CN204128805U - The mechanical meaurement device of deformable low-speed machine wing structure - Google Patents
The mechanical meaurement device of deformable low-speed machine wing structure Download PDFInfo
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- CN204128805U CN204128805U CN201420588139.8U CN201420588139U CN204128805U CN 204128805 U CN204128805 U CN 204128805U CN 201420588139 U CN201420588139 U CN 201420588139U CN 204128805 U CN204128805 U CN 204128805U
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Abstract
The utility model belongs to novel test mechanism, proposes a kind of mechanical meaurement device of deformable low-speed machine wing structure, comprising: testing table (12), and two upper and lower levels of wall mount (1) are on the hole being screwed onto sidewall; The back rest (3) of wing (13) is fastening to be inserted in the first girder fixture (4), first girder fixture (4) rear end is fixedly connected with first axle (5) of variant overstroke safety device, the front-axle beam (6) of wing (13) is fastening to be inserted in the second girder fixture (7), and the second girder fixture (7) rear end is fixedly connected with second axle (8) of variant overstroke safety device; Rotate stationary shaft (2) and control shaft sleeve (9) through the screw of erecting frame (1) and the rotation of unit protection casket cover (14) successively, and rotation stationary shaft (2) is fixedly connected with the screw of wall mount (1).
Description
Technical field
The invention belongs to novel test mechanism, relate to a kind of new low speed morphing aircraft aerofoil mechanical test check analysis mechanism.
Background technology
The mechanical response of morphing aircraft in deformation process is a long-standing problem in variant flight modeling and control problem, current mainstream solution both domestic and external has two kinds, the first utilizes large tunnel to blow test, it two is utilize simulation calculation software to carry out simulation analysis, but the former costly, and the latter's degree of accuracy cannot be guaranteed.For miniature self-service morphing aircraft, the testing scheme cost of tradition large tunnel is larger, the result degree of accuracy that simulation calculation software obtains then cannot be guaranteed, and such scheme all accurately can not provide the actual change of mechanical characteristic in deformation process simultaneously.
Summary of the invention
The object of the invention is: the mechanical meaurement device proposing a kind of deformable low-speed machine wing structure, can with economical, simple and easy, fast mode accurately measure the mechanical characteristic of morphing aircraft structure.
Technical scheme of the present invention is:
A mechanical meaurement device for deformable low-speed machine wing structure, comprising:
Testing table (12), described testing table (12) comprises base, base side is upwards provided with the sidewall erected, sidewall has hole, level is on the hole being screwed onto sidewall up and down for two wall mount (1), and in the middle part of upper and lower two wall mount (1), the position corresponding near side has screw;
Unit protection casket cover (16) is just to a side opening of wing, unit protection casket cover (14) has line concentration hole (11) back to the side of wing, unit protection casket cover (14) upper and lower surface relative position is provided with groove (10), is provided with the rotation run through up and down controls shaft sleeve (9) in the side of the groove (10) of unit protection casket cover (14);
The back rest (3) of wing (13) is fastening to be inserted in the first girder fixture (4), first girder fixture (4) rear end is fixedly connected with first axle (5) of variant overstroke safety device, the front-axle beam (6) of wing (13) is fastening to be inserted in the second girder fixture (7), and the second girder fixture (7) rear end is fixedly connected with second axle (8) of variant overstroke safety device;
First axle (5) of variant overstroke safety device and second axle (8) of variant overstroke safety device are inserted in unit protection casket cover (14), groove (10) along unit protection casket cover (14) slides, and the signal wire of wing (13) is drawn from line concentration hole (11);
Rotate stationary shaft (2) and control shaft sleeve (9) through the screw of erecting frame (1) and the rotation of unit protection casket cover (14) successively, and rotation stationary shaft (2) is fixedly connected with the screw of wall mount (1).
Advantage of the present invention is: propose a kind of novel for wing, the especially force measuring machine of Variable Geometry Wing.The cost that the vehicle aerodynamics reducing under the lower situation of accuracy requirement (mainly SUAV (small unmanned aerial vehicle)) is measured and difficulty, save Measuring Time.
Accompanying drawing explanation
Fig. 1 is a certain tested Variable Geometry Wing distortion front and back vertical view that the present invention relates to.
Fig. 2 is the present invention's same wing root sectional view.
Fig. 3 is the distortion of the present invention's same wing and indeformable position and rotating shaft schematic diagram (14 is variable part, and 15 is constant part).
Fig. 4 is that the present invention rotates stationary shaft and steady arm thereof.
Fig. 5 and Fig. 6 is that wing of the present invention is connected and fixed device.
Fig. 7 is unit protection casket cover.
Fig. 8 is that protection casket cover is connected and fixed the connected mode schematic diagram of device with wing.
Fig. 9 is intact device normal axomometric drawing of the present invention.
Figure 10 is the complete installation diagram of wing.
Figure 11 is strain sensing arranged in arrays scheme schematic diagram.
Figure 12 is device maintenance installment state schematic diagram after distortion.
Embodiment
Below device is described in detail:
A mechanical meaurement device for deformable low-speed machine wing structure, as shown in figs. 1-12, comprising:
Testing table (12), described testing table (12) comprises base, base side is upwards provided with the sidewall erected, sidewall has hole, level is on the hole being screwed onto sidewall up and down for two wall mount (1), and in the middle part of upper and lower two wall mount (1), the position corresponding near side has screw;
Unit protection casket cover (16) is just to a side opening of wing, unit protection casket cover (14) has line concentration hole (11) back to the side of wing, unit protection casket cover (14) upper and lower surface relative position is provided with groove (10), is provided with the rotation run through up and down controls shaft sleeve (9) in the side of the groove (10) of unit protection casket cover (14);
The back rest (3) of wing (13) is fastening to be inserted in the first girder fixture (4), first girder fixture (4) rear end is fixedly connected with first axle (5) of variant overstroke safety device, the front-axle beam (6) of wing (13) is fastening to be inserted in the second girder fixture (7), and the second girder fixture (7) rear end is fixedly connected with second axle (8) of variant overstroke safety device;
First axle (5) of variant overstroke safety device and second axle (8) of variant overstroke safety device are inserted in unit protection casket cover (14), groove (10) along unit protection casket cover (14) slides, and the signal wire of wing (13) is drawn from line concentration hole (11);
Rotate stationary shaft (2) and control shaft sleeve (9) through the screw of erecting frame (1) and the rotation of unit protection casket cover (14) successively, and rotation stationary shaft (2) is fixedly connected with the screw of wall mount (1).
1.1, device is installed and fixed relationship:
As Figure 10: it is a part body that wall mount (1) is connected with rotation stationary shaft (2), is installed on testing table (12) by wall mount (1), is fixed near metope thus by rotation axis simultaneously; Two wing girders (3,6) complete fixing with corresponding girder fixture (4,7) respectively, simultaneously girder fixture and wing edge join; Shaft portion (5,8) and the girder fixture consolidation of variant overstroke safety device.The axle (5,8) of variant overstroke safety device is harmonious with groove (10) and contacts, and completes the complete restriction to deformation process deformation stroke; Rotate stationary shaft (2) to be enclosed within rotation control shaft sleeve (9) of unit protection casket cover (be harmonious contact), be connected on model.
In sum, the fixed relationship of mechanism and the setting of installation process is completed.
1.2, wing is installed and is measured test process:
Wing (13) is by its two girders (3,6) be combined with girder fixture, through being installed on (as Figure 10) on device, by strain transducer arranged in arrays in aerofoil surface (as Figure 11 scheme), its signal lead by guiding line concentration hole (11) on the downside of wing into, by line concentration hole outgoing signal line; Signal wire is connected with computing machine, spreads out of corresponding strain signal.
Whole device is placed on fixation test platform [(12), shape is variable], on device and motion platform (platform can be free, as: carrier loader, track sled etc.).There is provided speed by motion platform motion, obtain corresponding speed windward; Change its current form by wing self actuator, obtain corresponding deformation process; Becoming device by height settles angle and position to change movement position established angle, obtains corresponding Windward angle.
During movement, corresponding strain information is provided by the distribution strain of strain sensing array, the force snesor forming limiter (5,8) and girder fixture (4,7) and syndeton place thereof by being arranged in variant returns corresponding stress information.Stress-strain is utilized to calculate and mechanics fundamental formular completes measuring and analysis to aircraft self mechanical characteristic and its air dynamic behaviour.
In body change procedure; the change of angle of sweep and area can be there is in wing; in overall change procedure; the fixed point of wing installation site is for rotating stationary shaft (2); the rotating shaft of its axle and wing self overlaps; for same rotating shaft, the control of other change locations is the change of girder position and angle before and after it, and its change procedure is by protecting casket to overlap and wing is connected and fixed the variant journey controller that device forms jointly and controls.During area change, wing girder position is moved, and the axle (5,8) of journey controller is mobile in groove (10), adaptive deformation process; During the change of angle of sweep, wing girder angle changes, and axle (5,8) motion in groove (10) of formation control device changes self-view simultaneously.As the unit state schematic diagram that Figure 12 is under a certain change mode.
Claims (1)
1. a mechanical meaurement device for deformable low-speed machine wing structure, is characterized in that, comprising:
Testing table (12), described testing table (12) comprises base, base side is upwards provided with the sidewall erected, sidewall has hole, level is on the hole being screwed onto sidewall up and down for two wall mount (1), and in the middle part of upper and lower two wall mount (1), the position corresponding near side has screw;
Unit protection casket cover (16) is just to a side opening of wing, unit protection casket cover (14) has line concentration hole (11) back to the side of wing, unit protection casket cover (14) upper and lower surface relative position is provided with groove (10), is provided with the rotation run through up and down controls shaft sleeve (9) in the side of the groove (10) of unit protection casket cover (14);
The back rest (3) of wing (13) is fastening to be inserted in the first girder fixture (4), first girder fixture (4) rear end is fixedly connected with first axle (5) of variant overstroke safety device, the front-axle beam (6) of wing (13) is fastening to be inserted in the second girder fixture (7), and the second girder fixture (7) rear end is fixedly connected with second axle (8) of variant overstroke safety device;
First axle (5) of variant overstroke safety device and second axle (8) of variant overstroke safety device are inserted in unit protection casket cover (14), groove (10) along unit protection casket cover (14) slides, and the signal wire of wing (13) is drawn from line concentration hole (11);
Rotate stationary shaft (2) and control shaft sleeve (9) through the screw of erecting frame (1) and the rotation of unit protection casket cover (14) successively, and rotation stationary shaft (2) is fixedly connected with the screw of wall mount (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420588139.8U CN204128805U (en) | 2014-10-11 | 2014-10-11 | The mechanical meaurement device of deformable low-speed machine wing structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420588139.8U CN204128805U (en) | 2014-10-11 | 2014-10-11 | The mechanical meaurement device of deformable low-speed machine wing structure |
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| CN204128805U true CN204128805U (en) | 2015-01-28 |
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| CN201420588139.8U Active CN204128805U (en) | 2014-10-11 | 2014-10-11 | The mechanical meaurement device of deformable low-speed machine wing structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289680A (en) * | 2016-08-01 | 2017-01-04 | 中国航天空气动力技术研究院 | Assay device for the quiet aeroelastic test of wind-tunnel |
| CN110589020A (en) * | 2019-09-24 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Structure and method for determining influence of surface quality defects of airplane |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
-
2014
- 2014-10-11 CN CN201420588139.8U patent/CN204128805U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106289680A (en) * | 2016-08-01 | 2017-01-04 | 中国航天空气动力技术研究院 | Assay device for the quiet aeroelastic test of wind-tunnel |
| CN106289680B (en) * | 2016-08-01 | 2018-11-23 | 中国航天空气动力技术研究院 | Experimental rig for the quiet aeroelastic test of wind-tunnel |
| CN110589020A (en) * | 2019-09-24 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Structure and method for determining influence of surface quality defects of airplane |
| CN112461644A (en) * | 2020-11-19 | 2021-03-09 | 航天彩虹无人机股份有限公司 | Clamping device for testing electrical performance of sensor antenna under static deformation of wing |
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