CN111177964B - 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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- CN111177964B CN111177964B CN201911356272.4A CN201911356272A CN111177964B CN 111177964 B CN111177964 B CN 111177964B CN 201911356272 A CN201911356272 A CN 201911356272A CN 111177964 B CN111177964 B CN 111177964B
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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 model z (ii) a Applying a vertical load F at a nose jacking point A in the full-machine finite element model Az And horizontal load F Ax (ii) a Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machine Bx Lateral linear displacement constraint delta By And vertical load F Bz (ii) a Respectively applying course linear displacement constraint delta to wing jacking points C in the finite element model of the whole machine Cx Lateral linear displacement constraint delta Cy And a vertical load F Cz (ii) a Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element model Gz Course angular displacement constraint gamma Gx Lateral angular displacement constraint gamma Gy And vertical angular displacement constraint gamma Gz 。
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 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 specified. 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 technical problem, 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 a 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 finite element model of the whole airplane according to the airplane structure;
according to the airplane mass distribution, applying a distributed vertical load G in the full-airplane finite element model z ；
Applying a vertical load F at a nose jacking point A in the whole-machine finite element model Az And horizontal load F Ax ；
Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machine Bx Lateral linear displacement constraint delta By And vertical load F Bz ；
Respectively applying course linear displacement constraint delta to wing jacking points C in the finite element model of the whole machine Cx Lateral linear displacement constraint delta Cy And a vertical load F Cz ；
Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element model Gz Course angular displacement constraint gamma Gx Lateral angular displacement constraint gamma Gy And vertical angular displacement constraint gamma Gz 。
Preferably, the method further comprises:
according to the G z 、F Az 、F Ax 、Δ Bx 、Δ By 、F Bz 、Δ Cx 、Δ Cy 、F Cz 、Δ Gz 、γ Gx 、γ Gy And gamma Gz And carrying out balance adjustment on the airplane in a jacking state.
Preferably, said F Az 、F Ax 、F Bz And F Cz Determined for jacking and mooring equipment requirements according to CCAR 25.519, 25 th cargo attachment airworthiness standard of China civil aviation regulation.
Preferably, said Δ Bx 、Δ By 、Δ Cx 、Δ Cy 、Δ Gz 、γ Gx 、γ Gy And gamma Gz Determined according to the actual state of the aircraft。
Preferably, according to said G z 、F Az 、F Ax 、Δ Bx 、Δ By 、F Bz 、Δ Cx 、Δ Cy 、F Cz 、Δ Gz 、γ Gx 、γ Gy And gamma Gz The balance adjustment of the aircraft in the jacking state specifically comprises the following steps:
using jacks and according to said G z 、F Az 、F Ax 、Δ Bx 、Δ By 、F Bz 、Δ Cx 、Δ Cy 、F Cz 、Δ Gz 、γ Gx 、γ Gy And gamma Gz And 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 distribution z (ii) a Applying a vertical load F at a nose jacking point A in the full-machine finite element model Az And horizontal load F Ax (ii) a Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machine Bx Lateral linear displacement constraint delta By And vertical load F Bz (ii) a Respectively applying heading linear displacement constraint delta to wing jacking points C in the finite element model of the whole aircraft Cx Lateral linear displacement constraint delta Cy And vertical load F Cz (ii) a Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element model Gz Course angular displacement constraint gamma Gx And lateral angular displacement constraint gamma Gy And vertical angular displacement constraint gamma Gz 。
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 present 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 are not intended 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 inclines 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 load and the horizontal load specified by the clause at one jacking point A, wherein the horizontal load is balanced by considering the horizontal load at the other two jacking points B, C; the rotation caused by the horizontal load is not considered. If the heading, lateral and vertical linear displacement is restrained at the B, C jacking point, the restraint reaction force vertical load and the horizontal load at the B, C jacking point are not consistent with the jacking load specified by the clause.
As shown in fig. 1 and fig. 2, according to the mass distribution of the jacking state of the airplane, a distributed vertical load generated by the mass distribution is applied to 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 vertical loads specified by the clauses are applied at jacking points B, C. And the support reaction force formed by the heading linear displacement constraint at the jacking point B, C and the support 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 trim adjustment of a jacking condition of an aircraft, 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 airplane mass distribution, applying a distributed vertical load G in the full-airplane finite element model z ；
Applying a vertical load F at a nose jacking point A in the whole-machine finite element model Az And horizontal load F Ax ；
Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machine Bx Lateral linear displacement constraint delta By And vertical load F Bz ；
Respectively applying course linear displacement constraint delta to wing jacking points C in the finite element model of the whole machine Cx Lateral linear displacement constraint delta Cy And vertical load F Cz ；
Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element model Gz Course angular displacement constraint gamma Gx Lateral angular displacement restraintγ Gy And vertical angular displacement constraint gamma Gz 。
2. The method of claim 1, further comprising:
according to the G z 、F Az 、F Ax 、Δ Bx 、Δ By 、F Bz 、Δ Cx 、Δ Cy 、F Cz 、Δ Gz 、γ Gx 、γ Gy And gamma Gz And carrying out balance adjustment on the airplane in a jacking state.
3. The method of claim 1, wherein F is Az 、F Ax 、F Bz And F Cz As determined by aviation standards.
4. The method of claim 1, wherein Δ is Bx 、Δ By 、Δ Cx 、Δ Cy 、Δ Gz 、γ Gx 、γ Gy And gamma Gz Is determined based on the actual state of the aircraft.
5. The method of claim 2, wherein G is the basis of z 、F Az 、F Ax 、Δ Bx 、Δ By 、F Bz 、Δ Cx 、Δ Cy 、F Cz 、Δ Gz 、γ Gx 、γ Gy And gamma Gz Carrying out balance adjustment on the airplane in a jacking state, and specifically comprising the following steps:
using jacks and according to G z 、F Az 、F Ax 、Δ Bx 、Δ By 、F Bz 、Δ Cx 、Δ Cy 、F Cz 、Δ Gz 、γ Gx 、γ Gy And gamma Gz And 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 distribution z (ii) a Applying a vertical load F at a nose jacking point A in the full-machine finite element model Az And horizontal load F Ax (ii) a Respectively applying course linear displacement constraint delta to wing jacking points B in the finite element model of the whole machine Bx Lateral linear displacement constraint delta By And vertical load F Bz (ii) a Respectively applying heading linear displacement constraint delta to wing jacking points C in the finite element model of the whole aircraft Cx Lateral linear displacement constraint delta Cy And vertical load F Cz (ii) a Imposing a vertical linear displacement constraint Δ at a center of gravity point G in the full-machine finite element model Gz Course angular displacement constraint gamma Gx Lateral angular displacement constraint gamma Gy And vertical angular displacement constraint gamma Gz 。
7. A balance adjustment device for a jacking state of an aircraft, comprising: a memory and a processor;
the memory configured to hold executable instructions;
the processor, when executing the executable instructions stored in the memory, is configured to implement the balance adjustment method for the jacking state of the aircraft according to any one of claims 1 to 5.
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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| CN113704878B (en) * | 2021-08-05 | 2023-10-10 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for applying load of landing gear by using aircraft structure full-aircraft finite element model |
Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB582083A (en) * | 1941-07-23 | 1946-11-05 | Walter Gordon Wilson | Improvements in and relating to the steering devices of air or water craft, torpedoes and the like |
| CN102235943A (en) * | 2010-05-06 | 2011-11-09 | 中国商用飞机有限责任公司 | Loading test device |
| CN102359848A (en) * | 2011-09-06 | 2012-02-22 | 上海福伊特水电设备有限公司 | Water turbine rotating wheel three-fulcrum weighing static balance device and static balance technology thereof |
| CN103954340A (en) * | 2014-04-28 | 2014-07-30 | 山东太古飞机工程有限公司 | Jack-up type aircraft weighing adaptor |
| CN104140060A (en) * | 2014-06-27 | 2014-11-12 | 中航飞机股份有限公司西安飞机分公司 | Synchronous jacking system of airplane |
| CN204056301U (en) * | 2014-09-01 | 2014-12-31 | 北京元恒大通科技有限公司 | A kind of canard aerodynamic arrangement aircraft decoy of monocoque |
| CN104598693A (en) * | 2015-02-02 | 2015-05-06 | 西北工业大学 | Method for determining thin-walled structure high-rigidity connecting area load transfer |
| EP2899118A1 (en) * | 2014-01-27 | 2015-07-29 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Rotorcraft with a fuselage and at least one main rotor |
| CN104933250A (en) * | 2015-06-23 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | Wing aerodynamics modeling method |
| CN105004884A (en) * | 2015-07-03 | 2015-10-28 | 北京航空航天大学 | SiC-based micro-optics high-temperature accelerometer and design method |
| CN106202699A (en) * | 2016-07-07 | 2016-12-07 | 中国飞机强度研究所 | A kind of sensitivity method for solving under many displacement constraints |
| CN206430927U (en) * | 2017-02-14 | 2017-08-22 | 成都飞机工业（集团）有限责任公司 | A kind of bearing test device of aircraft jack |
| CN107521695A (en) * | 2017-08-04 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body connects wing aircraft |
| CN108193604A (en) * | 2017-11-28 | 2018-06-22 | 中交二航局第二工程有限公司 | Ballasting method of weighing during box beam T structures balance swivel |
| CN108622435A (en) * | 2018-05-07 | 2018-10-09 | 中国商用飞机有限责任公司 | Six-freedom-degree APU (auxiliary Power Unit) installation adjusting device |
| CN108820245A (en) * | 2018-06-26 | 2018-11-16 | 北京航空航天大学 | A kind of solar powered aircraft aerofoil mask film tensioning installation equipment |
| CN109987541A (en) * | 2019-03-21 | 2019-07-09 | 沈阳飞研航空设备有限公司 | Aircraft intelligent electric machinery jacking apparatus |
| CN110002004A (en) * | 2019-04-02 | 2019-07-12 | 中国飞机强度研究所 | Complete aircraft structural floor strength test sidewise restraint control method and system |
| CN110182385A (en) * | 2018-12-11 | 2019-08-30 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of lateral force eliminating device of aircraft jack-up system |
| CN209797364U (en) * | 2019-03-21 | 2019-12-17 | 沈阳飞研航空设备有限公司 | Intelligent electric mechanical jacking device for airplane |
-
2019
- 2019-12-25 CN CN201911356272.4A patent/CN111177964B/en active Active
Patent Citations (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB582083A (en) * | 1941-07-23 | 1946-11-05 | Walter Gordon Wilson | Improvements in and relating to the steering devices of air or water craft, torpedoes and the like |
| CN102235943A (en) * | 2010-05-06 | 2011-11-09 | 中国商用飞机有限责任公司 | Loading test device |
| CN102359848A (en) * | 2011-09-06 | 2012-02-22 | 上海福伊特水电设备有限公司 | Water turbine rotating wheel three-fulcrum weighing static balance device and static balance technology thereof |
| EP2899118A1 (en) * | 2014-01-27 | 2015-07-29 | AIRBUS HELICOPTERS DEUTSCHLAND GmbH | Rotorcraft with a fuselage and at least one main rotor |
| CN103954340A (en) * | 2014-04-28 | 2014-07-30 | 山东太古飞机工程有限公司 | Jack-up type aircraft weighing adaptor |
| CN104140060A (en) * | 2014-06-27 | 2014-11-12 | 中航飞机股份有限公司西安飞机分公司 | Synchronous jacking system of airplane |
| CN204056301U (en) * | 2014-09-01 | 2014-12-31 | 北京元恒大通科技有限公司 | A kind of canard aerodynamic arrangement aircraft decoy of monocoque |
| CN104598693A (en) * | 2015-02-02 | 2015-05-06 | 西北工业大学 | Method for determining thin-walled structure high-rigidity connecting area load transfer |
| CN104933250A (en) * | 2015-06-23 | 2015-09-23 | 中国航空工业集团公司西安飞机设计研究所 | Wing aerodynamics modeling method |
| CN105004884A (en) * | 2015-07-03 | 2015-10-28 | 北京航空航天大学 | SiC-based micro-optics high-temperature accelerometer and design method |
| CN106202699A (en) * | 2016-07-07 | 2016-12-07 | 中国飞机强度研究所 | A kind of sensitivity method for solving under many displacement constraints |
| CN206430927U (en) * | 2017-02-14 | 2017-08-22 | 成都飞机工业（集团）有限责任公司 | A kind of bearing test device of aircraft jack |
| CN107521695A (en) * | 2017-08-04 | 2017-12-29 | 中国航空工业集团公司西安飞机设计研究所 | A kind of blended wing-body connects wing aircraft |
| CN108193604A (en) * | 2017-11-28 | 2018-06-22 | 中交二航局第二工程有限公司 | Ballasting method of weighing during box beam T structures balance swivel |
| CN108622435A (en) * | 2018-05-07 | 2018-10-09 | 中国商用飞机有限责任公司 | Six-freedom-degree APU (auxiliary Power Unit) installation adjusting device |
| CN108820245A (en) * | 2018-06-26 | 2018-11-16 | 北京航空航天大学 | A kind of solar powered aircraft aerofoil mask film tensioning installation equipment |
| CN110182385A (en) * | 2018-12-11 | 2019-08-30 | 中国航空工业集团公司北京长城计量测试技术研究所 | A kind of lateral force eliminating device of aircraft jack-up system |
| CN109987541A (en) * | 2019-03-21 | 2019-07-09 | 沈阳飞研航空设备有限公司 | Aircraft intelligent electric machinery jacking apparatus |
| CN209797364U (en) * | 2019-03-21 | 2019-12-17 | 沈阳飞研航空设备有限公司 | Intelligent electric mechanical jacking device for airplane |
| CN110002004A (en) * | 2019-04-02 | 2019-07-12 | 中国飞机强度研究所 | Complete aircraft structural floor strength test sidewise restraint control method and system |
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