CN108639338A - A kind of wing control device and aircraft - Google Patents
A kind of wing control device and aircraft Download PDFInfo
- Publication number
- CN108639338A CN108639338A CN201810720443.6A CN201810720443A CN108639338A CN 108639338 A CN108639338 A CN 108639338A CN 201810720443 A CN201810720443 A CN 201810720443A CN 108639338 A CN108639338 A CN 108639338A
- Authority
- CN
- China
- Prior art keywords
- wing
- spar
- supporting mechanism
- control device
- fixed
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
A kind of wing control device and aircraft are provided in the embodiment of the present application, wherein the wing control device includes：First wing supporting mechanism and the second wing supporting mechanism；The second wing supporting mechanism is connect by articulation piece with the first wing supporting mechanism；The second wing supporting mechanism is equipped with rotating mechanism, and compact, efficient, high-precision, the control of linear aerofoil may be implemented in the control device that the rotating mechanism drives the second wing supporting mechanism to rotate relative to the first wing supporting mechanism in the present embodiment.
Description
Technical field
This application involves vehicle technology field, more particularly to a kind of aerofoil for high aspect ratio bionic Aircraft controls
Mechanism and aircraft.
Background technology
Since the concept of minute vehicle proposes, since it is potential extremely wide at two aspect of military and civilian
Application prospect, it includes two major classes to imitate Bird Flight mainly, and one kind is the small-sized bionic aircraft of single flap, and one kind is more flaps
Large simulated aircraft.Although flapping wing aircraft flight efficiency is high, has bionical characteristic, more difficult to accomplish rapid flight.
Control of the aerofoil control mechanism of present high aspect ratio bionic Aircraft using the mechanism of double leval jib principle as aerofoil
Mechanism processed uses multiple connecting rods to carry out power transmissions, this can cause load path longer, and required quality is larger with bionical flight
Device loss of weight is disagreed.
Patent document application publication number is to disclose bionic Aircraft in CN105217032A, and bionical fly is referred in patent
Row device aerofoil control mechanism, including：Wherein one end of bent axle, bent axle is connected with transmission shaft driven, the song where the bent axle other end
Shaft portion relative rotation is connected with bent axle sleeve, and wing and inner edge bar are fixedly connected on bent axle sleeve, and inner edge bar is located at wing
Inside, inner edge bar free end are connected with multidirectional device, and multidirectional device includes shaft in the outer framework and multidirectional device of relative rotation connection, interior
Edge bar is connect with shaft relative rotation in multidirectional device.Whole device is excessively complicated, and precision is low, volume and quality are larger, and four connect
The transmission device of rod principle is non-linear controller, is unfavorable for flight control design.
Invention content
One of in order to solve the above problem, this application provides a kind of aerofoil control machines for high aspect ratio bionic Aircraft
Structure and aircraft.
According to the first aspect of the embodiment of the present application, a kind of wing control device is provided, which includes：First machine
Wing supporting mechanism and the second wing supporting mechanism；
The second wing supporting mechanism is connect by articulation piece with the first wing supporting mechanism；
The second wing supporting mechanism is equipped with rotating mechanism, and the rotating mechanism drives second wing to support machine
Structure rotates relative to the first wing supporting mechanism.
According to the second aspect of the embodiment of the present application, a kind of aircraft is provided, the wing of the aircraft is equipped with
Wing control device as described above.
Herein described technical solution makes aerofoil deform upon, and then generate aerodynamic force, realizes to flying by tearing aerofoil
The control of row device.The transmission device ratio double leval jib control device transmission chain that herein described technical solution uses will lack, required
Space and quality want small, precision wants high, and control efficiency is higher, while controlling the process that process is a LINEAR CONTINUOUS, makes machine
Wing control is simplified.
Description of the drawings
Attached drawing described herein is used for providing further understanding of the present application, constitutes part of this application, this Shen
Illustrative embodiments and their description please do not constitute the improper restriction to the application for explaining the application.In the accompanying drawings：
Fig. 1 shows the schematic diagram of herein described wing control device；
Fig. 2 shows the schematic diagrames of the herein described wing control device for removing covering；
Fig. 3 shows the partial enlarged view of herein described wing control device.
Drawing reference numeral
1, the first drive rod, the 2, second drive rod, 3, mounting blocks, 4, anti-dropout ring, the 5, first spar, the 6, second spar,
7, spar link block, the 8, first rib, the 9, second rib, 10, covering, 11, first gear, 12, second gear, 13, steering engine,
14, articulation piece.
Specific implementation mode
In order to make technical solution in the embodiment of the present application and advantage be more clearly understood, below in conjunction with attached drawing to the application
Exemplary embodiment be described in more detail, it is clear that described embodiment be only the application a part implement
Example, rather than the exhaustion of all embodiments.It should be noted that in the absence of conflict, the embodiment in the application and reality
The feature applied in example can be combined with each other.
The core ideas of this programme is so that part wing is twisted change relative to another part wing by rotating mechanism
Shape realizes the drive control to aircraft to generate aerodynamic force.
Embodiment one
As depicted in figs. 1 and 2, a kind of wing control device is present embodiments provided, which can be used for high aspect ratio
Bionic Aircraft wing control.Specifically, the wing control device includes:First wing supporting mechanism and the second wing
Supporting mechanism, the second wing supporting mechanism are connect by articulation piece 14 with the first wing supporting mechanism.In the present embodiment, lead to
The movement of the second wing supporting mechanism can be driven by crossing the movement of the first wing supporting mechanism, meanwhile, it can by articulation piece 14
Realize that the relative motion between two wing supporting mechanisms, the movement can imitate the action that birds flicker.Further,
The second wing supporting mechanism is equipped with rotating mechanism, the rotating mechanism drive the second wing supporting mechanism relative to
First wing supporting mechanism rotates.Aerofoil surface can be made to deform upon by the rotation of the second wing supporting mechanism,
To generate aerodynamic force, drive control is provided for aircraft.
In the present embodiment, the first wing supporting mechanism includes：First drive rod 1 and the second drive rod 2, first driving
One end of bar 1 and the second drive rod 2 is connect with articulation piece 14, and the other end of 1 and second drive rod 2 of the first drive rod is used for
It is connect with carry-on power plant；The fortune of the first drive rod 1 and the second drive rod 2 is driven by power plant on aircraft
It is dynamic, realize the folding movement of wing.
In the present embodiment, the second wing supporting mechanism includes：With 14 fixed mounting blocks 3 of articulation piece and with the mounting blocks
The supporting rack of 3 rotation connections.Second wing supporting mechanism is transferred by mounting blocks 3 and the first wing supporting mechanism, can be avoided
When the second wing supporting mechanism rotary motion movement interference is generated with the first wing supporting mechanism.Wherein, support frame as described above includes：
First spar 5, the second spar 6, the first rib 8 and the second rib 9；First spar 5 passes through spar link block 7 and the second spar 6
Connection, and the angle between first spar, 5 and second spar 6 is obtuse angle, when being installed with aircraft, the second spar 6 is partially
To the caudal directions of aircraft；First rib 8 and the first spar 5 are fixed, and the second rib 9 is fixed with spar link block 7, first wing
Rib 8 and the second rib 9 are each perpendicular to the first spar 5.The first spar 5 and the second spar 6 are utilized in the second wing supporting mechanism
As the support backbone of wing, using the first rib 8 and the second rib 9 as the support of wing.For example, can be on supporting rack
Flexible covering structure 10, which is arranged, is used as wing, described 10 one end of flexible covering structure to be fixed with mounting blocks 3, one end and second wing
Beam 6 is fixed；10 intermediate region of flexible covering structure is fixed with the first rib 8 and the second rib 9 respectively.
In the present embodiment, the first spar 5 is the pre-set through-hole on mounting blocks 3, and can be rotated in through-hole.
As shown in figure 3, one end of the first spar 5 is connect by spar link block 7 with the second spar 6, the other end is fixed with anti-dropout
Ring 4.First spar 5 is limited by anti-dropout ring 4, from the through-hole of mounting blocks 3 when preventing it from being rotated in mounting blocks 3
In skid off.
In the present embodiment, the rotating mechanism includes：It first gear 11, second gear 12 and is fixed on mounting blocks 3
Steering engine 13；The first gear 11 is fixed on the power output shaft of the steering engine 13, and the second gear 12 is fixed on support
On frame；12 engaged transmission of the first gear 11 and second gear.In the present embodiment, rotating mechanism is fixed base with mounting blocks 3
Plinth, steering engine 13 are fixed on by way of being clamped or being bonded on mounting blocks 3, and second gear 12 is fixed on the first spar of supporting rack
On 5, the power of steering engine 13 is passed to by supporting rack by the engaged transmission of first gear 11 and second gear 12, supporting rack passes through
The engaged transmission of gear, relative to the first wing supporting mechanism generate rotation, at this point, due to flexible covering structure 10 distal end with
Second rib 9 and the connection of second spar 6, and covering is fixed on proximally by splicing on mounting blocks 3, therefore flexible covering structure
10 will tearing because of the second rib 9 and the second spar 6, deform upon, and then generate aerodynamic force, realize the control to aircraft
System.
A kind of aircraft is additionally provided in the present embodiment, and power plant is provided on the aircraft；The power plant packet
It includes：Driving motor, gear set and crankshaft-link rod；Driving motor pass sequentially through gear set and crankshaft-link rod and the first drive rod 1 and
Second drive rod 2 connects；The fortune of fluttering of wing is realized by the cooperation of power plant and the first drive rod 1 and the second drive rod 2
It is dynamic.
Embodiment two
As shown in Figure 1 to Figure 3, a kind of wing control dress for high aspect ratio bionic Aircraft is present embodiments provided
It sets, which includes：First drive rod 1, the second drive rod 2, mounting blocks 3, anti-dropout ring 4, the first wing fine strain of millet, the second spar 6, the wing
The knots such as beam link block 7, the first rib 8, the second rib 9, covering, first gear 11, second gear 12, steering engine 13 and articulation piece 14
Structure.Wherein, the mounting blocks 3 are the square structure with through-hole, which is driven by axis and the first drive rod 1 and second
Bar 2 connects.Steering engine 13 is the power source of square structure, which is mounted on by bolt on mounting blocks 3.First spar 5 is pacified
In the through-hole of mounting blocks 3, and the through-hole rotation on mounting blocks 3 can be surrounded.Anti-dropout ring 4 is mounted on first by being glued
One end of spar 5 prevents the first spar 5 to be detached from the constraint of through-hole on mounting blocks 3 in rotation process.Spar link block 7 is different
There is a hole at type structure, both ends, and one end of the other end of the first spar 5 and the second spar 6 is fixed on the wing by way of splicing respectively
In the hole of beam link block 7；In the present embodiment, the first spar 5 is strip cylinder, and the second spar 6 is strip cylinder.First wing
Rib 8 is fixed with stressed-skin construction 10, and the stressed-skin construction 10 is not connect with the first spar 5；Second rib 9 be and air foil shape phase
The harden structure matched, and be fixed on spar link block 7 by way of splicing.First gear 11 is fixed on first wing by being glued
On beam 5, while 11 installation site of first gear prevents the first spar 5 to be detached from peace in rotation process close to the position of mounting blocks 3
Fill block 3；Second gear 12 is fixed on by being glued on the output shaft of steering engine 13, and second gear 12 is in engagement with first gear 11
Relationship.In the present embodiment, stressed-skin construction 10 is a flexible body, and distal end is connected with the second rib 9 and the second spar 6 by being glued
It connects, covering is fixed on proximally by splicing on mounting blocks 3.
For steering engine 13 under the control condition of flight control system, output shaft rotation drives first gear 11 to rotate, and first
Gear 11 by engage power drive second gear 12 rotate, second gear 12 rotate, drive the first spar 5, spar link block 7,
The supporting rack that second spar 6 and the second rib 9 are formed is rotated around the axis of second gear 12, due to flexible covering structure 10
Distal end is connect with the second rib 9 and the second spar 6, and stressed-skin construction 10 is fixed on proximally by splicing on mounting blocks 3, because
This, stressed-skin construction 10 will tearing because of the second rib 9 and the second spar 6, deform upon, and then generate aerodynamic force, realize
Control to aircraft.
For high aspect ratio bionic Aircraft in flight course, the control system of flight passes through flight control information, control flaps
The deflection angle that machine 13 exports, and then stressed-skin construction 10 generates deformation in control aerofoil, realizes the control to aircraft.
In the present embodiment by taking certain specific control mode as an example, the transmission ratio between first gear 11 and second gear 12
It is 2:When 1, then when steering engine 13 rotate deflection angle be+20 °, then the distal end of stressed-skin construction 10 then generate -10 ° rudder it is inclined；When
Steering engine 13 rotate deflection angle be -10 °, then the distal end of stressed-skin construction 10 then generate+5 ° rudder it is inclined.
Gear ratio in the present embodiment between first gear 11 and second gear 12 is not limited, the first drive rod
1 and second drive rod 2 it is unrestricted with the form of mounting blocks 3, the second spar 6 and the first spar 5 are simultaneously not arranged on the same straight line,
The distal end that the rotation of second spar 6 and the second rib 9 can tear covering is deformed.Control device in the present embodiment can be with
Realize compact, efficient, high-precision, the control of linear aerofoil.
Although the preferred embodiment of the application has been described, created once a person skilled in the art knows basic
Property concept, then additional changes and modifications may be made to these embodiments.So it includes excellent that the following claims are intended to be interpreted as
It selects embodiment and falls into all change and modification of the application range.
Obviously, those skilled in the art can carry out the application essence of the various modification and variations without departing from the application
God and range.In this way, if these modifications and variations of the application belong to the range of the application claim and its equivalent technologies
Within, then the application is also intended to include these modifications and variations.
Claims (10)
1. a kind of wing control device, which is characterized in that the device includes：First wing supporting mechanism and the second wing support machine
Structure；
The second wing supporting mechanism is connect by articulation piece (14) with the first wing supporting mechanism；
The second wing supporting mechanism is equipped with rotating mechanism, and the rotating mechanism drives the second wing supporting mechanism phase
It rotates for the first wing supporting mechanism.
2. wing control device according to claim 1, which is characterized in that the first wing supporting mechanism includes：The
One drive rod (1) and the second drive rod (2)；
One end of first drive rod (1) and the second drive rod (2) is connect with articulation piece (14), first drive rod (1)
It is used to connect with aircraft with the other end of the second drive rod (2).
3. wing control device according to claim 1, which is characterized in that the second wing supporting mechanism includes：With
Articulation piece (14) fixed mounting blocks (3) and the supporting rack being rotatablely connected with the mounting blocks (3).
4. wing control device according to claim 3, which is characterized in that support frame as described above includes：First spar (5) and
The second spar (6) being connect by spar link block (7) with the first spar (5).
5. wing control device according to claim 4, which is characterized in that support frame as described above further includes：With the first spar
(5) vertically disposed first rib (8) and the second rib (9)；
First rib (8) is fixed with the first spar (5), and second rib (9) is fixed with spar link block (7).
6. wing control device according to claim 5, which is characterized in that support frame as described above is equipped with flexible covering structure
(10)；Described flexible covering structure (10) one end is fixed with mounting blocks (3), and one end is fixed with the second spar (6)；The flexibility
Stressed-skin construction (10) intermediate region is fixed with the first rib (8) and the second rib (9) respectively.
7. wing control device according to claim 4, which is characterized in that first spar (5) and the second spar (6)
Between angle be obtuse angle.
8. wing control device according to claim 4, which is characterized in that the second wing supporting mechanism further includes：
It is fixed on the anti-dropout ring (4) of the first spar (5) other end；
First spar (5) passes through preset through-hole on mounting blocks (3), and limits the first spar (5) by anti-dropout ring (4)
Skid off the through-hole of mounting blocks (3).
9. wing control device according to claim 3, which is characterized in that the rotating mechanism includes：First gear
(11), second gear (12) and the steering engine (13) being fixed on mounting blocks (3)；
The first gear (11) is fixed on the power output shaft of the steering engine (13), and the second gear (12) is fixed on branch
On support；
The first gear (11) and second gear (12) engaged transmission.
10. a kind of aircraft, which is characterized in that the wing of the aircraft is equipped with as described in claim 1 to 9 any one
Wing control device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810720443.6A CN108639338A (en) | 2018-07-02 | 2018-07-02 | A kind of wing control device and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810720443.6A CN108639338A (en) | 2018-07-02 | 2018-07-02 | A kind of wing control device and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108639338A true CN108639338A (en) | 2018-10-12 |
Family
ID=63750436
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810720443.6A Pending CN108639338A (en) | 2018-07-02 | 2018-07-02 | A kind of wing control device and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108639338A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070138339A1 (en) * | 2003-06-18 | 2007-06-21 | Sinclair Peter L | Motion assisting apparatus for flying objects |
| US7651051B2 (en) * | 2005-11-08 | 2010-01-26 | University Of Delaware | Mechanism for biaxial rotation of a wing and vehicle containing such mechanism |
| CN103381886A (en) * | 2013-07-12 | 2013-11-06 | 南京航空航天大学 | Multidimensional dynamic active variant flapping wing aircraft |
| CN103523221A (en) * | 2013-10-11 | 2014-01-22 | 南京航空航天大学 | Bionic aircraft with active torsion control |
| CN104590560A (en) * | 2015-01-29 | 2015-05-06 | 北京航空航天大学 | Flapping-rotating wing with attack angle control device |
| CN105740575A (en) * | 2016-03-03 | 2016-07-06 | 北京航空航天大学 | Flapping wing analysis and design based on fluctuation propelling theory |
| CN106005405A (en) * | 2016-07-18 | 2016-10-12 | 上海交通大学 | High-frequency flapping-wing bionic insect aircraft with controllable passive torsion |
| CN106043692A (en) * | 2016-06-08 | 2016-10-26 | 中国民航大学 | Multi-freedom degree bird-like flapping wing air vehicle |
| CN106828923A (en) * | 2017-03-30 | 2017-06-13 | 梧州学院 | A kind of bionical dragonfly flapping wing and rotating mechanism |
-
2018
- 2018-07-02 CN CN201810720443.6A patent/CN108639338A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070138339A1 (en) * | 2003-06-18 | 2007-06-21 | Sinclair Peter L | Motion assisting apparatus for flying objects |
| US7651051B2 (en) * | 2005-11-08 | 2010-01-26 | University Of Delaware | Mechanism for biaxial rotation of a wing and vehicle containing such mechanism |
| CN103381886A (en) * | 2013-07-12 | 2013-11-06 | 南京航空航天大学 | Multidimensional dynamic active variant flapping wing aircraft |
| CN103523221A (en) * | 2013-10-11 | 2014-01-22 | 南京航空航天大学 | Bionic aircraft with active torsion control |
| CN104590560A (en) * | 2015-01-29 | 2015-05-06 | 北京航空航天大学 | Flapping-rotating wing with attack angle control device |
| CN105740575A (en) * | 2016-03-03 | 2016-07-06 | 北京航空航天大学 | Flapping wing analysis and design based on fluctuation propelling theory |
| CN106043692A (en) * | 2016-06-08 | 2016-10-26 | 中国民航大学 | Multi-freedom degree bird-like flapping wing air vehicle |
| CN106005405A (en) * | 2016-07-18 | 2016-10-12 | 上海交通大学 | High-frequency flapping-wing bionic insect aircraft with controllable passive torsion |
| CN106828923A (en) * | 2017-03-30 | 2017-06-13 | 梧州学院 | A kind of bionical dragonfly flapping wing and rotating mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| EP2740663B1 (en) | Apparatus, system, and method for pitching and twisting a blade of a rotorcraft | |
| CN104260882B (en) | Active twist flapping wing and the aircraft comprising which | |
| US6802473B2 (en) | Ornithopter with flexible fuselage | |
| CN105691592A (en) | electromechanical hinge-line rotary actuator | |
| CN111591462B (en) | Helicopter tail rotor simulation system for wind tunnel test | |
| CN105059536A (en) | Rotor wing device with variable pitch and multi-rotor-wing aircraft | |
| CN107264796A (en) | Propeller component with least two propeller blades | |
| CN103158870A (en) | Blade-pitch control system with feedback lever | |
| CN110171568A (en) | One kind can hover flapping wing aircraft | |
| CN108674651A (en) | Flapping wing device and flapping-wing aircraft | |
| CN103534169B (en) | The method of work of flapping wing device and flapping wing device | |
| US11053003B2 (en) | Cyclorotor thrust control, transmission and mounting system | |
| EP2907747A1 (en) | Cyclic pitch actuation system for counter-rotating propellers | |
| CN107161339A (en) | One kind is fluttered the bionical bird of twisted coupling | |
| CN108791857A (en) | Universal shaft type full rigidity twin-rotor helicopter altogether | |
| CN101966870B (en) | Steel wire hinged-type flapping-wing micro air vehicle (FMAV) driving mechanism | |
| CN110466757B (en) | Driving method of bionic flapping wing driving mechanism with active torsion and folding functions | |
| CN105480414A (en) | Coaxial double-rotor helicopter core and helicopter | |
| CN108639338A (en) | A kind of wing control device and aircraft | |
| JP5023330B2 (en) | Rotating blade mechanism, power generation device using the rotating blade mechanism, and moving device | |
| CN100591400C (en) | Steering mechanism for model helicopter | |
| CN110550205B (en) | Ornithopter steering control method, device and system | |
| CN110294120B (en) | Synchronous swing type four-flapping wing aircraft with rotatable wing pieces | |
| CN107719663A (en) | The drive mechanism and flapping wing aircraft of flapping wing aircraft | |
| US1656492A (en) | Flying machine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181012 |