Cabin clamping and fixing tool for repairing damaged airplane
By designing a three-axis movable gantry cockpit clamping and fixing tooling, the problem of component position offset during aircraft repair is solved, and effective clamping and fixing of cockpit components is achieved to ensure the stability and accuracy of the repair process.
Patent Information
- Application Number
- CN202411907146.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-24
- Publication Date
- 2025-02-25
AI Technical Summary
During the aircraft repair process, a tooling is required that can effectively clamp and fix the aircraft cockpit components to ensure that the components do not deviate in position during installation.
A three-axis movable gantry cockpit clamping and fixing tooling is designed, including a gantry frame, X-axis and Y-axis adjustment beam, hoisting mechanism and protective suspenders. The tooling realizes three-dimensional maneuvering through a three-axis adjustment mechanism, and can adjust the lifting position as needed, and clamp and fix the cockpit member with a C-type clamp.
Effectively clamp and fix the aircraft cockpit components to avoid position movement and ensure the smooth progress of the repair process.
Smart Images
Figure CN119503149A_ABST
Abstract
Description
Technical Field
[0001] The invention belongs to the technical field of aircraft maintenance, and in particular relates to a cockpit clamping and fixing tool for repairing a damaged aircraft. Background Art
[0002] During the repair process of a certain type of aircraft, the aircraft must be kept in a horizontal parking state. During the disassembly and replacement of aircraft cabin components, the installation position of each replacement component must be clamped and fixed, and the position will not be offset due to external forces. Through the analysis of the technical plan for repairing damaged aircraft and the tooling development task book, the tooling required for this aircraft generally includes three types: adjustment tooling, support tooling, and clamping and fixing tooling.
[0003] The main functions of each type of tooling are as follows:
[0004] 1. Adjustment tooling: When adjusting the level of the aircraft, use the tooling with lifting function to complete the height adjustment so that the aircraft reaches a horizontal state.
[0005] 2. Support tooling: It is used to maintain the position of the aircraft after the aircraft is adjusted to the level, and it also plays the role of supporting the main body of the aircraft.
[0006] 3. Clamping and fixing tooling: Clamp and fix the new components at the determined installation position so that their position will not change during the installation process.
[0007] In order to ensure the smooth progress of repairs on a certain type of aircraft, a set of cockpit clamping and fixing tooling for structural damage repair of a certain type of aircraft is urgently needed during the adjustment and clamping work. After the aircraft is adjusted to a level, the cockpit frame beam, rear wall panel, central floor and the upper half of the four frames are clamped and fixed by adjusting the lifting position. Summary of the invention
[0008] In order to solve the above problems existing in the background technology, the present invention provides a cockpit clamping and fixing tool for repairing a damaged aircraft.
[0009] The technical solution adopted by the present invention is as follows:
[0010] A cockpit clamping and fixing tool for repairing a damaged aircraft belongs to a component of the damaged aircraft repair tool. The bottom of the damaged aircraft repair tool is a ground platform. The cockpit clamping and fixing tool is installed on the ground platform and is used to clamp and fix the aircraft cockpit frame beam, rear wall panel, central floor and four frame upper half frames after the aircraft is adjusted to be level.
[0011] The cockpit clamping and fixing tooling is a three-axis movable gantry structure, including a gantry frame 1, an X-axis adjustment beam 3, a Y-axis adjustment beam 2, a lifting mechanism 4 and a protective sling 5; the gantry frame 1 is a detachable structure, a bottom plate is installed at the bottom of the gantry column for fixed connection with the ground platform, and a reinforcing rib plate is arranged between the bottom plate and the gantry column; the Y-axis adjustment beam 2 is provided with two in total, which are installed in parallel between the gantry columns, and the installation height of the two, that is, along the Z-axis direction, can be adjusted according to the actual position requirements; the X-axis adjustment beam 3 is provided with two in total, which are installed in parallel on the two Y-axis adjustment beams 2, and can adjust the installation position along the Y-axis adjustment beam 2, forming an adjustment mechanism for the XY-axis plane, and the X-axis adjustment beam 3 and the Y-axis adjustment beam 2 together form an XYZ three-dimensional mobile structure; the hoisting mechanism 4 is provided in plurality, the top of which is fixedly installed on the X-axis adjustment beam 3, and can adjust the installation position along the X-axis adjustment beam 3, and the bottom is a C-type clamp, which is used to clamp and fix the parts in the cockpit that need to be replaced and positioned at the installation position, and the repair process is ensured to be carried out in sequence by adjusting the hoisting position; the two ends of the protective sling 5 are connected to the crossbeam of the gantry frame 1, and are used to fix the head.
[0012] Beneficial effects of the present invention: As a part of the supporting tooling in the damaged aircraft repair tooling, the present invention can clamp and fix the components in the cockpit that need to be replaced and positioned at the installation position to avoid position movement. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 This is the overall schematic diagram of the damaged aircraft repair tooling.
[0014] Figure 2 This is the axonometric view of the cockpit clamping and fixing fixture.
[0015] Figure 3 Schematic diagram of the cockpit clamping and fixing tooling structure, where (a) is the main view, (b) is the top view, and (c) is the side view.
[0016] Figure 4 Schematic diagram of the stiffener plate.
[0017] Figure 5 Schematic diagrams of a lifting mechanism 4, wherein (a) and (b) are schematic diagrams of two lifting mechanisms 4 with different structures.
[0018] Figure 6 It is a schematic diagram of the fixed installation of the lifting mechanism 4.
[0019] In the figure: 1-gantry frame 1; 2-Y-axis adjustment beam 2; 3-X-axis adjustment beam 3; 4-hoisting mechanism 4; 5-protective lifting belt 5. DETAILED DESCRIPTION
[0020] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the specific implementation methods of the present invention will be described in detail below with reference to the technical solution.
[0021] The present invention provides a cockpit clamping and fixing tool for repairing a damaged aircraft, which belongs to a component of the damaged aircraft repair tool. The bottom of the damaged aircraft repair tool is a ground platform, and the cockpit clamping and fixing tool is installed on the ground platform at the bottom of the damaged aircraft repair tool. Figure 1 The cockpit clamping and fixing tool is a three-axis movable gantry structure, including a gantry frame 1, an X-axis adjustment beam 3, a Y-axis adjustment beam 2, a hoisting mechanism 4 and a protective sling 5. After the assembly is installed, Figure 2 and Figure 3 As shown; the overall inner dimensions of the gantry frame 1 are (3800×3000×4600) mm, and it is made of Q235A / (160×160×12) mm square steel pipes. Each gantry column is connected to the crossbeam by bolts. The entire frame is a detachable structure for easy transportation. A Q235A sheet with a thickness of δ20 mm is installed at the bottom of the gantry column as a bottom plate for fixed connection with the ground platform. Four reinforcing rib plates made of Q235A plates with a thickness of δ12 mm are welded between each bottom plate and the gantry column, such as Figure 4As shown, multiple φ5mm process holes of different heights are processed on the top of the gantry column (drilling is performed according to the actual size of the bolts during installation). After the gantry frame 1 is built, inclined braces can be installed according to the stability. One end of the inclined braces is screwed to the gantry column, and the other end is fastened to the ground platform; there are two Y-axis adjustment beams 2, which are installed in parallel between the gantry columns. The two are made of rectangular steel pipes of Q235A / (200×150×8)mm, and the flange structures made of Q235A / δ12mm steel plates at both ends are fixedly connected to the gantry columns through process holes. By connecting with process holes of different heights, the height along the Z-axis direction can be adjusted according to the actual position requirements. According to the actual working requirements, multiple φ5mm installation holes are prefabricated in the horizontal direction on the Y-axis adjustment beam 2; there are two X-axis adjustment beams 3, which are installed in parallel between the two Y-axis adjustment beams 2 The X-axis adjustment beam 3 and the Y-axis adjustment beam 2 are connected to each other through mounting holes. The mounting position of the Y-axis adjustment beam 2 can be adjusted by connecting different mounting holes to form an adjustment mechanism in the XY-axis plane. The X-axis adjustment beam 3 and the Y-axis adjustment beam 2 together form an XYZ three-dimensional mobile structure. The X-axis adjustment beam 3 is prefabricated with a plurality of φ5mm process holes in the horizontal direction according to the actual working requirements for the installation of the hoisting mechanism 4. The hoisting mechanism 4 is provided with a plurality of them, and the materials are all Q235A steel. The top of the hoisting mechanism 4 is fixedly installed on the process hole of the X-axis adjustment beam 3. The installation position of the X-axis adjustment beam 3 can be adjusted by connecting process holes at different positions. The bottom of the hoisting mechanism 4 is a C-type clamp, which is used to clamp and fix the components that need to be replaced and positioned in the cockpit at the installation position, such as Figure 5 As shown; the protective sling 5 is made of synthetic fiber round sling, which is made of high-strength polyester filament, and has the characteristics of soft texture, light weight, large lifting force, large safety factor, non-conductivity, strong wear resistance, etc. It will not cause scratches on the surface of the aircraft. The two ends of the protective sling 5 are connected to the crossbeam of the gantry frame 1 to fix the nose.
[0022] During installation, when the gantry frame 1 is mounted, all beams and gantry columns of the gantry frame 1 are laser calibrated at any time with reference to the coordinate system after the aircraft is adjusted to be horizontal, to ensure their horizontality and verticality; connect the two ends of the protective sling 5 to the beams of the gantry frame 1, and adjust the length to fix the nose; after the position of the lifting mechanism 4 is determined, drill threaded holes at the corresponding positions of the X-axis, and then use bolts to connect, and the C-type clamps will clamp and fix the parts in the cockpit that need to be replaced and positioned at the installation position, such as Figure 6 shown.
Claims
1. A cockpit clamping and fixing tool for repairing a damaged aircraft, characterized in that: It belongs to the components of the damaged aircraft repair tooling, the bottom of the damaged aircraft repair tooling is a ground platform, and the cockpit clamping and fixing tooling is installed on the ground platform to clamp and fix the aircraft cockpit frame beam, rear wall plate, central floor and the upper half of the four frames after the aircraft is adjusted to the level; The cockpit clamping and fixing tooling comprises a gantry frame (1), an X-axis adjustment beam (3), a Y-axis adjustment beam (2), and a lifting mechanism (4); the bottom of the gantry column of the gantry frame (1) is fixedly connected to the ground platform; two Y-axis adjustment beams (2) are provided, which are installed in parallel between the gantry columns, and the installation heights of the two can be adjusted according to actual position requirements; two X-axis adjustment beams (3) are provided, which are installed in parallel between the two Y-axis adjustment beams (2), and the installation position can be adjusted along the Y-axis adjustment beam (2); a plurality of lifting mechanisms (4) are provided, the top of which is fixedly installed on the X-axis adjustment beam (3), and the installation position can be adjusted along the X-axis adjustment beam (3), and the bottom of which is a C-shaped clamp, which is used to clamp and fix the components in the cockpit that need to be replaced and positioned at the installation position.
2. The cockpit clamping and fixing tool for repairing a damaged aircraft according to claim 1, characterized in that: The gantry frame (1) is a detachable structure.
3. The cockpit clamping and fixing tool for repairing damaged aircraft according to claim 1, characterized in that: A bottom plate is provided at the bottom of the gantry column of the gantry frame (1), which is fixedly connected to the ground platform, and a reinforcing rib plate is provided between the bottom plate and the gantry column.
4. The cockpit clamping and fixing tool for repairing damaged aircraft according to claim 1, characterized in that: A protective sling (5) is connected to the crossbeam of the gantry frame (1) and is used to fix the machine head.
5. The cockpit clamping and fixing tool for repairing damaged aircraft according to claim 4, characterized in that: The protective lifting belt (5) is a synthetic fiber round lifting belt.
6. The cockpit clamping and fixing tool for repairing a damaged aircraft according to claim 1, characterized in that: After the gantry frame (1) is built, diagonal braces can be installed according to the stability conditions. The diagonal braces are fixedly connected to the gantry columns, and the other end is fastened to the ground platform.