CN106295059A - A kind of full dynamics model nose-gear method for designing and simplification structure - Google Patents
A kind of full dynamics model nose-gear method for designing and simplification structure Download PDFInfo
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- CN106295059A CN106295059A CN201610707946.0A CN201610707946A CN106295059A CN 106295059 A CN106295059 A CN 106295059A CN 201610707946 A CN201610707946 A CN 201610707946A CN 106295059 A CN106295059 A CN 106295059A
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Abstract
The present invention relates to a kind of full dynamics model nose-gear method for designing, including step one: according to the size of true nose-gear and by pre-reduced than the design size obtaining full dynamics model nose-gear；Step 2: obtain the mechanical property of the nose-gear force transferring structure after the force transferring structure of model nose-gear, and simulation calculation simplification according to the force transferring structure of true nose-gear；Step 3: be fitted according to the hydraulic bjuffer in true nose-gear and tire capability parameter, obtains nose-gear and simplifies spring rate and tire capability parameter in structure；Step 4: spring rate and tire capability parameter that the mechanical property obtained according to step 2 and step 3 obtain recalculate spring and tire size；Step 5: iteration optimization obtains the optimal size of full dynamics model nose-gear.The full dynamics model nose-gear method for designing of the present invention completely ensures that force transferring structure and force-transfer characteristic can design and meets dynamic test requirement.
Description
Technical field
The invention belongs to aircraft structure strength experimental technique field, particularly relate to a kind of full dynamics model nose-gear
Method for designing and simplification structure.
Background technology
Nose-gear be aircraft bottom for take off landing or ground taxi time support aircraft attached for ground moving
Part device, nose-gear is also the parts of transmission load important during aircraft landing.In conventional kinetic model design
In, nose landing gear bumper is designed with following several method:
(1) front model Landing Gear Design is completely the same with true aircraft, and this nose landing gear bumper is with high costs, structure
Complicated；Simultaneously as model nose-gear dimensional space is limited, processing request is high；
(2) model nose-gear is single pole and assembling tyre, bufferless part, and in test, nose-gear only provides support
Effect, it is impossible to meet mechanical curves requirement in test.
Summary of the invention
It is an object of the invention to provide a kind of full dynamics model nose-gear method for designing, solve current kinetics
The defect problem of nose-gear design in model.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of full dynamics model nose-gear design
Method, including
Step one: according to the size of true nose-gear and obtain full dynamics model nose-gear by pre-reduced ratio
Design size；
Step 2: obtain the power transmission knot of full dynamics model nose-gear according to the force transferring structure of true nose-gear
The mechanical property of the full dynamics model nose-gear force transferring structure after structure, and simulation calculation simplification；
Wherein, force transferring structure changes to:
" main load path is by fuselage urceolus hydraulic bjuffer inner core tire " changes to " fuselage inner core bullet
Spring buffer urceolus tire "；
" secondary load path is by arm urceolus anti-twisted under arm anti-twisted on fuselage strut " changes to " fuselage strut
Urceolus "；
Step 3: be fitted according to the hydraulic bjuffer in true nose-gear and tire capability parameter, obtains full machine
Kinetic model nose-gear simplifies spring rate and tire capability parameter in structure；
Step 4: spring rate and tyre performance that the mechanical property obtained according to step 2 and step 3 obtain are joined
Number recalculates spring and tire size；
Step 5: iteration optimization, obtains the optimal size of full dynamics model nose-gear.
Further, described pre-reduced than the ratio for true nose-gear size Yu full dynamics moulded dimension.
Present invention also offers a kind of full dynamics model nose-gear simplification structure and include inner core, spring urceolus, support
Bar and tire, described tire is two and connects with wheel shaft, and fix vertical with described wheel shaft center of described urceolus one end is connected, institute
Stating the urceolus other end to be connected with described inner core one end by spring, the other end of described inner core is fixed with fuselage, described strut one
End is fixed with urceolus, the strut other end is fixed with fuselage, and described strut axis place straight line is the first straight line, described urceolus, bullet
Spring and inner core place straight line are the second straight line, and the line of the fixing point of described inner core and fuselage and the fixing point of strut and fuselage is
3rd straight line, described first straight line, the second straight line and the 3rd straight line triangle at a right angle.
Full dynamics model nose-gear method for designing and the simplification structural integrity of the present invention ensure force transferring structure and biography
Force characteristic；Under given parameters, optimum simplification landing gear structure.Structure is simple and clear, and between part, constraint requirements is clear, it is easy to meet examination
Test parameter request；Manufacturing cost and technological requirement are low；Experiment proves that, landing-gear structural design meets dynamic test requirement.
Accompanying drawing explanation
Accompanying drawing herein is merged in description and constitutes the part of this specification, it is shown that meet the enforcement of the present invention
Example, and for explaining the principle of the present invention together with description.
Fig. 1 is the true nose-gear structure power transmission schematic diagram of one embodiment of the invention.
Fig. 2 is that the full dynamics model nose-gear of one embodiment of the invention simplifies structure power transmission schematic diagram.
Fig. 3 is the spring rate matching schematic diagram of one embodiment of the invention.
Fig. 4 is the full dynamics model schematic of one embodiment of the invention.
Fig. 5 is that the full dynamics model nose-gear of one embodiment of the invention simplifies structural representation.
Detailed description of the invention
Clearer for the purpose making the present invention implement, technical scheme and advantage, below in conjunction with in the embodiment of the present invention
Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, the most identical or class
As label represent same or similar element or there is the element of same or like function.Described embodiment is the present invention
A part of embodiment rather than whole embodiments.The embodiment described below with reference to accompanying drawing is exemplary type, it is intended to use
In explaining the present invention, and it is not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people
The every other embodiment that member is obtained under not making creation type work premise, broadly falls into the scope of protection of the invention.Under
Face combines accompanying drawing and is described in detail embodiments of the invention.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", "front", "rear",
The orientation of the instruction such as "left", "right", " vertically ", " level ", " top ", " end ", " interior ", " outward " or position relationship are for based on accompanying drawing institute
The orientation shown or position relationship, be for only for ease of and describe the present invention and simplify description rather than instruction or the dress of hint indication
Put or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that protect the present invention
The restriction of scope.
The full dynamics model nose-gear method for designing of the present invention, concrete steps include:
Step one: reduced rise than before obtaining full dynamics model according to the size of true nose-gear and parameter and by pre-
Fall the design size (or claim contracting than size) of frame, and wherein, pre-reduced ratio is true nose-gear size and full dynamics mould
The ratio of molded dimension, as shown in Table 1 and Table 2 for the structural parameters size, structural parameters and the scale factor that relate in nose-gear
Relational expression and the embodiment of certain nose-gear concrete structure parameter；
Parameter is compared in table 1 contracting
Examples of parameters is compared in table 2 contracting
Step 2: simplify according to the force transferring structure of true nose-gear and change and obtain full dynamics model nose-gear
Force transferring structure, and simulation calculation simplify after the mechanical property of full dynamics model nose-gear force transferring structure.
Need first to study true nose-gear force transferring structure before but simplifying, as it is shown in figure 1, real nose-gear passes
Power route is the most set forth below:
(1) fuselage is connected with urceolus, hinged with strut, downward power transmission, and 6 non-coplanar force elements are transmitted by fuselage by urceolus,
The one direction power in strut transmission strut direction；
(2) fuselage power passes to hydraulic bjuffer by urceolus lower end, after hydraulic bjuffer effect, in passing to
Cylinder, is ultimately transferred to tire；
(3) anti-twisted arm prevents inner/outer tube from twisting motion, is not involved in the transmission of power.
Simplify real undercarriage force transferring structure, and simulation calculation mechanical property afterwards, be specially
(1) " main load path is by fuselage urceolus hydraulic bjuffer inner core tire " simplification changes to " fuselage
Inner core spring buffer urceolus tire "；
(2) " secondary load path is by arm urceolus (undercarriage top) anti-twisted under arm anti-twisted on fuselage strut " simplifies
Changing to " fuselage strut urceolus (gear down) ", strut is meeting original force-transfer characteristic simultaneously, also acts as anti-twisted
The effect of arm, therefore, cancels anti-twisted arm member and (because strut to be connected with gear down, and cannot arrange strut in structure
Be connected with inner core, thus urceolus under).
Step 3: be fitted according to the hydraulic bjuffer in true nose-gear and tire capability parameter, obtains full machine
Kinetic model nose-gear simplifies spring rate and tire capability parameter in structure and (i.e. calculates buffer, tyre performance
Parameter).
Owing to true nose-gear hydraulic bjuffer mechanical characteristic is curve, spring mechanical characteristic is straight line, accordingly, it would be desirable to
Matching buffer mechanics characteristic curve, obtains spring rate K, as shown in Figure 3.
Tire capability parameter is typically based on test mission and requires to obtain maximum load F and matching true tire curve obtains
k。
Step 4: spring rate and tyre performance that the mechanical property obtained according to step 2 and step 3 obtain are joined
Number recalculates spring and tire size parameter.
Under buffer design size and spring mechanical performance framework, design requirement according to spring, spring buffer is entered
Row design.
The k obtained according to maximum load F and matching true tire curve, available tire radius d > F/k, further according to rising and falling
Frame layout dimension obtains tire size parameter.
Step 5: iteration optimization, obtains the optimal size of full dynamics model nose-gear.
According to the undercarriage force transferring structure initial parameter determined, set up kinetic model, optimization aim: model center of gravity is vertical
Acceleration is minimum.These iteration optimization many, obtain undercarriage as shown in table 3 below, are before simplifying thick full dynamics model and rise
Fall the design parameter of shelf structure.
Parameter after table 3 iteration optimization
| Sequence number | Parameter | Numerical value |
| 1 | Front the free elongation of spring | 84.7375504mm |
| 2 | Cylinder size in front | 132.491mm |
| 3 | Front outer cylinder size | 103.183mm |
| 4 | Front tire radius | 60mm |
| 5 | Front tire vertical stiffness | 30000N/m |
| 6 | Front tire damped coefficient | 100kg/s |
| 7 | Front spring rate 100% | 6020N/m |
| 8 | Front spring damping coefficient | 300kg/s |
Finally, the full dynamics model nose-gear in the present invention is simplified structure and is further elaborated, in it includes
Cylinder 1, spring 2, urceolus 3, strut 4 and tire 5, described tire 5 is two and connects with wheel shaft, and described urceolus 3 one end is with described
Wheel shaft center is vertically fixing to be connected, and described urceolus 3 other end is connected with described inner core 1 by spring 2, described inner core 1 other end
Fixing with fuselage, described strut 4 one end is fixing with urceolus 3, the other end is fixed with fuselage, and described strut 4 place straight line is first
Straight line, described urceolus 3, spring 2 and inner core 1 place straight line are the second straight line, described inner core 1 and the fixing point of fuselage and strut 4
It is the 3rd straight line with the line of the fixing point of fuselage, described first straight line, the second straight line and the 3rd straight line triangle at a right angle.
The full dynamics model nose-gear method for designing of the present invention and simplification structure are using true nose-gear as ginseng
According to, at utmost retain undercarriage force transferring structure, and tyre performance carries out contracting ratio according to true nose-gear performance parameter, and
And hydraulic bjuffer is reduced to spring mechanism, matching buffer force diagram is designed.In the mechanical property ensureing undercarriage
With under moulded dimension premise, it is at utmost simplified, aircraft dynamics model undercarriage is given actual design, fall
Low design and processing cost, meet demanding kinetics and similarity requirement.
The above, the only optimum detailed description of the invention of the present invention, but protection scope of the present invention is not limited thereto,
Any those familiar with the art in the technical scope that the invention discloses, the change that can readily occur in or replacement,
All should contain within protection scope of the present invention.Therefore, protection scope of the present invention should be with the protection model of described claim
Enclose and be as the criterion.
Claims (3)
1. a full dynamics model nose-gear method for designing, it is characterised in that include
Step one: according to the size of true nose-gear and by pre-reduced than the design obtaining full dynamics model nose-gear
Size；
Step 2: obtain the force transferring structure of full dynamics model nose-gear according to the force transferring structure of true nose-gear, and
The mechanical property of the full dynamics model nose-gear force transferring structure after simulation calculation simplification；
Wherein force transferring structure changes to:
" main load path is by fuselage urceolus hydraulic bjuffer inner core tire " change to " fuselage inner core spring delay
Rush device urceolus tire "；
" secondary load path is by arm urceolus anti-twisted under arm anti-twisted on fuselage strut " changes to " outside fuselage strut
Cylinder "；
Step 3: be fitted respectively according to the hydraulic bjuffer in true nose-gear and tire capability parameter, obtains full machine
Kinetic model nose-gear simplifies spring rate and tire capability parameter in structure；
Step 4: spring rate that the mechanical property obtained according to step 2 and step 3 obtain and tire capability parameter weight
New calculating spring and tire size；
Step 5: iteration optimization, obtains the optimal size of full dynamics model nose-gear.
Full dynamics model nose-gear method for designing the most according to claim 1, it is characterised in that described pre-reduced
Than the ratio for true nose-gear size Yu full dynamics moulded dimension.
3. a full dynamics model nose-gear simplifies structure, it is characterised in that include inner core (1), spring (2) urceolus
(3), strut (4) and tire (5), two described tires (5) connect with wheel shaft, described urceolus (3) one end and described wheel shaft center
Vertical fixing connection, described urceolus (3) other end is connected with described inner core (1) one end by spring (2), described inner core (1)
The other end is fixed with fuselage, and described strut (4) one end is fixing with urceolus (3), strut (4) other end is fixed with fuselage, strut (4)
Axis place straight line is the first straight line, and urceolus (3), spring (2) and inner core (1) axis place straight line are the second straight line, described interior
The line of the fixing point of cylinder (1) and fuselage and the fixing point of strut (4) and fuselage is the 3rd straight line, described first straight line, second
Straight line and the 3rd straight line triangle at a right angle.
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| CN201610707946.0A CN106295059B (en) | 2016-08-23 | 2016-08-23 | Design method and simplified structure of full-aircraft dynamic model nose landing gear |
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| CN201610707946.0A CN106295059B (en) | 2016-08-23 | 2016-08-23 | Design method and simplified structure of full-aircraft dynamic model nose landing gear |
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| CN106295059B CN106295059B (en) | 2019-12-31 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110682751B (en) * | 2019-10-17 | 2022-07-15 | 哈尔滨工程大学 | Mechanism for assisting aircraft to land and water slide based on water-beating float principle |
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- 2016-08-23 CN CN201610707946.0A patent/CN106295059B/en active Active
Non-Patent Citations (1)
| Title |
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| 王细洋: "《航空概论》", 31 August 2006 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110682751B (en) * | 2019-10-17 | 2022-07-15 | 哈尔滨工程大学 | Mechanism for assisting aircraft to land and water slide based on water-beating float principle |
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