CN106096089A - A kind of aircraft dynamics scale model undercarriage buffer spring - Google Patents
A kind of aircraft dynamics scale model undercarriage buffer spring Download PDFInfo
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- CN106096089A CN106096089A CN201610374263.8A CN201610374263A CN106096089A CN 106096089 A CN106096089 A CN 106096089A CN 201610374263 A CN201610374263 A CN 201610374263A CN 106096089 A CN106096089 A CN 106096089A
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- buffer spring
- undercarriage
- buffer
- load
- undercarriage buffer
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/30—Circuit design
- G06F30/36—Circuit design at the analogue level
- G06F30/367—Design verification, e.g. using simulation, simulation program with integrated circuit emphasis [SPICE], direct methods or relaxation methods
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Abstract
The present invention relates to a kind of aircraft dynamics scale model undercarriage buffer spring, including step one: predicted ground load, and calculate landing-gear load, including nose-gear load FnWith main landing gear load Fm；Step 2: by predetermined ratio, undercarriage buffer size is carried out contracting and compare；Step 3: the static pressure curve of undercarriage buffer is fitted to linearity curve；Step 4: determine buffer spring design constraint parameter according to predetermined ratio；Step 5: set up buffer spring actual parameter computing formula；Step 6: iterative computation buffer spring actual parameter；Step 7: choose optimized parameter group.The aircraft dynamics scale model undercarriage buffer spring of the present invention is under the mechanical property ensureing undercarriage buffer and moulded dimension premise, it is at utmost simplified, actual design is given to aircraft dynamics model undercarriage buffer, reduce design and processing cost, meet demanding kinetics and similarity requirement.
Description
Technical field
The invention belongs to aircraft structure strength dynamic test technical field, particularly relate to a kind of aircraft dynamics contracting and compare mould
Type undercarriage buffer spring.
Background technology
Aircraft dynamics institute scale model be true aircraft is carried out Scaling after it is carried out various test, can mend
The deficiency of the word analysis that makes up the number simulation.Undercarriage is the medium of aircraft and ground effects, and undercarriage buffer spring performance determines
The performance of undercarriage.
In conventional kinetic model design, undercarriage buffer is designed with following several method:
1) design of model undercarriage buffer is completely the same with true aircraft, and this undercarriage buffer is with high costs, knot
Structure is complicated；
2) model undercarriage buffer is reduced to spring, is only capable of meeting rough mechanical property, it is impossible to meet size in design
Requirement；
3) model undercarriage buffer is reduced to spring, is only capable of meeting dimensional requirement, mechanical property；
Summary of the invention
It is an object of the invention to provide one, solve at present.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of aircraft dynamics scale model undercarriage delays
Rush device spring, including
Step one: predicted ground load, and calculate landing-gear load, including nose-gear load FnCarry with main landing gear
Lotus Fm；
Step 2: by predetermined ratio, undercarriage buffer size is carried out contracting and compare；
Step 3: the static pressure curve of undercarriage buffer is fitted to linearity curve；
Step 4: determine buffer spring design constraint parameter according to predetermined ratio；
Step 5: set up buffer spring actual parameter computing formula；
Step 6: iterative computation buffer spring actual parameter；
Step 7: choose optimized parameter group.
Further, described actual parameter includes spring wire diameter, mean diameter of coil, curls up ratio, curvature correction factor, maximum perhaps
With load, deformable surplus, pitch, number of active coils, number of end coils.
Further, the straight method of curve matching uses method of least square.
A kind of aircraft dynamics scale model undercarriage buffer spring of the present invention can rise and fall in guarantee
Under the mechanical property of frame buffer and moulded dimension premise, it is at utmost simplified, aircraft dynamics model is risen and fallen
Frame buffer gives actual design, reduces design and processing cost, meets demanding kinetics and similarity 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 scale model undercarriage erect-position front view of one embodiment of the invention.
Fig. 2 is the scale model undercarriage erect-position side view of one embodiment of the invention.
Fig. 3 is the main landing gear buffer static pressure curve matching schematic diagram of one embodiment of the invention.
Fig. 4 is the nose landing gear bumper static pressure curve matching schematic diagram of one embodiment of the invention.
Fig. 5 is the aircraft dynamics scale model undercarriage buffer spring flow process of one embodiment of the invention
Figure.
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.
Being front view and the side view of scale model undercarriage erect-position as shown in Figures 1 and 2, L1～L10 in figure is institute
Indicate size, the size that may relate to during calculating includes but not limited to L1～L10 of above-mentioned sign, thus should not be used as right
The restriction of the present invention.The aircraft dynamics scale model undercarriage buffer spring flow process of the present invention is as shown in Figure 5:
1) predicted ground load
It is 72.89kg that scale model penetrates test body Model on opportunity weight；Blocking test body Model on opportunity weight is
61.22kg.Buffer load is designed by maximum body model weight 72.89kg.
Position of centre of gravity is along course away from head 1100mm, and test model undercarriage erect-position is as shown in Figure 1 and Figure 2.
Use FnRepresent nose-gear load, use FmRepresent main landing gear load, use tricks to calculate landing-gear load.
Solve and before above equation group obtains, play load FnAnd led load Fm:
2) undercarriage buffer size contracting ratio, is shown in Table 1.
In the present embodiment, contracting is 7 than ratio, will aircraft dynamics scale model be the 1/7 of original aircraft.
Table 1
3) matching buffer curve, will fit to straight line, as shown in Figure 3 and Figure 4 by buffer static pressure curve.
4) buffer spring design constraint parameter is determined according to predetermined ratio
Scale model undercarriage is got by true undercarriage 1:7 contracting ratio, therefore includes spring inside diameter, drift, rigidity
It has been determined that.With spring processing factory existence conditions, select spring material 60Si2Mn.Initial restriction condition is as shown in table 2:
Table 2
5) buffer spring parameter calculation formula is set up
With maximum allowable load for service load 150% as design object, mainly there is following design variable.
A) spring wire diameter d
B) mean diameter of coil D
C) curl up and compare c
D) curvature correction factor K
E) maximum allowable load p
F) deformable surplus n*t
N*t=H0-(nz-0.5)*d
G) pitch t
Wherein, G is material shear modulus
H) number of active coils ny
I) number of end coils nz
Spring material allowable stress [τ] has a small amount of change with spring wire diameter, ignores it herein and changes on a small quantity.
6) iteration goes out buffer spring actual parameter, and the data volume gone out due to iterative computation is huge, the most unlisted.
7) select optimized parameter group, see table shown in 3.
Table 3
The aircraft dynamics scale model undercarriage buffer spring of the present invention is ensureing undercarriage buffer
Mechanical property and moulded dimension premise under, it is at utmost simplified, to aircraft dynamics model undercarriage buffer
Give actual design, reduce 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. an aircraft dynamics scale model undercarriage buffer spring, it is characterised in that include
Step one: predicted ground load, and calculate landing-gear load, including nose-gear load FnWith main landing gear load Fm；
Step 2: by predetermined ratio, undercarriage buffer size is carried out contracting and compare；
Step 3: the static pressure curve of undercarriage buffer is fitted to linearity curve；
Step 4: determine buffer spring design constraint parameter according to predetermined ratio；
Step 5: set up buffer spring actual parameter computing formula；
Step 6: iterative computation buffer spring actual parameter；
Step 7: choose optimized parameter group.
Rectangle spar wing model quick-release type fixture the most according to claim 1, it is characterised in that described actual parameter bag
Include spring wire diameter, mean diameter of coil, curl up ratio, curvature correction factor, maximum allowable load, deformable surplus, pitch, coil
Number, number of end coils.
Rectangle spar wing model quick-release type fixture the most according to claim 1, it is characterised in that curve fits to straight line
Method use method of least square.
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| CN201610374263.8A CN106096089B (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft dynamics scale model undercarriage buffer spring |
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| CN201610374263.8A CN106096089B (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft dynamics scale model undercarriage buffer spring |
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| CN106096089B CN106096089B (en) | 2019-05-24 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108009334A (en) * | 2017-11-22 | 2018-05-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft freight transport system hanger rail joint load computational methods |
| 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 |
| GB2569768A (en) * | 2017-05-15 | 2019-07-03 | Airbus Operations Ltd | Shock absorber dimension |
| CN111507017A (en) * | 2020-04-30 | 2020-08-07 | 中国飞机强度研究所 | Dynamics modeling method of oil-gas separation type buffer |
| CN112711810A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for processing gusty dynamic load file |
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| WO2000059781A1 (en) * | 1999-04-06 | 2000-10-12 | Bae Systems Plc | An aircraft landing gear |
| CN104156552A (en) * | 2014-04-17 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Undercarriage load calculation method for ski-jump takeoff of aircraft on sloping board |
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| WO2000059781A1 (en) * | 1999-04-06 | 2000-10-12 | Bae Systems Plc | An aircraft landing gear |
| CN104156552A (en) * | 2014-04-17 | 2014-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | Undercarriage load calculation method for ski-jump takeoff of aircraft on sloping board |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2569768A (en) * | 2017-05-15 | 2019-07-03 | Airbus Operations Ltd | Shock absorber dimension |
| US11267560B2 (en) | 2017-05-15 | 2022-03-08 | Airbus Operations Limited | Shock absorber dimension |
| CN108009334A (en) * | 2017-11-22 | 2018-05-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft freight transport system hanger rail joint load computational methods |
| CN108009334B (en) * | 2017-11-22 | 2021-03-30 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating load of hanger rail joint of aircraft freight system |
| 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 |
| CN111507017A (en) * | 2020-04-30 | 2020-08-07 | 中国飞机强度研究所 | Dynamics modeling method of oil-gas separation type buffer |
| CN111507017B (en) * | 2020-04-30 | 2023-07-21 | 中国飞机强度研究所 | Dynamics modeling method of oil-gas separation type buffer |
| CN112711810A (en) * | 2020-12-29 | 2021-04-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for processing gusty dynamic load file |
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| Publication number | Publication date |
|---|---|
| CN106096089B (en) | 2019-05-24 |
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