CN106295061A - A kind of full dynamics model main landing gear method for designing and simplification structure - Google Patents
A kind of full dynamics model main landing gear method for designing and simplification structure Download PDFInfo
- Publication number
- CN106295061A CN106295061A CN201610708288.7A CN201610708288A CN106295061A CN 106295061 A CN106295061 A CN 106295061A CN 201610708288 A CN201610708288 A CN 201610708288A CN 106295061 A CN106295061 A CN 106295061A
- Authority
- CN
- China
- Prior art keywords
- landing gear
- main landing
- tire
- urceolus
- dynamics model
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
-
- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/20—Design optimisation, verification or simulation
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Theoretical Computer Science (AREA)
- Geometry (AREA)
- General Physics & Mathematics (AREA)
- Evolutionary Computation (AREA)
- General Engineering & Computer Science (AREA)
- Computer Hardware Design (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Computational Mathematics (AREA)
- Mathematical Analysis (AREA)
- Mathematical Optimization (AREA)
- Pure & Applied Mathematics (AREA)
- Tires In General (AREA)
Abstract
The present invention relates to a kind of full dynamics model main landing gear method for designing, including step one: according to the size of true main landing gear and by pre-reduced than the design size obtaining full dynamics model main landing gear；Step 2: obtain the mechanical property of the main landing gear force transferring structure after the force transferring structure of model main landing gear, and simulation calculation simplification according to the force transferring structure of true main landing gear；Step 3: be fitted according to the hydraulic bjuffer in true main landing gear and tire capability parameter, obtains main landing 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 main landing gear.The full dynamics model main landing 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 main landing gear
Method for designing and simplification structure.
Background technology
Main landing gear is the medium of aircraft and ground effects, and in conventional kinetic model design, main landing gear buffers
Device is designed with following several method:
(1) design of model main landing gear is completely the same with true aircraft, and this main landing gear buffer is with high costs, structure
Complicated；Simultaneously as model main landing gear dimensional space is limited, processing request is high；
(2) model main landing gear is single pole and assembling tyre, bufferless part, and in test, main landing 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 main landing gear method for designing, solve current driving force mould
The defect problem of main landing gear design in type.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of full dynamics model main landing gear design
Method, including
Step one: according to the size of true main landing gear and obtain full dynamics model main landing gear by pre-reduced ratio
Design size；
Step 2: obtain the power transmission knot of full dynamics model main landing gear according to the force transferring structure of true main landing gear
The mechanical property of the full dynamics model main landing 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 urceolus bullet
Spring buffer inner core tire "；
Cancelling the Path of Force Transfer of original structure " strut fuselage urceolus ", fuselage is converted into by hinged with urceolus type of attachment
Fixing connection；
Step 3: be fitted according to the hydraulic bjuffer in true main landing gear and tire capability parameter, obtains full machine
Kinetic model main landing 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 main landing gear.
Further, described pre-reduced than the ratio for true main landing gear size Yu full dynamics moulded dimension.
Present invention also offers a kind of full dynamics model main landing gear and simplify structure, including urceolus, spring, inner core,
Upper anti-twisted arm, under anti-twisted arm, tire, termination, clip and lining, tire is installed on wheel shaft, and lining overlaps outer tube, inner core one
End is fixed on wheel shaft, the other end of inner core stretches into outer barrel and inner core is fixed with termination, and urceolus is fixed with fuselage, with inner core
The urceolus one end connected is provided with clip (8), spring housing outer tube and as between clip and wheel shaft, upper anti-twisted arm one end with
Urceolus is hinged, the other end with under one end of anti-twisted arm hinged, under the other end of anti-twisted arm be articulated with wheel shaft.
Full dynamics model main landing 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 main landing gear structure, structure is simple and clear, and between part, constraint requirements is clear, it is easy to meet
Test parameters requirement；Manufacturing cost and technological requirement are low；Experiment proves that, landing-gear structural design meets dynamic test to be wanted
Ask.
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 main landing gear structure power transmission schematic diagram of one embodiment of the invention.
Fig. 2 is that the full dynamics model main landing 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. 5-1 to Fig. 5-3 is the full dynamics model main landing gear of one embodiment of the invention and 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 main landing gear method for designing of the present invention, concrete steps include:
Step one: according to the size of true main landing gear and obtain full dynamics model main landing gear by pre-reduced ratio
Design size (or claiming contracting than size), wherein, pre-reduced ratio is true nose-gear size and full dynamics moulded dimension
Ratio, as shown in Table 1 and Table 2 for the structural parameters size related in nose-gear, the relation of structural parameters and scale factor
Formula 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 the mechanical property of full dynamics model nose-gear force transferring structure after simulation calculation change；
Need first to study true main landing gear force transferring structure before but simplifying, explain as it is shown in figure 1, load path is following
State:
(1) fuselage is hinged with urceolus, hinged with strut, downward power transmission, the stable triangular machine that fuselage, strut and urceolus are constituted
6 non-coplanar force elements are transmitted by structure by urceolus；
(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 and change real main landing gear force transferring structure, and simulation calculation mechanical property afterwards, be specially
(1) " main load path is by fuselage urceolus (strut) hydraulic bjuffer inner core tire " simplifies and changes to
" fuselage urceolus spring buffer inner core tire "；
(2) fuselage and urceolus type of attachment are converted into connected by hinged, and fuselage can transmit six spaces by urceolus joint
Power element；
(3) it is sufficient for landing load due to the model weight in the present embodiment at about 60kg, material properties, cancels former
" strut connects fuselage urceolus (undercarriage top) " this Path of Force Transfer in structure, namely that fuselage is hinged with urceolus,
The single Path of Force Transfer that stable triangular organisation conversion be fuselage urceolus hinged with strut；
(4) bumper portion is converted to spring buffer by hydraulic cylinder, substantially reduces physical dimension and processing cost；
(5) the upper and lower through hole in termination, when preventing inner/outer tube relative motion, in confined space, produces air spring force, impact
Mechanical property.
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 main landing gear buffer is hydraulic bjuffer, it is reduced to spring buffer.Hydraulic bjuffer power
Learning characteristic is curve, and spring mechanical characteristic is straight line, accordingly, it would be desirable to matching buffer mechanics characteristic curve, obtains spring rate
COEFFICIENT K.
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.
Scale model undercarriage by true main landing gear 1:6.5 contracting ratio get, therefore include spring inside diameter, drift,
Rigidity it has been determined that.With spring processing factory existence conditions, select spring material 60SiMn.Therefore, the initial of spring design is obtained
Restriction condition.
With maximum allowable load for service load 150% as design object, according to navigation mark " HB 3-51-2008 carbon element, conjunction
Gold steel wire cylindroid helical-coil compression spring ", design spring parameter.
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.
Parameter after table 3 iteration optimization
| Sequence number | Parameter | Numerical value |
| 1 | Lead the free elongation of spring | 117.5111mm |
| 2 | Cylinder size in having led | 195mm |
| 3 | Lead outer cylinder size | 181.5mm |
| 4 | Lead tire radius | 90mm |
| 5 | Lead tire vertical stiffness | 32000N/m |
| 6 | Lead tire damped coefficient | 100kg/s |
| 7 | Lead spring rate 100% | 12050N/m |
| 8 | Lead spring damping coefficient | 400kg/s |
Finally, in the present invention full dynamics model main landing gear simplify structure be further elaborated, as Fig. 5-1 to
Shown in Fig. 5-3, wherein Fig. 5-2 is front view, and Fig. 5-1 and Fig. 5-3 is respectively right view and sectional view, it include urceolus, spring,
Inner core, upper anti-twisted arm, under anti-twisted arm, tire, termination, clip and lining, tire is installed on wheel shaft, and inner core one end is fixed on wheel
Axle, its other end are cased with lining and are fixed with termination, insert into the inner portion from one end of urceolus afterwards, the other end of urceolus and fuselage
Fixing, the urceolus one end being connected with inner core is provided with clip, and spring housing is outer tube and as between clip and wheel shaft, upper anti-twisted
Arm one end is hinged with urceolus, its other end with under one end of anti-twisted arm hinged, under the other end of anti-twisted arm be articulated with wheel shaft.
The full dynamics model main landing gear method for designing of the present invention and simplification structure are using true main landing gear as ginseng
According to, at utmost retain main landing gear force transferring structure；Tyre performance carries out contracting ratio according to true main landing gear performance parameter；Hydraulic pressure
Buffer is reduced to spring mechanism, and matching hydraulic bjuffer force diagram is designed.In the mechanical property ensureing main landing gear
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 main landing gear method for designing, it is characterised in that include
Step one: according to the size of true main landing gear and by pre-reduced than the design obtaining full dynamics model main landing gear
Size；
Step 2: obtain the force transferring structure of full dynamics model main landing gear according to the force transferring structure of true main landing gear, and
The mechanical property of the full dynamics model main landing 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 " be reduced to " fuselage urceolus spring delay
Rush device inner core tire "；
Cancel the Path of Force Transfer of original structure " strut fuselage urceolus ", fuselage and urceolus type of attachment by hinged be converted into fixing
Connect；
Step 3: be fitted respectively according to the hydraulic bjuffer in true main landing gear and tire capability parameter, obtains full machine
Kinetic model main landing 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 main landing gear.
Full dynamics model main landing gear method for designing the most according to claim 1, it is characterised in that described pre-reduced
Than the ratio for true main landing gear size Yu full dynamics moulded dimension.
3. a full dynamics model main landing gear simplifies structure, it is characterised in that include urceolus (1), spring (2), inner core
(3), upper anti-twisted arm (4), under anti-twisted arm (5), tire (6), termination (7), clip (8) and lining (9), tire (6) is installed on wheel
On axle, lining (9) is enclosed within inner core (3) outward, and inner core (3) one end is fixed on wheel shaft, and the other end of inner core (3) stretches into urceolus (1)
Internal and inner core (3) is fixed with termination (7), urceolus (1) and fixing with fuselage, and urceolus (1) one end being connected with inner core (3) is installed
Have clip (8), spring (2) to be enclosed within inner core (3) outward and to be placed between clip (1) and wheel shaft, upper anti-twisted arm (4) one end and urceolus
(1) hinged, the other end with under one end of anti-twisted arm (5) hinged, under the other end of anti-twisted arm (5) be articulated with wheel shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610708288.7A CN106295061B (en) | 2016-08-23 | 2016-08-23 | Design method and simplified structure of main undercarriage of full-aircraft dynamic model |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610708288.7A CN106295061B (en) | 2016-08-23 | 2016-08-23 | Design method and simplified structure of main undercarriage of full-aircraft dynamic model |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106295061A true CN106295061A (en) | 2017-01-04 |
| CN106295061B CN106295061B (en) | 2019-12-31 |
Family
ID=57615001
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610708288.7A Active CN106295061B (en) | 2016-08-23 | 2016-08-23 | Design method and simplified structure of main undercarriage of full-aircraft dynamic model |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106295061B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109522636A (en) * | 2018-11-09 | 2019-03-26 | 中国直升机设计研究所 | A kind of simplified method of wheel undercarriage for the analysis of helicopter anti-crash |
| CN112069712A (en) * | 2020-09-07 | 2020-12-11 | 中国航空工业集团公司成都飞机设计研究所 | Method for rapidly analyzing landing load of support arm type undercarriage |
| CN112793805A (en) * | 2020-12-29 | 2021-05-14 | 中国航空工业集团公司西安飞机设计研究所 | Full-machine drop-out shrinkage ratio model test method |
-
2016
- 2016-08-23 CN CN201610708288.7A patent/CN106295061B/en active Active
Non-Patent Citations (1)
| Title |
|---|
| 王细洋: "《航空概论》", 31 August 2006 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109522636A (en) * | 2018-11-09 | 2019-03-26 | 中国直升机设计研究所 | A kind of simplified method of wheel undercarriage for the analysis of helicopter anti-crash |
| CN109522636B (en) * | 2018-11-09 | 2022-12-30 | 中国直升机设计研究所 | Wheel type undercarriage simplifying method for helicopter crash-resistant analysis |
| CN112069712A (en) * | 2020-09-07 | 2020-12-11 | 中国航空工业集团公司成都飞机设计研究所 | Method for rapidly analyzing landing load of support arm type undercarriage |
| CN112069712B (en) * | 2020-09-07 | 2022-10-11 | 中国航空工业集团公司成都飞机设计研究所 | Method for rapidly analyzing landing load of support arm type undercarriage |
| CN112793805A (en) * | 2020-12-29 | 2021-05-14 | 中国航空工业集团公司西安飞机设计研究所 | Full-machine drop-out shrinkage ratio model test method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106295061B (en) | 2019-12-31 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106295061A (en) | A kind of full dynamics model main landing gear method for designing and simplification structure | |
| CN102507065B (en) | Device for reducing thrust and vibration at pipeline ends | |
| EP2892740B1 (en) | An air spring with a linearized spring rate | |
| CN104912988A (en) | Suspension system of vehicle and design method thereof | |
| CN106096089A (en) | A kind of aircraft dynamics scale model undercarriage buffer spring | |
| CN104373494B (en) | A kind of multiple degrees of freedom metal-rubber damper | |
| CN206106852U (en) | Swing arm bush and swing arm liner assembly | |
| CN104832592B (en) | Adaptive equal-rigidity vibration isolator based on air-floatation-damping three-direction decoupling | |
| CN204755703U (en) | Suspension of vehicle | |
| CN206984323U (en) | A kind of landing gear structure of novel plant protection unmanned plane | |
| CN102330767A (en) | Air spring vibration isolator based on gas-solid damping and coupling action adjusted by air cylinder | |
| CN100361833C (en) | Shock-proof suspension for engineering vehicle front bridge | |
| CN106295059A (en) | A kind of full dynamics model nose-gear method for designing and simplification structure | |
| CN102146976A (en) | Sliding block adjustment-based air spring vibration isolator with gas-solid damping coupling effect | |
| CN109253314B (en) | Pipeline low frequency support and hanger | |
| CN109139769B (en) | Multi-annular tuning liquid damper based on extra-high voltage composite sleeve and method thereof | |
| CN206290634U (en) | Pick up rear shock absorber bushing and damper | |
| CN205365058U (en) | Shock attenuation wheel | |
| CN113606278B (en) | Multi freedom vibration isolation system | |
| CN112406554B (en) | Three-stage buffering vibration reduction system and method for adapting to collision vibration of double-track suspended vehicle body | |
| CN212386492U (en) | Transverse and longitudinal integrated non-power framework device with temperature-measurable axle box | |
| CN210971256U (en) | High-sealing automobile steering device | |
| CN202924692U (en) | Mounting structure of chassis balance weight, chassis and aerial work platform | |
| CN207173217U (en) | A kind of three mass suspension systems for chassis vibration damping | |
| CN106402259A (en) | Inner and outer spring bumper |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |