CN102514723A - Aerodynamic load simulation device - Google Patents
Aerodynamic load simulation device Download PDFInfo
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- CN102514723A CN102514723A CN2011103659888A CN201110365988A CN102514723A CN 102514723 A CN102514723 A CN 102514723A CN 2011103659888 A CN2011103659888 A CN 2011103659888A CN 201110365988 A CN201110365988 A CN 201110365988A CN 102514723 A CN102514723 A CN 102514723A
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Abstract
The invention discloses an aerodynamic load simulation device which belongs to the field of an aircraft landing gear folding and unfolding test system. A test bench of the device is fixed on the ground; the upper part of the test bench is provided with a support for supporting a hinged part between the landing gear and an aircraft body; a landing gear strut actuating cylinder is connected with an external hydraulic system; two sets of loading mechanisms are symmetrically arranged on both sides of the test bench which are arranged on the moving plane of the landing gear; each set of loading mechanism respectively connects the landing gear to a double-cam mechanism, then to a gear reducer and finally to a hydraulic actuating cylinder through two steel wire ropes. The inner and outer cam shapes in the double-cam mechanism are consistent with the loading curve which is required by a test; and according to the device, the hidden safety hazards during the test can be eliminated, the requirements on the stroke and rate of the hydraulic actuating cylinder can be reduced, and the fitting capability of the loading curve of the landing gear can be improved.
Description
Technical field
The present invention relates to a kind of aerodynamic loading analog machine, belong to undercarriage folding and unfolding pilot system.
Background technology
For improving the aerodynamic force in the aircraft flight, modern aircraft common design is a retractable undercarriage, and is when aloft flying that gear up is inner at fuselage or wing; Taking off, will gear down bear landing load in the landing process.That need accomplish alighting gear aloft when therefore, aircraft flies packs up and puts down action.Because the influence of air resistance, alighting gear can receive the influence of aerodynamic force when folding and unfolding, and this aerodynamic force level is uniformly distributed on the alighting gear, influences the folding and unfolding of pressurized strut of alighting gear strut and uplock.Therefore, in undercarriage design development, need carry out the normal condition of service of folding and unfolding test to it with the simulation alighting gear.
In the undercarriage control test, the simulation loading of aerodynamic loading is the difficult point of test always, and its difficulty is to guarantee the horizontal direction of aerodynamic loading and the size of simulation load at any time.Developed country is for the research comparative maturity of landing-gear system, generally adopts alighting gear modern designs technology, the simulation of taking off, landing among undercarriage is installed on wind-tunnel.This test method is comparatively near the true condition of service of alighting gear, and test results but is tested costlyly accurately and reliably, and the construction period is long, should not carry out at short notice.
Domestic research for the undercarriage control test is generally carried out under no wind-tunnel condition.Because the power that alighting gear receives in true folding and unfolding process is a distributed force system; Simulation is very difficult in test; Therefore generally this distributed force system is simplified, application hinge moment principle of equivalence is reduced to one or several concentrated force with this aerodynamic loading and puts on the alighting gear.Difference according to experimental set-up mainly is divided into following two kinds:
(a) hydraulic servo pressurized strut loading scheme
This scenario-frame is comparatively simple, and the tracking performance of load simulation is better, but its weak point is having relatively high expectations to hydraulic actuator.The first, bigger to the pressurized strut dimensional characteristic, the too small folding and unfolding that can't provide enough strokes to be used for alighting gear of pressurized strut, the excessive installation of pressurized strut possibly produce interference; The second, need to build a whole set of complete hydraulic servo control system, the test period is longer, drops into bigger.
(b) mass-cam-slide rail loading scheme
This scheme aerodynamic loading is comparatively near truth, and loading direction property is good, but its weak point following points: the first, structure design is comparatively complicated, and steel rope quantity too much causes being prone to producing interference with alighting gear; The second, it is corresponding with it to design unique cam face according to the size of aerodynamic loading on the alighting gear, possibly can't design corresponding cam corresponding to some load working condition and satisfy it and load requirement; The 3rd, there is certain potential safety hazard in mass along with the folding and unfolding meeting generation of alighting gear is rocked in the loading.
Summary of the invention
The present invention is directed to the deficiency of prior art; A kind of alighting gear aerodynamic loading analog machine is provided; Adopt hydraulic actuator-cam-slide rail load maintainer; This device changes the loading regime of mass into employing pressurized strut loading regime, has eliminated the potential safety hazard in the process of the test, has reduced stroke, rate requirement to hydraulic actuator simultaneously; Adopted twin cam Simulated Aerodynamic Loads size, improved capability of fitting greatly the loading curve of alighting gear.
For realizing above technical purpose, the present invention will take following technical scheme:
A kind of aerodynamic loading analog machine; Its T/S is fixedly installed on the testing ground; The bearing that is used to support alighting gear and fuselage hinged place is installed on T/S top; The pressurized strut of alighting gear strut connects external hydraulic system, and the bilateral symmetry that on T/S, is positioned at the alighting gear plane of movement is provided with two cover load maintainers, and every suit load maintainer comprises hydraulic actuator, gear reducer, interlock wheel disc, cam mechanism, a steel rope, No. two steel ropes, slide rail and little pulley sheaves; Said hydraulic actuator is fixedly installed in longeron place, T/S bottom; Slide rail and little pulley sheave are installed in T/S top; Cam mechanism is installed in the slide rail below, and an end of a steel rope is fixedly connected on the alighting gear, and the other end is walked around little pulley sheave and connected cam mechanism again; Little pulley sheave is installed on the slide rail and along with the folding and unfolding of alighting gear through dolly and on slide rail, slides; No. two steel rope one end is connected in cam mechanism, and other end bonded assembly is positioned at the interlock wheel disc of T/S bottom, interlock wheel disc and gear reducer engagement; A gear reducer input end and a tooth bar are meshing with each other, and tooth bar is connected on the hydraulic actuator.
The twin cam mechanism that above-mentioned cam mechanism preferably is made up of cam ring and external cam, both relative fixed, No. one steel rope connects cam ring, and No. two steel rope connects external cam.
The outer rim shape of cam ring and external cam and the loading curve of TR are consistent, and both relative fixed also are installed on the bracing frame.
Dolly is rolled in slide rail as little pulley sheave by 4 antifriction-bearing boxs.Slide rail is that 60 ° circular arc and the tangent line that is tangential on this circular arc are formed by one section radian then.
What hydraulic actuator provided is permanent load, and the load of alighting gear in the folding and unfolding process is a curve that changes according to the folding and unfolding angle, and the conversion of intermediate cycling load size is through using twin cam mechanism to realize.Through the cam of design contoured, make that acting on the pulling force on the steel rope is the required aerodynamic loading size of test.
According to above technical scheme, can realize following beneficial effect:
Test adopted two cover load maintainers respectively independently symmetry be installed on the alighting gear both sides, guaranteed the influence that pull of steel wire can not produce moment of torsion to alighting gear in the test;
2. hydraulic actuator is fixedly installed in longeron place, T/S bottom, only constant thrust need be provided during test, has eliminated the safety hazard of mass loading scheme, has reduced size and control requirement to hydraulic actuator;
3. adopted two-jawed mode analog variable aerodynamic loading, can be optimized, improved the particularity that aerodynamic loading loads according to the curve of aerodynamic loading shape to interior and exterior cam;
4. the quantity of steel rope is reduced to 4 from 12, and it is simple and clear that steel rope is pullled circuit, has reduced the possibility of interfering each other in the process of the test.
Description of drawings
Fig. 1 is a folding and unfolding test integral installation scheme drawing.
Fig. 2 is a folding and unfolding test loading scheme scheme drawing.
Fig. 3 is the twin cam scheme drawing.
Fig. 4 is slide rail and trolley type pulley scheme drawing.
Label title among the figure: 1, T/S, 2, alighting gear, 3, gear reducer, 4, the interlock wheel disc; 5, hydraulic actuator, 6, No. two steel ropes, 7, cam ring, 8, external cam; 9, steel rope, 10, bracing frame, 11, slide rail, 12, the strut pressurized strut; 13, little pulley sheave, 14, fixed pulley, 15, dolly.
The specific embodiment
Accompanying drawing discloses the structural representation of preferred embodiment involved in the present invention without limitation; Below will combine accompanying drawing that technical scheme of the present invention at length is described.
As depicted in figs. 1 and 2, aerodynamic loading analog machine of the present invention comprises hydraulic actuator 5, gear reducer 3, twin cam, slide rail 11 and trolley type pulley.This device is installed on the T/S 1 by particular requirement, and T/S 1 is fixedly installed on ground, the laboratory rail, and whole test is played fixing and supporting role.Alighting gear 2 is connected on the single, double fork auricular branch seat with the fuselage hinged place, adds oscillating bearing on the bearing, guarantees that undercarriage leg and anchor clamps intersection point directly do not bear moment, and by each intersection point force balance.The strut pressurized strut 12 of alighting gear connects external hydraulic system; This force-input device comprises two cover load maintainers, and every suit load maintainer is made up of hydraulic actuator 5, gear reducer 3, cam ring 7, external cam 8, slide rail 11 and trolley type pulley, and symmetry is installed on the T/S respectively.One end of a steel rope 9 is fixedly connected on the alighting gear 2, and the other end is walked around the pulley 13 on the dolly 15 and is connected in cam ring 7; Dolly 15 is installed on the slide rail 11 and along with the folding and unfolding of alighting gear and on slide rail, slides; No. two steel rope 6 one ends are connected in external cam 8, and the other end is connected on the interlock wheel disc 4, interlock wheel disc 4 and gear reducer 3 engagements; The input end of gear reducer 3 and a tooth bar are meshing with each other, and tooth bar is connected on the hydraulic actuator 5.
Like Fig. 3; Twin cam is made up of the cam of two contoured; Two cams rotate together in the undercarriage control process, have guaranteed that by the moment equivalence No. two steel ropes 6 are variable load for deciding steel rope of load 9, and test needs to use its most profile; The gear up special angle is corresponding to the certain radius of cam, and the profile that need not use in the test is directly by the outline of straight line transition.Like Fig. 4, sliding track mechanism is made up of four slide rails 11 that have groove, is wiped with grease in the groove, and shaped design adds tangent line by one section circular arc and forms, and guarantees that dolly 15 can be slided to topmost by the slide rail lowermost end.
Before on-test, alighting gear 2 is in down state, and hydraulic actuator 5 provides rated thrust, nominal thrust, keeps No. two steel ropes 6 and a steel rope 9 to be in tension.When on-test, the alighting gear hydraulic efficiency pressure system provides high pressure oil, promotes strut pressurized strut 12 toward overhanging, and alighting gear 2 is just along up packing up gradually with the hinge-point rotation of fuselage.In this process, dolly 15 is followed the rotation of alighting gear 2 and is hauled up motion, has guaranteed to pack up the level of load in the process.Simultaneously, 9, numbers steel ropes 9 of an alighting gear steel rope of pulling are on external cam 8, and external cam 8 clickwises drive cam ring 7 and therewith rotate, and spur No. two steel rope 6.No. two steel rope 6 other ends are wound on the interlock wheel disc 4, and pulling interlock wheel disc 4 is pressed clickwise.Gear reducer 3 is meshing with each other with interlock wheel disc 4 and does left-hand revolution, and the tooth bar on pulling hydraulic actuator 5 tops, hydraulic actuator 5 provide certain thrust to stop the motion of packing up of alighting gear 2.Run into uplock when alighting gear 2 is packed up to nominal angle and lock, pack up process and accomplish this moment.
Gear down process is with to pack up process opposite, puts down fully and locks smoothly up to alighting gear 2, and a folding and unfolding process finishes.
Claims (5)
1. aerodynamic loading analog machine; Its T/S (1) is fixedly installed on the testing ground; The bearing that is used to support alighting gear (2) and fuselage hinged place is installed on T/S (1) top; Alighting gear strut pressurized strut (12) connects external hydraulic system; It is characterized in that: the bilateral symmetry that on T/S (1), is positioned at the alighting gear plane of movement is provided with two cover load maintainers, and every suit load maintainer comprises hydraulic actuator (5), gear reducer (3), interlock wheel disc (4), cam mechanism, a steel rope (9), No. two steel ropes (6), slide rail (11) and little pulley sheave (13); Said hydraulic actuator (5) is fixedly installed in longeron place, T/S bottom; Slide rail (11) and little pulley sheave (13) are installed in T/S (1) top; Cam mechanism is installed in slide rail (11) below; One end of a steel rope (9) is fixedly connected on the alighting gear (2), and the other end is walked around little pulley sheave (13) and connected cam mechanism again; Little pulley sheave (13) is installed on slide rail (11) through dolly (15) and upward and along with the folding and unfolding of alighting gear (2) goes up slip at slide rail (11); No. two steel rope (6) one ends are connected in cam mechanism, and the other end connects the interlock wheel disc (4) that is positioned at T/S (1) bottom, interlock wheel disc (4) and gear reducer (3) engagement; Gear reducer (a 3) input end and a tooth bar are meshing with each other, and tooth bar is connected on the hydraulic actuator (5).
2. aerodynamic loading analog machine according to claim 1; It is characterized in that said cam mechanism is the twin cam mechanism that is made up of cam ring (7) and external cam (8), both relative fixed; A steel rope (9) connects cam ring (7), and No. two steel ropes (6) connect external cam (8).
3. aerodynamic loading analog machine according to claim 1 is characterized in that: the outer rim shape of cam ring (7) and external cam (8) and the loading curve of TR are consistent, and both are installed on the bracing frame (10) jointly.
4. aerodynamic loading analog machine according to claim 1 and 2 is characterized in that: dolly (15) is rolled in slide rail (11) as little pulley sheave (13) by 4 antifriction-bearing boxs.
5. aerodynamic loading analog machine according to claim 1 and 2 is characterized in that, slide rail (11) is that 60 ° circular arc and the tangent line that is tangential on this circular arc are formed by one section radian.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103659888A CN102514723A (en) | 2011-11-18 | 2011-11-18 | Aerodynamic load simulation device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011103659888A CN102514723A (en) | 2011-11-18 | 2011-11-18 | Aerodynamic load simulation device |
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| CN102514723A true CN102514723A (en) | 2012-06-27 |
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| CN2011103659888A Pending CN102514723A (en) | 2011-11-18 | 2011-11-18 | Aerodynamic load simulation device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107215480A (en) * | 2017-05-23 | 2017-09-29 | 中国民航大学 | A kind of Aircraft landing gear system brake dynamic simulation test bed frame |
| CN110827655A (en) * | 2018-11-27 | 2020-02-21 | 合肥工业大学 | Test loading device of assembled structure model |
| CN111198091A (en) * | 2020-01-15 | 2020-05-26 | 石家庄铁道大学 | Simulation device for researching distribution rule of aerodynamic loads in different cracks of tunnel lining |
| CN111846283A (en) * | 2020-07-29 | 2020-10-30 | 中航飞机起落架有限责任公司 | Undercarriage pneumatic load test device and design method thereof |
| CN112124620A (en) * | 2020-09-13 | 2020-12-25 | 中国运载火箭技术研究院 | Servo load moment calculation method and equipment applied to aircraft and storage medium |
| CN113232885A (en) * | 2021-03-25 | 2021-08-10 | 中国人民解放军空军工程大学 | Loading vehicle for simulated airplane |
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| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| EP1524513A2 (en) * | 2003-09-26 | 2005-04-20 | Airbus Deutschland GmbH | Means for exerting a large thrust on a preferably curved part of an aircraft |
| CN102095592A (en) * | 2010-12-09 | 2011-06-15 | 南京航空航天大学 | Rack and pinion hydraulic pressure horizontal loading retraction and extending test table mechanism |
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2011
- 2011-11-18 CN CN2011103659888A patent/CN102514723A/en active Pending
Patent Citations (3)
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| CN1514213A (en) * | 2002-12-31 | 2004-07-21 | 中国农业机械化科学研究院 | Full machine ground load on site calibration test method and its device |
| EP1524513A2 (en) * | 2003-09-26 | 2005-04-20 | Airbus Deutschland GmbH | Means for exerting a large thrust on a preferably curved part of an aircraft |
| CN102095592A (en) * | 2010-12-09 | 2011-06-15 | 南京航空航天大学 | Rack and pinion hydraulic pressure horizontal loading retraction and extending test table mechanism |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107215480A (en) * | 2017-05-23 | 2017-09-29 | 中国民航大学 | A kind of Aircraft landing gear system brake dynamic simulation test bed frame |
| CN107215480B (en) * | 2017-05-23 | 2019-04-19 | 中国民航大学 | A kind of Aircraft landing gear system brake dynamic simulation test bed frame |
| CN110827655A (en) * | 2018-11-27 | 2020-02-21 | 合肥工业大学 | Test loading device of assembled structure model |
| CN111198091A (en) * | 2020-01-15 | 2020-05-26 | 石家庄铁道大学 | Simulation device for researching distribution rule of aerodynamic loads in different cracks of tunnel lining |
| CN111198091B (en) * | 2020-01-15 | 2021-08-10 | 石家庄铁道大学 | Simulation device for researching distribution rule of aerodynamic loads in different cracks of tunnel lining |
| CN111846283A (en) * | 2020-07-29 | 2020-10-30 | 中航飞机起落架有限责任公司 | Undercarriage pneumatic load test device and design method thereof |
| CN111846283B (en) * | 2020-07-29 | 2022-04-12 | 中航飞机起落架有限责任公司 | Undercarriage pneumatic load test device and design method thereof |
| CN112124620A (en) * | 2020-09-13 | 2020-12-25 | 中国运载火箭技术研究院 | Servo load moment calculation method and equipment applied to aircraft and storage medium |
| CN113232885A (en) * | 2021-03-25 | 2021-08-10 | 中国人民解放军空军工程大学 | Loading vehicle for simulated airplane |
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Application publication date: 20120627 |