CN111177964A - Balance adjusting method and equipment for jacking state of airplane - Google Patents
Balance adjusting method and equipment for jacking state of airplane Download PDFInfo
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- CN111177964A CN111177964A CN201911356272.4A CN201911356272A CN111177964A CN 111177964 A CN111177964 A CN 111177964A CN 201911356272 A CN201911356272 A CN 201911356272A CN 111177964 A CN111177964 A CN 111177964A
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The embodiment of the invention discloses a balance adjusting method for an airplane jacking state, which comprises the following steps: obtaining airplane mass distribution in advance, and constructing a complete airplane finite element model according to the airplane structure; according to the aircraft mass distribution, applying a distributed vertical load G in the full-aircraft finite element modelz(ii) a Applying a vertical load F at a nose jacking point A in the full-machine finite element modelAzAnd horizontal load FAx(ii) a Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machineBxLateral linear displacement constraint deltaByAnd vertical load FBz(ii) a Respectively applying course linear displacement constraint delta to wing jacking points C in the finite element model of the whole machineCxLateral linear displacement constraint deltaCyAnd vertical load FCz(ii) a Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element modelGzCourse angular displacement constraint gammaGxLateral angular displacement constraint gammaGyAnd vertical angular displacement constraint gammaGz。
Description
Technical Field
The present application relates to, but not limited to, the field of aerospace engineering applications, and in particular, to a method and an apparatus for balancing and adjusting a jacking state of an aircraft.
Background
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 balance mode of jacking load is not stipulated explicitly. Local stress analysis is typically performed considering only the jacking point individual loads. 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
In order to solve the above technical problems, embodiments of the present invention provide a method and an apparatus for adjusting balance of a jacking state of an aircraft, so as to solve the problem in the prior art that a local stress analysis of a jacking point structure is single.
In a first aspect, an embodiment of the present invention provides a method for adjusting balance of a jacking state of an aircraft, where the method includes:
obtaining airplane mass distribution in advance, and constructing a complete airplane finite element model according to the airplane structure;
according to the aircraft mass distribution, applying a distributed vertical load G in the full-aircraft finite element modelz；
Applying a vertical load F at a nose jacking point A in the full-machine finite element modelAzAnd horizontal load FAx；
Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machineBxLateral linear displacement constraint deltaByAnd vertical load FBz；
Respectively applying course linear displacement constraint delta to wing jacking points C in the finite element model of the whole machineCxLateral linear displacement constraint deltaCyAnd vertical load FCz；
Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element modelGzCourse angular displacement constraint gammaGxLateral angular displacement constraint gammaGyAnd vertical angular displacement constraint gammaGz。
Preferably, the method further comprises:
according to the Gz、FAz、FAx、ΔBx、ΔBy、FBz、ΔCx、ΔCy、FCz、ΔGz、γGx、γGyAnd gammaGzJacking the airplaneAnd (4) balance adjustment in a state.
Preferably, said FAz、FAx、FBzAnd FCzDetermined for jacking and mooring equipment requirements according to article 25 airworthiness standard for transportation accessories CCAR under china civil aviation regulations, article 25.519.
Preferably, said ΔBx、ΔBy、ΔCx、ΔCy、ΔGz、γGx、γGyAnd gammaGzIs determined based on the actual state of the aircraft.
Preferably, according to said Gz、FAz、FAx、ΔBx、ΔBy、FBz、ΔCx、ΔCy、FCz、ΔGz、γGx、γGyAnd gammaGzThe balance adjustment of the aircraft in the jacking state specifically comprises the following steps:
using jacks and according to said Gz、FAz、FAx、ΔBx、ΔBy、FBz、ΔCx、ΔCy、FCz、ΔGz、γGx、γGyAnd gammaGzAnd carrying out balance adjustment on the airplane in a jacking state.
In a second aspect, an embodiment of the present invention provides a balance adjustment device for an aircraft jacking state, the device including a building unit and an applying unit, wherein:
the construction unit is used for obtaining airplane mass distribution in advance and constructing a complete airplane finite element model according to the airplane structure;
an applying unit for applying a distributed vertical load G in the full-aircraft finite element model according to the aircraft mass distributionz(ii) a Applying a vertical load F at a nose jacking point A in the full-machine finite element modelAzAnd horizontal load FAx(ii) a Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machineBxLateral linear displacement constraint deltaByAnd vertical load FBz(ii) a Respectively applying to the wing jacking point C in the whole finite element modelLinear displacement constraint delta of added navigation directionCxLateral linear displacement constraint deltaCyAnd vertical load FCz(ii) a Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element modelGzCourse angular displacement constraint gammaGxLateral angular displacement constraint gammaGyAnd vertical angular displacement constraint gammaGz。
In a third aspect, an embodiment of the present invention provides a balance adjustment apparatus for an aircraft jacking state, including: a memory and a processor;
the memory configured to hold executable instructions;
the processor is configured to implement the balance adjustment method for the jacking state of the airplane as described in any one of the above items when the executable instructions stored in the memory are executed.
In a fourth aspect, embodiments of the present invention provide a computer-readable storage medium, which stores executable instructions that, when executed by a processor, implement the balance adjustment method for the jacking state of an aircraft according to any one of the above methods.
The application provides a stress analysis method of jack direction 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, advance.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the example serve to explain the principles of the invention and not to limit the invention.
Fig. 1 is a schematic diagram illustrating a method for adjusting balance of a jacking state of an aircraft according to an embodiment of the present disclosure;
fig. 2 is a schematic diagram of another method for adjusting balance of a jacking state of an aircraft according to an embodiment of the present application.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the embodiments and features of the embodiments in the present application may be arbitrarily combined with each other without conflict.
The steps illustrated in the flow charts of the figures may be performed in a computer system such as a set of computer-executable instructions. Also, while a logical order is shown in the flow diagrams, in some cases, the steps shown or described may be performed in an order different than here.
The following specific embodiments of the present invention may be combined, and the same or similar concepts or processes may not be described in detail in some embodiments.
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 balance mode of jacking load is not stipulated explicitly. Local stress analysis is typically performed considering only the jacking point individual loads. According to the experience of actual models, the results of the local stress analysis of the jacking point structure are not conservative
The invention aims to provide a reasonable and reliable stress analysis method aiming at the actual jacking scene (each jacking point bears horizontal load in the opposite direction) when an airplane is jacked vertically and a jack is inclined in the direction.
In the prior art, the mass distribution of the jacking state of an airplane is considered, and the distributed vertical load generated by the mass distribution is applied to a finite element model of the whole airplane; applying the vertical and horizontal loads specified by the clauses at one jacking point a, the horizontal load being balanced by the horizontal loads at the other two jacking points B, C; the rotation caused by the horizontal load is not considered. If the heading, the lateral direction and the vertical linear displacement are restrained at the jacking point B, C, the restraining counter force vertical load and the horizontal load at the jacking point B, C are not consistent with the jacking load specified by the clause.
As shown in fig. 1 and 2, according to the mass distribution of the jacking state of the airplane, applying a distributed vertical load generated by the distributed mass in the finite element model of the whole airplane;
the vertical load and the horizontal load specified by the clause are applied at the jacking point a.
Heading linear displacement constraints, lateral linear displacement constraints and the provision specified vertical loads are applied at jacking point B, C. Wherein, the thrust reaction force formed by the course linear displacement constraint at the jacking point B, C and the thrust reaction force formed by the lateral linear displacement constraint are balanced with the horizontal load at the jacking point A.
And applying vertical linear displacement constraint, course angular displacement constraint, lateral angular displacement constraint and vertical angular displacement constraint at the gravity center point G. And the thrust reaction force formed by the vertical linear displacement constraint, the thrust reaction force formed by the course linear displacement constraint and the thrust reaction force formed by the lateral linear displacement constraint at the gravity center point G are 0, so that the airplane can be balanced in the jacking state.
The application provides a stress analysis method of jack direction 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, advance.
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 (8)
1. A method of balancing an aircraft jacking condition, the method comprising:
obtaining airplane mass distribution in advance, and constructing a complete airplane finite element model according to the airplane structure;
according to the aircraft mass distribution, applying a distributed vertical load G in the full-aircraft finite element modelz；
Applying a vertical load F at a nose jacking point A in the full-machine finite element modelAzAnd horizontal load FAx；
Respectively at wing jacking points B in the finite element model of the whole machineApplying course linear displacement constraint deltaBxLateral linear displacement constraint deltaByAnd vertical load FBz；
Respectively applying course linear displacement constraint delta to wing jacking points C in the finite element model of the whole machineCxLateral linear displacement constraint deltaCyAnd vertical load FCz；
Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element modelGzCourse angular displacement constraint gammaGxLateral angular displacement constraint gammaGyAnd vertical angular displacement constraint gammaGz。
2. The method of claim 1, further comprising:
according to the Gz、FAz、FAx、ΔBx、ΔBy、FBz、ΔCx、ΔCy、FCz、ΔGz、γGx、γGyAnd gammaGzAnd carrying out balance adjustment on the airplane in a jacking state.
3. The method of claim 1, wherein F isAz、FAx、FBzAnd FCzIs determined according to aviation standards.
4. The method of claim 1, wherein Δ isBx、ΔBy、ΔCx、ΔCy、ΔGz、γGx、γGyAnd gammaGzIs determined based on the actual state of the aircraft.
5. The method of claim 2, wherein G is the basis ofz、FAz、FAx、ΔBx、ΔBy、FBz、ΔCx、ΔCy、FCz、ΔGz、γGx、γGyAnd gammaGzJacking the airplaneThe balance adjustment specifically comprises:
using jacks and according to said Gz、FAz、FAx、ΔBx、ΔBy、FBz、ΔCx、ΔCy、FCz、ΔGz、γGx、γGyAnd gammaGzAnd carrying out balance adjustment on the airplane in a jacking state.
6. A balance adjustment device for a jacking state of an aircraft, the device comprising a construction unit and an application unit, wherein:
the construction unit is used for obtaining airplane mass distribution in advance and constructing a complete airplane finite element model according to the airplane structure;
an applying unit for applying a distributed vertical load G in the full-aircraft finite element model according to the aircraft mass distributionz(ii) a Applying a vertical load F at a nose jacking point A in the full-machine finite element modelAzAnd horizontal load FAx(ii) a Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machineBxLateral linear displacement constraint deltaByAnd vertical load FBz(ii) a Respectively applying course linear displacement constraint delta to wing jacking points C in the finite element model of the whole machineCxLateral linear displacement constraint deltaCyAnd vertical load FCz(ii) a Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element modelGzCourse angular displacement constraint gammaGxLateral angular displacement constraint gammaGyAnd vertical angular displacement constraint gammaGz。
7. An aircraft jacking state balance adjustment apparatus, comprising: a memory and a processor;
the memory configured to hold executable instructions;
the processor is configured to implement the balance adjustment method for the jacking state of the airplane according to any one of claims 1-5 when executing the executable instructions saved by the memory.
8. A computer-readable storage medium storing executable instructions that, when executed by a processor, implement a method of balancing jacking conditions of an aircraft according to any one of claims 1 to 5.
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Cited By (1)
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