CN106347704B - Fly control test device - Google Patents
Fly control test device Download PDFInfo
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- CN106347704B CN106347704B CN201610807093.8A CN201610807093A CN106347704B CN 106347704 B CN106347704 B CN 106347704B CN 201610807093 A CN201610807093 A CN 201610807093A CN 106347704 B CN106347704 B CN 106347704B
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Abstract
The present invention discloses a kind of winged control test device, wherein the winged control test device includes pedestal, outer shaft, internal axle sleeve and the rotating mechanism to realize unmanned plane static state flight test；The rotating mechanism includes turntable interconnected and connecting shaft, and the connecting shaft runs through the internal axle sleeve, and the outer shaft is socketed on the outside of the internal axle sleeve, and the outer shaft connects the pedestal；The internal axle sleeve includes casing and boss, and the boss is located in the middle part of described sleeve pipe periphery wall, and described sleeve pipe periphery wall is also socketed at least two first bearings, and at least two first bearings are abutted with the both ends of the boss respectively.Technical solution provided by the invention aims to ensure that flying control test device can be suitable for frequent unmanned plane static state flight test.
Description
Technical field
The present invention relates to air vehicle technique fields, and in particular to one kind flies control test device.
Background technique
With the development of science and technology, unmanned plane is more and more common in our real-life uses, unmanned plane is answered extensively
For in all trades and professions.When studying the flight attitude of unmanned plane and controlling it design, researcher passes through quiet mostly
State flight simulator is acquired and studies to data such as course angular dimensions, pitching angular dimensions under unmanned plane during flying state, but
Existing static state flight simulator structure is relatively simple, and not enough fastening is connected between each component, be not suitable for bearing it is frequent nobody
Machine static state flight test.
Summary of the invention
The main object of the present invention is to provide a kind of winged control test device for connecting and more fastening, it is intended to ensure to fly control test
Device can be suitable for frequent unmanned plane static state flight test.
To achieve the above object, winged control test device proposed by the present invention includes pedestal, outer shaft, internal axle sleeve and to reality
The rotating mechanism of existing unmanned plane static state flight test；The rotating mechanism includes turntable interconnected and connecting shaft, the company
Spindle runs through the internal axle sleeve, and the outer shaft is socketed on the outside of the internal axle sleeve, and the outer shaft connects the pedestal；Institute
Stating internal axle sleeve includes casing and boss, and the boss is located in the middle part of described sleeve pipe periphery wall, and described sleeve pipe periphery wall is also socketed
There are at least two first bearings, at least two first bearings are abutted with the both ends of the boss respectively.
Preferably, the turntable includes rotating platform, fixed plate, two fixing seats, shaft and to fixed unmanned plane
Installation part, two fixing seats are respectively arranged on the rotating platform both ends, and the both ends of the shaft is connected respectively two institutes
Fixing seat is stated, the rotating platform is set to the shaft by the fixed plate and the connection axis connection, the installation part.
Preferably, the winged control test device further includes connector, locating part and fixing piece, the connecting shaft, connector
It is successively socketed from the inside to the outside with locating part, and the connector is threadedly coupled with the fixed plate, deviating from for the locating part connects
The side of spindle connects the fixing piece, and the fixing piece is abutted away from one end of locating part with the outer shaft.
Preferably, the locating part includes the first locating part and the second locating part, and first locating part and second limit
Part is threadedly coupled, and one end far from the second locating part of first locating part is threadedly coupled with the fixing piece, and described second
One end far from the first locating part of locating part is threadedly coupled with the fixing piece.
Preferably, the connecting shaft is vertical with the plane where the rotating platform；The shaft and the rotating platform
The plane at place is parallel.
Preferably, the turntable further includes second bearing, and the second bearing is sheathed between the shaft and fixing seat,
The side that two fixing seats mutually deviate from is equipped with baffle.
Preferably, the installation part is two, and two installation parts are set between two fixing seats.
Preferably, the first bearing is four, one of them described first bearing is sheathed on the internal axle sleeve and fixation
Between part, first bearing described in the other three is sheathed between the internal axle sleeve and outer shaft.
Preferably, the pedestal includes bottom plate and column, and the column both ends are separately connected the bottom plate and outer shaft.
Preferably, logical between the first bearing and the outer shaft, between the first bearing and the fixing piece
Screw is crossed to fix.
In technical solution of the present invention, turntable of the winged control test device by connection axis connection to place unmanned plane,
So that the unmanned plane is capable of fixing in the turntable, and then by the synergistic effect of the connecting shaft and the turntable, so that nothing
It is man-machine to be able to achieve various flight attitudes, conveniently the flight attitude parameter of unmanned plane is acquired and is studied；And the connecting shaft
Outer sheath is equipped with internal axle sleeve and outer shaft, can further ensure that the stability of the connection axis connection, prevent because of repeatedly flight examination
Test and cause the generation for the case where connecting axle fracture, it is ensured that the winged control test device adapts to frequent flight test.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
The structure shown according to these attached drawings obtains other attached drawings.
Fig. 1 is the fractionation structural representation for flying the part-structure of control test device in one embodiment of the invention；
Fig. 2 is the fractionation structural representation for flying the turntable of control test device in another embodiment of the present invention；
Fig. 3 is the structural schematic diagram of outer shaft in Fig. 2, fixing piece, locating part, connector and fixed plate connection；
Fig. 4 is the top view of Fig. 3；
Fig. 5 is the cross-sectional view of B-B in Fig. 4；
Fig. 6 is the decomposition texture schematic diagram of outer shaft in Fig. 3.
Drawing reference numeral explanation:
| Label | Title | Label | Title |
| 10 | Turntable | 20 | Pedestal |
| 30 | Outer shaft | 40 | Internal axle sleeve |
| 50 | Connecting shaft | 60 | First bearing |
| 70 | Connector | 80 | Locating part |
| 90 | Fixing piece | 11 | Rotating platform |
| 12 | Fixed plate | 13 | Fixing seat |
| 14 | Shaft | 15 | Installation part |
| 16 | Second bearing | 17 | Baffle |
| 21 | Bottom plate | 22 | Column |
| 31 | Inner sleeve | 32 | Housing |
| 41 | Casing | 42 | Boss |
| 81 | First locating part | 82 | Second locating part |
| 83 | Cyclic structure | 84 | Lug |
| 85 | Plug connector |
The embodiments will be further described with reference to the accompanying drawings for the realization, the function and the advantages of the object of the present invention.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiment is only a part of the embodiments of the present invention, instead of all the embodiments.Base
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts it is all its
His embodiment, shall fall within the protection scope of the present invention.
It is to be appreciated that the directional instruction (such as up, down, left, right, before and after ...) of institute is only used in the embodiment of the present invention
In explaining in relative positional relationship, the motion conditions etc. under a certain particular pose (as shown in the picture) between each component, if should
When particular pose changes, then directionality instruction also correspondingly changes correspondingly.
In addition, the description for being such as related to " first ", " second " in the present invention is used for description purposes only, and should not be understood as
Its relative importance of indication or suggestion or the quantity for implicitly indicating indicated technical characteristic.Define as a result, " first ",
The feature of " second " can explicitly or implicitly include at least one of the features.In the description of the present invention, " multiple " contain
Justice is at least two, such as two, three etc., unless otherwise specifically defined.
In the present invention unless specifically defined or limited otherwise, term " connection ", " fixation " etc. shall be understood in a broad sense,
For example, " fixation " may be a fixed connection, it may be a detachable connection, or integral；It can be mechanical connection, be also possible to
Electrical connection；It can be directly connected, the connection inside two elements or two can also be can be indirectly connected through an intermediary
The interaction relationship of a element, unless otherwise restricted clearly.It for the ordinary skill in the art, can basis
Concrete condition understands the concrete meaning of above-mentioned term in the present invention.
It in addition, the technical solution between each embodiment of the present invention can be combined with each other, but must be general with this field
Based on logical technical staff can be realized, it will be understood that when the combination of technical solution appearance is conflicting or cannot achieve this
The combination of technical solution is not present, also not the present invention claims protection scope within.
The present invention proposes a kind of winged control test device.
Please refer to Fig. 1 to Fig. 5, in an embodiment of the present invention, this fly control test device, including pedestal 20, outer shaft 30,
Internal axle sleeve 40 and the rotating mechanism to realize unmanned plane static state flight test (not indicating)；The rotating mechanism includes mutually interconnecting
The turntable 10 and connecting shaft 50 connect, the connecting shaft 50 run through the internal axle sleeve 40, and the outer shaft 30 is socketed on the inner shaft
40 outside of set, and the outer shaft 30 connects the pedestal 20；The internal axle sleeve 40 includes casing 41 and boss 42, the boss
42 are located in the middle part of described sleeve pipe 41 periphery wall, and 41 periphery wall of described sleeve pipe is also socketed at least two first bearings 60, and two
The first bearing 60 is abutted with the both ends of the boss 42 respectively.
The winged control test device connects the turntable 10 to place unmanned plane by connecting shaft 50, so that the unmanned plane
It is capable of fixing in the turntable 10, and then by the synergistic effect of the connecting shaft 50 and the turntable 10, so that unmanned function is real
Existing various flight attitudes, it is convenient that the flight attitude parameter of unmanned plane is acquired and is studied.It is arranged on the outside of the connecting shaft 50
There are internal axle sleeve 40 and outer shaft 30, can further ensure that the stability that the connecting shaft 50 connects, prevent because of multiple flight test
And the generation for the case where causing connecting shaft 50 to be broken, it is ensured that the winged control test device adapts to frequent flight test.It is described
The both ends of boss 42 are respectively sleeved on first bearing 60, can bear the axial stress that heavier body generates, guarantee the connection
The fixation of 50 axis center of axis, and rubbing for the generation of internal axle sleeve 40 described in the winged control test device motion process can be effectively reduced
Wipe coefficient.
Referring in particular to Fig. 2, the turntable 10 includes rotating platform 11,12, two fixing seats 13 of fixed plate, 14 and of shaft
To the installation part 15 of fixed unmanned plane, two fixing seats 13 are respectively arranged on 11 both ends of rotating platform, the shaft
14 both ends are connected respectively two fixing seats 13, and the installation part 15 is set to the shaft 14, the rotating platform 11
It is fixedly connected by the fixed plate 12 with the connecting shaft 50.Specifically, unmanned plane is installed on the installation part 15, and described turn
14 rotatable movement of axis, and then can guarantee the smooth progress of the flight attitude of unmanned plane.
Please continue to refer to Fig. 1 and Fig. 3, the winged control test device further includes connector 70, locating part 80 and fixing piece 90；
The connecting shaft 50, connector 70 and locating part 80 are successively socketed from the inside to the outside, and the connector 70 and the fixed plate 12
It is threadedly coupled, the side away from connecting shaft 50 of the locating part 80 connects the fixing piece 90, and the fixing piece 90 is away from limit
One end of position part 80 is abutted with the outer shaft 30.
Specifically, the connecting shaft 50 sequentially passes through the connector 70, locating part 80 and fixing piece 90 from top to bottom, and
The locating part 80 is sheathed on 70 outside of connector, to fasten the connector 70, the both ends point of the fixing piece 90
The locating part and internal axle sleeve 40 are not connected, and at least one described is arranged between the internal axle sleeve 40 and the fixing piece 90
One bearing 60.The connector 70 is connect with the turntable 10, when unmanned plane is installed on turntable 10 and drives the turntable 10
When movement, and then the rotation of the connector 70, connecting shaft 50 can be driven, the inner shaft is driven by the connecting shaft 50 simultaneously
The rotation of set 40 and first bearing 60 enables the first bearing 60 to bear the axial stress of unmanned plane generation, it is ensured that described
Fly the static flight simulation movement that control test device adapts to complete unmanned plane.
Further, the locating part includes the first locating part 81 and the second locating part 82.It is preferred real of the invention one
It applies in scheme, the locating part further includes two cyclic structures 83, and the opening of two cyclic structures 83 is oppositely arranged with shape
At a circular ring structure；First locating part 81 be connected to a cyclic structure 83 away from its be open side, described second
Locating part 82 is connected to the side away from its opening of another cyclic structure 83.The opposite end of the cyclic structure is all provided with
It is equipped with lug 84, is provided on the lug 84 threaded hole (not indicating), screw passes through the threaded hole, can with nut cooperation
The tightness of two cyclic structures 83 is controlled with realizing, to make locating part fastening or pine from the connecting shaft 50.
In the present embodiment, respectively two threaded holes of setting, two screws pass through threaded hole for two cyclic annular knots to each lug 84
Structure 84 connects into a circular ring structure.First locating part 81 and the second locating part 82 generally triangular structure, described first
Locating part 81 and second locating part 82 are provided with a through-hole (not indicating) far from one end of the cyclic structure 83, and one inserts
Fitting 85 passes through the through-hole, and the locating part and the fixing piece 90 is fixed, so that when locating part is fastenedly connected axis 50
When, connecting shaft 50 is unable to the rotation of opposed fixed member 90.It is appreciated that the corresponding plug connector 85 of the fixing piece 90 and described logical
Hole is provided with spliced eye (not indicating), and the plug connector 85 passes through the through-hole and is fixed in the spliced eye, the grafting
Part 85 can be screw, and the spliced eye corresponds to threaded hole, and certainly, the plug connector 85 can also not have screw thread, only need
It is inserted into spliced eye and realizes the fixation of locating part and fixing piece 90.
The winged control test of unmanned plane rotation attitude and posture of turning on one's side may be implemented in the winged control test device.The rotation appearance
The attitude test switching of state and the rollover posture is carried out by regulating and controlling the locating part 80, when posture is turned on one's side in test, is needed
Ensure that unmanned plane will not rotate, i.e., connecting shaft 50 is no longer rotated relative to internal axle sleeve 40, outer shaft 30, only need to gently be screwed at this time convex
Nut at ear 84, the cyclic structure 83 fasten the connecting shaft 50, then pass through through-hole with plug connector 85 again, make to limit
Part 80 and fixing piece 90 are fixed, so that connecting shaft 50 will not be rotated relative to control test device lower half is flown.When testing rotation attitude,
Plug connector 85 is extracted out of through-hole, then slightly unclamps the screw between first locating part 81 and the second locating part 82, then
The connector 70 can according to unmanned plane drive turntable 10 rotation and rotate, it is ensured that the rotation attitude of unmanned plane it is smooth into
Row.
It should be noted that the connecting shaft 50 is vertical with the plane where the rotating platform 11；The shaft 14 with
Plane where the rotating platform 11 is parallel, and then can ensure that the winged control test device is able to achieve unmanned plane different angle
Flight attitude.
Referring to figure 2., the turntable 10 further includes second bearing 16, the second bearing 16 be sheathed on the shaft 14 with
Between fixing seat 13, the side of two fixing seats 13 mutually deviated from is equipped with baffle 17.The second bearing 16 passes through
Screw is connect with the fixing seat 13, and can be reduced the spin friction coefficient of the shaft 14, and the fixing seat 13 is born described
The radial stress of second bearing 15, and fixed function is played to the second bearing 15；The baffle 16 can withstand described second
The axial stress that bearing 15 generates.
Preferably, the installation part 15 is two, and two installation parts 15 are set between two fixing seats 13, is used
To facilitate the installation of unmanned plane.
In a preferred embodiment of the invention, the first bearing 60 is four, wherein 60 sets of a first bearing
Between the internal axle sleeve 40 and fixing piece 90, first bearing 60 described in the other three is successively sheathed on the inner shaft from top to bottom
Between set 40 and outer shaft 30.Wherein, 90 lower edge of fixing piece is abutted with the outer shaft 30, and then by the first axle
It is completely obscured to hold 60, it is ensured that the aesthetics of the winged control test device shape.It should be noted that in four bearings 60,
What the bearing 60 of intermediate two was born is the axial stress of connecting shaft 50, and what another two bearing was born is the diameter of connecting shaft 50
To stress.
Referring in particular to Fig. 6, in a preferred embodiment of the present invention, the outer shaft 30 includes inner sleeve 31 and housing
32,32 one end inner wall of housing is equipped with internal screw thread, and 31 one end periphery wall of inner sleeve is equipped with external screw thread corresponding with internal screw thread,
So that the inner sleeve 31 and housing 32 are threadedly coupled, the installing and dismounting of the outer shaft 30 is further facilitated.
Preferably, the pedestal 20 includes bottom plate 21 and column 22, and 22 both ends of column are separately connected the bottom plate 21
With outer shaft 30.
It should be noted that between the first bearing 25 and the outer shaft 30, the first bearing 25 with it is described solid
Determine to be screwed between part 90.
The above description is only a preferred embodiment of the present invention, is not intended to limit the scope of the invention, all at this
Under the design of invention, using equivalent structure transformation made by description of the invention and accompanying drawing content, or directly/it is used in it indirectly
He is included in scope of patent protection of the invention relevant technical field.
Claims (10)
1. one kind fly control test device, which is characterized in that including pedestal, outer shaft, internal axle sleeve and to realize unmanned plane static state
The rotating mechanism of flight test；The rotating mechanism includes turntable interconnected and connecting shaft, and the connecting shaft is through described
Internal axle sleeve, the outer shaft are socketed on the outside of the internal axle sleeve, and the outer shaft connects the pedestal；The internal axle sleeve includes
Casing and boss, the boss are located in the middle part of described sleeve pipe periphery wall, and described sleeve pipe periphery wall is also socketed at least two the
One bearing, at least two first bearings are abutted with the both ends of the boss respectively.
2. as described in claim 1 fly control test device, which is characterized in that the turntable includes rotating platform, fixed plate, two
A fixing seat, shaft and the installation part to fixed unmanned plane, two fixing seats are respectively arranged on the rotating platform both ends,
The both ends of the shaft is connected respectively two fixing seats, and the rotating platform passes through the fixed plate and the connecting shaft
Connection, the installation part are set to the shaft.
3. as claimed in claim 2 fly control test device, which is characterized in that the winged control test device further include connector,
Locating part and fixing piece, the connecting shaft, connector and locating part are successively socketed from the inside to the outside, and the connector with it is described solid
Fixed board is threadedly coupled, and the side away from connecting shaft of the locating part connects the fixing piece, and the fixing piece deviates from locating part
One end abutted with the outer shaft.
4. as claimed in claim 3 fly control test device, which is characterized in that the locating part includes the first locating part and second
Locating part, first locating part and the second locating part are threadedly coupled, one far from the second locating part of first locating part
End is threadedly coupled with the fixing piece, and one end far from the first locating part of second locating part connects with the fixing piece screw thread
It connects.
5. as claimed in claim 2 fly control test device, which is characterized in where the connecting shaft and the rotating platform
Plane is vertical；The shaft is parallel with the plane where the rotating platform.
6. as claimed in claim 2 fly control test device, which is characterized in that the turntable further includes second bearing, and described the
Two bearing holder (housing, cover)s are set between the shaft and fixing seat, and the side that two fixing seats mutually deviate from is equipped with baffle.
7. as claimed in claim 2 fly control test device, which is characterized in that the installation part is two, two installations
Part is set between two fixing seats.
8. as claimed in claim 3 fly control test device, which is characterized in that the first bearing is four, one of institute
It states first bearing to be sheathed between the internal axle sleeve and fixing piece, first bearing described in the other three is sheathed on the internal axle sleeve and outer
Between axle sleeve.
9. as claimed in claim 8 fly control test device, which is characterized in that the pedestal includes bottom plate and column, described vertical
Column both ends are separately connected the bottom plate and outer shaft.
10. as claimed in claim 8 fly control test device, which is characterized in that between the first bearing and the outer shaft,
It is fixed by screw between the first bearing and the fixing piece.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610807093.8A CN106347704B (en) | 2016-09-06 | 2016-09-06 | Fly control test device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610807093.8A CN106347704B (en) | 2016-09-06 | 2016-09-06 | Fly control test device |
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| CN106347704A CN106347704A (en) | 2017-01-25 |
| CN106347704B true CN106347704B (en) | 2019-04-26 |
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| CN201610807093.8A Active CN106347704B (en) | 2016-09-06 | 2016-09-06 | Fly control test device |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107336845B (en) * | 2017-06-12 | 2020-06-30 | 工业和信息化部计算机与微电子发展研究中心（中国软件评测中心） | Electric unmanned aerial vehicle navigation flight control system test bed |
| CN107839897A (en) * | 2017-11-15 | 2018-03-27 | 深圳市科比特航空科技有限公司 | The disconnected oar test device of unmanned plane |
| WO2019104625A1 (en) * | 2017-11-30 | 2019-06-06 | 深圳市大疆创新科技有限公司 | Connection structure, power system and unmanned aerial vehicle |
| CN109466795B (en) * | 2018-12-04 | 2022-03-29 | 湖南山河科技股份有限公司 | Automatic test platform of unmanned helicopter |
| CN112399066B (en) * | 2019-08-15 | 2023-11-14 | 中国科学院长春光学精密机械与物理研究所 | Aviation reconnaissance load inclined distance focusing device |
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| WO2012009198A2 (en) * | 2010-07-14 | 2012-01-19 | University Of Florida Research Foundation, Inc. | System and method for assessing the performance of an attitude control system for small satellites |
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| Publication number | Publication date |
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| CN106347704A (en) | 2017-01-25 |
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Effective date of registration: 20191204 Address after: Room 812, enterprise service center, No. 17, section 3, west section of Changjiang North Road, Lingang Economic Development Zone, Yibin City, Sichuan Province Patentee after: Sichuan Yidian Aviation Technology Co., Ltd Address before: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Co-patentee before: Shenzhen AEE Technology Co., Ltd. Patentee before: Shenzhen Yidian Aviation Technology Co., Ltd. |
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