CN203638109U - Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft - Google Patents
Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft Download PDFInfo
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- CN203638109U CN203638109U CN201320621462.6U CN201320621462U CN203638109U CN 203638109 U CN203638109 U CN 203638109U CN 201320621462 U CN201320621462 U CN 201320621462U CN 203638109 U CN203638109 U CN 203638109U
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- gear
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- tie
- drive
- rod
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Abstract
The utility model provides a special motion distribution device for ground test equipment of a foldable double wing plate bracket of an aircraft. A transmission shaft I and a transmission shaft II extend out of a shell through a shaft sleeve I and a shaft sleeve II respectively; a servo motor A is used for driving a tie bar drive wheel; the tie bar drive wheel is coaxially and fixedly connected with the transmission shaft II, a left tie bar fixing wheel and a gear IV; the gear IV is engaged with a gear III; the transmission shaft I and a right tie bar fixing wheel are coaxially and fixedly connected with the gear III; a servo motor B is used for driving a loading drive wheel; the loading drive wheel is coaxially and fixedly connected with a right side wing center wheel and a gear I; the gear I is engaged with the gear II; the shaft sleeve II and a left wing plate center wheel are coaxially and fixedly connected with the gear II. According to the special motion distribution device, the motion and the power of the ground test equipment of the foldable double wing plate bracket of the aircraft can be distributed and transmitted, the overall structure of the equipment is optimized, the manufacturing cost is reduced, and the overall working performance and the technical economic index of the equipment are improved.
Description
Technical field
The present invention relates to a kind of motion assignment device.
Background technology
In existing foldable double-wing-plate support of aircraft ground-testing plant, the servo-actuated tie-rod in left and right and load maintainer adopt separately independently drive system and control system, the complex structure of device driver system, the interrelated degree of control system is high, and there is intrinsic discreteness in propulsion source (motor) self parameter, cause the debugging difficulty of equipment large, move stablely not, make Whole Equipment performance be difficult to the mode of operation that keeps reliable and stable.
The defect of prior art is mainly manifested in the following aspects:
1. the servo-actuated tie-rod in left and right has independently drive motor separately, and left and right load maintainer also has independently drive motor separately, has four motors, quadruplet driving system, and electric and too complexity of physical construction, the difficulty of mutually coordinating is large;
2. when folded wing plate rotary expansion, when servo-actuated tie-rod is followed the tracks of wing plate and is rotated, the discreteness of and mechanical parameter electric due to motor self, the state of kinematic motion of left and right tie-rod there are differences, i.e. and instantaneous rotational displacement can not be consistent;
3. when folded wing plate rotary expansion, when both sides simulation aerodynamic lift force-input device loads, the discreteness of and mechanical parameter electric due to motor self, the simulation pneumatically loading power value that left and right sides force-input device provides can not be consistent;
4. in the process of folded wing plate support ground spreading test, servo-actuated tie-rod is in following the tracks of wing plate rotation, also to ensure the synchronous rotation of left and right tie-rod, also to ensure that force-input device loads according to predetermined rule coordination simultaneously, due to the discreteness of four motor self electrical equipment in equipment package and mechanical parameter, cause the difficulty of Control System Design, debugging to strengthen, make the performance of equipment be difficult to meet operating needs.
According to result for retrieval on internet, do not find the special motion assignment device of foldable double-wing-plate support of aircraft ground-testing plant of similar structures.
Summary of the invention
In order to overcome the deficiencies in the prior art, the invention provides the special motion assignment device of a kind of foldable double-wing-plate support of aircraft ground-testing plant, realize the motion of foldable double-wing-plate support of aircraft ground-testing plant and the distribution of power and transmission, the integral structure of optimized device, reduce manufacturing cost, improve integral working and the technical and economic index of equipment.
The technical solution adopted for the present invention to solve the technical problems is: in a closure casing, the transmission shaft I being parallel to each other and transmission shaft II are stretched out outside housing by axle sleeve I and axle sleeve II respectively, the control of the controlled system of servomotor A, drive tie-rod drive wheel to rotate, the transmission shaft II that tie-rod drive wheel is coaxially connected can drive the left tie-rod tight pulley and the gear IV that are coaxially connected, gear IV engaging gear III, transmission shaft I and right tie-rod tight pulley and gear III are coaxially connected; Control system is sent work order to another servo motor B simultaneously, drive load drive wheel rotates, drive with load driver and take turns the right side wing plate center gear and the gear I that are coaxially connected, gear I engaging gear II, axle sleeve II and left wing plate center gear and gear II are coaxially connected; Left tie-rod tight pulley and right tie-rod tight pulley drive the tie-rod of both sides synchronously to rotate by positive drive chain, the simulation aerodynamic lift in the process of collapsible wing plate rotary expansion, wing plates on two sides being applied, left wing plate center gear and right side wing plate center gear drive respectively the force-input device of both sides to realize by synchronous cog belt and load.
Described gear I, gear II, gear III are identical with the number of teeth of gear IV, and modulus is identical.
The invention has the beneficial effects as follows:
1) between the servo-actuated tie-rod in left and right, adopt the structure of positive drive chain, eliminated the difference of the servo-actuated state that between two motors, performance perameter difference is brought, ensure that tie-rod follows the tracks of the servo-actuated state synchronized of wing plate expanded position, improved the stability of equipment work;
2) between the center gear of left and right, adopt the structure of positive drive chain, eliminate the difference of the simulation pneumatically loading power value that between two motors, performance perameter difference is brought, ensure the synchronous of left and right center gear intermittent angle displacement, ensured the conformability of the Simulated Aerodynamic Loads that left and right sides wing plate bears;
3) servomotor is reduced to two by four, has simplified control system, has reduced the difficulty of design and the debugging of control system;
4) this device can be suitable for the ground-testing plant of any expanded angle, has expanded the range of use of equipment.
5) reduce the manufacturing cost of equipment, improved the stability of equipment operation.
Brief description of the drawings
Fig. 1 is the structural representation of folding double-wing-plate support, wherein, (a) is folded state schematic diagram, is (b) deployed condition schematic diagram;
Fig. 2 is collapsible wing plate ground-testing plant constructional drawing;
Fig. 3 is motion assignment apparatus structure schematic diagram;
In figure, 1-right wing plate, the rotating shaft of 2-wing plate, 3-rolling linear guide, 4-development mechanism, 5-left wing plate, 6-tie-rod, 7-center frame, 8-wing plate support, 9-motion assignment device, 10-synchronous cog belt, 11-load maintainer, 12-base, 13-right wing plate center gear, 14-axle sleeve I, 15-gear III, the right tie-rod tight pulley of 16-, 17-housing, the left tie-rod tight pulley of 18-, 19-gear IV, 20-left wing plate center gear, 21-axle sleeve II, 22-gear II, 23-transmission shaft II, 24-tie-rod drive wheel, 25-load driver wheel, 26-transmission shaft I, 27-gear I.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described, the present invention includes but be not limited only to following embodiment.
As shown in Figure 1, in folded wing plate support product, between the wing plate of left and right, be rigidity linkage status, share the propulsion source of a combustion gas pressurized strut while launching as wing plate, promote collapsible wing plate and be converted to by folded state the deployed condition of normal work.
As shown in Figure 2, flexible wing board mount ground-testing plant structure diagram, in the present invention, special motion assignment device is an important component part of this equipment, and its radical function is state of kinematic motion and the power that propulsion source is provided, and is dispensed to concrete actuating unit according to predetermined scheme transmission.
As shown in Figure 3, in the present invention, utilize the type of drive of straight gear engagement, between the tie-rod of left and right, form fixing interaction relation, with not marking in a servomotor A(figure) drive tie-rod drive wheel to rotate, drive left side tie-rod tight pulley by transmission shaft II again, and drive right tie-rod tight pulley to rotate by gear IV, gear III, transmission shaft I, realize the synchronous rotation of arranged on left and right sides tie-rod.In the process of folded wing plate rotary expansion, the angle signal of the instantaneous rotary expansion of wing plate detected by photoelectric encoder, after control system is processed, to servomotor, A sends work order, by positive drive chain, drives the tie-rod of the left and right sides synchronously to rotate.According to designing requirement, in the process of collapsible wing plate rotary expansion, the simulation aerodynamic lift that wing plates on two sides is applied, all should equate in any transient state moment, require force-input device to load to wing plate according to predetermined Changing Pattern simultaneously, send work order by control system to another servo motor B (not marking in figure), drive load drive wheel rotates, drive right side wing plate center gear to rotate, and by gear I, gear II, the positive drive chain of axle sleeve II composition, drive left wing plate center gear to rotate, pass through again synchronous cog belt, drive respectively the force-input device of the left and right sides to realize loading.Due to the positive drive chain that messenger chain is made up of straight gear, the equivalence of realizing synchronous any time of arranged on left and right sides loads.
The relation of each assembly correlation parameter:
The number of teeth of transmission gear: Z
1=Z
2=Z
3=Z
4(note: Z
1for the number of teeth of gear I, the like);
The modulus of transmission gear: m
1=m
2=m
3=m
4(note: m
1for the modulus of gear I, the like).
As shown in Figure 3, this device adopts two to overlap independently propulsion source and driving system, is uniaxial drive, twin shaft output, and the effect of Tu Zhong mechanism each several part is described below:
1) control system is sent after instruction, in servomotor A(figure, do not mark) by tie-rod drive wheel, transmission shaft II, driving left tie-rod tight pulley to drive left side tie-rod to follow the tracks of left side wing plate rotates, by gear IV, gear III, transmission shaft I, drive right tie-rod tight pulley to drive right side tie-rod to follow the tracks of right side wing plate and rotate simultaneously.Because being connected by gear IV, gear III between left tie-rod tight pulley and right tie-rod tight pulley, and transmitting ratio is 1:1, can guarantee that the two synchronously rotates.
2) control system is sent after instruction, servo motor B (not marking in figure) by load driver take turns, axle sleeve I, drive right wing plate center gear to rotate, simultaneously by gear I, gear II, axle sleeve II, drive left wing plate center gear to rotate.Because being connected by gear I, gear II between left wing plate center gear and right wing plate center gear, and transmitting ratio is 1:1, can guarantee that the two synchronously rotates, then load through synchronous cog belt band dynamic simulated pneumatics, and the power value that realizes both sides simulation pneumatically loading equates.
1. the mounting structure brief introduction of motion assignment device:
The lower end of motion assignment device is fixed on the center frame of equipment, and upper end is connected with aircraft flexible wing board mount, and Gear axis is plumb position, and perpendicular to floor installation face, two transmission shafts must keep coaxial with the axis of revolution of wing plates on two sides.
2. the transmission principle brief introduction of motion assignment device:
This device adopts two to overlap independently propulsion source and driving system, is uniaxial drive, twin shaft output.
Propulsion source is inputted by both sides transmission shaft respectively, is convenient to the integral layout design of ground-testing plant.
Axle sleeve type structure can meet exports rotatablely moving of two kinds of different Changing Patterns on same rotation axis.
3. the lubricated program profile of motion assignment device:
Because device intermediate solid drive shaft all adopts vertical, and casing is Open architecture, and mode of operation is intermittence running, so, between bearing and gear, all adopt grease lubrication, can meet the lubricating requirement of device.
Embodiment:
1. the moving chain of the transmission of motion assignment device:
Known by movement relation: transmitting ratio: i
12=i
34=1
The number of teeth of transmission gear: Z
1=Z
2=Z
3=Z
4
The modulus of transmission gear: m
1=m
2=m
3=m
4
2. embodiment: as shown in Figure 3, the parameter of selecting device is:
The width between centers of two wing plate rotating shafts: 270 ± 0.05,58 ° of corners when wing plate launches.
1) number of teeth of transmission gear: Z
1=Z
2=Z
3=Z
4=90;
2) modulus of transmission gear: m
1=m
2=m
3=m
4=3;
3) left and right wing plate center gear all adopts circular arc synchronous cog belt belt wheel;
4) left and right tie-rod tight pulley adopts flange connection mode and tie-rod to connect firmly;
5) left tie-rod tight pulley and gear IV are fixed in transmission shaft II, ensure that the two synchronously rotates;
6) right tie-rod tight pulley and gear III are fixed in transmission shaft I, ensure that the two synchronously rotates;
7) left wing plate center gear and gear II are fixed in axle sleeve II, ensure that the two synchronously rotates;
8) right wing plate center gear and gear I are fixed in axle sleeve I, ensure that the two synchronously rotates;
9) tie-rod drive wheel is fixed in transmission shaft II, ensures that the two synchronously rotates;
10) load driver wheel is fixed in axle sleeve I, ensures that the two synchronously rotates;
11) between transmission shaft I and axle sleeve I, ball ball-bearing casing is connected;
12) between transmission shaft II and axle sleeve II, ball ball-bearing casing is connected.
Foregoing is the main structure parameters of motion assignment device.
Claims (2)
1. the special motion assignment device of foldable double-wing-plate support of aircraft ground-testing plant, it is characterized in that: in a closure casing, the transmission shaft I being parallel to each other and transmission shaft II are stretched out outside housing by axle sleeve I and axle sleeve II respectively, the control of the controlled system of servomotor A, drive tie-rod drive wheel to rotate, the transmission shaft II that tie-rod drive wheel is coaxially connected can drive the left tie-rod tight pulley and the gear IV that are coaxially connected, gear IV engaging gear III, transmission shaft I and right tie-rod tight pulley and gear III are coaxially connected; Control system is sent work order to another servo motor B simultaneously, drive load drive wheel rotates, drive with load driver and take turns the right side wing plate center gear and the gear I that are coaxially connected, gear I engaging gear II, axle sleeve II and left wing plate center gear and gear II are coaxially connected; Left tie-rod tight pulley and right tie-rod tight pulley drive the tie-rod of both sides synchronously to rotate by positive drive chain, the simulation aerodynamic lift in the process of collapsible wing plate rotary expansion, wing plates on two sides being applied, left wing plate center gear and right side wing plate center gear drive respectively the force-input device of both sides to realize by synchronous cog belt and load.
2. the special motion assignment device of foldable double-wing-plate support of aircraft ground-testing plant according to claim 1, is characterized in that: described gear I, gear II, gear III are identical with the number of teeth of gear IV, and modulus is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320621462.6U CN203638109U (en) | 2013-09-30 | 2013-09-30 | Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320621462.6U CN203638109U (en) | 2013-09-30 | 2013-09-30 | Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203638109U true CN203638109U (en) | 2014-06-11 |
Family
ID=50869376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320621462.6U Expired - Lifetime CN203638109U (en) | 2013-09-30 | 2013-09-30 | Special motion distribution device for ground test equipment of foldable double wing plate bracket of aircraft |
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|---|---|
| CN (1) | CN203638109U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019205462A1 (en) * | 2018-04-27 | 2019-10-31 | 深圳市大疆创新科技有限公司 | Folding apparatus |
| CN110954395A (en) * | 2019-11-12 | 2020-04-03 | 航天时代飞鸿技术有限公司 | Elastic loading device and method for folding missile wing performance test |
| CN111959820A (en) * | 2020-07-05 | 2020-11-20 | 西安科为实业发展有限责任公司 | Gap detection method for folding wing of high-aspect-ratio unmanned aerial vehicle |
-
2013
- 2013-09-30 CN CN201320621462.6U patent/CN203638109U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019205462A1 (en) * | 2018-04-27 | 2019-10-31 | 深圳市大疆创新科技有限公司 | Folding apparatus |
| CN110954395A (en) * | 2019-11-12 | 2020-04-03 | 航天时代飞鸿技术有限公司 | Elastic loading device and method for folding missile wing performance test |
| CN111959820A (en) * | 2020-07-05 | 2020-11-20 | 西安科为实业发展有限责任公司 | Gap detection method for folding wing of high-aspect-ratio unmanned aerial vehicle |
| CN111959820B (en) * | 2020-07-05 | 2023-11-28 | 西安科为实业发展有限责任公司 | Gap detection method for folding wings of high aspect ratio unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140611 |