CN220764704U - Assembly mechanism capable of rapidly adjusting installation posture of airplane - Google Patents
Assembly mechanism capable of rapidly adjusting installation posture of airplane Download PDFInfo
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- CN220764704U CN220764704U CN202322337708.3U CN202322337708U CN220764704U CN 220764704 U CN220764704 U CN 220764704U CN 202322337708 U CN202322337708 U CN 202322337708U CN 220764704 U CN220764704 U CN 220764704U
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- 238000009434 installation Methods 0.000 title claims abstract description 14
- 238000001514 detection method Methods 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 238000000034 method Methods 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000003028 elevating effect Effects 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
Abstract
The utility model discloses an assembly mechanism capable of quickly adjusting the installation posture of an airplane, which comprises the following components: frame main part, fuselage bracket, fixed connection pole, adjustment mechanism, the fuselage bracket liftable set up in on the frame main part, adjustment mechanism drives fixed connection pole go up and down and translational motion in the frame main part for the fixed connection pole is connected with the joint in the aircraft, in order to fix the aircraft on the frame main part. Through the mode, the assembly mechanism capable of rapidly adjusting the mounting posture of the aircraft can rapidly and accurately adjust the posture of the aircraft in the assembly process, improves the accuracy and the working efficiency of the assembly of the aircraft, improves the universality of the assembly mechanism and reduces the production cost.
Description
Technical Field
The utility model relates to the technical field of aviation equipment, in particular to an assembly mechanism capable of quickly adjusting the installation posture of an aircraft.
Background
Currently, in the manufacturing process of an aircraft (airplane), an assembly bench is required to fix a fuselage and a wing so as to facilitate the subsequent assembly.
However, the conventional assembly jig has the following problems:
(1) The universality is poor, flexible conversion or use between products of different types is difficult, different assembly benches are required to be prepared to meet different installation requirements, and the production cost is greatly increased;
(2) The traditional tool rack is not provided with a horizontal and angle accurate installation indicating device, so that the problems of poor assembly precision, long assembly time and the like are easily caused, and the productivity and economic benefits are directly influenced;
(3) The traditional tool rack needs to be recalibrated before the second assembly, the calibration procedure is complex, and the time cost is high.
Disclosure of Invention
The assembly mechanism capable of quickly adjusting the installation posture of the aircraft has the advantages of high reliability, accurate positioning, compact structure and the like, and has wide market prospect in the application and popularization of aviation equipment.
In order to solve the technical problems, the utility model adopts a technical scheme that:
the utility model provides a but assembly devices of quick adjustment aircraft installation gesture, it includes: the frame body, the frame bracket, the fixed connecting rod and the adjusting mechanism are arranged on the frame body in a lifting way, the adjusting mechanism drives the fixed connecting rod to lift and move in a translational way on the frame body, so that the fixed connecting rod is connected with a joint in the aircraft to fix the aircraft on the frame body,
the adjusting mechanism comprises a sliding seat, a horizontal adjusting handle, a horizontal adjusting screw rod, a horizontal screw rod connecting seat, a lifting adjusting handle, a lifting adjusting screw rod, a lifting screw rod connecting seat, a color difference sensor and a color difference sensing belt, wherein the sliding seat is movably arranged on a frame main body, the horizontal adjusting handle is rotatably arranged on the side wall of the sliding seat, one end of the horizontal adjusting screw rod is rotatably connected with the horizontal screw rod connecting seat on the frame main body, the other end of the horizontal adjusting screw rod penetrates through the sliding seat and is in threaded connection with the horizontal adjusting handle, and the horizontal adjusting handle is matched with the horizontal adjusting screw rod to drive the sliding seat to horizontally move on the frame main body; the two ends of the fixed connecting rod are respectively connected with a lifting screw rod connecting seat, the lifting adjusting handle is rotatably arranged at the top of the sliding seat, the lifting adjusting screw rod is in threaded connection with the lifting adjusting handle, the top of the lifting adjusting screw rod is rotatably connected with the lifting screw rod connecting seats, and the lifting adjusting handle is matched with the lifting adjusting screw rod to drive the fixed connecting rod to move in a lifting manner; the color difference sensor is arranged on the sliding seat, and a color difference sensing belt matched with the color difference sensor for detection is arranged on the horizontal adjusting screw rod and the lifting adjusting screw rod.
In a preferred embodiment of the present utility model, the bracket elevating screw is screwed to the frame body, and the upper end thereof is rotatably connected to the bottom of the body bracket, so that the body bracket is driven to elevate by the rotation of the bracket elevating screw.
In a preferred embodiment of the present utility model, the bracket lifting screw is provided with an adjusting turntable to drive the bracket lifting screw to rotate.
In a preferred embodiment of the utility model, the fuselage tray comprises a tray and a contoured tray removably disposed on the tray.
In a preferred embodiment of the present utility model, the frame body is provided with a guide rail, and the sliding seat is slidably connected with the guide rail through a sliding block.
In a preferred embodiment of the present utility model, guide rails are disposed on both sides of the sliding seat.
In a preferred embodiment of the present utility model, the lifting screw rod connecting seat is provided with a horizontal angle gauge.
In a preferred embodiment of the present utility model, the screw is rotatably connected to the screw connection base by a ball bearing.
The beneficial effects of the utility model are as follows: the attitude of the aircraft in the assembly process can be quickly and accurately adjusted, the assembly accuracy and the working efficiency of the aircraft are improved, the universality of the assembly mechanism is improved, and the production cost is reduced.
Drawings
For a clearer description of the technical solutions of the embodiments of the present utility model, the drawings that are needed in the description of the embodiments will be briefly introduced below, it being obvious that the drawings in the description below are only some embodiments of the present utility model, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art, wherein:
FIG. 1 is a schematic view of a mounting mechanism for rapidly adjusting the mounting attitude of an aircraft according to a preferred embodiment of the present utility model;
FIG. 2 is a schematic partial structural view of a preferred embodiment of an assembly mechanism for rapidly adjusting the mounting attitude of an aircraft according to the present utility model.
Detailed Description
The following description of the technical solutions in the embodiments of the present utility model will be clear and complete, and it is obvious that the described embodiments are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-2, an embodiment of the present utility model includes:
the utility model provides an assembly devices of but quick adjustment aircraft installation gesture for the installation of EVTOL fuselage has been proposed and ability that possesses quick adjustment aircraft fuselage pitch angle and levelness, height is included in its structure: the frame body 1, the frame body bracket 2, the fixed connecting rod 3 and the adjusting mechanism 4 play an auxiliary supporting role, the frame body bracket can be lifted and arranged on the frame body, and the adjusting mechanism drives the fixed connecting rod to lift and move in a translational mode on the frame body, so that the fixed connecting rod is connected with a joint in an airplane to fix the airplane on the frame body.
Further preferably, the bracket lifting screw 5 is in threaded connection with the frame body, and the upper end of the bracket lifting screw is rotatably connected with the bottom of the body bracket, and the body bracket is driven to move up and down by the rotation of the bracket lifting screw.
Further preferably, an adjusting turntable 6 is arranged on the bracket lifting screw to drive the bracket lifting screw to rotate.
Further preferably, the machine body bracket comprises a tray 21 and a profiling bracket 22, the profiling bracket is fixed on the tray through bolts, and the profiling brackets with different shapes can be replaced after the fixing bolts are disassembled, so that different use requirements are met.
The adjusting mechanism comprises a sliding seat 41, a horizontal adjusting handle 42, a horizontal adjusting screw 43, a horizontal screw connecting seat 44, a lifting adjusting handle 45, a lifting adjusting screw 46, a lifting screw connecting seat 47, a color difference sensor 48 and a color difference sensing belt.
The sliding seat is movably arranged on the frame main body, the horizontal adjusting handle is rotatably arranged on the side wall of the sliding seat, one end of the horizontal adjusting screw rod is rotatably connected with the horizontal screw rod connecting seat on the frame main body, and the other end of the horizontal adjusting screw rod penetrates through the sliding seat and is in threaded connection with the nut 49 on the horizontal adjusting handle, so that the horizontal adjusting handle and the horizontal adjusting screw rod are matched to drive the sliding seat to move horizontally and horizontally on the frame main body.
The two ends of the fixed connecting rod are respectively connected with one lifting screw rod connecting seat, the lifting adjusting handle is rotationally arranged at the top of the sliding seat, the lifting adjusting screw rod is in threaded connection with a nut on the lifting adjusting handle, and the top of the lifting adjusting screw rod is in rotatable connection with the lifting screw rod connecting seat, so that the lifting adjusting handle and the lifting adjusting screw rod are matched to drive the fixed connecting rod to move up and down, and the translation and lifting of the fixed connecting rod are realized.
The color difference sensor is arranged on the sliding seat, and a color difference sensing belt matched with the color difference sensor for detection is arranged on the horizontal adjusting screw rod and the lifting adjusting screw rod.
Further preferably, the frame body is provided with a guiding sliding rail 410, and the sliding seat is slidably connected with the guiding sliding rail through a sliding block, so as to improve the accuracy of the translational movement.
Further preferably, guide sliding rails are arranged on two sides of the sliding seat.
Further preferably, the lifting screw rod connecting seat is provided with a horizontal angle meter 7 for checking the space attitude of the aircraft. The level angle meter has the function of displaying information such as parallelism and angle.
When the device is used, the height of the body bracket is adjusted according to the size specification of the body wing so as to fix the body wing, the horizontal position and the vertical height of the fixed connecting rods are adjusted by utilizing the adjusting mechanism, so that the levelness and the relative vertical height of the body wing are adjusted to proper positions, meanwhile, the relative vertical height positions of the front fixed connecting rod and the rear fixed connecting rod are cooperatively adjusted by the lifting adjusting handle, so that the pitch angle of the body is adjusted, in addition, the fixed connecting rods have certain elasticity or the fixed connecting rods are of a sectional structure (one lifting screw connecting seat is provided with one section of rod body, and the two sections of rod bodies can be not contacted or movably/elastically connected), so that the roll angle of the body can be cooperatively adjusted by respectively adjusting the height of each rod body; the space attitude of the aircraft is checked through the horizontal angle meter, so that the positioning of the aircraft body can be completed on the basis of taking the space reference coordinate point of the aircraft as a reference, the assembly accuracy and the working efficiency are improved, and meanwhile, in the later iteration, even if the design angle is changed, the mechanism can be repeatedly used, the repeated utilization rate and the universality of the rack are improved, and the cost is reduced. When the position is adjusted for the first time, the corresponding position is marked by the color difference induction belt, and the color difference sensor is utilized for recording, so that the posture of the machine body can be quickly adjusted by utilizing the color difference induction belt when the machine body is installed next time, the capability of quickly checking the mounting point precision of the tool for the second time is provided, and the time cost of tool checking is reduced.
The assembly mechanism capable of quickly adjusting the installation posture of the aircraft has the beneficial effects that:
1. the universality of the assembly mechanism is improved, and the production cost is reduced;
2. the assembly fixture can be calibrated rapidly and with low cost, and the calibration efficiency is improved;
3. the attitude of the aircraft in the assembly process can be quickly and accurately adjusted, the assembly accuracy and the working efficiency of the aircraft are improved, and the productivity is improved.
The foregoing description is only illustrative of the present utility model and is not intended to limit the scope of the utility model, and all equivalent structures or equivalent processes or direct or indirect application in other related arts are included in the scope of the present utility model.
Claims (8)
1. An assembly mechanism capable of rapidly adjusting the installation posture of an aircraft, comprising: the frame body, the frame bracket, the fixed connecting rod and the adjusting mechanism are arranged on the frame body in a lifting way, the adjusting mechanism drives the fixed connecting rod to lift and move in a translational way on the frame body, so that the fixed connecting rod is connected with a joint in the aircraft to fix the aircraft on the frame body,
the adjusting mechanism comprises a sliding seat, a horizontal adjusting handle, a horizontal adjusting screw rod, a horizontal screw rod connecting seat, a lifting adjusting handle, a lifting adjusting screw rod, a lifting screw rod connecting seat, a color difference sensor and a color difference sensing belt, wherein the sliding seat is movably arranged on a frame main body, the horizontal adjusting handle is rotatably arranged on the side wall of the sliding seat, one end of the horizontal adjusting screw rod is rotatably connected with the horizontal screw rod connecting seat on the frame main body, the other end of the horizontal adjusting screw rod penetrates through the sliding seat and is in threaded connection with the horizontal adjusting handle, and the horizontal adjusting handle is matched with the horizontal adjusting screw rod to drive the sliding seat to horizontally move on the frame main body; the two ends of the fixed connecting rod are respectively connected with a lifting screw rod connecting seat, the lifting adjusting handle is rotatably arranged at the top of the sliding seat, the lifting adjusting screw rod is in threaded connection with the lifting adjusting handle, the top of the lifting adjusting screw rod is rotatably connected with the lifting screw rod connecting seats, and the lifting adjusting handle is matched with the lifting adjusting screw rod to drive the fixed connecting rod to move in a lifting manner; the color difference sensor is arranged on the sliding seat, and a color difference sensing belt matched with the color difference sensor for detection is arranged on the horizontal adjusting screw rod and the lifting adjusting screw rod.
2. The assembly mechanism for rapidly adjusting an aircraft mounting attitude according to claim 1, wherein a bracket lifting screw is screwed to the frame body and an upper end thereof is rotatably connected to a bottom of the fuselage bracket to drive the fuselage bracket to move up and down by rotation of the bracket lifting screw.
3. The assembly mechanism capable of quickly adjusting the mounting posture of an aircraft according to claim 2, wherein the bracket lifting screw is provided with an adjusting turntable to drive the bracket lifting screw to rotate.
4. The assembly machine of claim 1, wherein the fuselage cradle comprises a tray and a contoured cradle removably mounted to the tray.
5. The assembly mechanism capable of quickly adjusting the installation posture of an aircraft according to claim 1, wherein the frame body is provided with a guide sliding rail, and the sliding seat is slidably connected with the guide sliding rail through a sliding block.
6. The assembly device for quickly adjusting an aircraft mounting position according to claim 5, wherein guide rails are provided on both sides of the slide base.
7. The assembly mechanism capable of quickly adjusting the installation posture of an aircraft according to claim 1, wherein the lifting screw rod connecting seat is provided with a horizontal angle meter.
8. The assembly mechanism for quickly adjusting the mounting attitude of an aircraft according to claim 1, wherein the screw is rotatably connected to the screw connection base by a ball bearing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322337708.3U CN220764704U (en) | 2023-08-30 | 2023-08-30 | Assembly mechanism capable of rapidly adjusting installation posture of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322337708.3U CN220764704U (en) | 2023-08-30 | 2023-08-30 | Assembly mechanism capable of rapidly adjusting installation posture of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220764704U true CN220764704U (en) | 2024-04-12 |
Family
ID=90601522
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322337708.3U Active CN220764704U (en) | 2023-08-30 | 2023-08-30 | Assembly mechanism capable of rapidly adjusting installation posture of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220764704U (en) |
-
2023
- 2023-08-30 CN CN202322337708.3U patent/CN220764704U/en active Active
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