CN203811349U - Rotor dynamic test device - Google Patents
Rotor dynamic test device Download PDFInfo
- Publication number
- CN203811349U CN203811349U CN201420148453.4U CN201420148453U CN203811349U CN 203811349 U CN203811349 U CN 203811349U CN 201420148453 U CN201420148453 U CN 201420148453U CN 203811349 U CN203811349 U CN 203811349U
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- servomotor
- rotor
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- force arm
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- 238000012360 testing method Methods 0.000 title claims abstract description 29
- 230000033001 locomotion Effects 0.000 claims abstract description 80
- 238000004088 simulation Methods 0.000 claims abstract description 45
- 238000005096 rolling process Methods 0.000 claims abstract description 33
- 230000007246 mechanism Effects 0.000 claims abstract description 29
- 238000002474 experimental method Methods 0.000 claims abstract description 9
- 230000003028 elevating effect Effects 0.000 claims description 4
- 238000011160 research Methods 0.000 abstract description 4
- 238000013519 translation Methods 0.000 abstract description 2
- 230000008859 change Effects 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 241001672694 Citrus reticulata Species 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
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Abstract
The utility model provides a rotor dynamic test device. The rotor dynamic test device comprises a model rotor system, a pitching motion simulation mechanism, a rolling motion simulation mechanism, a course rotation simulation mechanism, an x-y-z axis translation device and an experiment accessory device. According to the utility model, seven servo motors which are independently controlled are employed, and the seven servo motors respectively drive vertical motion, lateral motion, transverse rectilinear motion, pitching motion, rolling motion, course rotation motion and model rotor rotation. The seven servo motors are respectively provided with an independent control system, under the control of a central industrial control computer, movement rules in six degrees of freedom and the rotating speed of a rotor can be controlled in a dynamic and combined manner, model test research on influence of helicopter dynamic maneuvering flight on a plurality of aspects such as pneumatic aspect, flight mechanics, dynamics and the like of the rotor, and motion combination tests in different degrees of freedom can be carried out as needed.
Description
Technical field
The utility model relates to Aviation Test platform field, specifically a kind of rotor dynamic testing equipment.
Background technology
The working environment of helicopter rotor blade is more than the working environment complexity of fixed wing aircraft wing, especially at dynamic mobility in-flight, the non-stationary motion of helicopter causes rotor trailing vortex response lag, geometric configuration to produce complicated dynamical distortion, change the oar dish distribution characteristics that becomes a mandarin, and the additional inertia causing due to body movement of rotor is coupled, to there is marked change in the non-permanent Airflow Environment of rotor now, and cause rotor to produce the dynamic perfromance more complicated than steady flight state, further increase the pneumatic of rotor and dynamic analysis difficulty.
Theoretical research for lifting airscrew in the time that dynamic mobility flies need to be using experimental verification as inspection, conventional lifting airscrew testing table is mainly used in carrying out hovering simulation test at present, and steady flight in the constant situation of tunnel simulation wind speed blowing simulation test, for dynamic analog test ability Shortcomings, do not possess variable motion test simulation ability.
Utilize the three direction rotational freedoms motions that the flight simulation platform of hydraulic actuator design can helicopter simulating body, but due to the restriction of hydraulic actuation stroke, and there is Non-linear coupling in the motion of all directions, while utilizing conventional flight simulation platform to simulate rectilinear motion, stroke is smaller, decoupling zero difficulty, higher to the difficulty of attitude motion control, motion simulation is limited in one's ability, for realizing the motion simulation of larger stroke, testing equipment volume also can be larger.
In the time of the dynamic mobility simulated experiment of carrying out lifting airscrew, from the motion simulation of the single degree of freedom, the coupled simulation of several freedoms of motion, until the coupled simulation of space six-freedom motion all has demand, require higher for the control accuracy demand of motion and the decoupling zero of each degree of freedom motion, can carry out helicopter simulating and aloft move and rotor is affected to the testing equipment of modeling effort owing to lacking, need to carry out Flight Test by prototype, research cost and risk are improved, limited carry out based on high-precision rotor non-permanent pneumatic, the checking research of the advanced theoretical method such as flight mechanics and many-body dynamics.
Utility model content
The utility model is in order to solve the problem of prior art, provide one to there is independently rolling, pitching, driftage, lifting, the motion simulation ability of front and back translation and sidesway six-freedom degree, under the manipulation of control system, can realize the rotor dynamic testing equipment of the simulation of body compound movement, for carrying out the experimental study of body dynamic mobility on rotor impact.
The utility model comprises model rotor system, luffing simulation mechanism, rolling movement simulation mechanism, course rotation simulation mechanism, xyz axle translating device and experiment auxiliary equipment;
Described course is rotated simulation mechanism and is comprised course rotating force arm and course rotation servomotor, and course rotating force arm rotates servomotor by course and is connected with xyz axle translating device, and course rotating force arm rotates under servomotor drive and rotates around z axle in course;
Described rolling movement simulation mechanism comprises connected rolling servomotor and rolling rotating force arm, and rolling servomotor is connected with course rotating force arm, the rotation under rolling servomotor drives of rolling rotating force arm;
Described model rotor system is installed on rolling rotating force arm, comprises model rotor, rotor servomotor, and model rotor rotates under rotor servomotor drives; Experiment auxiliary equipment is housed in model rotor system;
Described luffing simulation mechanism is installed between model rotor system and rolling movement simulation mechanism, comprise pitching servomotor, pitching hydraulic cylinder and the push rod thereof and the pitching rotating force arm that connect successively, wherein, pitching servomotor is connected with rolling rotating force arm, pitching rotating force arm is connected with model rotor system, pitching servomotor is by pitching hydraulic cylinder and top rod driving pitching rotating force arm thereof, and implementation model rotor system is done luffing;
Further improve, in described course rotating force arm, have groove, rolling servomotor is installed in the groove of course rotating force arm, in described rolling rotating force arm, has groove, and pitching servomotor is installed in the groove of rolling rotating force arm.By groove design, make the structure of whole system compacter.
Further improve, described xyz axle translating device comprises linear longitudinal movement simulation mechanism, side direction rectilinear motion simulation mechanism and elevating movement simulation mechanism;
Described linear longitudinal movement simulation mechanism comprises the sole plate with slide rail, on slide rail, be connected with the longitudinal sliding block with slide rail, longitudinal sliding block is connected with servo longitudinal motor by longitudinal screw mandrel, longitudinal sliding block under servo longitudinal driven by motor along the slide rail lengthwise movement of sole plate;
Described side direction rectilinear motion simulation mechanism comprises sideway movement slide block, and sideway movement slide block is connected with side direction servomotor by sideway movement screw mandrel, the longitudinally slide rail sideway movement of slide block under side direction servomotor drives of sideway movement slide block.
Described elevating movement simulation mechanism comprises stand column and vertical movement column, in platform machine column, vertical servomotor is housed, vertical servomotor is connected with vertical movement column by down-feed screw, vertical movement column rotates servomotor with course and is connected, and vertical movement column moves up and down under vertical servomotor drives in stand column.
Described experiment auxiliary equipment comprises measures harvester and pitch control device.
The utility model beneficial effect is:
1, the utility model uses the servomotor of seven platform independent controls, drives longitudinally respectively, side direction, the laterally rotation of rectilinear motion and pitching, rolling, course rotational motion and model rotor.Seven servomotors are all equipped with independently control system, and under the manipulation of central industrial computer, the equal capable of dynamic combination of the characteristics of motion of six-freedom degree and gyroplane rotate speed is controlled.Can carry out that the flight of helicopter dynamic mobility is pneumatic on rotor, the model investigation of many-sided impact such as flight mechanics and dynamics, and carry out as required the movement combination test between different degree of freedom.
2, compact conformation, utilizes the designing technique of this dynamic testing equipment, can be widely used in carrying out all kinds of experimental studies in wind-tunnel.
Brief description of the drawings
Fig. 1 is stereographic map of the present utility model.
Fig. 2 is front view of the present utility model.
Fig. 3 is side view of the present utility model.
Fig. 4 is rear view of the present utility model.
Embodiment
Below in conjunction with accompanying drawing, the utility model is described in further detail.
As shown in Figure 1, front view, side view and rear view are respectively as shown in Figure 2, Figure 3 and Figure 4 for stereographic map of the present utility model.
In the time carrying out test, sole plate 1 fixes on the ground, and the servo longitudinal motor 3 on sole plate 1 is passed to longitudinal sliding block 4 through longitudinal screw mandrel 2 by power, and longitudinal sliding block 4 is made front and back rectilinear motion along guide rail, thereby realizes longitudinal rectilinear motion simulation.
The side direction servomotor 6 being arranged on lengthwise movement slide block is passed to sideway movement slide block 7 through sideway movement screw mandrel 5 by power, and sideway movement slide block 7, along guide rail moving linearly, is simulated thereby realize side direction rectilinear motion.
By the down-feed screw 20 that is arranged on stand column 8 inside, power is passed to catenary motion column 9, pushing tow catenary motion column 9 is vertically motion in stand column 8, thereby realizes vertical rectilinear motion simulation.
The course rotating force arm 11 of rotor dynamic testing equipment is arranged on vertical movement column 9, by course rotate servomotor 10 through speed reduction unit by power by gear transmission to the fluted disc on rotating force arm, the moving course of driving gear dribbling rotating force arm 11 rotates, thereby realizes the gyration simulation of yaw angle.
By rolling servomotor 13, power is passed to the rolling arm of force 12, the rolling arm of force 12 drives model rotor 18 to turn round, thereby realizes the gyration of roll angle.
Pitching servomotor 16 drives pitching rotating force arm by pitching hydraulic cylinder and push rod 15 thereof, and implementation model rotor system is done luffing;
Model rotor 18 systems are arranged on the luffing arm of force 14, drive rotor to rotate by rotor servomotor 17 independently, experiment auxiliary equipment 19 is installed in model rotor system, comprise measurement and the control device such as balance collector ring and auto-bank unit, for controlling the pitch of rotor and the kinetic measurement signal of collection rotor.
The concrete application approach of the utility model is a lot; the above is only preferred implementation of the present utility model; should be understood that; for those skilled in the art; do not departing under the prerequisite of the utility model principle; can also make some improvement, these improve and also should be considered as protection domain of the present utility model.
Claims (8)
1. a rotor dynamic testing equipment, is characterized in that: comprise model rotor system, luffing simulation mechanism, rolling movement simulation mechanism, course rotation simulation mechanism, xyz axle translating device and experiment auxiliary equipment (19);
Described course is rotated simulation mechanism and is comprised course rotating force arm (11) and course rotation servomotor (10), course rotating force arm (11) rotates servomotor (10) by course and is connected with xyz axle translating device, and course rotating force arm (11) rotates under servomotor (10) drive and rotates around z axle in course;
Described rolling movement simulation mechanism comprises connected rolling servomotor (13) and rolling rotating force arm (12), rolling servomotor (13) is connected with course rotating force arm (11), rolling rotating force arm (12) rotation under rolling servomotor (13) drives;
It is upper that described model rotor system is installed on rolling rotating force arm (12), comprises model rotor (18), rotor servomotor (17), and model rotor (18) rotates under rotor servomotor (17) drives; Experiment auxiliary equipment (19) is housed in model rotor system;
Described luffing simulation mechanism is installed between model rotor system and rolling movement simulation mechanism, comprise pitching servomotor (16), pitching hydraulic cylinder and the push rod (15) thereof and the pitching rotating force arm (14) that connect successively, wherein, pitching servomotor (16) is connected with rolling rotating force arm (12), pitching rotating force arm (14) is connected with model rotor system, pitching servomotor (16) is by pitching hydraulic cylinder and top rod driving pitching rotating force arm (14) thereof, and implementation model rotor system is done luffing.
2. rotor dynamic testing equipment according to claim 1, is characterized in that: in described course rotating force arm (11), have groove, rolling servomotor (13) is installed in the groove of course rotating force arm (11).
3. rotor dynamic testing equipment according to claim 1, is characterized in that: in described rolling rotating force arm (12), have groove, pitching servomotor (16) is installed in the groove of rolling rotating force arm (12).
4. according to the rotor dynamic testing equipment described in claim 1 or 2 or 3, it is characterized in that: described xyz axle translating device comprises linear longitudinal movement simulation mechanism, side direction rectilinear motion simulation mechanism and elevating movement simulation mechanism.
5. rotor dynamic testing equipment according to claim 4, it is characterized in that: described linear longitudinal movement simulation mechanism comprises the sole plate (1) with slide rail, on slide rail, be connected with the longitudinal sliding block (4) with slide rail, longitudinal sliding block (4) is connected with servo longitudinal motor (3) by longitudinal screw mandrel (2), longitudinal sliding block (4) under servo longitudinal driven by motor along the slide rail lengthwise movement of sole plate (1).
6. rotor dynamic testing equipment according to claim 5, it is characterized in that: described side direction rectilinear motion simulation mechanism comprises sideway movement slide block (7), sideway movement slide block (7) is connected with side direction servomotor (6) by sideway movement screw mandrel (5), sideway movement slide block (7) longitudinally slide rail sideway movement of slide block (4) under side direction servomotor (6) drives.
7. rotor dynamic testing equipment according to claim 6, it is characterized in that: described elevating movement simulation mechanism comprises stand column (8) and vertical movement column (9), in platform machine column (8), vertical servomotor is housed, vertical servomotor is connected with vertical movement column (9) by down-feed screw (20), vertical movement column (9) rotates servomotor (10) with course and is connected, and vertical movement column (9) moves up and down under vertical servomotor drives in stand column (8).
8. according to the rotor dynamic testing equipment described in claim 1 or 2 or 3, it is characterized in that: described experiment auxiliary equipment (19) comprises measures harvester and pitch control device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420148453.4U CN203811349U (en) | 2014-03-31 | 2014-03-31 | Rotor dynamic test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420148453.4U CN203811349U (en) | 2014-03-31 | 2014-03-31 | Rotor dynamic test device |
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| Publication Number | Publication Date |
|---|---|
| CN203811349U true CN203811349U (en) | 2014-09-03 |
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| CN201420148453.4U Expired - Lifetime CN203811349U (en) | 2014-03-31 | 2014-03-31 | Rotor dynamic test device |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103954426A (en) * | 2014-03-31 | 2014-07-30 | 南京航空航天大学 | Rotor wing dynamic test device |
| CN104458197A (en) * | 2014-11-14 | 2015-03-25 | 扬州大学 | Wind tunnel testing model supporting mechanism based on parallelogram mechanism |
| CN104457449A (en) * | 2014-12-12 | 2015-03-25 | 晋西工业集团有限责任公司 | Rotational flexibility detector for rotatable stabilizer |
| CN104792490A (en) * | 2015-04-21 | 2015-07-22 | 中国航空工业集团公司沈阳飞机设计研究所 | External store side-sway frequency and yaw frequency decoupling device of wind tunnel flutter model |
| CN106482941A (en) * | 2016-11-23 | 2017-03-08 | 晋西工业集团有限责任公司 | A kind of rocket projectile projectile tail device for detecting flexibility |
| CN106644389A (en) * | 2015-11-04 | 2017-05-10 | 北京卫星环境工程研究所 | High precision five-freedom degree position and pose adjusting mechanism used for space environment test |
| CN106927064A (en) * | 2017-04-21 | 2017-07-07 | 北京建中数字科技有限公司 | One kind intersects DCB Specimen depopulated helicopter ground test platform |
| CN108844711A (en) * | 2018-07-19 | 2018-11-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile two-freedom dynamic flow tunnel testing device |
| CN110793747A (en) * | 2019-10-10 | 2020-02-14 | 中国直升机设计研究所 | Multi freedom removes measuring mechanism |
| CN116242575A (en) * | 2023-05-08 | 2023-06-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual flight test device of low-speed wind tunnel |
-
2014
- 2014-03-31 CN CN201420148453.4U patent/CN203811349U/en not_active Expired - Lifetime
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103954426B (en) * | 2014-03-31 | 2016-08-17 | 南京航空航天大学 | A kind of rotor dynamic testing equipment |
| CN103954426A (en) * | 2014-03-31 | 2014-07-30 | 南京航空航天大学 | Rotor wing dynamic test device |
| CN104458197A (en) * | 2014-11-14 | 2015-03-25 | 扬州大学 | Wind tunnel testing model supporting mechanism based on parallelogram mechanism |
| CN104458197B (en) * | 2014-11-14 | 2017-09-01 | 扬州大学 | A kind of model in wind tunnel supporting mechanism based on parallel-crank mechanism |
| CN104457449B (en) * | 2014-12-12 | 2017-03-08 | 晋西工业集团有限责任公司 | A kind of rotatable stabilising arrangement rotates device for detecting flexibility |
| CN104457449A (en) * | 2014-12-12 | 2015-03-25 | 晋西工业集团有限责任公司 | Rotational flexibility detector for rotatable stabilizer |
| CN104792490A (en) * | 2015-04-21 | 2015-07-22 | 中国航空工业集团公司沈阳飞机设计研究所 | External store side-sway frequency and yaw frequency decoupling device of wind tunnel flutter model |
| CN104792490B (en) * | 2015-04-21 | 2018-04-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of wind-tunnel flutter model store Combinations side-sway frequency and yaw frequency decoupling device |
| CN106644389A (en) * | 2015-11-04 | 2017-05-10 | 北京卫星环境工程研究所 | High precision five-freedom degree position and pose adjusting mechanism used for space environment test |
| CN106644389B (en) * | 2015-11-04 | 2019-05-28 | 北京卫星环境工程研究所 | High-precision five degree of freedom pose regulating mechanism applied to space environment test |
| CN106482941A (en) * | 2016-11-23 | 2017-03-08 | 晋西工业集团有限责任公司 | A kind of rocket projectile projectile tail device for detecting flexibility |
| CN106927064A (en) * | 2017-04-21 | 2017-07-07 | 北京建中数字科技有限公司 | One kind intersects DCB Specimen depopulated helicopter ground test platform |
| CN108844711A (en) * | 2018-07-19 | 2018-11-20 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of aerofoil profile two-freedom dynamic flow tunnel testing device |
| CN110793747A (en) * | 2019-10-10 | 2020-02-14 | 中国直升机设计研究所 | Multi freedom removes measuring mechanism |
| CN116242575A (en) * | 2023-05-08 | 2023-06-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Virtual flight test device of low-speed wind tunnel |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20140903 Effective date of abandoning: 20160817 |
|
| C25 | Abandonment of patent right or utility model to avoid double patenting |