CN109094798A - A kind of unmanned plane and its winged control component - Google Patents
A kind of unmanned plane and its winged control component Download PDFInfo
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- CN109094798A CN109094798A CN201811180095.4A CN201811180095A CN109094798A CN 109094798 A CN109094798 A CN 109094798A CN 201811180095 A CN201811180095 A CN 201811180095A CN 109094798 A CN109094798 A CN 109094798A
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- winged control
- control component
- mounting plate
- control module
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- 238000012423 maintenance Methods 0.000 description 10
- 238000004519 manufacturing process Methods 0.000 description 8
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D43/00—Arrangements or adaptations of instruments
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Connection Of Plates (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Abstract
The present invention relates to air vehicle technique fields, disclose a kind of unmanned plane and its winged control component, wherein, the winged control component, it include: a kind of winged control component, it is characterised in that it includes winged control module and the mounting plate set on the unmanned plane, the winged control module are installed on the mounting plate by buckle structure.By the above-mentioned means, can realize that the winged control module of the winged control component is convenient for disassembly and assembly with mounting plate, efficiency is higher.
Description
[technical field]
The present invention relates to air vehicle technique field more particularly to a kind of unmanned plane and its fly control component.
[background technique]
Unmanned plane is the complication system for covering the multidisciplinary field such as flight control, vision algorithm, cradle head control, each function
The modularization and standardization of system are conducive to the research and development and manufacturing process that accelerate unmanned plane, facilitate the use and dimension in later period
Shield.
Flight control modules (hereinafter collectively referred to as flying control module) are subsystem important in UAV system, major function
It is the measurement status informations such as unmanned plane during flying posture, and the flight of real-time control unmanned plane.In order to guarantee the accuracy of measurement, nothing
It is man-machine installation fly control module after, it is necessary to first carry out fly control module calibration and calibration.
The commercial control module mounting arrangement that flies existing at present only has gluing and is screwed two kinds.Adhesive type mount scheme
Reliability is low, and although screw-fixing type mount scheme improves reliability, but still cannot be guaranteed to produce assembling process in enormous quantities
In fly control module positioning accuracy.That is, flying the installation site of control module in mass production, in different unmanned planes can not protect
End of certificate is exactly the same.Therefore, it for each unmanned plane in producing in enormous quantities, is required to devote a tremendous amount of time to winged control module
It is demarcated and is calibrated, this undoubtedly reduces assembly efficiency.And during flying the use and maintenance of control module in the later period, Wu Fashi
Existing " primary calibration calibration, repeatedly handling maintenance ".
[summary of the invention]
In order to solve the above-mentioned technical problem, the embodiment of the present invention provides a kind of unmanned plane and its winged control component, the winged control
The winged control module of component is convenient for disassembly and assembly with mounting plate, and efficiency is higher.
In order to solve the above-mentioned technical problem, the embodiment of the present invention the following technical schemes are provided:
On the one hand, a kind of winged control component is provided, including flying control module and set on the mounting plate of the unmanned plane, the winged control
Module is installed on the mounting plate by buckle structure.
In some embodiments, the buckle structure include at least two be set to the mounting plate on buckles, it is described extremely
Few two buckles are clamped with the winged control module respectively, and at least two buckle is separately positioned on the two of the winged control module
Side.
In some embodiments, any one buckle at least two buckle includes being connected with the mounting plate
Main part and from the main part to it is described it is winged control module bending extend clamping part.
In some embodiments, the clamping part and the main part be generally vertically.
In some embodiments, the clamping part and the main part are integrally formed.
In some embodiments, the clamping part has the first guiding surface, and first guiding surface is to the installation
Plate inclination.
In some embodiments, it is oblique to be equipped with the second guiding cooperated with first guiding surface for the winged control module
Face.
In some embodiments, the buckle is Elastic buckle.
In some embodiments, the winged control component further includes the bullet between the winged control module and the mounting plate
Property gasket, the elastomeric pad when the winged control module is connected with the mounting plate be in compressive state.
In some embodiments, the winged control component further includes thrust structure, and the thrust structure is for limiting described fly
Control module is moved along the first direction for being parallel to the mounting plate.
In some embodiments, the thrust structure includes the limited block on the mounting plate, and the limited block is set
In the side of the winged control module.
In some embodiments, the limited block has to the inclined third guiding surface of the mounting plate.
In some embodiments, it is oblique to be equipped with the 4th guiding cooperated with the third guiding surface for the winged control module
Face.
In some embodiments, the quantity of the limited block is 2, two limit block gap settings.
In some embodiments, the winged control component further includes the first location structure, and first location structure is for limiting
It makes the winged control module to move along the second direction for being parallel to the mounting plate, the second direction and the first direction phase
Instead.
In some embodiments, first location structure includes the first positioning region in the winged control module and sets
In the second positioning region on the mounting plate, first positioning region and second positioning region are contacted by line, to limit
Winged control module is stated to move along the direction for being parallel to the mounting plate.
In some embodiments, first positioning region is the positioning column with arc surface, and second positioning region includes
Positioning plate on the mounting plate and the V-shaped groove for being opened in the positioning plate, the opening of the V-shaped groove is towards the winged control
Module, the arc surface of the positioning column are abutted with the cell wall of the V-shaped groove and are contacted with forming line.
In some embodiments, the winged control module includes substrate, and the positioning column is set to the substrate.
In some embodiments, the winged control module further includes substrate, and first location structure includes being set to the base
The first positioning hole of plate is set to the mounting plate and second location hole corresponding with the first positioning hole position and passes through institute
State the positioning pin of first positioning hole and the second location hole.
In some embodiments, the positioning pin is taper bolt.
In some embodiments, the winged control component further includes the second location structure, and second location structure is for limiting
The winged control module is made around the straight line rotation perpendicular to the mounting plate.
In some embodiments, second location structure includes set on the winged third positioning region for controlling module and being set to
4th positioning region of the mounting plate, the third positioning region and the 4th positioning region limit the winged control mould by face contact
Block is around the straight line rotation perpendicular to the mounting plate.
In some embodiments, the third positioning region is the first keyway, and the 4th positioning region is flat key.
In some embodiments, first keyway and the flat key clearance fit.
In some embodiments, first keyway is in U-shape.
In some embodiments, the 4th positioning region further includes the second keyway, and the flat key is set to second keyway
It is interior.
In some embodiments, first location structure and second location structure are located on the same line.
On the other hand, a kind of unmanned plane is provided, including fuselage, the horn being connected with the fuselage, set on the horn
Power device, which is characterized in that the unmanned plane further includes winged control component as described above.
Winged control component proposed by the present invention solves the problems, such as the quick accurate positioning for flying control module and installation, simplifies
The process of unmanned plane batch Assembling Production, improves the efficiency of mass production.And winged control component proposed by the present invention, it can be achieved that
" primary calibration calibration, repeatedly handling maintenance ".That is, even across multiple disassembly and installation, winged control component of the invention still may be used
Guarantee that positioning accuracy is constant, therefore the calibration after dismounting each time and calibration steps can be omitted, simplifies later period handling maintenance
Process.Meanwhile the present invention flies the accurate fixed and positioned of control module by plane restriction, coaxial constraint and point constraint to realize,
Realize the holonomic constriants to the winged control full freedom degree of module and the positioning of degree of precision.With simple to operate, machining
The advantages that at low cost.
[Detailed description of the invention]
One or more embodiments are illustrated by corresponding attached drawing, these exemplary illustrations not structure
The restriction of pairs of embodiment, the element with same reference numbers label is expressed as similar element in attached drawing, unless there are special
It declares, composition does not limit the figure in attached drawing.
Fig. 1 is a kind of structural schematic diagram of present invention unmanned plane that wherein an embodiment provides；
Fig. 2 is the schematic perspective view of the winged control component of unmanned plane shown in FIG. 1；
Fig. 3 is the top view of winged control component shown in Fig. 2；
Fig. 4 is the exploded view of winged control component shown in Fig. 2；
Fig. 5 is the exploded view of winged control another angle of component shown in Fig. 4；
Fig. 6 is the exploded view of winged control component shown in Fig. 2 in some other embodiments, and part of components are saved
Slightly.
[specific embodiment]
To facilitate the understanding of the present invention, with reference to the accompanying drawings and detailed description, the present invention is carried out in more detail
It is bright.It should be noted that be expressed " being fixed on " another element when element, it can directly on the other element or
There may be one or more elements placed in the middle therebetween.When an element is expressed " connection " another element, it be can be directly
It is connected to another element in succession or there may be one or more elements placed in the middle therebetween.Term used in this specification
"vertical", "horizontal", "left" and "right", "inner", "outside" and similar statement are for illustrative purposes only.
Unless otherwise defined, technical and scientific term all used in this specification is led with technology of the invention is belonged to
The normally understood meaning of the technical staff in domain is identical.It is specific to be intended merely to description for used term in the description of the invention
Embodiment purpose, be not intended to limitation the present invention.Term "and/or" used in this specification includes one or more
Any and all combinations of relevant listed item.
Referring to Fig. 1, wherein an embodiment provides a kind of unmanned plane 500 to the present invention, the unmanned plane 500 includes: fuselage
100, the horn 200 being connected with the fuselage 100 set on the power device 300 of the horn 200, and is set to the fuselage
100 winged control component 400.Wherein, the horn 200 may be a fixed connection, be integrally formed with the fuselage 100, can also be with
Be it is detachable or by can relative to the fuselage 100 fold in a manner of connect.The power device 300 generally include motor and with
The connected propeller of the motor shaft of motor.The rotation of motor driven propeller is to provide the lift that the unmanned plane 500 flies.One
In a little others embodiments, the unmanned plane 500 is also possible to fixed-wing unmanned plane.
Fig. 2 to Fig. 5 is please referred to, the winged control component 400 includes mounting plate 10, flies control module 20, buckle structure 30.Its
In, the winged control module 20 is installed on the mounting plate 10 by the buckle structure 30.In one embodiment of this invention, institute
Stating mounting plate 10 has towards the winged datum level 11 for controlling module 20.In the present embodiment, datum level 11 is on mounting plate 10
The plane of certain flatness is made it have by processing.It should be noted that the mounting plate 10 can be set on the fuselage
An individual component in 100, is also possible to the part processed in the fuselage 100.
As shown in figure 4, in one embodiment of this invention, the winged control module 20 include fly control module bodies 21 and with
The connected substrate 22 of the winged control module bodies 21.The planar dimension for installing the winged control module bodies 21 of substrate 22 omits
The planar dimension contacted greater than winged control module bodies 21 with substrate 22.It should be noted that the substrate 22 can be individually
Components can also be integrally formed with the winged control module bodies 21.In other possible embodiments, substrate 22 can also be saved
Slightly.
It is equipped with flight control system in the winged control module bodies 21, flight control system (not shown go out) is for stablizing unmanned plane 500
Flight attitude and control that unmanned plane 500 is autonomous or semi-autonomous flight.Flight control system can acquire each sensor of unmanned plane in real time
The Flight Condition Data of measurement receives control instruction and data that controlling terminal is sent, and the control instruction and data is exported
To executing agency's (such as power device 300) to realize to unmanned plane during flying posture or execute the control of task.
As shown in figs 2-4, in one embodiment of this invention, the buckle structure 30 is clamped with 22 phase of substrate.
When omitting substrate 22, buckle structure 30 can also be directly clamped with winged control module bodies 21.
In one embodiment of this invention, the buckle structure 30 includes at least two cards being set on the datum level 11
Button 31, at least two buckle 31 are symmetrically set in the two sides of the winged control module 20.More preferably, in one embodiment of the invention
In, the buckle structure 30 includes that 4 buckles, 31,4 buckles 31 are symmetrical arranged relative to reference line S.That is, two pairs buckle 31 points
It is not set to the two sides of the substrate 22, the two sides uniform force of the substrate 22 can be made, prevents the two sides of the substrate 22
Between any side because of the tilting caused by unbalance stress relative to the datum level 11.Reference line S is that the present invention conveniently retouches
The virtual straight line of excessively described 10 symmetrical centre of mounting plate defined in stating, is parallel to the longer of the mounting plate 10
Side.
As shown in figure 4, in one embodiment of this invention, any one buckle 31 at least two buckle 31 is
Extend including the main part 310 being connected with the datum level 11 and from the main part 310 to the winged bending of control module 20
Clamping part 311.Preferably, the clamping part 311 with the main part 310 generally vertically.
In the present embodiment, the clamping part 311 has the first guiding surface 312.First guiding surface 312 deviates from
The datum level 11 is arranged, and first guiding surface 312 from its one end far from the winged control module 20 towards it close to institute
One end inclination for flying control module 20 is stated, so that resistance is smaller when the winged control module 20 is installed from top to bottom to mounting plate 10,
It installs more smooth.In one embodiment of this invention, position corresponding with the first guiding surface 312 can be on substrate 22
Equipped with the second guiding surface 220, the second guiding surface 220 is identical as the inclined direction of the first guiding surface 312 and angle, can
Further decrease the resistance of installation.
After being engaging in place, the substrate 22 is between the clamping part 311 and the datum level 11, so that described fly
Control module 20 is fixed on mounting plate 10.
In the present embodiment, the buckle 31 is Elastic buckle, can be by having the plastic material of certain elasticity to be made.It can be with
Understand, according to the actual situation, the buckle 31 is simultaneously not only limited to plastic material, can also by other metals, it is nonmetallic or
The composite material that the two combines is made, as long as the buckle 31 has elasticity.
In one embodiment of this invention, buckle 31 can be integrally formed with mounting plate 10.In other possible embodiments
In, buckle 31 can also be fixedly connected with mounting plate 10 by the be bonded, modes such as be spirally connected.Buckle 31 is integrally formed with mounting plate 10
The cost of processing can be reduced.In the present embodiment, the clamping part 311 is integrally formed with the main part 310.It is understood that
, due to integrally formed buckle 31 generally plastic material, dismounted in the winged control module 20 and the mounting plate 10 secondary
In the case that number is excessive, it is easy to cause 31 fatigue fractures of the buckle.Therefore, in other possible embodiments, the clamping part
311 can also be connected by a hinge with the main part 310, although clamping part 311 and main part 310 hingedly can avoid because described in
Fly control module and the mounting plate 10 dismounts excessive 31 fracture of caused buckle, but precision is not as good as integrally formed buckle 31
It is high.
To avoid the gap occurred between clamping part 311 and substrate 22 caused by main part 310 is excessively high, the winged control component
400 further include the elastomeric pad 40 between the winged control module 20 and the mounting plate 10.The elastomeric pad 40 clamps
Between the substrate 22 and the datum level 11.
The elastomeric pad 40 is in compressive state when the winged control module 20 is installed on the mounting plate 10, to give
The winged control module 20 provides an elastic pre-stress, so that the connection flown between control module 20 and mounting plate 10 is stronger.Institute
Stating elastomeric pad 40 can be by having the materials such as plastic cement, the sponge of certain elasticity to be made.The elastomeric pad 40 is in the substrate 22
Compressive state is in when being connected with the mounting plate 10, to provide the pretightning force for deviating from the datum level 11 to the substrate 22,
The substrate 22 is in close contact with the clamping part 311, so that the substrate 22 is along the direction perpendicular to the datum level 11
On it is fixed relative to the mounting plate 10.It is worth noting that by being arranged between the substrate 22 and the datum level 11
The elastomeric pad 40 can be such that the substrate 22 is in close contact with the clamping part 311, keep the substrate 22 opposite to reach
The datum level 11 is fixed, for the other side, it is difficult to ensure that the clamping part 311 and the distance value of the datum level 11 are complete
The thickness value of the substrate 22 is matched, to achieve the purpose that make the relatively described datum level 11 of the substrate 22 fixed, so, pass through
Elastomeric pad 40 is set between the datum level 11 and the substrate 22, the clamping part 311 and the datum level 11 away from
From the thickness value that value only is slightly greater than the substrate 22, difficulty of processing is low.
Buckle structure 30 of the invention can limit fly control module 20 along Z axis to far from the mounting plate 10 direction move,
And the limitation winged control module 20 is around X-axis and around the rotation of Y-axis.Therefore, buckle structure 30, which can limit, flies control module 20
Three degree of freedom.And buckle structure 30 can simplify the installation operation for flying control module 20, realize and fly the tool-free fast of control module 20
Speed installation.
As shown in Fig. 2, in one embodiment of this invention, the winged control component 400 further includes thrust structure 50, first is fixed
Bit architecture 60 and the second location structure 70.Wherein, the thrust structure 50 is described along being parallel to for limiting the substrate 22
The first direction of datum level 11 is mobile (i.e. the negative direction of X-axis in Fig. 2), and the first direction is parallel to the reference line S.
The thrust structure 50, first location structure 60 and second location structure 70 are used for the winged control
Module 20 is positioned, and the winged control module 20 is made to occupy determining position on the mounting plate 10.It is i.e. proposed by the present invention to fly
Component is controlled, it can be achieved that " primary calibration calibration, repeatedly handling maintenance ".Specifically, even across multiple disassembly and installation, this hair
Bright winged control component still can guarantee that position location is constant, keeps certain positioning accuracy, therefore can omit every when later maintenance
Calibration and calibration steps after primary dismounting, simplify the process of later period handling maintenance.
In one embodiment of this invention, the thrust structure 50 includes on the datum level 11 of the mounting plate 10
Limited block 51.The limited block 51 is connected to the substrate 22 of the winged control module 20, and the limited block 51 is located at the substrate 22
Side.In some other embodiments, the surface of the substrate 22 towards the datum level 11 is provided with for collecting post
The container of limited block 51 is stated, the limited block 51 can be contained in the container and be connected to the cell wall of the container.
In one embodiment of this invention, the quantity of the limited block 51 is 2, two interval of limited block 51 settings,
More preferably, two limited blocks 51 are symmetrical relative to the reference line S.In one embodiment of this invention, the limit
Position block 51 has third guiding surface 510.The third guiding surface 510 deviates from the datum level 11, and the third is led
It is tilted to face 510 from its one end far from the winged control module 20 towards one end of its close winged control module 20, so that institute
It states substrate 22 and the mounting plate 10 is more convenient during installation.In some other embodiments, as shown in fig. 6, substrate 22
On in position corresponding with the third guiding surface 510, the 4th guiding surface 221, the 4th guiding surface 221 can also be set
It is identical as the inclined direction of third guiding surface 510 and angle, to further facilitate installation.
The limited block 51 can be by having the material of certain elasticity to be made, in the present embodiment, and the limited block 51 is bullet
Piece, when the limited block 51 is connected to the substrate 22 along the first direction, the limited block 51 is towards far from the substrate
22 side is slightly bent, to provide the thrust towards the second direction, the second direction and first party to the substrate 22
To opposite (positive direction that second direction is X-axis in Fig. 2).It is understood that according to the actual situation, the limited block 51 is not
It is limited to elastic slice, for example, the limited block 51 can also be spring, elastic rubber ball etc., as long as the limited block 51 can limit
The winged control module 20 is made along the movement of first direction.
In the present embodiment, the limited block 51 can be integrally formed with the mounting plate 10.It should be noted that according to reality
Border situation, in some other embodiments, the limited block 51 and the mounting plate 10 can also by it is be bonded, be bolted
Deng.
As shown in figs 2-4, first location structure 60 moves in a second direction for limiting the winged control module 20.
First location structure 60 is located on the reference line S, is located at the winged control with the thrust structure 30
The two sides of module 20.In one embodiment of this invention, first location structure 60 includes the on the substrate 22
One positioning region 61 and the second positioning region 62 on the datum level 11.First positioning region 61 and second positioning region
62 are contacted by line, are moved with limiting the winged control module 20 along the direction for being parallel to the datum level 11, that is, limit described fly
Module 20 X and Y direction along Fig. 2 is controlled to move.
In one embodiment of this invention, first positioning region 61 be the positioning column 610 with arc surface, described second
Positioning region 62 includes the positioning plate 620 on the datum level 11 and the V-shaped groove 621 for being opened in the positioning plate 620, described
The opening of V-shaped groove 621 towards the substrate 22, the arc surface of the positioning column 620 abutted with the cell wall of the V-shaped groove 621 with
Form line contact.
Specifically, the arc surface of the positioning column 620 have central axes O, when the positioning column 620 arc surface with it is described
When the cell wall of V-shaped groove 621 forms line contact, the central axes O is perpendicular to datum level 11.The V-shaped groove 621 has the first cell wall
6210 and second cell wall 6211.First cell wall 6210 and second the cell wall 6211 generally vertically datum level 11, institute
It is in default angle setting, the angular bisector and the base of the default angle that the first cell wall 6210, which is stated, with second cell wall 6211
Directrix S coincides.The cylindrical surface of the positioning column 620 simultaneously with first cell wall 6210,6211 line of the second cell wall
When contact, the central axes O intersects at a point with the reference line S.
The cooperation of V-shaped groove 621 and 620 arc surface of positioning column can be achieved in automatic look for, that is, does not need to precisely align, passes through V
The central axes O of the effect of shape slot 621 and positioning column 620, positioning column 620 is eventually fallen on the angular bisector of V-shaped groove 621, from
And realize quickly positioning.In addition, may be implemented to limit to the line constraint of winged control module 20 and fly control module in conjunction with thrust structure 30
20 two translational degree of freedom, i.e. moving along X and Y direction in Fig. 2.
It should be noted that the V-shaped groove 621 may be implemented the cylindrical surface central axes O and the reference line S phase
It hands over, and the V-shaped groove 621 and the positioning plate 620 can be directly molded on the mounting plate 10, there is no need to carry out machinery
Processing, can be improved the efficiency of mass production.
In some other embodiments, first location structure 60 includes the first positioning set on the substrate 22
Hole is positioned set on the datum level 10 and second location hole corresponding with the first positioning hole position and across described first
The positioning pin in hole and the second location hole, it is preferable that the positioning pin is taper bolt.Taper bolt and first positioning hole and the
Coaxial constraint of the first positioning hole with second location hole may be implemented in the cooperation of two location holes, to limit the winged control module
Relative to the position of unmanned aerial vehicle body, can limit fly control module in Fig. 2 in X direction with the movement in Y-direction.Meanwhile circle
The taper that taper pin has, so that taper bolt has good mechanical self-latching performance, registration is assembled and disassembled also more convenient.
As shown in figure 4, in one embodiment of this invention, second location structure 70 is for limiting described 20 around vertical
In straight line (the i.e. described central axes O) rotation perpendicular to the datum level 11.
Second location structure 70 is located on the reference line S, and second location structure 70 includes being set to the base
The third positioning region of plate 22 and set on the 4th positioning region of the datum level 11.The third positioning region and the 4th positioning region
The substrate 22 is limited around the straight line rotation perpendicular to the datum level 11 by face contact.
In one embodiment of this invention, the third positioning region is the first keyway 71, and the 4th positioning region is flat key
72.The flat key 72 is contained in first keyway 71, and the flat key 72 can be by being connected to first keyway 71
Cell wall, to limit the substrate 22 around the straight line rotation perpendicular to the datum level 11.
First keyway 71 is set to the substrate 22 towards the surface of the datum level 11.Preferably, described first
Keyway 71 is in U-shape, i.e., the opening of described first keyway 71 penetrates through a side of the substrate 22, in order to the flat key 72 receiving
In first keyway 71.
In one embodiment of this invention, first keyway 71 and 72 clearance fit of flat key, therefore the flat key
72 only single sides are abutted with the single cell wall of first keyway 71, to effectively prevent the generation of Planar Mechanisms phenomenon.
For example, the second of the first bearing surface 710 (cell wall of i.e. described first keyway 71) of first keyway 71 and the flat key 72
Bearing surface 720 (side of the i.e. described flat key) abuts.
It is worth noting that there are two effects for the tool of flat key 72.First is that the effect similar to sliding rail guiding can be provided,
So that in assembling process, the substrate 22 can datum level 11 described in rapid alignment, complete positioning.Second is that by reasonable
Tolerance fit designs (clearance fit between the flat key 72 and first keyway 71), effectively prevent the production of Planar Mechanisms phenomenon
It is raw.
In the present embodiment, the 4th positioning region can also include the second keyway 73, and second keyway 73 is set to institute
Datum level 11 is stated towards the surface of the substrate 22.The flat key 72 is set in second keyway 73.In other possible realities
It applies in example, the flat key 72 can also be directly molded on the datum level 11, i.e., the described flat key 72 can also be with the mounting plate
10 are integrally formed.
It in the present embodiment, is reference, the height value and the positioning plate 620 of the limited block 51 with the datum level 11
Height value be all larger than the height value of the flat key so that in the substrate and the mounting plate in assembly, the mounting plate
10 are first positioned with the limited block 51, the positioning plate 620.
For the winged control component 400 in assembly, detailed process is as follows:
Firstly, by the insertion of elastomeric pad 40 by buckle structure 30, thrust structure 50, the first location structure 60 and the second positioning
In the region that structure 70 is enclosed.Need to do basic alignment operation before being packed into winged control module 20, that is, respectively by first
Keyway 71 is directed at flat key 72 and positioning column 620 is directed at V-shaped groove 621, and then pressing downward to winged control module 20 makes its substrate 22
It is contacted with the first guiding surface 312 of the third guiding surface 510 of limited block 51 and/or clamping part 311, to facilitate limited block 51
Thrust is generated to winged control module 20, guarantees that positioning column 620 and V-shaped groove 621 are fitted close.Finally from top to bottom by winged control module 20
In indentation buckle 31, the installation and positioning for flying control module 20 are realized.
Winged control component proposed by the present invention, solve the problems, such as fly control module it is quick accurate positioning and install, it can be achieved that
Tool-free installation simplifies the process of unmanned plane batch Assembling Production, improves the efficiency of mass production.And the present invention proposes
Winged control component, it can be achieved that " primary calibration calibration, repeatedly handling maintenance ".That is, even across multiple disassembly and installation, the present invention
Winged control component still can guarantee position location it is constant, keep certain positioning accuracy, therefore can omit each when later maintenance
Calibration and calibration steps after secondary dismounting simplify the process of later period handling maintenance.Meanwhile the present invention passes through plane restriction, same
Axis constraint and point constraint fly the accurate fixed and positioned of control module to realize, realize to the winged control full freedom degree of module it is complete about
The positioning of beam and degree of precision.With simple to operate, the advantages such as machining cost is low.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；At this
It under the thinking of invention, can also be combined between the technical characteristic in above embodiments or different embodiment, step can be with
It is realized with random order, and there are many other variations of different aspect present invention as described above, for simplicity, they do not have
Have and is provided in details；Although the present invention is described in detail referring to the foregoing embodiments, the ordinary skill people of this field
Member is it is understood that it is still possible to modify the technical solutions described in the foregoing embodiments, or to part of skill
Art feature is equivalently replaced；And these are modified or replaceed, each reality of the present invention that it does not separate the essence of the corresponding technical solution
Apply the range of a technical solution.
Claims (28)
1. one kind flies control component, which is characterized in that including flying control module and set on the mounting plate of the unmanned plane, the winged control mould
Block is installed on the mounting plate by buckle structure.
2. winged control component according to claim 1, which is characterized in that the buckle structure includes at least two set on described
Buckle on mounting plate, at least two buckle are clamped with the winged control module respectively, and at least two buckles difference
The two sides of the winged control module are set.
3. winged control component according to claim 2, which is characterized in that any one buckle at least two buckle
The clamping part for including the main part being connected with the mounting plate and extending from the main part to the winged control module bending.
4. winged control component according to claim 3, which is characterized in that the clamping part and the main part are generally vertically.
5. winged control component according to claim 3 or 4, which is characterized in that the clamping part and main part one at
Type.
6. the winged control component according to any one of claim 3-5, which is characterized in that the clamping part has the first guiding
Inclined-plane, first guiding surface are tilted to the mounting plate.
7. winged control component according to claim 6, which is characterized in that the winged control module is equipped with and first guiding
Second guiding surface of inclined-plane cooperation.
8. the winged control component according to any one of claim 2-7, which is characterized in that the buckle is Elastic buckle.
9. winged control component according to claim 1 to 8, which is characterized in that the winged control component further includes being set to
Elastomeric pad between the winged control module and the mounting plate, the elastomeric pad is in the winged control module and the mounting plate
Compressive state is in when being connected.
10. winged control component according to claim 1 to 9, which is characterized in that the winged control component further includes stopping
Selection structure, the thrust structure are used to limit the winged control module and move along the first direction for being parallel to the mounting plate.
11. winged control component according to claim 10, which is characterized in that the thrust structure includes being set to the mounting plate
On limited block, the limited block be set to it is described it is winged control module side.
12. winged control component according to claim 11, which is characterized in that the limited block, which has to the mounting plate, to be tilted
Third guiding surface.
13. winged control component according to claim 12, which is characterized in that the winged control module is equipped with and leads with the third
The 4th guiding surface cooperated to inclined-plane.
14. winged control component described in any one of 1-13 according to claim 1, which is characterized in that the quantity of the limited block is
2, two limit block gap settings.
15. winged control component described in any one of 0-14 according to claim 1, which is characterized in that the winged control component further includes
First location structure, first location structure are used to limit the winged control module along the second direction for being parallel to the mounting plate
Mobile, the second direction is opposite to the first direction.
16. winged control component according to claim 15, which is characterized in that first location structure includes being set to described fly
The first positioning region in module and the second positioning region on the mounting plate are controlled, first positioning region and described second are determined
Position portion is contacted by line, is moved with limiting the winged control module along the direction for being parallel to the mounting plate.
17. winged control component according to claim 16, which is characterized in that first positioning region is to determine with arc surface
Position column, second positioning region include the positioning plate on the mounting plate and the V-shaped groove for being opened in the positioning plate, described
The opening of V-shaped groove is abutted with the cell wall of the V-shaped groove towards the winged control module, the arc surface of the positioning column to form line and connect
Touching.
18. winged control component according to claim 17, which is characterized in that the winged control module includes substrate, the positioning
Column is set to the substrate.
19. winged control component according to claim 15, which is characterized in that the winged control module further includes substrate, and described
One location structure include set on the substrate first positioning hole, be set to the mounting plate and with the first positioning hole position pair
The second location hole answered and the positioning pin across the first positioning hole and the second location hole.
20. winged control component according to claim 19, which is characterized in that the positioning pin is taper bolt.
21. winged control component described in any one of 5-20 according to claim 1, which is characterized in that the winged control component further includes
Second location structure, second location structure are used to limit the winged control module and turn around the straight line perpendicular to the mounting plate
It is dynamic.
22. winged control component according to claim 21, which is characterized in that second location structure includes being set to described fly
Control the third positioning region of module and the 4th positioning region set on the mounting plate, the third positioning region and the 4th positioning region
The winged control module is limited around the straight line rotation perpendicular to the mounting plate by face contact.
23. winged control component according to claim 22, which is characterized in that the third positioning region is the first keyway, described
4th positioning region is flat key.
24. winged control component according to claim 23, which is characterized in that first keyway is matched with the flat key gap
It closes.
25. the winged control component according to claim 23 or 24, which is characterized in that first keyway is in U-shape.
26. the winged control component according to any one of claim 23-25, which is characterized in that also wrap the 4th positioning region
The second keyway is included, the flat key is set in second keyway.
27. the winged control component according to any one of claim 21-26, which is characterized in that first location structure and
Second location structure is located on the same line.
28. a kind of unmanned plane, including fuselage, the horn being connected with the fuselage, set on the power device of the horn, feature
It is, the unmanned plane further includes the winged control component as described in any one of claim 1-27.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811180095.4A CN109094798A (en) | 2018-10-10 | 2018-10-10 | A kind of unmanned plane and its winged control component |
| PCT/CN2019/104238 WO2020073755A1 (en) | 2018-10-10 | 2019-09-03 | Unmanned aerial vehicle and flight control component thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811180095.4A CN109094798A (en) | 2018-10-10 | 2018-10-10 | A kind of unmanned plane and its winged control component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109094798A true CN109094798A (en) | 2018-12-28 |
Family
ID=64868391
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811180095.4A Pending CN109094798A (en) | 2018-10-10 | 2018-10-10 | A kind of unmanned plane and its winged control component |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN109094798A (en) |
| WO (1) | WO2020073755A1 (en) |
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| WO2020073755A1 (en) * | 2018-10-10 | 2020-04-16 | 深圳市道通智能航空技术有限公司 | Unmanned aerial vehicle and flight control component thereof |
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| WO2020073755A1 (en) | 2020-04-16 |
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