CN109738147A - A kind of equivalent drop-test method of more pillar undercarriages - Google Patents
A kind of equivalent drop-test method of more pillar undercarriages Download PDFInfo
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- CN109738147A CN109738147A CN201811286449.3A CN201811286449A CN109738147A CN 109738147 A CN109738147 A CN 109738147A CN 201811286449 A CN201811286449 A CN 201811286449A CN 109738147 A CN109738147 A CN 109738147A
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- undercarriage
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Abstract
The invention discloses a kind of more equivalent drop-test methods of pillar undercarriage, include the following steps: that Landing Gear Design parameter filling medium physical parameter is estimated；More pillar undercarriage virtual tests；The distribution of more pillar undercarriage function amounts and wheel contact to earth subsidence velocity；Each pillar undercarriage equivalent quality；Each single strut landing gear physics drop-test；Physical/virtual tests correlation analysis；The identification of filling medium physical parameter；Step 2 is repeated to step 7 at least once.The present invention gives the test parameters calculation methods and testing program of more equivalent drop-tests of pillar undercarriage, solve the problems, such as that more pillar landing gear drop tests are decomposed into each single strut landing gear test, a kind of new technological approaches is created for undercarriage dynamic test verifying, a large number of experiments funds can be saved and effectively shortens the test period.
Description
Technical field
The invention belongs to undercarriage dynamic tests to verify field, in particular to a kind of more pillar undercarriages are equivalent to fall shake examination
Proved recipe method is mainly used in the cushion performance verification test of more pillar undercarriages, solves more pillar landing gear drop tests etc.
Effect is the problem of how equivalent test parameter determines when each single strut landing gear is tested and experiment process is formulated.
Background technique
Large aircraft is since structure is big, loads weight, the general structure total arrangement for using multi-wheel and multi-support undercarriage, mesh
Be in order to effectively disperse and mitigate aircraft landing is sliding run when shock loading, mitigate airfield runway shock resistance design strength,
Reduce the design rigidity and design weight of undercarriage.
Due to the landing gear drop test facility cost for verifying Design of Aircraft Landing Gears and aircraft landing load
Valuableness, any design group can not constantly update and expand its landing gear drop test facility as large transport airplane develops
Scale.Therefore, how to convert each single strut landing gear test for more pillar landing gear drop tests is effectively to solve this to ask
The key of topic.
More equivalent drop-test parameters of pillar undercarriage include that top rake is installed in each single strut landing gear test, wheel contacts to earth
Subsidence velocity, aircraft equivalent quality and airplane ascensional force coefficient etc., difficult point are the determinations of aircraft equivalent quality.It is usual for aircraft
Two o'clock it is horizontal or tail-down symmetrical landing situation, national military standard (GJB67.4-85) regulation airframe two sides main landing gear relate to
And aircraft equivalent quality (md) it is respectively the half (M of aircraft landing designing qualityz/2).If main of airframe two sides
It falls frame and is made of two independent undercarriages, then the aircraft equivalent quality of each single undercarriage can not be simply divided into winged
The a quarter of machine landing designing quality, and must can just be determined by further investigation.
It is proposed the present invention is based on energy equivalence Principle and a kind of more pillar landing gear drop tests is equivalent to each one-mast support
The method of gear test.This method is in such a way that a kind of physical test and virtual test combine, wherein the void of more pillars
Quasi- test is that the distribution of function amount and undercarriage wheel in order to obtain more pillar undercarriages are contacted to earth subsidence velocity, for use in equivalent examination
Test the determination of parameter.
Summary of the invention
Goal of the invention
It is an object of the invention to propose a kind of solve with the more pillars of existing one-mast support drop-test appointed condition verifying
The test method for falling frame cushion performance, provides the equivalent drop-test scheme of more pillar undercarriages and equivalent drop-test parameter calculates
Method.
Inventive technique solution
In order to achieve the above-mentioned object of the invention, the present invention uses following technical solutions:
A kind of equivalent drop-test method of more pillar undercarriages, include the following steps: step 1: Landing Gear Design parameter is filled
Fill out medium physics parameter Estimation；Step 2: more pillar undercarriage virtual tests；Step 3: more pillar undercarriage function amount distribution and machine
Take turns the subsidence velocity that contacts to earth；Step 4: each pillar undercarriage equivalent quality；Step 5: each single strut landing gear physics drop-test；Step
Rapid 6: physical/virtual tests correlation analysis；Step 7: the identification of filling medium physical parameter；Step 8: repeating step 2 to step 7
At least once.
Preferably, for the twin props main landing gear of forward and backward arrangement, the calculation method of undercarriage function amount distribution in step 3
It is as follows: twin props undercarriage dynamic analysis model being established according to known conditions, and passes through aircraft horizontal landing or tail-down
The imitative liter to land landings impact simulation analysis, can obtain the function amount A of forward and backward main landing gear absorption in the case of various landingsBeforeWith
AAfterwards
In formula, MdFor twin props undercarriage equivalent quality, wherein including pillar lower motion component and wheel quality；Vy is
Aircraft subsidence velocity, A are that forward and backward main landing gear absorbs total work amount.
Preferably, for the twin props main landing gear of forward and backward arrangement, wheel contacts to earth the calculating side of subsidence velocity in step 3
Method are as follows: since whether aircraft horizontal landing or tail-down are landed, after being usually at first master lands, and therefore, leads afterwards
Landing subsidence velocity be aircraft landing subsidence velocity Vy, and the landing subsidence velocity V that preceding master risesBefore yV should be less thany, this
It is to have led absorbed a part of kinetic energy of aircraft afterwards because preceding master rises when landing；I.e.
And
In formula, when Δ A is that preceding master lands, a part of landing kinetic energy of the aircraft absorbed, P have been led afterwardsAfterwardsFor rear master
The ground vertical load risen, ycCenter of gravity of airplane displacement after landing for twin props undercarriage, Δ y are to be landed by rear master to preceding master
Act the center of gravity of airplane displacement to land.
Preferably, for the twin props main landing gear of forward and backward arrangement, the calculation method of step 4 are as follows: according to undercarriage energy
It absorbs equivalence principle, and in view of twin props undercarriage lands the variation of subsidence velocity, following forward and backward main landing gear can be obtained
The equivalent quality M of equivalent drop-testBeforeAnd MAfterwards。
Advantages of the present invention
The present invention has the advantages that
The test parameters calculation method and testing program of more equivalent drop-tests of pillar undercarriage are given, solves more
Column landing gear drop test is decomposed into the problem of each single strut landing gear test, creates one for undercarriage dynamic test verifying
Kind new technological approaches can save a large number of experiments funds and effectively shorten the test period.
Detailed description of the invention
Fig. 1 is a kind of flow diagram of more equivalent drop-test methods of pillar undercarriage of the invention.
Specific embodiment
In conjunction with summary of the invention general introduction and attached drawing, the specific embodiment that the present invention will be described in detail.
A kind of equivalent drop-test method of more pillar undercarriages, flow diagram is shown in Fig. 1, using a kind of physical test and void
It is quasi- to test the mode combined, wherein the virtual test of more pillars is the distribution of function amount and the front row in order to obtain more pillar undercarriages
Undercarriage wheel contacts to earth subsidence velocity, for use in the determination of equivalent test parameter.
Include the following steps: step 1: the estimation of Landing Gear Design parameter filling medium physical parameter；Step 2: more pillars rise
Fall frame virtual test；Step 3: the distribution of more pillar undercarriage function amounts and wheel contact to earth subsidence velocity；Step 4: each pillar undercarriage
Equivalent quality；Step 5: each single strut landing gear physics drop-test；Step 6: physical/virtual tests correlation analysis；Step
7: the identification of filling medium physical parameter；Step 8: repeating step 2 to step 7 at least once.
Due to the certain parameters of filling medium (such as air polytropic index of compression and oilhole discharge coefficient) must by test/point
The correlation analysis of analysis result can just provide its exact value, need to carry out step 8 to obtain correct equivalent drop-test result.
In the past, for the twin props main landing gear arranged afterwards, the equivalent drop-test parameter of more pillar undercarriages is illustrated really
Determine method.
Known conditions is twin props undercarriage equivalent quality Md(component of lower motion containing pillar and wheel quality) and aircraft
Subsidence velocity Vy；Each damper leg structure of undercarriage and oilhole pattern, geometric dimension, pillar oil gas chamber filling parameters and wheel are rigid
It writes music line；It is risen in aircraft landing sinking watching again than being 1.
According to above-mentioned known conditions, establish twin props undercarriage dynamic analysis model, and by aircraft horizontal landing or
The imitative liter that tail-down is landed landings impact simulation analysis, can obtain what forward and backward main landing gear in the case of various landings absorbed
Function amount ABeforeAnd AAfterwards, it is clear that
Since whether aircraft horizontal landing or tail-down are landed, after being usually at first master lands, therefore, rear main
The landing subsidence velocity risen is the landing subsidence velocity V of aircrafty, and the landing subsidence velocity V that preceding master risesBefore yV should be less thany,
This is because preceding master rises when landing, leads absorbed a part of kinetic energy of aircraft afterwards.I.e.
And
In formula, when Δ A is that preceding master lands, a part of landing kinetic energy of the aircraft absorbed, P have been led afterwardsAfterwardsFor rear master
The ground vertical load risen, ycCenter of gravity of airplane displacement after landing for twin props undercarriage, Δ y are to be landed by rear master to preceding master
Act the center of gravity of airplane displacement to land.
It, can according to undercarriage energy absorption equivalence principle, and in view of twin props undercarriage lands the variation of subsidence velocity
To obtain the equivalent quality of the following forward and backward equivalent drop-test of main landing gear.
The present invention is based on the principle of equal effects, consider more pillar undercarriage landing subsidence velocity difference, propose a kind of completely new more
The equivalent drop-test concept of pillar undercarriage and experimental technique, physical test is combined with virtual test, passes through more pillars
Virtual test obtains the function amount distribution of more pillar undercarriages and undercarriage wheel contacts to earth subsidence velocity, is used for one-mast support equivalent test
The determination of parameter, to obtain a kind of slow by the more pillar undercarriages of the equivalent verifying large aircraft of single strut landing gear drop-test
The test method of punching performance solves the effective use more pillar undercarriage resiliencies of single strut landing gear drop-test device authentication
The approach of energy.
Claims (4)
1. a kind of equivalent drop-test method of more pillar undercarriages, which comprises the steps of:
Step 1: the estimation of Landing Gear Design parameter filling medium physical parameter；
Step 2: more pillar undercarriage virtual tests；
Step 3: the distribution of more pillar undercarriage function amounts and wheel contact to earth subsidence velocity；
Step 4: each pillar undercarriage equivalent quality；
Step 5: each single strut landing gear physics drop-test；
Step 6: physical/virtual tests correlation analysis；
Step 7: the identification of filling medium physical parameter；
Step 8: repeating step 2 to step 7 at least once.
2. a kind of more equivalent drop-test methods of pillar undercarriage as described in claim 1, which is characterized in that for forward and backward
The twin props main landing gear of arrangement, the calculation method of undercarriage function amount distribution is as follows in step 3: establishing double branch according to known conditions
Column undercarriage dynamic analysis model, and emulation point is landinged impact by the imitative liter that aircraft horizontal landing or tail-down are landed
Analysis can obtain the function amount A of forward and backward main landing gear absorption in the case of various landingsBeforeAnd AAfterwards
In formula, MdFor twin props undercarriage equivalent quality, wherein including pillar lower motion component and wheel quality；Vy is aircraft
Subsidence velocity, A are that forward and backward main landing gear absorbs total work amount.
3. a kind of more equivalent drop-test methods of pillar undercarriage as claimed in claim 2, which is characterized in that for forward and backward
The twin props main landing gear of arrangement, wheel contacts to earth the calculation method of subsidence velocity in step 3 are as follows:
Since whether aircraft horizontal landing or tail-down are landed, after being usually at first master lands, and therefore, has led afterwards
Landing subsidence velocity is the landing subsidence velocity V of aircrafty, and the landing subsidence velocity V that preceding master risesBefore yV should be less thany, this is
Because when preceding master lands, having led absorbed a part of kinetic energy of aircraft afterwards；I.e.
And
In formula, when Δ A is that preceding master lands, a part of landing kinetic energy of the aircraft absorbed, P have been led afterwardsAfterwardsIt is risen for rear master
Ground vertical load, ycCenter of gravity of airplane displacement after landing for twin props undercarriage, Δ y are to be landed by rear master to preceding master to play
The center of gravity of airplane displacement on ground.
4. a kind of more equivalent drop-test methods of pillar undercarriage as claimed in claim 3, which is characterized in that for forward and backward
The twin props main landing gear of arrangement, the calculation method of step 4 are as follows:
According to undercarriage energy absorption equivalence principle, and in view of twin props undercarriage lands the variation of subsidence velocity, can obtain
Obtain the equivalent quality M of the equivalent drop-test of forward and backward main landing gear as followsBeforeAnd MAfterwards。
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110589019A (en) * | 2019-09-09 | 2019-12-20 | 中国航空工业集团公司北京长城航空测控技术研究所 | Force loading method and loading device for high-speed retraction and extension test of 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 |
| CN117465691A (en) * | 2023-12-28 | 2024-01-30 | 中国飞机强度研究所 | Aircraft landing gear drop test device and method considering high temperature influence |
| CN117556552A (en) * | 2024-01-12 | 2024-02-13 | 中国飞机强度研究所 | Data-driven-based aircraft landing gear drop test optimization method |
| CN117622514A (en) * | 2024-01-25 | 2024-03-01 | 中国飞机强度研究所 | Device and method for simulating landing gear drop test environment of aircraft by considering high-temperature influence |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110589019A (en) * | 2019-09-09 | 2019-12-20 | 中国航空工业集团公司北京长城航空测控技术研究所 | Force loading method and loading device for high-speed retraction and extension test of undercarriage |
| CN110589019B (en) * | 2019-09-09 | 2021-07-13 | 中国航空工业集团公司北京长城航空测控技术研究所 | Force loading method and loading device for high-speed retraction and extension test of 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 |
| CN117465691A (en) * | 2023-12-28 | 2024-01-30 | 中国飞机强度研究所 | Aircraft landing gear drop test device and method considering high temperature influence |
| CN117465691B (en) * | 2023-12-28 | 2024-03-08 | 中国飞机强度研究所 | Aircraft landing gear drop test device and method considering high temperature influence |
| CN117556552A (en) * | 2024-01-12 | 2024-02-13 | 中国飞机强度研究所 | Data-driven-based aircraft landing gear drop test optimization method |
| CN117556552B (en) * | 2024-01-12 | 2024-04-12 | 中国飞机强度研究所 | Data-driven-based aircraft landing gear drop test optimization method |
| CN117622514A (en) * | 2024-01-25 | 2024-03-01 | 中国飞机强度研究所 | Device and method for simulating landing gear drop test environment of aircraft by considering high-temperature influence |
| CN117622514B (en) * | 2024-01-25 | 2024-04-16 | 中国飞机强度研究所 | Device and method for simulating landing gear drop test environment of aircraft by considering high-temperature influence |
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