CN110254690A - A kind of balanced compensated wing head of unmanned plane and its balanced compensated method - Google Patents
A kind of balanced compensated wing head of unmanned plane and its balanced compensated method Download PDFInfo
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- CN110254690A CN110254690A CN201910593040.4A CN201910593040A CN110254690A CN 110254690 A CN110254690 A CN 110254690A CN 201910593040 A CN201910593040 A CN 201910593040A CN 110254690 A CN110254690 A CN 110254690A
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- wing
- unmanned plane
- universal joint
- firm
- rotation
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of balanced compensated wing head of unmanned plane and its balanced compensated methods, the balanced compensated wing head of the unmanned plane includes: a kind of balanced compensated wing head of unmanned plane, it is characterized in that, it include: shaft, the compensation disk that the shaft bottom end is set, the balance bridge on the shaft top, and the first wing frame, the second wing frame, third wing frame and the 4th wing frame that are axially arranged along the shaft are set；The first wing frame, the second wing frame, third wing frame and the 4th wing frame are four groups of same units being axially arranged, and support component is equipped between every two groups of same units.The present invention designs four groups of identical wing framves, it is attached between every two groups of wing framves by support component, so that after unmanned plane wing stops operating, due to being attached by support component between every two groups of wing framves, so that there is a support degree, so that wing will not be perpendicular with horizontal plane after stopping operating between every group of wing frame.
Description
Technical field
The present invention relates to a kind of compensation wing head, the balanced compensated wing head of specifically a kind of unmanned plane is related to intelligence manufacture neck
Domain.
Background technique
The outstanding feature of unmanned plane is can to do low latitude (from the ground several meters), low speed (since hovering) and heading not
The maneuvering flight of change, especially can be in the VTOL of small area place.Since these features make it have wide purposes and hair
Exhibition prospect.Military aspect is widely used to air-to-ground attack, machine drop is logged in, weapon transport, logistics support, rescue of battlefield, detectd
Examine patrol, command and control, liaison, antisubmarine clearance, electronic countermeasure etc..
And the mostly important component of unmanned plane is compensation wing head, the wing head of unmanned plane is mainly used to carry out to unmanned plane wing
Rotational angle compensate so that the inclination angle of two groups of opposite unmanned plane wings is identical, and then reduces unmanned plane and planted on flight way
Jitter phenomenon.
And the balanced compensated wing head of existing unmanned plane, when wing during rotation, the resistance of wing wind-engaging changes, machine
The wing is changed inclination angle, and then balanced compensated wing head is driven to be balanced, compensate automatically, and existing balanced compensated wing head is in nothing
After man-machine landing, due to there is no design support component, so that wing is easy to be perpendicular with horizontal plane after stopping operating, and machine
When being again started up unmanned plane after the wing and horizontal plane, due to wing and horizontal plane, wing is suffered during rotation
Air drag will increase, and then be easy so that jitter phenomenon occurs when taking off for unmanned plane.
Summary of the invention
Goal of the invention: a kind of balanced compensated wing head of unmanned plane and its balanced compensated method are provided, to solve the prior art
The existing above problem.
A kind of technical solution: the balanced compensated wing head of unmanned plane, comprising:
Shaft, the compensation disk that the shaft bottom end is arranged in, are arranged in the balance bridge on the shaft top, and along described turn
The first wing frame, the second wing frame, third wing frame and the 4th wing frame that axis is axially arranged；
The first wing frame, the second wing frame, third wing frame and the 4th wing frame are four groups of same units being axially arranged,
And support component is equipped between every two groups of same units.
In a further embodiment, the same unit includes the rotating device being fixedly connected with the shaft, and
The wing fastener of rotating device described in grafting.
In a further embodiment, the wing fastener includes the connecting shaft being fixedly connected with the rotating device, if
Set the wing seam in the connecting shaft end, the rotating connector being fixedly connected with the shaft, and with the rotation
The rotation connection bar of connector connection；The both ends of the rotation connection bar are respectively equipped with the second rotation universal joint and the first rotation ten thousand
Xiang Jie, the rotating connector are connect with the second rotation universal joint, and the second rotation universal joint is socketed universal joint bolt,
The second rotation universal joint passes through universal joint bolt and the rotating connector grafting and is equipped with scheduled movable amplitude；It is described
It is provided with fixed jack on wing seam, it is scheduled reserved mainly for component has in active procedure to design cating nipple
Movable amplitude, if will be unable to carry out activity between component, and then can not carry out to wing using the mode being fixedly connected
It is balanced compensated.
In a further embodiment, the support component includes being arranged in wing seam far from rotating connector side
Firm seam, the firm bar connecting with the firm seam is bonded part, Yi Jiyu with what the firm bar was connect
The firm disk for being bonded part and being fixedly connected；The both ends of the firm bar are respectively equipped with the second firm universal joint and first surely
Gu universal joint, the second firm universal joint and the firm seam carry out grafting and the second firm universal joint is consolidated with described
Scheduled event amplitude is equipped between seam, the first firm universal joint and described be bonded between part are equipped with scheduled event
Amplitude；The firm disk is connect with the rotating device in adjacent wing frame, and design support component to stop in unmanned plane wing
After rotation, due to being attached by support component between every two groups of wing framves, so that having a support between every group of wing frame
Dynamics, so that wing will not be perpendicular with horizontal plane after stopping operating, and then shake occurs when taking off for unmanned plane now
As, and then increase the stability that unmanned plane takes off.
In a further embodiment, the rotating device includes rotating cylinder, with what the rotating cylinder was spirally connected is connected cylinder, and described
The rotary spacing mouth that is fixedly connected of linking cylinder, and penetrate the rotary spacing mouth and with the rack for being connected cylinder and being fixedly connected
Fixed cylinder.
In a further embodiment, the side of the rack fixed cylinder is provided with wing socket, and the wing socket is square
Shape；The two sides of the wing socket are equipped with wing keeper, are provided with two groups of threaded holes inside the wing keeper, and described two
Group threaded hole is respectively the first threaded hole and the second threaded hole；First threaded hole and the second threaded hole be socketed the first bolt with
Second bolt.
In a further embodiment, the rack fixed cylinder is fixedly installed with the rotary spacing mouth opposite side
It is rotatablely connected frame；The rack fixed cylinder is bonded mouth being provided with the wing socket opposite side.
In a further embodiment, the first rotation universal joint is socketed Fixed latches, and the Fixed latches penetrate institute
It states the first rotation universal joint to connect with the compensation disk, predetermined live is equipped between the first rotation universal joint and the compensation disk
Dynamic amplitude.
A kind of balanced compensated method of the balanced compensated wing head of unmanned plane, comprising:
S1: when unmanned plane takes off, by the rotation of shaft, so that effect of the wing by centrifugal force；
S2: wing will be unfolded by the effect of centrifugal force at this time；
S3: it since the angle of the expansion of each wing is different after wing expansion, needs to be balanced compensation at this time；
S4: the angle at this time by wing expansion is different, and then rotation connection bar is driven to be risen, when rotation connection bar rises
Afterwards, connecting rod will drive the one side of compensation disk to be tilted upwards along shaft, and the other one side for compensating disk at this time will dip down
Tiltedly, it is driving rotation connection rod piece to move downward from compensation disk to the one side tilted down at this time, and then is driving rotating connector
It moves downward, and then connecting shaft is driven to be rotated, and then drive and rotated with the cylinder that is connected that connecting shaft is fixedly connected, in turn
So that linking cylinder is rotated along sleeve, and then the wing of other side is driven to be changed inclination angle, so that side wing
And other side wing is identical as the angle of horizontal plane；
S5: and when being rotatablely connected bar and being declined, connecting rod will drive the one side of compensation disk to tilt down along shaft, and this
When compensation disk other one side will tilt upwards, to be rotatablely connected rod piece upward being driven by the acclivitous one side of compensation disk at this time
Movement, and then drive rotating connector to move upwards, and then rotating connector is driven to move downward, and then connecting shaft is driven to carry out
Rotation, and then drive and rotated with the cylinder that is connected that connecting shaft is fixedly connected, so that linking cylinder is rotated along sleeve, into
And the wing of other side is driven to be changed inclination angle, so that the angle of side wing and other side wing and horizontal plane
It is identical；
S6: when the wing angle with horizontal plane when two sides is identical, the wing on front and back two sides is also influenced by compensation disk simultaneously at this time,
And then it is identical as the angle of horizontal plane also to will form front and back two sides wing；
S7: and after unmanned plane lands stopping flight, it is attached between every group of wing frame by support component, and then will not go out
Wing on existing wing frame occurs forming vertical phenomenon with horizontal plane, and then completes work.
The utility model has the advantages that designing four groups of identical wing framves, and every the invention discloses a kind of balanced compensated wing head of unmanned plane
It is attached between two groups of wing framves by support component, and the both ends of support component are designed as universal structure and make, so that at nobody
After machine wing stops operating, due to being attached by support component between every two groups of wing framves, so that having between every group of wing frame
There is a support degree, so that wing will not be perpendicular with horizontal plane after stopping operating, and then unmanned plane is when taking off
Jitter phenomenon occurs.
Detailed description of the invention
Fig. 1 is structural schematic diagram of the invention.
Fig. 2 is the first wing frame schematic enlarged-scale view of the invention.
Fig. 3 is rotating device structural schematic diagram of the invention.
Fig. 4 is linking cylinder diagrammatic cross-section of the invention.
Fig. 5 is rotating cylinder diagrammatic cross-section of the invention.
Appended drawing reference are as follows: be bonded mouth 1, rotating cylinder 2, rotation screw thread 201, rotary spacing mouth 3, rack fixed cylinder 4, wing
Socket 5, the first threaded hole 501, the second threaded hole 502, wing keeper 6, linking screw thread 7, linking cylinder 8, rotation connection frame 9,
Compensation disk 10, the first wing frame 12, firm disk 1201, is bonded part 1202, is the first firm universal joint 1203, steady shaft 11
Solid rod 1204, firm seam 1206, wing seam 1207, fixed jack 1208, is fixed and is inserted second firm universal joint 1205
Pin 1209, first rotates universal joint 1210, rotation connection bar 1211, rotating connector 1212, second and rotates universal joint 1213, the
Two wing framves 13, third wing frame 14, the 4th wing frame 15, balance bridge 16, rotating device 17.
Specific embodiment
In the following description, a large amount of concrete details are given so as to provide a more thorough understanding of the present invention.So
And it is obvious to the skilled person that the present invention may not need one or more of these details and be able to
Implement.In other examples, in order to avoid confusion with the present invention, for some technical characteristics well known in the art not into
Row description.
By researching and analysing for applicant, the reason of this problem (jitter phenomenon occurs when taking off for unmanned plane) occur exists
In, at present unmanned plane in flight, when wing during rotation, the resistance of wing wind-engaging changes, and wing is changed inclination angle,
And then drive balanced compensated wing head to be balanced, compensate automatically, and existing balanced compensated wing head unmanned plane land after, by
In no design support component, so that wing is easy to be perpendicular with horizontal plane after stopping operating, and wing and horizontal plane
After when being again started up unmanned plane, due to wing and horizontal plane, suffered air drag will increase wing during rotation,
And then be easy so that jitter phenomenon occurs when taking off for unmanned plane, and the present invention between every two groups of wing framves by support component into
Row connection, and the both ends of support component are designed as universal structure and make, so that after unmanned plane wing stops operating, due to every two groups
It is attached by support component between wing frame, so that there is a support degree, so that wing between every group of wing frame
Will not be perpendicular with horizontal plane after stopping operating, and then jitter phenomenon occurs when taking off for unmanned plane.
The balanced compensated wing head of a kind of unmanned plane, comprising: be bonded mouth 1, rotating cylinder 2, rotation screw thread 201, rotary spacing
Mouthfuls 3, rack fixed cylinder 4, wing socket 5, the first threaded hole 501, the second threaded hole 502, wing keeper 6, linking screw thread 7,
Linking cylinder 8, compensation disk 10, shaft 11, the first wing frame 12, firm disk 1201, is bonded part 1202, the at rotation connection frame 9
One firm universal joint 1203, firm bar 1204, the second firm universal joint 1205, firm seam 1206, wing seam 1207,
Fixed jack 1208, Fixed latches 1209, first rotate universal joint 1210, rotation connection bar 1211, rotating connector 1212, the
Two rotation universal joints 1213, the second wing frame 13, third wing frame 14, the 4th wing frame 15, balance bridge 16, rotating device
17。
Wherein, the shaft 11 is flexibly connected with the compensation disk 10, and the top of the shaft 11 is equipped with balance bridge 16,
The axial direction of the shaft 11 is equipped with four groups of wing framves, is respectively as follows: the first wing frame 12, the second wing frame 13, third wing frame
14 and the 4th wing frame 15, the first wing frame 12, the second wing frame 13, third wing frame 14 and the 4th wing frame 15 are
Four groups of same units being axially arranged, and support component is equipped between every group of wing frame, every group of wing frame includes and institute
State the wing fastener of rotating device 17 described in the rotating device 17 and grafting that shaft 11 is fixedly connected.
The support component includes that the support component includes being arranged in wing seam 1207 far from rotating connector
The firm seam 1206 of 1212 sides, the firm bar 1204 being connect with the firm seam 1206, with the firm bar
1204 connections are bonded part 1202, and with the firm disk 1201 for being bonded part 1202 and being fixedly connected；It is described steady
The both ends of solid rod 1204 are respectively equipped with the second firm universal joint 1205 and the first firm universal joint 1203, described second consolidate it is universal
Section 1205 and the firm seam 1206 carry out grafting and the second firm universal joint 1205 and the firm seam 1206 it
Between be equipped with scheduled event amplitude, the first firm universal joint 1203 and it is described be bonded between part 1202 be equipped with scheduled event
Amplitude；The firm disk 1201 is connect with the rotating device 17 in adjacent wing frame, and design support component makes in unmanned plane machine
After the wing stops operating, due to being attached by support component between every two groups of wing framves, so that having one between every group of wing frame
A support degree, so that wing will not be perpendicular with horizontal plane after stopping operating, and then unmanned plane is when taking off
Jitter phenomenon, and then increase the stability that unmanned plane takes off.
The wing fastener includes the connecting shaft being fixedly connected with the rotating device 17, is arranged in the connecting shaft end
Wing seam 1207, the rotating connector 1212 being fixedly connected with the shaft 11, and with the rotating connector
The rotation connection bar 1211 of 1212 connections；The both ends of the rotation connection bar 1211 are respectively equipped with 1213 He of the second rotation universal joint
First rotation universal joint 1210, the rotating connector 1212 are connect with the second rotation universal joint 1213, and described second turn
Dynamic universal joint 1213 is socketed universal joint bolt, and the second rotation universal joint 1213 passes through universal joint bolt and the rotation connection
1212 grafting of part and be equipped with scheduled movable amplitude；It is provided with fixed jack 1208 on the wing seam 1207, designs universal
Mechanism is saved mainly for component has scheduled reserved movable amplitude in active procedure, if using the mode being fixedly connected,
It will be unable to carry out activity between component, and then can not carry out to the balanced compensated of wing, the balanced compensated course of work is, when
After the inclination angle of wing changes, wing will drive rotating connector 1212 to rotate, and then drive rotation connection bar 1211
Elevating movement is carried out, and then compensation disk 10 is driven to be tilted or tilted down upwards, and compensates inclining on one side for disk 10
Tiltedly, in addition three faces also will be influenced to tilt by inclined surface, and then the wing frame in other three face is driven incline to wing
Angle is changed, and then carries out the compensation to wing angle.
The rotating device 17 is connected cylinder 8 including rotating cylinder 2, with what the rotating cylinder 2 was spirally connected, is connected the fixed company of cylinder 8 with described
The rotary spacing mouth 3 connect, and penetrate the rotary spacing mouth 3 and with the rack fixed cylinder 4 for being connected cylinder 8 and being fixedly connected,
The rotation screw thread 201 of pre- fixing turn is provided with inside the rotating cylinder 2, linking screw thread 7 is convex screw thread, and the rotation screw thread 201 is
Concavity screw thread, the linking screw thread 7 are adapted to rotation screw thread 201.
The side of the rack fixed cylinder 4 is provided with wing socket 5, and the wing socket 5 is rectangular-shaped；The wing socket
5 two sides are equipped with wing keeper 6, are provided with two groups of threaded holes inside the wing keeper 6, two groups of threaded holes are respectively
First threaded hole 501 and the second threaded hole 502；First threaded hole 501 and the second threaded hole 502 are socketed the first bolt and the
Two bolts.
The rack fixed cylinder 4 is being fixedly installed with rotation connection frame 9 with 3 opposite side of rotary spacing mouth；It is described
Rack fixed cylinder 4 is bonded mouth 1 being provided with 5 opposite side of wing socket.
The first rotation universal joint 1210 is sleeved and fixed bolt 1209, and the Fixed latches 1209 penetrate described first turn
Dynamic universal joint 1210 is connect with the compensation disk 10, is equipped between the first rotation universal joint 1210 and the compensation disk 10 pre-
Determine movable amplitude.
Working principle illustrates: since the angle of the expansion of each wing is different after wing expansion, needing to carry out at this time flat
Weighing apparatus compensation, the angle by wing expansion is different at this time, and then rotation connection bar 1211 is driven to be risen, when rotation connection bar
After 1211 rise, connecting rod will drive the one side of compensation disk 10 to be tilted upwards along shaft 11, and compensate the another of disk 10 at this time
Outer one side will tilt down, and drive 1211, rotation connection bar fortune downwards from compensation disk 10 to the one side tilted down at this time
It is dynamic, and then drive rotating connector 1212 to move downward, and then connecting shaft is driven to be rotated, and then drive and fix with connecting shaft
The linking cylinder 8 of connection is rotated so that linking cylinder 8 rotated along sleeve, and then drive other side wing into
Row changes inclination angle, so that side wing and other side wing are identical as the angle of horizontal plane, and when rotation connection bar
1211 when being declined, and connecting rod will drive the one side of compensation disk 10 to tilt down along shaft 11, and compensate disk 10 at this time
Other one side will tilt upwards, 1211, bar of rotation connection fortune upwards is being driven by the acclivitous one side of compensation disk 10 at this time
It is dynamic, and then drive rotating connector 1212 to move upwards, and then rotating connector 1212 is driven to move downward, and then drive connection
Axis is rotated, so drive rotated with the cylinder 8 that is connected that connecting shaft is fixedly connected so that be connected cylinder 8 along sleeve into
Row rotation, and then the wing of other side is driven to be changed inclination angle, so that side wing and other side wing and water
The angle of plane is identical, when the wing of two sides change inclination angle angle with horizontal plane is identical, and then also will form front and back two sides machine
The wing on the wing two sides of front and back at this time identical as the angle of horizontal plane is also influenced by compensation disk 10 simultaneously, and then also will form front and back
The wing situation identical as the angle of horizontal plane in two sides constructs identical herein not superfluous because four groups of wing framves are same unit
The course of work of other two groups of wing framves is stated, and after unmanned plane lands stopping flight, pass through support group between every group of wing frame
Part is attached, and then is not in that wing on wing frame occurs forming vertical phenomenon, and the two of support component with horizontal plane
End is designed as gimbal structure, and then support component has scheduled movable amplitude, and then is not in locked or scope of activities
The case where not doing completes work in turn.The present invention designs four groups of identical wing framves, and passes through support component between every two groups of wing framves
It is attached, and the both ends of support component are designed as universal structure and make, so that after unmanned plane wing stops operating, due to every two
It is attached by support component between group wing frame, so that there is a support degree, so that machine between every group of wing frame
The wing will not be perpendicular with horizontal plane after stopping operating, and then jitter phenomenon occurs when taking off for unmanned plane.
In the description of the present invention, it should be noted that term " center ", "upper", "lower", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "inner", "outside" be based on the orientation or positional relationship shown in the drawings, merely to
Convenient for description the present invention and simplify description, rather than the device or element of indication or suggestion meaning must have a particular orientation,
It is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.In addition, term " first ", " second ",
" third " is used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance.
It is described the prefered embodiments of the present invention in detail above in conjunction with attached drawing, still, the present invention is not limited to above-mentioned realities
The detail in mode is applied, within the scope of the technical concept of the present invention, technical solution of the present invention can be carried out a variety of etc.
With transformation, these equivalents are all belonged to the scope of protection of the present invention.
Claims (9)
1. a kind of balanced compensated wing head of unmanned plane, characterized in that include:
Shaft, the compensation disk that the shaft bottom end is arranged in, are arranged in the balance bridge on the shaft top, and along described turn
The first wing frame, the second wing frame, third wing frame and the 4th wing frame that axis is axially arranged；
The first wing frame, the second wing frame, third wing frame and the 4th wing frame are four groups of same units being axially arranged,
And support component is equipped between every two groups of same units.
2. a kind of balanced compensated wing head of unmanned plane according to claim 1, it is characterized in that: the same unit include with
The wing fastener of rotating device described in rotating device that the shaft is fixedly connected and grafting.
3. a kind of balanced compensated wing head of unmanned plane according to claim 2, it is characterized in that: the wing fastener include with
The connecting shaft that the rotating device is fixedly connected is arranged in the wing seam of the connecting shaft end, fixes with the shaft
The rotating connector of connection, and the rotation connection bar being connect with the rotating connector；The both ends point of the rotation connection bar
Not She You second rotation universal joint and first rotation universal joint, the rotating connector with it is described second rotate universal joint connect,
The second rotation universal joint is socketed universal joint bolt, and the second rotation universal joint is connected by universal joint bolt and the rotation
Fitting grafting and be equipped with scheduled movable amplitude；Fixed jack is provided on the wing seam.
4. the balanced compensated wing head of a kind of unmanned plane according to claim 1, it is characterized in that: the support component includes setting
The firm seam in wing seam far from rotating connector side is set, the firm bar being connect with the firm seam, with
The firm bar connection is bonded part, and with the firm disk for being bonded part and being fixedly connected；The firm bar
Both ends are respectively equipped with the second firm universal joint and the first firm universal joint, the second firm universal joint and the firm seam
Carry out grafting and between the second firm universal joint and the firm seam be equipped with scheduled event amplitude, described first consolidate it is universal
Section and it is described be bonded between part be equipped with scheduled event amplitude；Rotating device in the firm disk and adjacent wing frame connects
It connects.
5. the balanced compensated wing head of a kind of unmanned plane according to claim 4, it is characterized in that: the rotating device includes turning
Cylinder with what the rotating cylinder was spirally connected is connected cylinder, and the rotary spacing mouth for being connected cylinder and being fixedly connected, and penetrates the rotation and limit
Position mouth and with the rack fixed cylinder for being connected cylinder and being fixedly connected.
6. the balanced compensated wing head of a kind of unmanned plane according to claim 5, it is characterized in that: the side of the rack fixed cylinder
Portion is provided with wing socket, and the wing socket is rectangular-shaped；The two sides of the wing socket are equipped with wing keeper, the wing
Two groups of threaded holes are provided with inside keeper, two groups of threaded holes are respectively the first threaded hole and the second threaded hole；Described first
Threaded hole and the second threaded hole are socketed the first bolt and the second bolt.
7. a kind of balanced compensated wing head of unmanned plane according to claim 5, it is characterized in that: the rack fixed cylinder with
The rotary spacing mouth opposite side is fixedly installed with rotation connection frame；The rack fixed cylinder is opposite with the wing socket
Side, which is provided with, is bonded mouth.
8. the balanced compensated wing head of a kind of unmanned plane according to claim 3, it is characterized in that: the first rotation universal joint
It is sleeved and fixed bolt, the Fixed latches penetrate the first rotation universal joint and connect with the compensation disk, first rotation
Scheduled event amplitude is equipped between universal joint and the compensation disk.
9. a kind of balanced compensated method of the balanced compensated wing head of unmanned plane, characterized in that include:
S1: when unmanned plane takes off, by the rotation of shaft, so that effect of the wing by centrifugal force；
S2: wing will be unfolded by the effect of centrifugal force at this time；
S3: it since the angle of the expansion of each wing is different after wing expansion, needs to be balanced compensation at this time；
S4: the angle at this time by wing expansion is different, and then rotation connection bar is driven to be risen, when rotation connection bar rises
Afterwards, connecting rod will drive the one side of compensation disk to be tilted upwards along shaft, and the other one side for compensating disk at this time will dip down
Tiltedly, it is driving rotation connection rod piece to move downward from compensation disk to the one side tilted down at this time, and then is driving rotating connector
It moves downward, and then connecting shaft is driven to be rotated, and then drive and rotated with the cylinder that is connected that connecting shaft is fixedly connected, in turn
So that linking cylinder is rotated along sleeve, and then the wing of other side is driven to be changed inclination angle, so that side wing
And other side wing is identical as the angle of horizontal plane；
S5: and when being rotatablely connected bar and being declined, connecting rod will drive the one side of compensation disk to tilt down along shaft, and this
When compensation disk other one side will tilt upwards, to be rotatablely connected rod piece upward being driven by the acclivitous one side of compensation disk at this time
Movement, and then drive rotating connector to move upwards, and then rotating connector is driven to move downward, and then connecting shaft is driven to carry out
Rotation, and then drive and rotated with the cylinder that is connected that connecting shaft is fixedly connected, so that linking cylinder is rotated along sleeve, into
And the wing of other side is driven to be changed inclination angle, so that the angle of side wing and other side wing and horizontal plane
It is identical；
S6: when the wing angle with horizontal plane when two sides is identical, the wing on front and back two sides is also influenced by compensation disk simultaneously at this time,
And then it is identical as the angle of horizontal plane also to will form front and back two sides wing；
S7: and after unmanned plane lands stopping flight, it is attached between every group of wing frame by support component, and then will not go out
Wing on existing wing frame occurs forming vertical phenomenon with horizontal plane, and then completes work.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910593040.4A CN110254690A (en) | 2019-07-03 | 2019-07-03 | A kind of balanced compensated wing head of unmanned plane and its balanced compensated method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910593040.4A CN110254690A (en) | 2019-07-03 | 2019-07-03 | A kind of balanced compensated wing head of unmanned plane and its balanced compensated method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110254690A true CN110254690A (en) | 2019-09-20 |
Family
ID=67924045
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910593040.4A Pending CN110254690A (en) | 2019-07-03 | 2019-07-03 | A kind of balanced compensated wing head of unmanned plane and its balanced compensated method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111405783A (en) * | 2020-04-14 | 2020-07-10 | 南京安立特电子科技有限公司 | Be applied to unmanned aerial vehicle's remote controller casing |
| CN112678195A (en) * | 2020-12-31 | 2021-04-20 | 王小燕 | Unmanned aerial vehicle |
-
2019
- 2019-07-03 CN CN201910593040.4A patent/CN110254690A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111405783A (en) * | 2020-04-14 | 2020-07-10 | 南京安立特电子科技有限公司 | Be applied to unmanned aerial vehicle's remote controller casing |
| CN112678195A (en) * | 2020-12-31 | 2021-04-20 | 王小燕 | Unmanned aerial vehicle |
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