CN113051785A - Stress analysis method for jacking point structures of airplane in jacking state - Google Patents
Stress analysis method for jacking point structures of airplane in jacking state Download PDFInfo
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- CN113051785A CN113051785A CN201911387587.5A CN201911387587A CN113051785A CN 113051785 A CN113051785 A CN 113051785A CN 201911387587 A CN201911387587 A CN 201911387587A CN 113051785 A CN113051785 A CN 113051785A
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Abstract
A stress analysis method for each jacking point structure in an airplane jacking state is provided, aiming at the actual scene that the horizontal acceleration is generated due to shaking of an airplane when the airplane is jacked, and therefore, the jacking area structure bears the horizontal load in addition to the vertical load, and the reasonable stress analysis method for each jacking point structure in the airplane jacking state is provided, so that the stress analysis result of the jacking area structure is more accurate.
Description
Technical Field
The invention belongs to the field of application of aviation engineering, relates to a stress analysis method for a jacking point structure of an airplane in a jacking state, and has important significance for reducing the weight of the structure and improving the reasonability and safety of the structural design.
Technical Field
When the airworthiness standard stipulates that the airplane is jacked, the structure is designed to bear vertical load and horizontal load which act on each jacking point independently, and the source and the balance mode of the jacking load are not specified. And generally, only considering the maximum vertical load and the horizontal load of a jacking point and restraining the structure of a jacking area, and performing local stress analysis. According to the experience of actual models, the result of the analysis of the local stress of the jacking point structure is inaccurate.
Disclosure of Invention
Aiming at solving the problem of the accuracy of the stress analysis of the local jacking structure of the airplane, the invention provides a reasonable and accurate stress analysis method of each jacking point structure in the jacking state of the airplane aiming at the actual scene that the structure of a jacking area bears horizontal loads in addition to vertical loads because the airplane shakes to generate horizontal acceleration when the airplane is jacked.
A stress analysis method for each jacking point structure in an airplane jacking state is characterized by comprising the following steps of knowing an integral structure digital model of an airplane, the total mass and the mass distribution of the airplane, and the positions of three jacking points of the airplane, the maximum vertical load and the maximum horizontal load of each jacking point:
1) establishing a finite element model of the whole structure of the airplane according to the numerical model of the whole structure of the airplane;
2) applying a distributed load generated by airplane mass distribution on the finite element model;
3) on a finite element model, applying the maximum vertical load of the jacking point and the concentrated horizontal load in the worst direction to the jacking point to one of the jacking points;
4) on the finite element model, applying constraint conditions to the gravity center of the airplane;
5) on the finite element model, carrying out stress analysis on the whole machine, wherein the stress analysis result is the structural stress of the jacking point;
6) on the finite element model, applying the maximum vertical load of the jacking point and the concentrated horizontal load in the worst direction to the other jacking point, and repeating the step 4) and the step 5) to obtain the structural stress of the jacking point;
7) and according to the step 6), applying the maximum vertical load of the jacking point and the concentrated horizontal load in the direction which is the most unfavorable to the jacking point to the rest jacking points, and repeating the step 4) and the step 5) to obtain the structural stress of the rest jacking points.
The beneficial effect of this application lies in: the method can accurately simulate the horizontal acceleration generated by shaking the airplane when jacking the airplane, thereby generating the actual use scene of the horizontal load at the jacking point and similar scenes, and enabling the structural stress analysis result of the jacking area to be more accurate.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic diagram of horizontal load distribution at each jacking point of an aircraft;
FIG. 2 is a schematic diagram of the vertical load distribution at each jacking point of the aircraft;
the numbering in the figures illustrates: 1 first jacking point, 2 second jacking points, 3 third jacking points and 4 airplane gravity centers
Detailed Description
In the prior art, the stress analysis of the structure of the jacking region of the airplane is to establish a local model of the jacking region, constrain the local model outside the jacking region, apply a vertical load and a horizontal load specified by a clause at the jacking point, and balance the vertical load and the horizontal load by considering the constraint point. The mass distribution of the jacking state of the airplane is not considered, the transmission relation between the vertical load and the horizontal load of the analyzed jacking area structure and the structures of the adjacent areas is not considered, and the stress distribution of the adjacent areas of the analyzed jacking area structure is not accurate.
Referring to the attached drawings, the task and the purpose of the invention are to provide a reasonable and reliable stress analysis method aiming at the actual jacking scene that the aircraft can horizontally shake when vertically jacking (each jacking point bears the horizontal load in the same direction).
The method comprises the steps that the digital model of the integral structure of the airplane, the total mass and the mass distribution of the airplane and the position of the center of gravity of the airplane are known, the airplane of the embodiment has three jacking points, the first jacking point 1 is located at the front part of the lower side of the airplane body, the second jacking point is located at the lower side of the right side wing of the airplane, the third jacking point is located at the lower side of the left side wing of the airplane, and the positions of the three jacking points of the airplane, the maximum vertical load and the maximum horizontal load of each jacking. The structural stress analysis steps of each jacking point are as follows:
firstly, establishing a finite element model of a full-aircraft structure according to an integral structure digital model of an aircraft; the distributed loads generated by the aircraft mass distribution are applied to the finite element model. The distributed load generated by the aircraft mass distribution comprises the aircraft massResulting distributed vertical load GZAnd distributing the horizontal load GX。
On the finite element model, applying the maximum vertical load F of the jacking point to the first jacking point 1AZAnd carrying the most unfavorable direction of concentrated horizontal load F to the jacking pointAX；
Applying the maximum vertical load F of the jacking point to the first jacking point 1AZAnd horizontal load FAXAnd meanwhile, corresponding vertical load and horizontal load are respectively applied to the second jacking point 2 and the third jacking point 3, and the horizontal load direction of the second jacking point 2 and the third jacking point 3 is the same as that of the first jacking point 1.
Distributed horizontal loads G generated by aircraft massXHorizontal load F of direction and first jacking point 1AXIn the opposite direction, the distributed horizontal loads G produced by the aircraft massesXAnd distributing the vertical load GZIs equal to the horizontal load F of the first jacking point 1AXTo vertical load FAZThe ratio of (a) to (b).
Then, on the finite element model, constraints are imposed on the aircraft at the center of gravity 4.
The constraint conditions are course, lateral and vertical linear displacement constraint and angular displacement constraint, the actual constraint counter force is 0, and the constraint moment generated by the horizontal load is not 0.
And on the finite element model, carrying out stress analysis on the whole machine, wherein the stress analysis result is the structural stress of the first jacking point 1.
And performing structural stress analysis on the second jacking point 2 and the third jacking point 3 by adopting the same method.
On the finite element model, applying the maximum vertical load F of the jacking point to the second jacking pointBZAnd carrying the most unfavorable direction of concentrated horizontal load F to the jacking pointBXAnd meanwhile, corresponding vertical loads and horizontal loads are applied to the first jacking point 1 and the third jacking point 3 respectively, and the horizontal load directions of the first jacking point 1 and the third jacking point 3 are the same as the horizontal load direction of the second jacking point 2. The distribution horizontal load GX direction generated by the aircraft mass and the horizontal load F of the second jacking point 2BXIn the opposite direction, the ratio of the distributed horizontal load GX and the distributed vertical load GZ generated by the aircraft mass is equal to the horizontal load F of the second jacking point 2BXTo vertical load FBZThe ratio of (a) to (b). And then applying constraint conditions to the position of the center of gravity 4 of the airplane on the finite element model. The constraint conditions are course, lateral and vertical linear displacement constraints and angular displacement constraints. And finally, carrying out stress analysis on the whole machine, wherein the stress analysis result is the structural stress of the second jacking point 2.
Finally, on the finite element model, applying the maximum vertical load F of the jacking point to the third jacking point 3CZAnd carrying the most unfavorable direction of concentrated horizontal load F to the jacking pointCXAnd meanwhile, corresponding vertical loads and horizontal loads are applied to the first jacking point 1 and the second jacking point 2 respectively, and the horizontal load directions of the first jacking point 1 and the second jacking point 2 are the same as the horizontal load direction of the third jacking point 3. The distribution horizontal load GX direction generated by the aircraft mass and the horizontal load F of the third jacking point 3CXIn the opposite direction, the ratio of the distributed horizontal load GX and the distributed vertical load GZ generated by the aircraft mass is equal to the horizontal load F of the third jacking point 3CXTo vertical load FCZThe ratio of (a) to (b). And then applying constraint conditions to the position of the center of gravity 4 of the airplane on the finite element model. The constraint conditions are course, lateral and vertical linear displacement constraints and angular displacement constraints. And finally, carrying out stress analysis on the whole machine, wherein the stress analysis result is the structural stress of the third jacking point 3.
The application provides a stress analysis method that aircraft level was rocked is considered to aircraft jacking state, compares traditional stress analysis method, and the result is more reasonable, reliable, can be used to aircraft structure detailed design, makes structural design safer, advanced.
Although the embodiments of the present invention have been described above, the above description is only for the convenience of understanding the present invention, and is not intended to limit the present invention. It will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (4)
1. A stress analysis method for each jacking point structure in an airplane jacking state is characterized by comprising the following steps of knowing an integral structure digital model of an airplane, the total mass and the mass distribution of the airplane, and the positions of three jacking points of the airplane, the maximum vertical load and the maximum horizontal load of each jacking point:
1) establishing a finite element model of the whole structure of the airplane according to the numerical model of the whole structure of the airplane;
2) applying a distributed load generated by airplane mass distribution on the finite element model;
3) on a finite element model, applying the maximum vertical load of the jacking point and the concentrated horizontal load in the worst direction to the jacking point to one of the jacking points;
4) on the finite element model, applying constraint conditions to the gravity center of the airplane;
5) on the finite element model, carrying out stress analysis on the whole machine, wherein the stress analysis result is the structural stress of the jacking point;
6) on the finite element model, applying the maximum vertical load of the jacking point and the concentrated horizontal load in the worst direction to the other jacking point, and repeating the step 4) and the step 5) to obtain the structural stress of the jacking point;
7) and according to the step 6), applying the maximum vertical load of the jacking point and the concentrated horizontal load in the direction which is the most unfavorable to the jacking point to the rest jacking points, and repeating the step 4) and the step 5) to obtain the structural stress of the rest jacking points.
2. The method for analyzing the stress of each jacking point structure under the jacking condition of the airplane as claimed in claim 1, wherein in the step 2) and the step 3), the distributed loads generated by the mass distribution of the airplane comprise distributed vertical loads and distributed horizontal loads generated by the mass of the airplane, the direction of the distributed horizontal loads is opposite to the direction of the horizontal loads of the jacking points to be analyzed, and the ratio of the distributed horizontal loads to the distributed vertical loads is equal to the ratio of the horizontal loads to the vertical loads of the jacking points to be analyzed.
3. The method for analyzing the stress of each jacking point structure under the jacking state of the airplane as claimed in claim 1, wherein in the step 3), the maximum vertical load and the maximum horizontal load of the jacking point are applied to one jacking point, and simultaneously, the corresponding vertical load and the corresponding horizontal load are respectively applied to the other two jacking points, and the direction of the horizontal loads of the other two jacking points is the same as the direction of the horizontal load of the jacking point to be analyzed.
4. The method for analyzing the stress of each jacking point structure under the jacking state of the airplane as claimed in claim 1, wherein in the step 4), constraint conditions are applied to the gravity center of the airplane, the constraint conditions comprise course direction, lateral and vertical linear displacement constraints and angular displacement constraints, the actual constraint counter force is 0, and the constraint moment generated by the horizontal load is not 0.
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| CN201911387587.5A CN113051785A (en) | 2019-12-27 | 2019-12-27 | Stress analysis method for jacking point structures of airplane in jacking state |
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| CN201911387587.5A CN113051785A (en) | 2019-12-27 | 2019-12-27 | Stress analysis method for jacking point structures of airplane in jacking state |
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