CN112340054B - Multi-axis main follow-up attitude adjusting method and attitude adjusting device for large part of airplane - Google Patents
Multi-axis main follow-up attitude adjusting method and attitude adjusting device for large part of airplane Download PDFInfo
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- CN112340054B CN112340054B CN202010989504.6A CN202010989504A CN112340054B CN 112340054 B CN112340054 B CN 112340054B CN 202010989504 A CN202010989504 A CN 202010989504A CN 112340054 B CN112340054 B CN 112340054B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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Abstract
The invention provides a multi-axis main follow-up posture adjustment method and a posture adjustment device for a large part of an airplane.
Description
Technical Field
The invention belongs to the technical field of posture adjustment of large parts of aviation airplanes, and particularly relates to a multi-axis main follow-up posture adjustment method and a posture adjustment device for the large parts of airplanes.
Background
With the continuous progress and development of science and technology, the upgrading and upgrading of airplanes and the improvement of the manufacturing level, the airplane assembly technology is provided with high quality, high efficiency and low cost, the airplane assembly technology can meet the production requirements of various products, the demand on the airplane automatic assembly technology is more and more strong, and the realization of the digital and automatic assembly of civil airplanes has necessary technical foundation due to the leap development of various new assembly process technologies and computer technologies. Aviation enterprises in advanced countries have developed and applied airplane digitalization and automation assembly technology to the development and production of various civil airplanes, and remarkable effect is achieved, but the problem that continuous perfection and simplification are needed is to ensure that large parts of airplanes are not subjected to external stress and the assembly quality of products through multi-axis cooperative motion in the digital attitude adjusting process.
Disclosure of Invention
Aiming at the requirements of the prior art, the invention provides a multi-axis main follow-up posture adjusting method and a posture adjusting device for a large part of an airplane.
The specific implementation content of the invention is as follows:
the invention provides a multi-axis main follow-up attitude adjusting method for a large part of an airplane, which is based on a multi-axis main follow-up attitude adjusting device for the large part of the airplane and realizes multi-axis main follow-up attitude adjusting through the linkage of motion axes of two numerical control locators in a numerical control locator No. 1, a numerical control locator No. 2, a numerical control locator No. 3 and a numerical control locator No. 4; the method specifically comprises the following steps:
when the airplane large component moves in the X-axis direction, the No. 2 numerical control positioner and the No. 4 numerical control positioner are controlled to move in the X-axis direction to drive the No. 1 numerical control positioner and the No. 3 numerical control positioner to move in the X-axis direction, and the Z motion axis and the Y motion axis of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are kept still; ensuring that two of the four numerical control positioners are linked in the X-axis direction and follow up in the X-axis direction;
when the large part of the airplane moves in the Y-axis direction, the No. 1 numerical control positioner and the No. 2 numerical control positioner are controlled to move in the Y-motion-axis direction to drive the No. 3 numerical control positioner and the No. 4 numerical control positioner to move in the Y-motion-axis direction, and the rest motion axes of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are kept still;
when the large part of the airplane moves in the Z-axis direction, the Z motion axes of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are controlled to move, and the X motion axis and the Y motion axis of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are kept still;
when a large part of the airplane rotates around the X-axis direction, the No. 1 numerical control positioner and the No. 2 numerical control positioner are controlled to move in the Z motion axis direction to drive the No. 3 numerical control positioner and the No. 4 numerical control positioner to follow up in the Y motion axis direction, and the rest motion axes of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are kept still;
when a large part of the airplane rotates around the Y-axis direction, the No. 2 numerical control positioner and the No. 4 numerical control positioner are controlled to move in the Z motion axis direction to drive the No. 1 numerical control positioner and the No. 3 numerical control positioner to follow up in the X motion axis direction, and the rest motion axes of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are kept still;
when the large part of the airplane is rotated around the Z-axis direction for posture adjustment, the XYZ motion axes of the No. 2 numerical control positioner are kept still, and the posture adjustment is carried out through the motion of the No. 4 numerical control positioner in the X motion axis direction and the motion of the No. 1 numerical control positioner in the Y motion axis direction.
The invention also provides a multi-axis main follow-up attitude adjusting method for the large airplane component, based on the multi-axis main follow-up attitude adjusting device for the large airplane component, when the large airplane component moves in the X-axis direction, the numerical control positioner No. 2 and the numerical control positioner No. 4 are controlled to move in the X-axis direction to drive the numerical control positioner No. 1 and the numerical control positioner No. 3 to move in the X-axis direction, and the Z motion axis and the Y motion axis of the numerical control positioner No. 1, the numerical control positioner No. 2, the numerical control positioner No. 3 and the numerical control positioner No. 4 are kept still.
The invention also provides a multi-axis main follow-up attitude adjusting method for the large airplane component, based on the multi-axis main follow-up attitude adjusting device for the large airplane component, when the large airplane component moves in the Y-axis direction, the numerical control positioner No. 1 and the numerical control positioner No. 2 are controlled to move in the Y-axis direction to drive the numerical control positioner No. 3 and the numerical control positioner No. 4 to move in the Y-axis direction, and the rest of the movement axes of the numerical control positioner No. 1, the numerical control positioner No. 2, the numerical control positioner No. 3 and the numerical control positioner No. 4 are kept still.
The invention also provides a multi-axis main follow-up attitude adjusting method for the large airplane component, which is based on the multi-axis main follow-up attitude adjusting device for the large airplane component, and is used for controlling the Z motion axis motion of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner and keeping the X motion axis and the Y motion axis of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner still when the large airplane component moves in the Z axis direction.
The invention also provides a large-part multi-axis main follow-up attitude adjusting method for the airplane, based on the large-part multi-axis main follow-up attitude adjusting device for the airplane, when the large part of the airplane rotates around the X-axis direction, the No. 1 numerical control positioner and the No. 2 numerical control positioner are controlled to move in the Z movement axis direction to drive the No. 3 numerical control positioner and the No. 4 numerical control positioner to follow up in the Y movement axis direction, and the rest movement axes of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are kept still.
The invention also provides a multi-axis main follow-up attitude adjusting method for the large airplane component, based on the multi-axis main follow-up attitude adjusting device for the large airplane component, when the large airplane component rotates around the Y-axis direction, the No. 2 numerical control positioner and the No. 4 numerical control positioner are controlled to move in the Z movement axis direction to drive the No. 1 numerical control positioner and the No. 3 numerical control positioner to follow up in the X movement axis direction, and the rest movement axes of the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are kept still.
The invention also provides a multi-axis main follow-up attitude adjusting method for the large part of the airplane, based on the multi-axis main follow-up attitude adjusting device for the large part of the airplane, when the large part of the airplane is rotated around the Z-axis direction for attitude adjustment, the XYZ motion axes of the No. 2 numerical control positioner are kept motionless, and attitude adjustment is realized through the motion of the No. 4 numerical control positioner in the X motion axis direction and the motion of the No. 1 numerical control positioner in the Y motion axis direction and the 2-axis linkage.
In order to better implement the present invention, further, the movement distances of the numerical control positioner No. 4 in the X movement axis direction and the numerical control positioner No. 1 in the Y movement axis direction are respectively set as
And
：
the described
And
satisfies the relationship:
wherein:
the distance between the No. 1 numerical control positioner and the No. 2 numerical control positioner is the ball head distance;
The invention also provides a multi-axis main follow-up posture adjusting device for the large part of the airplane, which is used for adjusting the posture of the large part of the airplane and closing the large part of the airplane and comprises an integral framework, and a lower positioning adjusting component, an upper positioning adjusting component and a positioning checking component which are arranged on the integral framework;
the integral framework is of a frame panel structure, the lower positioning adjusting assembly is arranged on the frame panel structure, and the upper positioning adjusting assembly comprises upper positioning adjusting frame bodies which are distributed on two sides of the frame panel structure in pairs and upper adjusting numerical control positioners which are respectively arranged on the upper positioning adjusting frame bodies and used for adjusting the posture; the upper adjusting numerical control positioner can move in the directions of XYZ three axes;
the positioning and checking assembly comprises a 24-frame positioning and checking assembly for performing positioning and checking detection on the lower positioning and adjusting assembly and a 1-frame positioning and checking assembly for performing positioning and checking detection on the upper positioning and adjusting assembly;
the upper adjusting numerical control positioner comprises a No. 1 numerical control positioner positioned at the front section of the left side of the integral framework, a No. 3 numerical control positioner positioned at the rear section of the left side of the integral framework, a No. 2 numerical control positioner positioned at the front section of the right side of the integral framework and a No. 4 numerical control positioner positioned at the rear section of the right side of the integral framework;
and the No. 1 numerical control positioner, the No. 2 numerical control positioner, the No. 3 numerical control positioner and the No. 4 numerical control positioner are all provided with a ball head and a ball socket for mounting the ball head.
In order to better implement the invention, further, the lower positioning adjustment assembly further comprises a 23-frame positioning adjustment assembly, a 9-frame positioning adjustment assembly and a 1-frame positioning adjustment assembly; the 23-frame positioning adjusting component, the 9-frame positioning adjusting component and the 1-frame positioning adjusting component are arranged on the integral framework and are of structures capable of being adjusted in an up-and-down lifting manner;
still include sliding guide, sliding guide installs on whole skeleton, just 24 location inspection subassemblies pass through sliding guide and realize the sliding connection with whole skeleton.
Compared with the prior art, the invention has the following advantages and beneficial effects:
the large parts of the airplane are protected from external stress, and the assembly quality of the product is ensured.
Drawings
FIG. 1 is a schematic view of a numerically controlled positioner;
FIG. 2 is a schematic view of the present invention in angular alignment about the X-axis and Y-axis;
FIG. 3 is a schematic view of the attitude adjustment around the Z-axis direction;
FIG. 4 is a schematic view of the apparatus of the present invention;
FIG. 5 is a schematic view of an upper positioning adjustment assembly;
FIG. 6 is a schematic view of a lower positioning adjustment assembly.
Wherein: 1. the whole framework, 2, 24 frames of positioning and checking components, 3, lower positioning and adjusting components, 4, upper positioning and adjusting components, 5, 1 frame of positioning and adjusting components, 6, upper adjusting numerical control locators, 7, sliding guide rails, 8, 23 frames of positioning and adjusting components, 9 frames of positioning and adjusting components, 10, 1 frame of positioning and adjusting components, 11, 1 number of numerical control locators, 12, 2 number of numerical control locators, 13, 3 number of numerical control locators, 14, 4 number of numerical control locators, 15, ball sockets, 16, ball heads, 17 and airplane large components.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "disposed," "connected" or "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1:
the invention provides a multi-axis main follow-up attitude adjusting method for a large part of an airplane, which is based on a multi-axis main follow-up attitude adjusting device for the large part of the airplane as shown in a figure 1, a figure 2 and a figure 3, and realizes multi-axis main follow-up attitude adjusting through the linkage of motion axes of two numerical control positioners in a number 1 numerical control positioner 11, a number 2 numerical control positioner 12, a number 3 numerical control positioner 13 and a number 4 numerical control positioner 14; the method specifically comprises the following steps:
when the airplane large component 17 moves in the X-axis direction, the No. 2 numerical control positioner 12 and the No. 4 numerical control positioner 14 are controlled to move in the X-axis direction to drive the No. 1 numerical control positioner 11 and the No. 3 numerical control positioner 13 to move in the X-axis direction, and the Z motion axis and the Y motion axis of the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 are kept still; ensuring that two of the four numerical control positioners are linked in the X-axis direction and follow up in the X-axis direction;
when the airplane large component 17 moves in the Y-axis direction, the No. 1 numerical control positioner 11 and the No. 2 numerical control positioner 12 are controlled to move in the Y-motion-axis direction to drive the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 to move in the Y-motion-axis direction, and the rest motion axes of the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 are kept still;
when the large part 17 of the airplane moves in the Z-axis direction, the Z motion axis motion of the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 is controlled, and the X motion axis and the Y motion axis of the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 are kept still;
when the airplane large component 17 rotates around the X-axis direction, the No. 1 numerical control positioner 11 and the No. 2 numerical control positioner 12 are controlled to move in the Z motion axis direction to drive the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 to follow up in the Y motion axis direction, and the rest motion axes of the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 are kept still;
when the airplane large component 17 rotates around the Y-axis direction, the No. 2 numerical control positioner 12 and the No. 4 numerical control positioner 14 are controlled to move in the Z motion axis direction to drive the No. 1 numerical control positioner 11 and the No. 3 numerical control positioner 13 to follow up in the X motion axis direction, and the rest motion axes of the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 are kept still;
when the airplane large component 17 is rotated around the Z-axis direction for posture adjustment, the XYZ motion axes of the No. 2 numerical control positioner 12 are kept still, and the posture adjustment is carried out through the movement of the No. 4 numerical control positioner 14 in the X motion axis direction and the movement of the No. 1 numerical control positioner 11 in the Y motion axis direction.
Example 2:
as shown in fig. 2, when the large aircraft component 17 is moved in the X-axis direction, the numerical control locators 12 and 14 No. 2 are controlled to move in the X-axis direction to drive the numerical control locators 11 and 13 No. 1 to move in the X-axis direction, and the Z-axis and Y-axis of the numerical control locators 11 No. 1, 12 No. 2, 13 No. 4 and 14 No. 1 are kept still.
Example 3:
as shown in fig. 2, when the large aircraft component 17 is moved in the Y-axis direction, the numerical control positioner No. 1 11 and the numerical control positioner No. 2 12 are controlled to move in the Y-axis direction to drive the numerical control positioner No. 3 13 and the numerical control positioner No. 4 14 to move in the Y-axis direction, and the rest of the movement axes of the numerical control positioner No. 1 11, the numerical control positioner No. 2, the numerical control positioner No. 3, and the numerical control positioner No. 4 14 remain stationary.
Example 4:
the embodiment further provides an airplane large component multi-axis main follow-up posture adjustment method, as shown in fig. 3, based on the airplane large component multi-axis main follow-up posture adjustment device, when the airplane large component 17 is moved in the Z-axis direction, the Z motion axis motion of the numerical control locators 11 No. 1, 12 No. 2, 13 No. 3 and 14 No. 4 is controlled, and the X motion axis and the Y motion axis of the numerical control locators 11 No. 1, 12 No. 2, 13 and 14 No. 4 are kept motionless.
Example 5:
the embodiment also provides an airplane large component multi-axis main follow-up posture adjusting method, based on the airplane large component multi-axis main follow-up posture adjusting device, when the airplane large component 17 rotates around the X-axis direction, the number 1 numerical control positioner 11 and the number 2 numerical control positioner 12 are controlled to move in the Z movement axis direction to drive the number 3 numerical control positioner 13 and the number 4 numerical control positioner 14 to follow up in the Y movement axis direction, and the rest movement axes of the number 1 numerical control positioner 11, the number 2 numerical control positioner 12, the number 3 numerical control positioner 13 and the number 4 numerical control positioner 14 are kept motionless.
Example 6:
the embodiment also provides an airplane large component multi-axis main follow-up posture adjusting method, based on the airplane large component multi-axis main follow-up posture adjusting device, when the airplane large component 17 rotates around the Y-axis direction, the No. 2 numerical control positioner 12 and the No. 4 numerical control positioner 14 are controlled to move in the Z movement axis direction to drive the No. 1 numerical control positioner 11 and the No. 3 numerical control positioner 13 to follow up in the X movement axis direction, and the rest movement axes of the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 are kept still.
Example 7:
the embodiment also provides an airplane large component multi-axis main follow-up posture adjustment method, based on the airplane large component multi-axis main follow-up posture adjustment device, when the airplane large component 17 is rotated around the Z-axis direction for posture adjustment, the XYZ motion axes of the No. 2 numerical control positioner 12 are kept motionless, and posture adjustment is realized through the movement of the No. 4 numerical control positioner 14 in the X motion axis direction and the movement of the No. 1 numerical control positioner 11 in the Y motion axis direction, and 2 axes are linked.
In order to better implement the present invention, further, it is assumed that the movement distances of the numerical control positioner No. 4 in the X movement axis direction and the numerical control positioner No. 1 in the Y movement axis direction are respectivelyIs composed of
And
：
the above-mentioned
And
satisfies the relationship:
wherein:
the distance between the No. 1 numerical control positioner and the No. 2 numerical control positioner is the ball head distance;
Example 8:
the embodiment also provides a multi-axis main follow-up posture adjusting device for large airplane components, which is used for adjusting and closing the posture of a large airplane component 17 as shown in fig. 4, 5 and 6, and comprises an integral framework 1, and a lower positioning adjusting component 3, an upper positioning adjusting component 4 and a positioning checking component which are arranged on the integral framework 1;
the integral framework 1 is of a frame panel structure, the lower positioning adjusting assembly 3 is arranged on the frame panel structure, and the upper positioning adjusting assembly 4 comprises upper positioning adjusting frame bodies which are distributed on two sides of the frame panel structure in pairs and upper adjusting numerical control positioners 6 which are respectively arranged on the upper positioning adjusting frame bodies and used for adjusting the posture; the upper adjusting numerical control positioner 6 can move in the directions of XYZ three axes;
the positioning and checking assembly comprises a 24-frame positioning and checking assembly 2 for performing positioning, checking and detecting on the lower positioning and adjusting assembly 3 and a 1-frame positioning and checking assembly 5 for performing positioning, checking and detecting on the upper positioning and adjusting assembly 4;
the upper adjusting numerical control positioner 6 comprises a No. 1 numerical control positioner 11 positioned at the front section of the left side of the integral framework 1, a No. 3 numerical control positioner 13 positioned at the rear section of the left side of the integral framework 1, a No. 2 numerical control positioner 12 positioned at the front section of the right side of the integral framework 1 and a No. 4 numerical control positioner 14 positioned at the rear section of the right side of the integral framework 1;
the No. 1 numerical control positioner 11, the No. 2 numerical control positioner 12, the No. 3 numerical control positioner 13 and the No. 4 numerical control positioner 14 are all provided with a ball head 16 and a ball socket 15 for mounting the ball head 16.
In order to better implement the present invention, further, the lower positioning adjustment assembly 3 further includes 23 frame positioning adjustment assemblies 8, 9 frame positioning adjustment assemblies 9, 1 frame positioning adjustment assembly 10; the 23-frame positioning adjusting assembly 8, the 9-frame positioning adjusting assembly 9 and the 1-frame positioning adjusting assembly 10 are installed on the integral framework 1 and can be adjusted in an up-down lifting mode.
In order to better implement the invention, the positioning and checking device further comprises a sliding guide rail 7, wherein the sliding guide rail 7 is installed on the integral framework 1, and the 24-frame positioning and checking assembly 2 is in sliding connection with the integral framework 1 through the sliding guide rail 7.
The working principle is as follows: in the process of upper and lower involution, the lower part is accurately adjusted and positioned through the lower positioning adjusting component 3, and then the upper part and the lower part are accurately and automatically involuted through the upper positioning adjusting component 4.
The integral framework 1 is formed by welding square steel to form an upper and lower involution integral rigid body, so that the standard unification of a large part involution system is ensured, and the foundation reformation is avoided.
The integral framework 1 is connected with the ground of a factory through series of leveling foundation screws and is guaranteed to be horizontal.
The integral framework 1 ensures integrity between the locators.
As shown in fig. 4, 5 and 6, the upper positioning adjustment assembly 4 includes an upper adjustment numerically controlled positioner 6, so as to realize upper automatic adjustment and lower involution.
The upper numerical control positioners are 4 groups in total and can respectively realize linear motion in X/Y/Z directions.
As shown in fig. 5, the lower positioning adjustment assembly 3 includes 23 frame adjustment assemblies 8, 9 frame adjustment assemblies 9, and 1 frame adjustment assembly 10, and adopts purely mechanical attitude adjustment to realize lower attitude adjustment.
The 24-frame positioning inspection assembly 2 slides through the slide guide 7.
The 23-frame adjusting components 8, 9-frame adjusting components 9 and 1-frame adjusting component 10 realize the support and adjustment of the lower part.
The 23-frame adjusting assemblies 8, 9-frame adjusting assemblies 9 and 1-frame adjusting assembly 10 realize position adjustment through a spiral structure.
The 1-frame positioning inspection component 5 not only realizes the positioning of the frame, but also completes the inspection of the 1-frame posture.
The 24-frame positioning inspection assembly 2 performs both frame positioning and 24-frame pose inspection.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (2)
1. A multi-axis main follow-up posture adjusting device for large airplane components is used for adjusting and closing the postures of the large airplane components (17), and is characterized by comprising an integral framework (1), and a lower positioning adjusting component (3), an upper positioning adjusting component (4) and a positioning checking component which are arranged on the integral framework (1);
the integral framework (1) is of a frame panel structure, the lower positioning adjusting assembly (3) is arranged on the frame panel structure, and the upper positioning adjusting assembly (4) comprises upper positioning adjusting frame bodies which are distributed on two sides of the frame panel structure in pairs and upper adjusting numerical control positioners (6) which are respectively arranged on the upper positioning adjusting frame bodies and used for adjusting the posture; the upper adjusting numerical control positioner (6) can move in the directions of XYZ three axes;
the positioning and checking assembly comprises a 24-frame positioning and checking assembly (2) for performing positioning, checking and detecting on the lower positioning and adjusting assembly (3) and a 1-frame positioning and checking assembly (5) for performing positioning, checking and detecting on the upper positioning and adjusting assembly (4);
the upper adjusting numerical control positioner (6) comprises a No. 1 numerical control positioner (11) positioned at the front section of the left side of the integral framework (1), a No. 3 numerical control positioner (13) positioned at the rear section of the left side of the integral framework (1), a No. 2 numerical control positioner (12) positioned at the front section of the right side of the integral framework (1) and a No. 4 numerical control positioner (14) positioned at the rear section of the right side of the integral framework (1);
the No. 1 numerical control positioner (11), the No. 2 numerical control positioner (12), the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) are respectively provided with a ball head (16) and a ball socket (15) for mounting the ball head (16);
based on the airplane large component multi-axis main follow-up attitude adjusting device, the following operations are carried out:
the multi-axis main follow-up posture adjustment is realized through the linkage of the motion axes of two numerical control positioners in a No. 1 numerical control positioner (11), a No. 2 numerical control positioner (12), a No. 3 numerical control positioner (13) and a No. 4 numerical control positioner (14); the method specifically comprises the following steps:
when an airplane large component (17) moves in the X-axis direction, a No. 2 numerical control positioner (12) and a No. 4 numerical control positioner (14) are controlled to move in the X-motion-axis direction to drive a No. 1 numerical control positioner (11) and a No. 3 numerical control positioner (13) to move in the X-motion-axis direction, and the Z motion axis and the Y motion axis of the No. 1 numerical control positioner (11), the No. 2 numerical control positioner (12), the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) are kept still; ensuring that two of the four numerical control positioners are linked in the X-axis direction and follow up in the X-axis direction;
when an airplane large component (17) moves in the Y-axis direction, a No. 1 numerical control positioner (11) and a No. 2 numerical control positioner (12) are controlled to move in the Y-motion-axis direction to drive a No. 3 numerical control positioner (13) and a No. 4 numerical control positioner (14) to move in the Y-motion-axis direction, and the rest motion axes of the No. 1 numerical control positioner (11), the No. 2 numerical control positioner (12), the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) are kept still;
when the large part (17) of the airplane moves in the Z-axis direction, the Z motion axes of the No. 1 numerical control positioner (11), the No. 2 numerical control positioner (12), the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) are controlled to move, and the X motion axis and the Y motion axis of the No. 1 numerical control positioner (11), the No. 2 numerical control positioner (12), the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) are kept still;
when an airplane large component (17) rotates around the X-axis direction, the No. 1 numerical control positioner (11) and the No. 2 numerical control positioner (12) are controlled to move in the Z motion axis direction to drive the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) to follow up in the Y motion axis direction, and the rest motion axes of the No. 1 numerical control positioner (11), the No. 2 numerical control positioner (12), the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) are kept still;
when an airplane large component (17) rotates around the Y-axis direction, the No. 2 numerical control positioner (12) and the No. 4 numerical control positioner (14) are controlled to move in the Z motion axis direction to drive the No. 1 numerical control positioner (11) and the No. 3 numerical control positioner (13) to follow the X motion axis direction, and the rest motion axes of the No. 1 numerical control positioner (11), the No. 2 numerical control positioner (12), the No. 3 numerical control positioner (13) and the No. 4 numerical control positioner (14) are kept still;
when the airplane large component (17) is rotated around the Z-axis direction to adjust the posture, the XYZ motion axis of the No. 2 numerical control positioner (12) is kept still, and the posture is adjusted by the movement of the No. 4 numerical control positioner (14) in the X motion axis direction and the movement of the No. 1 numerical control positioner (11) in the Y motion axis direction.
2. The aircraft large component multi-axis main follow-up attitude adjusting device according to claim 1, wherein the lower positioning adjustment assembly (3) further comprises 23 frames of positioning adjustment assemblies (8), 9 frames of positioning adjustment assemblies (9) and 1 frame of positioning adjustment assemblies (10); the 23-frame positioning adjusting component (8), the 9-frame positioning adjusting component (9) and the 1-frame positioning adjusting component (10) are arranged on the integral framework (1) and are of a structure capable of being adjusted by lifting up and down;
still include sliding guide (7), sliding guide (7) are installed on whole skeleton (1), just 24 frame location inspection subassembly (2) realize through sliding guide (7) with the sliding connection of whole skeleton (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010989504.6A CN112340054B (en) | 2020-09-18 | 2020-09-18 | Multi-axis main follow-up attitude adjusting method and attitude adjusting device for large part of airplane |
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