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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 PDF

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Publication number
CN106800095A
CN106800095A CN201510843783.4A CN201510843783A CN106800095A CN 106800095 A CN106800095 A CN 106800095A CN 201510843783 A CN201510843783 A CN 201510843783A CN 106800095 A CN106800095 A CN 106800095A
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China
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load
calibration
design
compression travel
operating mode
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CN201510843783.4A
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CN106800095B (en
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蒋启登
原正庭
郭正旺
王海平
张多源
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Chinese Flight Test Establishment
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Chinese Flight Test Establishment
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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

Telescopic landing gear calibration load based on buffer compression travel determines method
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.
CN201510843783.4A 2015-11-26 2015-11-26 Method is determined based on the telescopic landing gear calibration load of buffer compression travel Active CN106800095B (en)

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Cited By (5)

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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

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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

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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

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Cited By (10)

* Cited by examiner, † Cited by third party
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
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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