are not intended to limit the indicated devices, elements, or components to having a specific orientation, or to be constructed and operated in a specific orientation.
[0020] Furthermore, some of the aforementioned terms, besides indicating location or positional relationships, may also have other meanings. For example, the term "above" may, in certain circumstances, indicate a dependency or connection. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances. Additionally, the term "multiple" should mean two or more.
[0021] It should be noted that, where there is no conflict, the embodiments and features of the present invention can be combined with each other. The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.
[0022] Example 1: refer to Figure 1This embodiment provides an aircraft assembly jig, including a fuselage positioning assembly 1, a wing positioning assembly 8, a tail positioning assembly 9, an inner motor arm positioning assembly 4, and an outer motor arm positioning assembly 6. The fuselage positioning assembly 1 includes a forward fuselage inspection module 2, a rear fuselage inspection module 3, and two identical fuselage positioning modules 101. The two fuselage positioning modules 101 are positioned between the forward fuselage inspection module 2 and the rear fuselage inspection module 3, and are coaxially arranged along the length of the fuselage. There are two wing positioning assemblies 8, symmetrically arranged on both sides of the fuselage positioning assembly 1, with their positions adapted to the fuselage model. There are two tail positioning assemblies 9, symmetrically arranged on both rear sides of the fuselage positioning assembly 1, with their positions adapted to the fuselage model. There are two inner motor arm positioning components 4, symmetrically arranged on both sides of the fuselage positioning component, so that the inner motor arm positioning component 4, wing positioning component 8, and tail fin positioning component 9 are arranged sequentially from front to back along the length of the fuselage positioning component. There are two sets of outer motor arm positioning components 6, symmetrically arranged on both sides of the fuselage positioning component 1, and each set of outer motor arm positioning components 6 is located outside the inner motor arm positioning component 4 relative to the fuselage positioning component 1.
[0023] refer to Figure 2 and Figure 3 In this embodiment, the fuselage positioning module 101 includes a positioning support frame 102, two sets of connecting blocks 10, and mounting seats 11. The two mounting seats 11 are located at both ends of the positioning support frame 102. The connecting block 10 includes a positioning part 7 and a second conical pin 12. The positioning part 7 has a protrusion structure, and bolts for connecting to the fuselage to be assembled are also provided on its periphery. A recessed portion that fits into the positioning part 7 is provided at the positioning position of the fuselage to be assembled. During assembly, the positioning part 7 is inserted into the recessed portion, and the bolts are used to achieve a detachable connection and positioning between the connecting block 10 and the fuselage to be assembled. The mounting seat 11 is provided with a guide hole 111, and the second conical pin 12 is inserted into the guide hole 111 to connect with the mounting seat 11. The two sets of connecting blocks 10 and mounting seats 11 achieve stable installation and positioning of the fuselage. Furthermore, a first vent groove 13 is provided on the side of the second conical pin 12, and a second vent groove 14 penetrating the guide hole 111 is provided on the mounting seat 11. Figure 2 and Figure 3 As shown, when the fuselage is hoisted and lowered, the second conical pin 12 automatically aligns and inserts into the guide hole 111 using the guiding effect of its conical surface, achieving rapid positioning. During this process, the first exhaust groove 13 and the second exhaust groove 14 are interconnected to form an exhaust channel, which can promptly expel air between the mating surfaces, preventing the fuselage from failing to land smoothly or making unloading difficult due to a vacuum suction effect caused by air compression. Furthermore, reference... Figure 4 and Figure 5The fuselage positioning assembly 1 also includes a front fuselage inspection module 2 and a rear fuselage inspection module 3, which are rigidly fixed to the front and rear ends of the fuselage positioning assembly 1, respectively, serving as inspection benchmarks for the entire assembly. In this embodiment, the front fuselage inspection module 2 is provided with two first inspection positioning holes 202, which correspond to the positioning holes provided at the front end of the fuselage. The connection between the front fuselage positioning holes and the first inspection positioning holes 202 is checked to determine whether the installation position of the front end of the fuselage meets the standard. If the two can be connected, the installation position of the front end of the fuselage is determined to meet the standard; otherwise, the inspection fails. The rear inspection module 3 is provided with two second inspection positioning holes 301, which correspond to the positioning holes provided at the rear end of the fuselage. The connection between the rear fuselage positioning holes and the second inspection positioning holes 301 is checked to determine whether the installation position of the rear end of the fuselage meets the standard. If the two can be connected, the installation position of the rear end of the fuselage is determined to meet the standard; otherwise, the inspection fails. This allows for direct verification of whether the fuselage's position on fuselage positioning component 1 meets assembly tolerance requirements.
[0024] refer to Figure 6 and Figure 7The wing positioning assembly 8 includes a wing support base 245 and a first lifting adjustment module 15. Two first slide rails 242 are symmetrically arranged on the wing support base 245, and mounting sliders 244 are slidably mounted on the first slide rails 242. The first lifting adjustment module 15 is fixedly positioned in the middle of the mounting sliders 244. A multi-directional displacement module 16 is provided on the first lifting adjustment module 15, and a wing mounting module 17 for connecting the wing is provided on the multi-directional displacement module 16. Specifically, the first lifting adjustment module 15 is a screw lifting mechanism. The multi-directional displacement module 16 includes a base plate 23, a mounting base plate 24, and a cover plate 241. The base plate 23 is connected to the lifting end of the screw lifting mechanism. The cover plate 241 has an inverted U-shaped structure. During installation, the cover plate 241 is fastened to the base plate 23 to form a through-hole receiving space between them, in which the mounting base plate 24 is placed. Multiple ball bearings 22 are movably arranged on the base plate 23, and the mounting base plate 24 rolls against the ball bearings 22. The cover plate 241 and the base plate 23 are connected by bolts to lock or loosen, thereby locking and adjusting the position of the mounting base plate 24. When fine-tuning of the mounting base plate 24 is required, the bolts can be loosened to adjust its position. This allows the mounting base plate 24 to be translated along the X / Y axis and rotated around the Z axis in the horizontal plane, thus compensating for docking deviations caused by wing manufacturing errors. It should be understood that although this embodiment uses a lead screw lifting mechanism and ball bearings as the preferred implementation, in other embodiments, the first lifting adjustment module 15 can also use an electric push rod, hydraulic cylinder, or rack and pinion mechanism; the multi-directional displacement module 16 can also use a ball joint, cross slider, or air-bearing platform, etc., which can achieve multi-degree-of-freedom kinematic pairs, as long as the lifting and multi-dimensional fine-tuning functions are met.
[0025] Furthermore, the wing mounting module 17 includes a first mounting bracket 18 and a second mounting bracket 19. The first mounting bracket 18 has connectors 181 at both ends for connecting the wing; during wing docking, the wing is fixedly connected to the connectors 181. The second mounting bracket 19 has at least two first tapered pins 20, and the mounting base plate 24 has limiting holes 201 corresponding to the positions of the first tapered pins 20; the first tapered pins 20 are inserted into the mounting base plate 24 through the limiting holes 201. After each wing installation, a reference position for the wing mounting module 17 needs to be set. For this purpose, reference positioning rods 50 are provided at both ends of the mounting slider 244. The first and second ends of the second mounting bracket 19 are detachably connected to the reference positioning rods 50 on the corresponding sides via third fixing pins 243. When the third fixing pins 243 lock the mounting slider 244 and the second mounting bracket 19, this is the reference wing installation height. When the wing's installation height needs adjustment, the third fixing pin 243 is loosened to separate the mounting slider 244 and the second mounting bracket 19. This, combined with the height adjustment structure 15, allows for precise positioning of the wing's installation position. The first end of the first mounting bracket 18 is hinged to the first end of the second mounting bracket 19 via a lockable first fixing pin 191. The second end of the second mounting bracket 19 is provided with a connecting plate 192, on which a set screw 21 is threaded. The end of the set screw 21 abuts against the second end of the first mounting bracket 18, allowing adjustment of the pitch angle of the first mounting bracket 18 by screwing the set screw 21 in or out. The second end of the first mounting bracket 18 and the second end of the second mounting bracket 19 are detachably connected via a second fixing pin 193. When the pitch angle of the first mounting bracket 18 needs adjustment, the second fixing pin 193 is removed, and the set screw 21 is rotated to adjust the pitch angle of the first mounting bracket 18. When no pitch angle adjustment of the first mounting bracket 18 is required, the first mounting bracket 18 and the second mounting bracket 19 are locked together by the second fixing pin 193 to ensure the stability of the wing position to be connected. Through the above settings, the split connection structure of this embodiment is realized. When only the wing pitch angle needs to be adjusted, the second fixing pin 193 on the set screw 21 side can be released to achieve complete decoupling of the wing mounting position adjustment freedom. After the wing is installed, the wing is disassembled from the connector 181, and the mounting slider 244 is pushed to move the wing mounting module 17 to a position that will not affect the remaining installation work.
[0026] refer to Figure 8 , Figure 9 and Figure 10The tail wing positioning assembly 9 includes a tail wing support base 261, on which a second lifting adjustment module 25 is mounted. The second lifting adjustment module 25 has a tail wing mounting module 26 for clamping the tail wing. The second lifting adjustment module 25 is a screw-driven lifting mechanism. The tail wing mounting module 26 includes an upper clamping plate 262 and a lower clamping plate 263 adapted to the shape of the tail wing to be installed. The upper clamping plate 262 and the lower clamping plate 263 cooperate to clamp and fix the tail wing. The lower clamping plate 263 is fixedly connected to the lifting end of the screw-driven lifting mechanism. The two ends of the upper clamping plate 262 and the lower clamping plate 263 are fixedly connected by an assembly slider 264. The assembly slider 264 is a lockable structure; by loosening the assembly slider 264, the clamping thickness of the upper clamping plate 262 and the lower clamping plate 263 can be adjusted. The tail wing support 261 has two ends with second slide rails 271 along the lifting adjustment direction of the second lifting adjustment module 25. The mounting slider 264 is slidably connected to the second slide rails 271 to adjust the installation height of the tail wing to be installed along the second slide rails 271.
[0027] refer to Figure 11 and Figure 12The aircraft assembly jig also includes an inner motor arm positioning assembly 4 and an outer motor arm positioning assembly 6. The inner motor arm positioning assembly 4 is used to position the inner motor to be installed, thereby positioning the inner motor arm and its connecting joint, facilitating subsequent hinge machining to install the inner motor onto the tail fin. The outer motor arm positioning assembly 6 is used to position the outer motor to be installed, thereby enabling the outer motor to be installed onto the wing. There are two inner motor arm positioning assemblies 4, symmetrically arranged on both sides of the fuselage positioning assembly 1. The inner motor arm positioning assembly 4 includes an inner motor support frame 41 and an inner motor positioning clamping plate 42 disposed on top of the inner motor support frame 41. The inner motor support frame 41 serves as a basic load-bearing structure, providing stable height support. The inner motor positioning clamping plate 42 has a ring-shaped structure. Further, a crossbeam spans across the inner motor positioning clamping plate 42, and the crossbeam and / or the inner motor positioning clamping plate 42 are provided with multiple locking elements 43 for fixing and positioning the inner motor, exemplarily, adjusting bolts with handles or quick clamps. During actual assembly, the inner motor is placed on the inner motor positioning plate 42, and multiple locking elements 43 are operated to clamp and lock the inner motor. This multi-point surrounding locking structure can effectively eliminate assembly gaps and ensure the absolute positional stability of the inner motor arm during subsequent connection with the wing and co-hinge processing. Furthermore, the outer motor arm positioning assembly 6 consists of two sets, symmetrically arranged on both sides of the fuselage positioning assembly 1, with the two outer motor arm positioning assemblies 6 in each set located at the front and rear of the fuselage positioning assembly 1, respectively. The outer motor arm positioning assembly 6 includes an outer motor support frame 61 and an outer motor positioning plate 62 located on top of the outer motor support frame 61. The outer motor positioning plate 62 has a ring structure, and a crossbeam spans across the outer motor positioning plate 62. Multiple locking elements 43 for fixing and positioning the outer motor are provided on the crossbeam and / or the outer motor positioning plate 62. Through the combination structure of the outer motor positioning plate 62 and the spanning crossbeam, in conjunction with the multi-point locking elements, rigid positioning of the inner and outer motors is achieved. It overcomes the shortcomings of traditional single-point or semi-circular supports that are prone to deflection, and can adapt to the installation requirements of different motor models, greatly improving the assembly accuracy of the motor arm and the coordination of the overall frame.
[0028] refer to Figures 8-11The tail fin positioning assembly 9 also includes a common hinge guide module 27, which is disposed on one side of the tail fin mounting module 26. The common hinge guide module 27 is used to mount the inner motor and tail fin after common hinge machining. The common hinge guide module 27 includes a front guide block 28 and a rear guide block 29. A first drill sleeve 30 is disposed on the front guide block 28, and a second drill sleeve 31 is disposed on the rear guide block 29. The axes of the first drill sleeve 30 and the second drill sleeve 31 are collinear, providing guidance during the common machining of the connection joint between the tail fin and the inner motor arm. The common hinge guide module 27 also includes a common hinge tool 32, which includes a coaxially arranged cutting section 323, a front guide section 321, and a rear guide section 322. The inner diameter of the first drill sleeve 30 is adapted to the outer diameter of the front guide section 321, and the inner diameter of the second drill sleeve 31 is adapted to the outer diameter of the rear guide section 322. The common hinge tool 32 is configured to feed along the side of the drill sleeve with the larger inner diameter. In this embodiment, for example, the inner diameter of the second drill sleeve 31 is larger than the inner diameter of the first drill sleeve 30. Therefore, the common reamer 32 is configured to feed from the second drill sleeve 31 towards the first drill sleeve 30, so that the leading section 321 and the cutting part 323 pass through the second drill sleeve 31, thereby limiting and guiding the common reamer 32 during the hole reaming process. This achieves the formation of two assembly holes at once with a single reamer, directly adapting to the assembly dimensions, while also realizing process compensation.
[0029] Example 2: refer to Figures 1 to 10 This embodiment provides an aircraft assembly method based on the above-mentioned aircraft assembly jig, used for the overall assembly of an aircraft, specifically including the following steps: The fuselage is hoisted onto the fuselage positioning assembly 1. The connecting block 10, which is fixed to the fuselage, automatically aligns and inserts into the guide hole 111 of the mounting base 11 through the conical guide surface of the second conical pin 12, achieving rapid positioning of the fuselage. During this process, the first exhaust groove 13 on the side of the second conical pin 12 and the second exhaust groove 14 through the guide hole 111 of the mounting base 11 are interconnected to form an exhaust channel, which promptly discharges air between the mating surfaces, preventing the fuselage from failing to be smoothly positioned or difficult to remove due to vacuum adsorption caused by air compression. After the fuselage is positioned, the fuselage position is inspected through the front inspection module 2 and the rear inspection module 3. Specifically, inspection pins are inserted into the first inspection positioning hole 202 on the front inspection module 2 and the second inspection positioning hole 301 on the rear inspection module 3. If the inspection pins can smoothly guide the corresponding positioning holes at the front and rear ends of the fuselage, it is determined that the installation positions of the front and rear ends of the fuselage meet the standards, thus visually verifying that the position of the fuselage on the frame meets the assembly tolerance requirements.
[0030] The wing is hoisted onto the wing positioning assembly 8, and the connectors 181 at both ends of the wing and the first mounting bracket 18 are fixedly connected. The first tapered pin 20 on the second mounting bracket 19 is inserted into the limiting hole 201 on the mounting base plate 24 to achieve rapid guiding and positioning of the wing mounting module 17. Subsequently, the wing height is adjusted by the first lifting adjustment module 15, and the mounting base plate 24 is finely adjusted by horizontal X / Y axis translation and Z-axis rotation using multiple ball bearings 22 on the base plate 23 to compensate for wing manufacturing errors. If the pitch angle needs to be adjusted, the second fixing pin 193 is removed, and the set screw 21 on the connecting plate 192 is rotated to make the first mounting bracket 18 rotate around the first fixing pin 191, achieving decoupled adjustment of the pitch angle. Through the above multi-degree-of-freedom fine adjustment, the wing and fuselage are precisely aligned. After docking and installation, the first mounting bracket 18 is separated from the wing, the locking bolts of the cover plate 241 and the base plate 23 are loosened, and the mounting slider 244 is pushed to slide along the first slide rail 242, so that the wing positioning assembly 8 is moved to a non-docked installation position to make room for subsequent assembly.
[0031] The inner motor is hoisted onto the inner motor arm positioning assembly 4, and then placed within the annular space of the inner motor positioning plate 42 on top of the inner motor support frame 41. The inner motor is clamped and locked by operating the crossbeam and multiple locking components 43 on the plate. This precisely positions the inner motor arm's connecting joint to the target installation position where it is hinged with the tail fin, ensuring absolute positional stability during subsequent hinge processing.
[0032] The tail fin is placed on the lower clamping plate 263 of the tail fin mounting module 26, and the upper clamping plate 262 is closed. The clamping thickness is adjusted and locked by loosening the assembly slider 264 to achieve stable clamping of the tail fin. The height of the tail fin is adjusted using the second lifting adjustment module 25 to align it with the connection joint of the inner motor arm. Subsequently, the common reaming tool 32 is fed from the side of the second drill sleeve 31 with a larger inner diameter, advancing towards the first drill sleeve 30. During this process, the leading and trailing sections of the common reaming tool 32 pass through the first drill sleeve 30 and the second drill sleeve 31, respectively. The double-ended drill sleeves provide synchronous limiting and guidance for the tool, performing common reaming and enlarging machining on the connection joint between the tail fin and the inner motor arm. By utilizing the synchronous constraint of the double-ended drill sleeves, two assembly holes are formed at once with a single reamer, directly adapting to the size of the assembly parts, while simultaneously achieving process compensation and effectively reducing installation stress.
[0033] The above embodiments do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can occur depending on design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.
Claims
1. An aircraft assembly jig, characterized in that, This includes fuselage positioning components, wing positioning components, tail fin positioning components, inner motor arm positioning components, and outer motor arm positioning components; The fuselage positioning components are arranged coaxially along the length of the fuselage. The wing positioning components are two in number, symmetrically arranged on both sides of the fuselage positioning components, including a first lifting adjustment module, a multi-directional displacement module provided on the first lifting adjustment module, and a wing mounting module for connecting the wing movably disposed on the multi-directional displacement module. The tail fin positioning components are two in number, symmetrically arranged on both sides of the rear of the fuselage positioning components, including a second lifting adjustment module, on which a tail fin mounting module for clamping the tail fin is provided; There are two internal motor arm positioning components, which are symmetrically arranged on both sides of the body positioning component; The external motor arm positioning components are in two sets, symmetrically arranged on both sides of the body positioning components; The internal motor arm positioning assembly, wing positioning assembly, and tail wing positioning assembly are arranged sequentially from front to back along the length of the fuselage positioning assembly.
2. The aircraft assembly jig according to claim 1, characterized in that, The first lifting adjustment module is a lead screw lifting mechanism; The multi-directional displacement module includes a base plate and a mounting base plate, and the base plate is connected to the lifting end of the lead screw lifting mechanism. Multiple ball bearings are movably disposed on the base plate, and the mounting base plate rolls against the ball bearings; The wing mounting module is detachably connected to the mounting base plate.
3. The aircraft assembly jig according to claim 2, characterized in that, The wing mounting module includes a first mounting bracket and a second mounting bracket; The second mounting bracket is provided with at least two first tapered pins; A limiting hole is provided on the mounting base plate corresponding to the position of the first tapered pin, and the first tapered pin is inserted into the limiting hole; The first end of the first mounting bracket is hinged to the first end of the second mounting bracket by a lockable fixing pin. The second end of the second mounting bracket is provided with a connecting plate, and a set screw is threaded onto the connecting plate. The end of the set screw abuts against the second end of the first mounting bracket, so as to adjust the pitch angle of the first mounting bracket by screwing in or out the set screw.
4. The aircraft assembly jig according to claim 2, characterized in that, The wing mounting module also includes a wing support base, on which a first slide rail is provided, and a mounting slider is slidably mounted on the first slide rail. The first lifting adjustment module is mounted on the mounting slider. The sliding direction of the mounting slider is perpendicular to the lifting direction of the lead screw lifting mechanism.
5. The aircraft assembly jig according to claim 1, characterized in that, The fuselage positioning assembly includes a connecting block and a mounting base, and the connecting block includes a positioning part and a second tapered pin; The mounting base is provided with a guide hole, and the second tapered pin is inserted into the mounting base through the guide hole; The second tapered pin has a first vent groove on its side, and the mounting base has a second vent groove that penetrates the guide hole.
6. The aircraft assembly jig according to claim 1, characterized in that, The tail fin positioning assembly also includes a common hinge guide module, which includes a front guide block and a rear guide block. A first drill sleeve is provided on the front guide block, and a second drill sleeve is provided on the rear guide block. The first drill bushing and the second drill bushing are spaced apart along the length of the machine body, and the axes of the first drill bushing and the second drill bushing are collinear.
7. The aircraft assembly jig according to claim 6, characterized in that, It also includes a shared hinge tool, which comprises a cutting section, a leading section and a trailing section arranged coaxially; The inner diameter of the first drill sleeve is adapted to the outer diameter of the leading section, and the inner diameter of the second drill sleeve is adapted to the outer diameter of the rear leading section. The common reamer is configured to feed along the second drill bushing toward the first drill bushing, so that the leading section and the trailing section pass through the first drill bushing and the second drill bushing respectively, thereby limiting and guiding the common reamer during the hole reaming process.
8. The aircraft assembly jig according to claim 1, characterized in that, The fuselage positioning assembly also includes a front fuselage inspection module and a rear fuselage inspection module; The front fuselage inspection module and the rear fuselage inspection module are respectively located at the front end and rear end of the fuselage positioning component; Both the front inspection module and the rear inspection module of the fuselage are provided with inspection positioning holes, which are adapted to the positioning holes on the fuselage.
9. The aircraft assembly jig according to claim 1, characterized in that, The inner motor arm positioning assembly includes an inner motor support frame and an inner motor positioning plate disposed on the top of the inner motor support frame. The inner motor positioning plate has a ring structure and a crossbeam is provided across the inner motor positioning plate. The crossbeam and / or the inner motor positioning plate are provided with multiple locking parts for fixing and positioning the inner motor.
10. The aircraft assembly jig according to claim 1, characterized in that, The external motor arm positioning assembly includes an external motor support frame and an external motor positioning plate disposed on the top of the external motor support frame. The external motor positioning plate has a ring structure and a crossbeam is provided across the external motor positioning plate. The crossbeam and / or the external motor positioning plate are provided with multiple locking parts for fixing and positioning the external motor.
11. An aircraft assembly method, applied to the aircraft assembly jig as described in any one of claims 1-10, characterized in that, Includes the following steps: The fuselage is hoisted to the fuselage positioning assembly. The connecting block fixed to the fuselage is quickly positioned by inserting into the guide hole through the guiding action of the second conical pin. The air between the mating surfaces is discharged through the first and second exhaust grooves to prevent vacuum adsorption. After the fuselage is positioned, the fuselage position is inspected through the front inspection module and the rear inspection module. The wing is hoisted onto the wing positioning assembly, connected to the first mounting bracket, and quickly guided and positioned by inserting the first tapered pin into the limiting hole; the wing is finely adjusted in multiple degrees of freedom by the first lifting adjustment module and the multi-directional displacement module to dock the wing with the fuselage; after docking and installation, the first mounting bracket is separated from the wing, and the installation slider is pushed to slide along the slide rail to the non-dock installation position. The inner motor is hoisted to the inner motor arm positioning assembly, and the inner motor is positioned and supported by the inner motor positioning plate, so as to position the connecting joint of the inner motor arm to the target installation position. The tail wing is clamped to the tail wing mounting module, and the height of the tail wing is adjusted using the second lift adjustment module. The co-reaming tool is fed from the second drill sleeve toward the first drill sleeve. The first and second drill sleeves are used to synchronously limit and guide the front and rear guide sections. The co-reaming is performed on the joint connecting the tail fin and the inner motor arm.