CN102750408A - Pull rod installing layout method of airplane auxiliary power device - Google Patents
Pull rod installing layout method of airplane auxiliary power device Download PDFInfo
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- CN102750408A CN102750408A CN2012101889042A CN201210188904A CN102750408A CN 102750408 A CN102750408 A CN 102750408A CN 2012101889042 A CN2012101889042 A CN 2012101889042A CN 201210188904 A CN201210188904 A CN 201210188904A CN 102750408 A CN102750408 A CN 102750408A
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Abstract
The invention belongs to the installation technology of airplane airborne equipment and relates to an installing structure layout optimized method of an auxiliary power device. According to the pull rod installing layout method of the airplane auxiliary power device, engineering design software is utilized for structure parameterized modeling, and the data transfer from the parameterized entity structure to the finite element analysis software is realized under the invoking effect of flow process optimization control program; and in the finite element software, entities are subjected to meshing, in addition, the application of conditions of materials, restraining, loads and the like of an installing system is carried out, the structure stress or deformation of a rod system is calculated, and the optimum structure of the installing system is determined by an optimizing flow process according to optimizing targets such as the system weight, good manufacturability and the like. The method has the advantages that the installing structure with the minimum structure weight and the optimal stress form can be obtained, the structure weight is lightened, the vibration transfer is reduced, the installation efficiency and the installing quality are improved, and the layout optimization requirement of the installing system of the airplane auxiliary power device is met.
Description
Technical field
The invention belongs to aircraft airborne equipment field engineering, relate to a kind of method of auxiliary power unit mounting structure layout optimization.
Background technology
One of main difficult point of design of engine installation system is the layout and the structure optimization of installation system.At present, the optimization of parts (or leverage) configuration and space layout is not carried out in the design of engine installation system basically, makes that the system unit weight that designs is big, and the volume occupy-place is big.Along with the designing technique progress, generally all adopt Optimization Design in the aeroplane structure design both at home and abroad, not only reduced the design difficulty and the risk of installation system, and guaranteed that the installation system design objective is optimum, make system unit light and handy, reduced research cost.And when APU installs, generally only consider the layout convenience of pull bar at present both at home and abroad, and do not carry out layout optimization based on mechanical property.
Summary of the invention
The objective of the invention is: a kind of aircraft auxiliary power plant that can effectively improve installation effectiveness and installation quality is installed the pull bar layout method
Technical scheme of the present invention is: a kind of aircraft auxiliary power plant is installed the pull bar layout method, and it comprises following concrete steps:
Step 1, data are prepared
Confirm the installation site of aircraft auxiliary power plant installation system, design feature and self performance parameter, and as starting condition and boundary condition;
Step 2: confirm to optimize the independent variable constraints
With the full machine coordinate system coordinate of each pull bar of aircraft auxiliary power plant and aircaft configuration intersection point as independent variable;
Limit by the aircaft configuration position, with the volume coordinate variation range of each bar and aircaft configuration intersection point as independent variable constraint condition;
Step 3: confirm optimization aim
The axial maximum stress minimum that adopts all pull bars is as optimization aim;
Step 4: optimizing process
Step 1: the stress of amounting to of tension member and compression rod is handled
Different according to tension member and compression rod bearer properties are introduced and are amounted to the stress level that stress contrasts bar, wherein, for tension, amount to the stress that stress promptly equals bar; For compressive stress, then amount to stress and be:
Wherein, σ finds σ by amounting to stress relation figure
bBe yield stress, σ
CrBe limit stress, σ
CvFor amounting to stress;
Step 2: calculate to each the pull bar axial stress under the layout according to independent variable and intersecting point coordinate initial value, find out the maximum axial stress value;
Step 3: on intersecting point coordinate initial value basis,, and find out the maximum axial stress value, the maximum axial stress value in this maximum axial stress value and the step 2 is compared, get smaller value by each the pull bar axial stress under this layout of certain step size computation;
Step 4: through increasing step-length, travel through all position coordinates combinations, circulation step 3 through comparing the maximum axial stress value under each layout, obtains minimum value as final optimization aim, and the minimum layout of maximum axial stress value is the layout after the final optimization pass;
Step 4:, accomplish the concrete design of structural members such as APU installation system pull bar, joint according to Optimization result.
In the optimizing process, also comprise disposal route, when the optimization of installation system, only consider the elasticity item of vibroshock, and adopt the Hookean spring unit to simulate the spring function of vibroshock vibroshock.
Technique effect of the present invention is: the present invention has set up a cover and has been applicable to the aircraft auxiliary power plant installation system method of optimizing distribution; Standard the flow process of layout optimization, comprise the calculating of erecting frame load, stressed result's evaluation, layout optimization process, and according to the characteristics of erecting frame; And iterative processing; Finally obtain to obtain the mounting structure of the minimum construction weight and the stress form of optimum, alleviated construction weight, reduced transfer of vibration; Improve installation effectiveness and installation quality, satisfied aircraft auxiliary power plant installation system layout optimization demand.
Description of drawings
Fig. 1 is the process flow diagram that aircraft auxiliary power plant of the present invention is installed the pull bar layout method.
Embodiment
Below through specific embodiment and combine accompanying drawing that the present invention is further described:
Aircraft auxiliary power plant of the present invention is installed the pull bar layout method and is utilized engineering design software to carry out the parametric modeling of structure, under the calling who optimizes the flow process control program, realizes the data transfer of parametrization entity structure to finite element analysis software; In finite element software, entity carried out grid dividing and installation system carried out applying of conditions such as material, constraint, load; Calculate the structure stress or the distortion of leverage; By optimizing flow process, confirm the optimum structure of installation system according to optimization aim such as system weight, good manufacturability.
Be that example is explained aircraft auxiliary power plant installation pull bar layout method of the present invention with certain type aircraft auxiliary power plant (APU) installation system now.In the present embodiment, this APU installation system is made up of three installation joints of 7 installation pull bars, 3 vibration dampers, fixture and APU, and wherein, the end that seven installation pull bars of APU link to each other with the vibroshock center is a stiff end, and an end that links to each other with aircaft configuration is a movable end.
See also Fig. 1 below, it provides the detailed process that aircraft auxiliary power plant of the present invention is installed the pull bar layout method, and concrete steps are following:
Step 1, data are prepared
Designing requirement according to aircraft APU installation system; And APU system layout and main body structure profile aboard; Confirm the designing requirement of APU installation system, like the installation site, design feature and self performance parameter (like pull bar size, stress) etc. are as starting condition and boundary condition;
Step 2: confirm to optimize the independent variable constraints
As independent variable, in this embodiment, because the end that seven pull bars of APU link to each other with aircaft configuration is a movable end, this intersection point is movable intersection point with the full machine coordinate system coordinate of each pull bar and aircaft configuration intersection point;
Limit by the aircaft configuration position, with the volume coordinate variation range of each bar and aircaft configuration intersection point as independent variable constraint condition;
Step 3: confirm optimization aim
The axial maximum stress minimum that adopts all seven pull bars is as optimization aim; Under certain leverage layout; The axial maximum stress of each bar hour; Can think that the distribution of each stick force is that this leverage layout is thought to optimize structure uniformly, can obtain minimum construction weight and optimum stress form;
Step 4: optimizing process
Step 1: tension member and compression rod amount to that stress is handled and vibroshock is handled
Different according to tension member and compression rod bearer properties are the stress level between convenient more different bars, introduce and amount to the stress level that stress contrasts bar, are adjusted to identical level with the demonstration load-bearing capacity with bar,
Wherein, for tension, amount to the stress that stress promptly equals bar; For compressive stress, then amount to stress and be:
Wherein, σ finds σ by amounting to stress relation figure
bBe yield stress, σ
CrBe limit stress, σ
CvFor amounting to stress;
The processing of vibroshock
Vibroshock is the critical elements that reduces engine and aircraft transfer of vibration; General vibroshock can be reduced to elasticity item and damping term; Wherein damping term mainly acts on dynamic loading, like the amplitude that reduces vibration, the phase place that changes vibratory response, and does not generally consider in static load.
So in current installation system static load structure optimization, only consider the elasticity item of vibroshock, when the optimization of installation system, adopt the Hookean spring unit to simulate the spring function of vibroshock.The experimental result k=4.5353 that the rigidity of vibroshock provides by manufacturer * 10
6N/m.
Step 2: calculate to each the pull bar axial stress under the layout according to independent variable and intersecting point coordinate initial value, find out the maximum axial stress value;
Step 3: on intersecting point coordinate initial value basis; By each the pull bar axial stress under this layout of certain step size computation; And find out the maximum axial stress value, and the maximum axial stress value in this maximum axial stress value and the step 2 is compared, get smaller value; Wherein, step sizes need be confirmed by actual computation;
Step 4: through increasing step-length, travel through all position coordinates combinations, circulation step 3 through comparing the maximum axial stress value under each layout, obtains minimum value as final optimization aim.
Step 4:, accomplish the concrete design of structural members such as APU installation system pull bar, joint according to Optimization result.
Provided the numerical value before and after optimizing through table 1 and table 2 below, the two compares.
Table 1 compares before and after optimizing
Table 2 flexing bar compares before and after optimizing
Through the comparison before and after optimizing, can find that leverage maximum stress and mount pad support reaction are all reduced, the stressed of leverage becomes more even, and safety coefficient increases, and can think that the leverage distribution form that obtains is the optimal location form.Therefore not only can reduce the suffered load of pull bar through pull bar distribution form and the vibroshock index of optimizing, can make pull bar reach the area of section that higher margin of safety perhaps reduces pull bar, alleviate the weight of installation system.
In addition, in this embodiment, set up the optimization flow process with the ISIGHT Optimization Software, iSight provides the master data of optimizing process, gives process execution program to carry out concrete calculating, reclaims calculation result data and is optimized interpretation of result.Through traveling through all possible tie point position grouping situation,, provide the unique layout that satisfies optimization aim by the result of calculation of the continuous recursive call PATRAN of ISIGHT.
Wherein, Process execution program: the working procedure that adopts the establishment of C++Builder platform; Its function is change in location mode (equation) and the variation range (position limit) by topology layout scheme and periodical system installation node; And, set up the finite element modeling and the calculation command stream of the periodical architecture of optimized point, and start finite element program and carry out structural modeling and calculating according to the optimization data of iSight.User's subroutine: the subroutine that adopts the FORTRAN establishment; Be affiliated in finite element program; Be used for obtaining the information such as stress, strain, displacement of structural key position, and output to document form and be optimized process and interpretation of result in the iSight program to feed back to.
Claims (2)
1. an aircraft auxiliary power plant is installed the pull bar layout method, it is characterized in that, comprises following concrete steps:
Step 1, data are prepared
Confirm the installation site of aircraft auxiliary power plant installation system, design feature and self performance parameter, and as starting condition and boundary condition;
Step 2: confirm to optimize the independent variable constraints
With the full machine coordinate system coordinate of each pull bar of aircraft auxiliary power plant and aircaft configuration intersection point as independent variable;
Limit by the aircaft configuration position, with the volume coordinate variation range of each bar and aircaft configuration intersection point as independent variable constraint condition;
Step 3: confirm optimization aim
The axial maximum stress minimum that adopts all pull bars is as optimization aim;
Step 4: optimizing process
Step 1: the stress of amounting to of tension member and compression rod is handled
Different according to tension member and compression rod bearer properties are introduced and are amounted to the stress level that stress contrasts bar,
Wherein, for tension, amount to the stress that stress promptly equals bar; For compressive stress, then amount to stress and be:
Wherein, σ finds σ by amounting to stress relation figure
bBe yield stress, σ
CrBe limit stress, σ
CvFor amounting to stress;
Step 2: calculate to each the pull bar axial stress under the layout according to independent variable and intersecting point coordinate initial value, find out the maximum axial stress value;
Step 3: on intersecting point coordinate initial value basis,, and find out the maximum axial stress value, the maximum axial stress value in this maximum axial stress value and the step 2 is compared, get smaller value by each the pull bar axial stress under this layout of certain step size computation;
Step 4: through increasing step-length, travel through all position coordinates combinations, circulation step 3 through comparing the maximum axial stress value under each layout, obtains minimum value as final optimization aim, and the minimum layout of maximum axial stress value is the layout after the final optimization pass;
Step 4:, accomplish the concrete design of structural members such as APU installation system pull bar, joint according to Optimization result.
2. aircraft auxiliary power plant according to claim 1 is installed the pull bar layout method; It is characterized in that; In the optimizing process, also comprise treatment step, when the optimization of installation system to vibroshock; Only consider the elasticity item of vibroshock, and adopt the Hookean spring unit to simulate the spring function of vibroshock.
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| CN103020350A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Fastener load-deformation curve numerical simulation method |
| CN103218474A (en) * | 2013-03-08 | 2013-07-24 | 王平 | Method and system for distributing original load of airplane nodes |
| CN103729520A (en) * | 2014-01-16 | 2014-04-16 | 中国人民解放军国防科学技术大学 | Equipment maintainability layout design method based on human factor potential field |
| CN103984803A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Finite element load application method |
| CN104392120A (en) * | 2014-11-07 | 2015-03-04 | 中冶京诚工程技术有限公司 | Design method of horizontal pull rod of high furnace bustle pipe |
| CN104655064A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Determination method of engine mounted pull rod tolerance value |
| CN107480351A (en) * | 2017-07-28 | 2017-12-15 | 中国航空工业集团公司西安飞机设计研究所 | Engine hanging structure Optimization Design |
| CN107563039A (en) * | 2017-08-28 | 2018-01-09 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of intensity layout design method of aircraft engine installation system |
| CN111177853A (en) * | 2019-12-31 | 2020-05-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing type framework design method |
| CN111914352A (en) * | 2020-07-06 | 2020-11-10 | 西安飞机工业（集团）有限责任公司 | Design method for installation pull rod of airplane auxiliary power device |
| CN113111436A (en) * | 2021-04-15 | 2021-07-13 | 泉州装备制造研究所 | Airplane large component pre-connection layout and multi-constraint action sequence optimization method |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103020350A (en) * | 2012-12-10 | 2013-04-03 | 中国飞机强度研究所 | Fastener load-deformation curve numerical simulation method |
| CN103218474A (en) * | 2013-03-08 | 2013-07-24 | 王平 | Method and system for distributing original load of airplane nodes |
| CN103218474B (en) * | 2013-03-08 | 2016-09-28 | 王平 | Aircraft node raw payload distribution method and system |
| CN104655064B (en) * | 2013-11-22 | 2017-04-19 | 中国航空工业集团公司西安飞机设计研究所 | Determination method of engine mounted pull rod tolerance value |
| CN104655064A (en) * | 2013-11-22 | 2015-05-27 | 中国航空工业集团公司西安飞机设计研究所 | Determination method of engine mounted pull rod tolerance value |
| CN103729520A (en) * | 2014-01-16 | 2014-04-16 | 中国人民解放军国防科学技术大学 | Equipment maintainability layout design method based on human factor potential field |
| CN103984803A (en) * | 2014-04-17 | 2014-08-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Finite element load application method |
| CN103984803B (en) * | 2014-04-17 | 2017-02-15 | 中国航空工业集团公司沈阳飞机设计研究所 | Finite element load application method |
| CN104392120A (en) * | 2014-11-07 | 2015-03-04 | 中冶京诚工程技术有限公司 | Design method of horizontal pull rod of high furnace bustle pipe |
| CN104392120B (en) * | 2014-11-07 | 2017-07-21 | 中冶京诚工程技术有限公司 | The design method of blast-furnace hot-air surrounding pipes girt |
| CN107480351A (en) * | 2017-07-28 | 2017-12-15 | 中国航空工业集团公司西安飞机设计研究所 | Engine hanging structure Optimization Design |
| CN107563039A (en) * | 2017-08-28 | 2018-01-09 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of intensity layout design method of aircraft engine installation system |
| CN111177853A (en) * | 2019-12-31 | 2020-05-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Wing type framework design method |
| CN111914352A (en) * | 2020-07-06 | 2020-11-10 | 西安飞机工业（集团）有限责任公司 | Design method for installation pull rod of airplane auxiliary power device |
| CN111914352B (en) * | 2020-07-06 | 2023-11-21 | 西安飞机工业（集团）有限责任公司 | Design method for mounting pull rod of auxiliary power device of airplane |
| CN113111436A (en) * | 2021-04-15 | 2021-07-13 | 泉州装备制造研究所 | Airplane large component pre-connection layout and multi-constraint action sequence optimization method |
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