CN106800095A - Telescopic landing gear calibration load based on buffer compression travel determines method - Google Patents
Telescopic landing gear calibration load based on buffer compression travel determines method Download PDFInfo
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Abstract
Determine method the invention provides the telescopic landing gear calibration load based on buffer compression travel, including:It is determined that calibration compression travel, in buffer compression travel scope of design, chooses appropriate calibration stroke range;The fixed compression travel of classification;Orthogonal design calibrates operating mode;Selected calibration load operating mode:The maximum unidirectional load and combined load and its correspondence course in design maneuvering load situation are chosen as the primary source for determining calibration load operating mode;Equivalent determination calibration load:The equivalent different size of calibration load being mapped under each classification stroke after the design maneuvering load of primary election is reduced in specific proportions using load-transfer mechanism principle.Undercarriage calibration load involved in the present invention determines that method can be used to become the telescopic landing gear calibration load operating condition design under buffer compression travel, the articulated landing gear containing buffer is also applied for, with wide applicability and practicality.
Description
Technical field
Patent Aircraft Flight Test field of the present invention, is related to the column support type based on buffer compression travel to rise
The frame calibration load that falls determines method.
Background technology
The measurement of undercarriage external applied load is generally carried out using electromotive strain method, main to include strain
The committed steps such as meter repacking, the calibration of load ground and flight actual measurement.Wherein load ground calibrates to
Close important, how to simulate aircraft stand under load for the most important thing.Because undercarriage Path of Force Transfer is single,
Mechanism's link is more, the rigidity of structure is big, the bearing coupled complicated, stand under load of multi -components is with draft gear travel
The distinguishing feature such as nonlinear change is serious, draft gear travel change is loaded with great shadow to undercarriage
Ring, this brings huge difficulty to load accurate measurement, therefore in the big amplitude variation of calibration test stroke
Calibration load magnitude and structural strain response are effectively improved under conditions of change, load calibration essence is ensured
Degree.
Under different strokes, the stand under load strain-responsive characteristic on many structure positions of undercarriage has
Significant difference.From Structure & Intensity design angle, generally directed to undercarriage difference operational phase
Corresponding design load and corresponding compression work stroke level value are proposed, and from load measurement and is flown
Angle is, it is necessary to landing-gear load under drawing arbitrary distance of run, the i.e. time of load and compression travel
Course.How a certain specific load situation under a certain different strokes under design conditions to be transformed to
Different calibration load situations under strokes at different levels, it is of interest to be that landing-gear load calibration load determines
Emphasis.Past uses and for the specific load situation under a certain different strokes to transform to strokes at different levels
Under same load situation, the design of such calibration load situation has school under big compression travel
Quasi- load is less than normal, and structural strain response is small, and structural response non-linear effects seriously wait adverse effect,
So as to cause calibration accuracy to be deteriorated.
The content of the invention
It is an object of the invention to provide a kind of telescopic landing gear based on buffer compression travel
Calibration load determines method.
Calibrated the invention provides a kind of telescopic landing gear based on buffer compression travel and carried
Lotus determines method, it is characterised in that comprise the following steps:
1) calibration compression travel is determined:According to buffer compression travel 0~S of scope of design, choose
0.1S~0.9S as calibration stroke range, with avoid calibration load when buffer knot
Strain gauge wrecks on structure internal injury and piston rod;
2) it is classified fixed compression travel:According to calibration accuracy requirement and test efficiency target, and
The load design of landing gear structure and estimated service condition, by calibration row journey scope
0.1S~0.9S is evenly or unevenly divided into 3~5 grades, be such as divided into 0.1S, 0.5S,
0.9S or 0.1S, 0.3S, 0.5S, 0.7S, 0.9S or 0.1S, 0.4S, 0.9S
Or 0.1S, 0.3S, 0.5S, 0.8S, 0.9S;
3) orthogonal design calibration operating mode:Calibration loaded load operating mode includes various unidirectional (such as vertical
Pz, positive/negative course ± Px, positive/negative lateral ± Fy), containing vertical two to combination (such as
Vertical+positive/negative course Pz ± Px, vertical+positive/negative lateral Pz ± Fy) and three-dimensional
Composite condition (such as vertical+positive/negative course+positive/negative lateral Pz ± Px ± Fy), so as to true
It is real to simulate actual loading conditions and reach the purpose of high-precision calibration and reliable prediction;
4) calibration load operating mode is selected:(containing loading direction, carried according to various design load situations
Lotus size and corresponding compression travel), choose the unidirectional load of maximum in design conditions
Lotus and its correspondence course are used as the primary source 1 for determining calibration load operating mode;Selection sets
Multidirectional (vertical+course, vertical+lateral, course+vertical+boat in meter situation
To) as the primary source 2 for expanding calibration load operating mode or inspection load working condition;According to
According to the ability of test facilities, it is contemplated that the structure of undercarriage installation flight test after experiment
Security needs, select 50~70% design maneuvering loads as in each operating mode calibration load
Limit;
5) equivalent determination calibration load:In view of the reality need that stroke changes when load is calibrated, adopts
It is with load-transfer mechanism principle that the calibration load operating mode of 50~70% selected sizes is (a certain
A certain unidirectional load situation under stroke) transformed mappings to it is each classification stroke under difference
Size unidirectional or two is to calibration load, and should meeting undercarriage, to fix hinge load small
In the corresponding fixed hinge load of 100% design limit load.
It is an advantage of the invention that:Compared with conventional method, can be true according to invention method
Surely the calibration load operating mode set that can change with compression travel for meeting safety condition is given, for
It is any to require all provide the satisfied calibration load no more than use limitation under calibration test stroke
Lotus, such that it is able to greatly improve calibration load magnitude, improves load calibration accuracy, enriches calibration
Load working condition sample.
Undercarriage calibration load involved by this patent determines that method can be used to become buffer compression
Telescopic landing gear calibration load operating condition design under stroke, is also applied for the rocking arm containing buffer
Formula undercarriage, with wide applicability and practicality.
Brief description of the drawings
Fig. 1 is column support type oil gas bumper undercarriage and its stand under load schematic diagram.
Specific embodiment
1) calibration compression travel is determined:According to undercarriage buffer compression travel 0~S of scope of design,
It is 0.1S~0.9S to choose load calibration stroke range, it is to avoid buffering during calibration loading
Device inside configuration is damaged and wrecked with strain gauge on piston rod;
2) it is classified fixed compression travel:According to load calibration accuracy and test efficiency requirement, and
The load design of landing gear structure and estimated service condition, by calibration row journey scope
0.1S~0.9S is evenly or unevenly divided into 3~5 grades, be such as divided into Li=0.1S, 0.5S,
0.9S (i=3) or Li=0.1S, 0.3S, 0.5S, 0.7S, 0.9S (i=5) etc.;
According to landing gear structure load design and frequency of usage situation, by calibration row journey
0.1S~0.9S is unevenly divided into Li=0.1S, 0.4S, 0.9S or Li=0.1S,
0.3S, 0.5S, 0.8S, 0.9S etc.;Using the side full of fluid of being deflated to buffer
Formula realizes that compression travel classification is fixed;
3) orthogonal design calibration operating mode:For simulate true loading conditions and reach high-precision calibration and
The purpose of reliable inspection, calibration loaded load operating mode should include it is various it is unidirectional (vertical Pz,
Positive/negative course ± Px, positive/negative lateral ± Fy), containing vertical two to combination (it is vertical+
Positive/negative course Pz ± Px, vertical+positive/negative lateral Pz ± Fy) and three-dimensional combination work
Condition (vertical+positive/negative course+positive/negative lateral Pz ± Px ± Fy);
4) equivalent determination calibration load:According to the design load for completing already and pass through slow test
Situation (contains loading direction, magnitude of load and corresponding compression travel), and selection sets
Maximum unidirectional load and its correspondence course in meter situation is used as determination calibration load work
The primary source 1 of condition;Choose design conditions in two to (vertical+course, it is vertical
+ lateral) as the primary source 2 for expanding calibration load operating mode;According to test facilities
Ability, it is contemplated that after experiment undercarriage install flight test structure security needs,
(proportionality coefficient k is maximum calibration load and design maneuvering load to choose 50~70%
The ratio between) maneuvering load is designed as the calibration load upper limit;
5) the equivalent determination of calibration load:In view of the reality need that stroke changes when load is calibrated, root
Reflected the calibration load operating mode of 50~70% sizes of primary election is equivalent according to load-transfer mechanism principle
Be mapped to different size of unidirectional under each classification stroke or two to or three directional loads situation,
And it is corresponding less than 100% design limit load to meet undercarriage fixation hinge load
Fixed hinge load.Telescopic landing gear shown in Fig. 1, its projective transformation matrix is
Third-order plant in formula.
Embodiment
Calibration load sees below formula with the relation of design maneuvering load situation.Known a certain design is used
Load condition (Pxlim, Fylim, Pzlim) and the known stroke L1 of correspondence, column support type rise and fall
The wheel rolling radius of frame is R0, a length of L0 of wheel shaft, outer below the hinge of strut and pillar
Tube length degree is B, then to determine in desired calibration stroke Li (load calibration stroke classification numbers
Calibration load (Pxi, Fyi, the Pzi) of i=1~3 or i=1~5), and meet L1 and Li is equal
In calibration stroke 0.1S~0.9S, the undercarriage in calibration stroke Li is in calibration load
(the usual main force transferring structure of undercarriage uses three to hinge Oj under (Pxi, Fyi, Pzi) effect
Point articulated static determinacy is constrained on airframe or wing, and undercarriage is hinged points for 3,
The restraint forces (PxOij, FyOij, PzOij) of j=1~3) no more than maneuvering load (Pxlim,
Fylim, Pzlim) corresponding hinge Oj restraint forces (PxOj, FyOj, PzOj).
Claims (2)
1. the telescopic landing gear calibration load based on buffer compression travel determines method, it is characterised in that
Comprise the following steps:
1) calibration compression travel is determined:In buffer compression travel scope of design, appropriate removal stroke border
Afterwards, calibration stroke range is chosen;
2) it is classified fixed compression travel:According to calibration accuracy requirement and Landing Gear Design service condition, will calibrate
Stroke range is evenly or unevenly divided into 3~5 grades, and oil is full of again step by step using being deflated to buffer
The mode drained the oil realizes that compression travel is fixed;
3) orthogonal design calibration operating mode:Under the fixed compression travel of each classification, choose it is various it is unidirectional, contain
Vertical two are to the calibration load operating mode such as combination and three-dimensional combination;
4) calibration load operating mode is selected:Choose the maximum unidirectional load and its right in each design maneuvering load situation
Stroke is answered as unidirectional calibration load operating mode;Choose in design maneuvering load situation two to (vertical
It is ± course, vertical ± lateral) as two to calibration load operating mode;Extract design maneuvering load situation
In two to load condition, form three-dimensional calibration load operating mode after superposition three directional loads;According to examination
Facility ability and flight structure safety are tested, 50~70% is chosen and is designed maneuvering load as in calibration load
Limit;
5) equivalent determination calibration load:Using load-transfer mechanism principle by the calibration load of 50~70% sizes of primary election
Operating mode is equivalent to be mapped to different size of unidirectional under each classification stroke or two to load condition, and should
Meet undercarriage and fix hinge load fixed hinge load corresponding less than 100% design limit load.
2. the telescopic landing gear calibration load based on buffer compression travel according to claim 1 is true
Determine method, it is characterised in that the equivalent determination method of calibration load that step 2 determines is by under certain one stroke
50~70% design maneuvering load situations are the school under different classification calibration strokes by power and the conversion of the torque principle of equal effects
Quasi- load.
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Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN107766612A (en) * | 2017-09-08 | 2018-03-06 | 中国飞行试验研究院 | One kind connection wing structure form wing loads measuring method |
CN109703778A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of undercarriage buffer rigidifying method for Aircraft Load calibration test |
CN110683075A (en) * | 2019-10-29 | 2020-01-14 | 燕山大学 | Calibration device for nose landing gear rotary loader |
CN111169653A (en) * | 2019-12-11 | 2020-05-19 | 中国飞机强度研究所 | Hinge point force testing device of nose landing gear and load calibration method |
CN113460331A (en) * | 2021-07-10 | 2021-10-01 | 中国飞机强度研究所 | Analysis and judgment method for load of constraint point of strength test |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102126563A (en) * | 2011-01-21 | 2011-07-20 | 南京航空航天大学 | Aircraft landing gear drop lifting force simulating device |
CN105083587A (en) * | 2015-08-14 | 2015-11-25 | 中国航空工业集团公司西安飞机设计研究所 | Load correction method applied to undercarriage loading |
-
2015
- 2015-11-26 CN CN201510843783.4A patent/CN106800095B/en active Active
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN102126563A (en) * | 2011-01-21 | 2011-07-20 | 南京航空航天大学 | Aircraft landing gear drop lifting force simulating device |
CN105083587A (en) * | 2015-08-14 | 2015-11-25 | 中国航空工业集团公司西安飞机设计研究所 | Load correction method applied to undercarriage loading |
Non-Patent Citations (2)
Title |
---|
杨全伟等: "飞机起落架载荷测量中的线性变换与鲁棒性", 《应用力学学报》 * |
汤阿妮等: "基于加载平台的起落架载荷地面校准技术研究", 《强度与环境》 * |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
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CN107766612A (en) * | 2017-09-08 | 2018-03-06 | 中国飞行试验研究院 | One kind connection wing structure form wing loads measuring method |
CN107766612B (en) * | 2017-09-08 | 2023-04-18 | 中国飞行试验研究院 | Method for measuring wing load in connecting wing structure form |
CN109703778A (en) * | 2018-10-26 | 2019-05-03 | 中国飞行试验研究院 | A kind of undercarriage buffer rigidifying method for Aircraft Load calibration test |
CN109703778B (en) * | 2018-10-26 | 2022-05-27 | 中国飞行试验研究院 | Undercarriage buffer rigidization method for aircraft load calibration test |
CN110683075A (en) * | 2019-10-29 | 2020-01-14 | 燕山大学 | Calibration device for nose landing gear rotary loader |
CN110683075B (en) * | 2019-10-29 | 2020-12-01 | 燕山大学 | Calibration device for nose landing gear rotary loader |
CN111169653A (en) * | 2019-12-11 | 2020-05-19 | 中国飞机强度研究所 | Hinge point force testing device of nose landing gear and load calibration method |
CN111169653B (en) * | 2019-12-11 | 2021-10-15 | 中国飞机强度研究所 | Hinge point force testing device of nose landing gear and load calibration method |
CN113460331A (en) * | 2021-07-10 | 2021-10-01 | 中国飞机强度研究所 | Analysis and judgment method for load of constraint point of strength test |
CN113460331B (en) * | 2021-07-10 | 2023-07-07 | 中国飞机强度研究所 | Analysis and judgment method for load of constraint point of strength test |
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