CN109131835A - A kind of adjustable wing structure of fixed-wing unmanned plane - Google Patents
A kind of adjustable wing structure of fixed-wing unmanned plane Download PDFInfo
- Publication number
- CN109131835A CN109131835A CN201811046124.8A CN201811046124A CN109131835A CN 109131835 A CN109131835 A CN 109131835A CN 201811046124 A CN201811046124 A CN 201811046124A CN 109131835 A CN109131835 A CN 109131835A
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- China
- Prior art keywords
- wing
- face
- bearing base
- telescopic rod
- unmanned plane
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/10—Wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of adjustable wing structures of fixed-wing unmanned plane, including bearing base, wing-body, turntable mechanism, flexible shroud, strengthen telescopic rod, angular transducer, wind pressure sensor and control circuit, bearing base rear end is connect with unmanned plane body outer surface, front end face is hinged by turntable mechanism and reinforcing telescopic rod with wing-body rear end face, wing-body rear end face sets locating slot, locating slot is respectively coated by bearing base, on the outside of turntable mechanism and reinforcing telescopic rod, flexible shroud is coated on outside bearing base, angular transducer is mounted on turntable mechanism and strengthens on telescopic rod, wind pressure sensor is evenly arranged on front end face and the lower end surface of wing-body along wing-body axis.One aspect of the present invention installing and dismounting is easy, and bearing capacity is good, and positioning accuracy is high, and wing configurations structure is on the other hand adjusted flexibly according to the usage requirement, and to meet the needs of different flight operations, and adjustment Operation control precision and operation automation precision are high.
Description
Technical field
The present invention relates to a kind of wing structures, are exactly a kind of adjustable wing structure of fixed-wing unmanned plane.
Background technique
Fixed-wing unmanned plane is a kind of important housing construction in current unmanned machine equipment, and usage amount is huge, currently right
Fixed-wing unmanned plane finds during being produced, used and transported etc., the traditional machine being all made of due to fixed-wing unmanned plane
The wing connect connection with fuselage, often efficient and convenient can not carry out disassembly and assembly with fuselage so as to cause wing, and flying
In the process, the distributed architecture of wing can not be adjusted flexibly effectively according to the needs of use, is flying so as to cause fixed-wing unmanned plane
Often state of flight is single during row, is unable to the needs for meeting a variety of different flight operations of efficient, flexible.Therefore it is directed to this
One status, there is an urgent need to develop a kind of completely new fixed-wing unmanned plane wing structures, to meet the needs of actual use.
Summary of the invention
In view of the shortcomings of the prior art, the present invention provides a kind of fixed-wing unmanned plane adjustable wing structure, it should
New invention structure is simple, flexible and convenient to use, and versatility is good, and one side installing and dismounting is easy, and bearing capacity is good, positioning accuracy
On the other hand wing configurations structure is adjusted flexibly in height according to the usage requirement, to meet the needs of different flight operations, and adjust
Operation control precision and operation automation precision are high, improve fixed-wing unmanned plane using flexible and convenient so as to effectively reach
Property.
To achieve the goals above, the present invention is to realize by the following technical solutions:
A kind of adjustable wing structure of fixed-wing unmanned plane, including bearing base, wing-body, turntable mechanism, flexible shield
Set strengthens telescopic rod, angular transducer, wind pressure sensor and control circuit, bearing base rear end and unmanned plane body outer surface
Connection, front end face are hinged by turntable mechanism and reinforcing telescopic rod with wing-body rear end face, wing-body axis with hold
Carrying pedestal front end face is in 0 ° -90 ° angles, and wherein turntable mechanism is coaxially distributed with bearing base front end face, strengthens telescopic rod at least
It is three, uniformly distributed around turntable mechanism axis, strengthen flexible rod axis and wing-body axis is in 0 ° -90 ° angles, wing-body
Rear end face sets locating slot, and locating slot is respectively coated by bearing base, turntable mechanism and strengthens on the outside of telescopic rod, and outside bearing base
Side is connected with each other with wing-body rear end face by flexible shroud rear end face, flexible shroud be coated on bearing base it is outer and with hold
It carries pedestal to be coaxially distributed, angular transducer is several, is separately mounted to turntable mechanism and strengthens on telescopic rod and be located at turntable mechanism
With reinforcing telescopic rod and wing-body contact surface position, wind pressure sensor is evenly arranged on the front end of wing-body along wing-body axis
Face and lower end surface, wing-body front end face and lower end surface are all provided at least two wind pressure sensors, and wing-body front end face is under
Be spaced apart from each other distribution between the wind pressure sensor of end face, control circuit is embedded in bearing base rear end face, and respectively with turntable mechanism, strong
Change telescopic rod, angular transducer, wind pressure sensor electrical connection.
Further, the bearing base side surface is evenly distributed at least four pressure sensors, the pressure sensor
Axis and bearing base side surface vertical distribution, and spacing is not more than between pressure sensor and the locating slot inner surface of wing-body
20 millimeters, and the pressure sensor is electrically connected with control circuit.
Further, the bearing base side surface is evenly distributed at least four elastic cushion blocks, and the elastic cushion block is surround
Bearing base axis is uniformly distributed and offsets with the locating slot medial surface of wing-body.
Further, the turntable mechanism is the three-dimensional turntable driven by servomotor.
Further, the reinforcing telescopic rod is electric telescopic rod, and the reinforcing telescopic rod both ends are all provided with bulb
Hinge, and be hinged respectively with bearing base, wing-body by button-head hinge.
Further, the control circuit is based on the circuit system based on single-chip microcontroller, and the control system
In set at least one serial communication port.
The configuration of the present invention is simple, flexible and convenient to use, versatility is good, and one side installing and dismounting is easy, and bearing capacity is good, fixed
Position precision is high, and wing configurations structure is on the other hand adjusted flexibly according to the usage requirement, to meet the needs of different flight operations,
And adjustment Operation control precision and operation automation precision are high, improve fixed-wing unmanned plane using flexible so as to effectively reach
And convenience.
Detailed description of the invention
The following describes the present invention in detail with reference to the accompanying drawings and specific embodiments.
Fig. 1 is schematic structural view of the invention；
Specific embodiment
To be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, below with reference to
Specific embodiment, the present invention is further explained.
The adjustable wing structure of a kind of fixed-wing unmanned plane as described in Figure 1, including bearing base 1, wing-body 2, turn
Platform mechanism 3, flexible shroud 4 strengthen telescopic rod 5, angular transducer 6, wind pressure sensor 7 and control circuit 8, after bearing base 1
End is connect with 9 outer surface of unmanned plane body, and front end face is by turntable mechanism 3 and strengthens telescopic rod 5 and 2 rear end face phase of wing-body
It is mutually hinged, before 2 axis of wing-body and 1 front end face of bearing base are in 0 ° -90 ° angles, wherein turntable mechanism 3 and bearing base 1
End face is coaxially distributed, and strengthens telescopic rod 5 at least three, uniformly distributed around 3 axis of turntable mechanism, strengthens 5 axis of telescopic rod and wing
1 axis of main body is in 0 ° -90 ° angles, and 1 rear end face of wing-body sets locating slot 10, locating slot 10 be respectively coated by bearing base 1,
5 outside of turntable mechanism 3 and reinforcing telescopic rod, and 1 lateral surface of bearing base and 2 rear end face of wing-body pass through after flexible shroud 4
End face is connected with each other, flexible shroud 4 be coated on bearing base 1 it is outer and with the coaxial distribution of bearing base 1, angular transducer 6 is several,
It is separately mounted to turntable mechanism 3 and strengthens on telescopic rod 5 and be located at turntable mechanism 3 and strengthen telescopic rod 5 contact with wing-body 2
Face position, wind pressure sensor 7 are evenly arranged on front end face and the lower end surface of wing-body 1 along 1 axis of wing-body, before wing-body 2
End face and lower end surface are all provided at least two wind pressure sensors 7, and between 2 front end face of wing-body and the wind pressure sensor 7 of lower end surface
Be spaced apart from each other distribution, control circuit 8 is embedded in 1 rear end face of bearing base, and respectively with turntable mechanism 3, strengthen telescopic rod 5, angle
Sensor 6, wind pressure sensor 7 are electrically connected.
In the present embodiment, 1 side surface of bearing base is evenly distributed at least four pressure sensors 11, and the pressure passes
11 axis of sensor and 1 side surface vertical distribution of bearing base, and 10 inner surface of locating slot of pressure sensor 11 and wing-body 2
Between spacing be not more than 20 millimeters, and the pressure sensor 11 with control circuit 8 be electrically connected.
In the present embodiment, 1 side surface of bearing base is evenly distributed at least four elastic cushion blocks 12, the elastic cushion block
12 are evenly distributed with around 1 axis of bearing base and offset with 10 medial surface of the locating slot of wing-body 2.
In the present embodiment, the turntable mechanism 3 is the three-dimensional turntable driven by servomotor.
In the present embodiment, the reinforcing telescopic rod 5 is electric telescopic rod, and the reinforcing telescopic rod both ends are all provided with ball
Head hinge, and be hinged respectively with bearing base 1, wing-body 2 by button-head hinge.
In the present embodiment, the control circuit 8 is based on the circuit system based on single-chip microcontroller, and the control system
At least one serial communication port is set in system.
The present invention is in specific implementation, flexible to bearing base, wing-body, turntable mechanism, flexible shroud, reinforcing first
Bar, angular transducer, wind pressure sensor and control circuit are assembled, and the present invention after assembling is then installed to unmanned plane
At assigned work position, finally the governor circuit of control circuit and unmanned plane is electrically connected, installation of the invention can be completed
Positioning.
In unmanned plane during flying operation process, detected between current airfoils and unmanned aerial vehicle body by angular transducer first
Then distribution parameter detects the specific pressure value born in current airfoils operational process by wind pressure sensor, then can root
According to needs are used, by control circuit driving turntable mechanism, strengthens telescopic rod operation, actively carry out the adjustment of wing position, and adjusting
During whole, wing position adjusted is accurately positioned by angular transducer, while wing is held by wind pressure sensor
By pressure detecting, avoids causing unmanned plane lift insufficient because of wing structure adjustment or cause wing impaired existing because pressure is excessive
As occurring.
It in addition to this, can also be according to the pressure and unmanned plane during flying state that wing is currently born, by control circuit to machine
Wing distributed architecture is adjusted, and so that unmanned plane wing is born pressure and is matched with state of flight demand, to complete unmanned plane machine
The purpose of wing adjustment, and during the adjustment, location and range detection is adjusted to wing by angular transducer, is avoided because of adjustment
It measures excessive and causes wing structure impaired.
The configuration of the present invention is simple, flexible and convenient to use, versatility is good, and one side installing and dismounting is easy, and bearing capacity is good, fixed
Position precision is high, and wing configurations structure is on the other hand adjusted flexibly according to the usage requirement, to meet the needs of different flight operations,
And adjustment Operation control precision and operation automation precision are high, improve fixed-wing unmanned plane using flexible so as to effectively reach
And convenience
It should be understood by those skilled in the art that the present invention is not limited to the above embodiments.Above-described embodiment and explanation
It is merely illustrated the principles of the invention described in book.Without departing from the spirit and scope of the present invention, the present invention also has
Various changes and modifications.These changes and improvements all fall within the protetion scope of the claimed invention.The claimed scope of the invention
It is defined by the appending claims and its equivalent thereof.
Claims (6)
1. a kind of adjustable wing structure of fixed-wing unmanned plane, it is characterised in that: the adjustable wing of the fixed-wing unmanned plane
Structure includes bearing base, wing-body, turntable mechanism, flexible shroud, strengthens telescopic rod, angular transducer, wind pressure sensor
And control circuit, the bearing base rear end are connect with unmanned plane body outer surface, front end face passes through turntable mechanism and reinforcing
Telescopic rod is hinged with wing-body rear end face, and the wing-body axis and bearing base front end face are in 0 ° -90 ° folders
Angle, wherein the turntable mechanism is coaxially distributed with bearing base front end face, the reinforcing telescopic rod at least three surround and turns
Platform mechanism axis is uniformly distributed, and the flexible rod axis of the reinforcing and wing-body axis are in 0 ° -90 ° angles, the wing-body
Rear end face sets locating slot, and the locating slot is respectively coated by bearing base, turntable mechanism and strengthens on the outside of telescopic rod, and described
Bearing base lateral surface be connected with each other with wing-body rear end face by flexible shroud rear end face, the described flexible shroud cladding
It is coaxially distributed outside bearing base and with bearing base, the angular transducer is several, is separately mounted to turntable mechanism and strong
Change on telescopic rod and be located at turntable mechanism and strengthen telescopic rod and wing-body contact surface position, the wind pressure sensor is along machine
Wing main body axis is evenly arranged on front end face and the lower end surface of wing-body, and wing-body front end face and lower end surface are all provided at least two
Wind pressure sensor, and distribution is spaced apart from each other between wing-body front end face and the wind pressure sensor of lower end surface, the control circuit
It is electrically connected embedded in bearing base rear end face, and respectively with turntable mechanism, reinforcing telescopic rod, angular transducer, wind pressure sensor.
2. a kind of adjustable wing structure of fixed-wing unmanned plane according to claim 1, it is characterised in that: the carrying
Pedestal side surface is evenly distributed at least four pressure sensors, and the pressure sensor axis is vertical with bearing base side surface to be divided
Cloth, and spacing is not more than 20 millimeters between pressure sensor and the locating slot inner surface of wing-body, and the pressure sensor is equal
It is electrically connected with control circuit.
3. a kind of adjustable wing structure of fixed-wing unmanned plane according to claim 1, it is characterised in that: the carrying
Pedestal side surface is evenly distributed at least four elastic cushion blocks, and the elastic cushion block is evenly distributed with around bearing base axis and and wing-body
Locating slot medial surface offset.
4. a kind of adjustable wing structure of fixed-wing unmanned plane according to claim 1, it is characterised in that: the turntable
Mechanism is the three-dimensional turntable driven by servomotor.
5. a kind of adjustable wing structure of fixed-wing unmanned plane according to claim 1, it is characterised in that: the reinforcing
Telescopic rod is electric telescopic rod, and the reinforcing telescopic rod both ends are all provided with button-head hinge, and by button-head hinge respectively with hold
Carry pedestal, wing-body is hinged.
6. a kind of adjustable wing structure of fixed-wing unmanned plane according to claim 1, it is characterised in that: the control
Circuit is that at least one serial communication port is set based on the circuit system based on single-chip microcontroller, and in the control system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811046124.8A CN109131835A (en) | 2018-09-07 | 2018-09-07 | A kind of adjustable wing structure of fixed-wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811046124.8A CN109131835A (en) | 2018-09-07 | 2018-09-07 | A kind of adjustable wing structure of fixed-wing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109131835A true CN109131835A (en) | 2019-01-04 |
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ID=64824054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811046124.8A Pending CN109131835A (en) | 2018-09-07 | 2018-09-07 | A kind of adjustable wing structure of fixed-wing unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109131835A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152912A (en) * | 2020-01-09 | 2020-05-15 | 南京航空航天大学 | A stiffness compensation device for a flexible wing and its working method |
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|---|---|---|---|---|
| GB490151A (en) * | 1936-05-08 | 1938-08-10 | Bayerische Flugzeugwerke A G H | Improvements relating to folding wings for aeroplanes |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
| CN106516080A (en) * | 2016-12-06 | 2017-03-22 | 昆山鲲鹏无人机科技有限公司 | Tilting wing unmanned aerial vehicle with aerodynamic layout and tilting mechanisms and method for detecting whether wings get loose or not |
| CN106715263A (en) * | 2014-09-25 | 2017-05-24 | 庞巴迪公司 | Morphing skin for an aircraft |
| CN206520755U (en) * | 2017-03-02 | 2017-09-26 | 浙江工业职业技术学院 | A kind of electromagnetism adhesive rotary type bionic flapping-wing device |
| CN108202568A (en) * | 2016-12-16 | 2018-06-26 | 深圳光启合众科技有限公司 | Hovercar |
| CN207594668U (en) * | 2017-10-23 | 2018-07-10 | 天津飞眼无人机科技有限公司 | The control system of empty land two-purpose traffic tool |
-
2018
- 2018-09-07 CN CN201811046124.8A patent/CN109131835A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB490151A (en) * | 1936-05-08 | 1938-08-10 | Bayerische Flugzeugwerke A G H | Improvements relating to folding wings for aeroplanes |
| CN106715263A (en) * | 2014-09-25 | 2017-05-24 | 庞巴迪公司 | Morphing skin for an aircraft |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN105173061A (en) * | 2015-08-13 | 2015-12-23 | 中国航空工业集团公司西安飞机设计研究所 | Plane in supersonic speed plane layout |
| CN106516080A (en) * | 2016-12-06 | 2017-03-22 | 昆山鲲鹏无人机科技有限公司 | Tilting wing unmanned aerial vehicle with aerodynamic layout and tilting mechanisms and method for detecting whether wings get loose or not |
| CN108202568A (en) * | 2016-12-16 | 2018-06-26 | 深圳光启合众科技有限公司 | Hovercar |
| CN206520755U (en) * | 2017-03-02 | 2017-09-26 | 浙江工业职业技术学院 | A kind of electromagnetism adhesive rotary type bionic flapping-wing device |
| CN207594668U (en) * | 2017-10-23 | 2018-07-10 | 天津飞眼无人机科技有限公司 | The control system of empty land two-purpose traffic tool |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111152912A (en) * | 2020-01-09 | 2020-05-15 | 南京航空航天大学 | A stiffness compensation device for a flexible wing and its working method |
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| PB01 | Publication | ||
| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190104 |