CN108974354A - A kind of flapping wing and fixed-wing lotus root close configuration aircraft - Google Patents
A kind of flapping wing and fixed-wing lotus root close configuration aircraft Download PDFInfo
- Publication number
- CN108974354A CN108974354A CN201710405360.3A CN201710405360A CN108974354A CN 108974354 A CN108974354 A CN 108974354A CN 201710405360 A CN201710405360 A CN 201710405360A CN 108974354 A CN108974354 A CN 108974354A
- Authority
- CN
- China
- Prior art keywords
- wing
- flapping
- motor
- fixed
- plate
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C37/00—Convertible aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of flapping wings and fixed-wing lotus root to close configuration aircraft, it includes: body, empennage, switching mechanism, flapping mechanism, flapping wing, propulsion device；The body is in streamline shape, and body two sides are equipped with plate, and plate is equipped with hole；The switching mechanism, flapping mechanism are mounted on plate, and flapping wing is mounted on flapping mechanism；The empennage is arranged in switching mechanism described in the rear portion of body and is mounted on plate, is symmetrical set；The present invention is for the disadvantage that overcomes current conventional configuration micro air vehicle pneumatic efficiency low, solve the contradiction required the size and payload of existing micro air vehicle, and the characteristics of meeting stronger mobility, propose the Flight Vehicle Design of a kind of flapping wing and fixed-wing combination.
Description
Technical field
The invention belongs to concretely relate to flapping wing the invention belongs to micro air vehicle design and manufacturing technology field
The Flight Vehicle Design method and manufacturing technology organically combined with fixed-wing.
Background technique
Since ancient times, the mankind never stop exploring always the flight of birds, manufactured by the A Erxitasi from ancient Greek
Mechanical dove, Australia boomerang, to China hot balloon and kite all have close relationship with flight, the mankind's
Flight dream is tentatively realized since flapping wing aircraft from fixed-wing.1992, the U.S. was submitted by Rand Corporation of the U.S.
DARPA (Defense Advanced Research Project Agency, national defence Advanced Research Projects Agency) it is a about
The research report of future military technology has been put forward for the first time the concept of minute vehicle.Compared with conventional unmanned vehicle, microminiature
Aircraft has a small in size, flying platform advantage that light weight and cost is low, and easy to operate, maneuverability, noise be small, concealment
It is good, either in military field still in civil field, there is very wide application prospect, thus cause countries in the world
Extensive concern.
Traditional micro air vehicle can be divided into three classes by flight characteristic: fixed-wing, rotor and flapping wing.Microminiature fixed-wing flies
The characteristics of row device is that structure is simple, fixed-wing technological accumulation comparative maturity, but this kind of aircraft needs certain flying speed
Generating lift could stop in the sky, and since the limitation of size causes minimum level speed larger, it is solid to limit microminiature
Determine the application range of rotor aircraft.Microminiature flapping-wing type aircraft is a kind of imitation birds and insect flying, former based on bionics
Manage the course of new aircraft manufactured and designed.It compares with fixed-wing formula with rotary aircraft, has the considerable advantage that as can be with
Hover or advance under low reynolds number, there is stronger mobility, it is good will be possessed by rotor and fixed-wing formula aircraft
Advantage concentrates in together, while in the case where same characteristic features size, and flapping-wing type aircraft has higher flight efficiency.But
Since current bionical and technology develops to reach ideal bionical effect, therefore existing microminiature flapping flight
Device is although can be well realized flight, but payload is very low, or have to achieve the purpose that be promoted payload
Take the configuration of larger size, these disadvantages make microminiature flapping wing aircraft need the application aspect of larger payload by
Severely restricts are arrived.For the disadvantage for overcoming current conventional configuration micro air vehicle pneumatic efficiency low, solve to existing small
The contradiction that the size and payload of type aircraft require, and the characteristics of meet stronger mobility, propose a kind of flapping wing
The Flight Vehicle Design organically combined with fixed-wing.
Summary of the invention
In order to solve the disadvantage that existing aircraft, flapping wing aircraft and Fixed Wing AirVehicle are organically combined, mentioned
A kind of flapping wing and fixed-wing lotus root has been supplied to close configuration aircraft.
A kind of flapping wing and fixed-wing lotus root close configuration aircraft, it includes: body, empennage, switching mechanism, flapping mechanism, flutters
The wing, propulsion device；The body is in streamline shape, and body two sides are equipped with plate, and plate is equipped with hole；The interpreter
Structure, flapping mechanism are mounted on plate, and flapping wing is mounted on flapping mechanism；The rear portion of body is arranged in the empennage；
Further, the switching mechanism is mounted on plate, is symmetrical set；The switching mechanism include: L plate,
Articulated shaft, motor fixing frame, motor；The articulated shaft is mounted in the bore；The L plate is equipped with hinge hole on one side, separately
It is equipped with motor fixing hole of fluttering on one side, the left and right sides for motor fixing hole of fluttering is equipped with pivoting support；The pivoting support
Axis horizontal setting；The L plate is arranged on plate top, and hinge hole is matched with articulated shaft；The motor is through motor
Fixed frame is fixed on plate, and the axis of motor is connected with articulated shaft；
Further, propulsion device fixed part is additionally provided on the empennage；
Further, the flapping mechanism includes flutter motor, rocking bar, frame of fluttering；The motor of fluttering, which is mounted on, to be flutterred
In dynamic motor fixing hole；The rocking bar is in zigzag, and rocking bar is fixed on the output shaft for motor of fluttering；The frame of fluttering
In gate, the end for frame of fluttering and pivoting support are hinged；It is set on the frame of fluttering there are two traveller, traveller is propped up with hinged
Seat axis is arranged in parallel；
Further, the distance of two travellers is 1-1.2 times of rocking bar diameter；
Further, the propulsion device includes propulsion electric machine, propeller；The propeller is mounted on the defeated of propulsion electric machine
On shaft；The propulsion electric machine is mounted on propulsion device fixed part；
Further, the end of the flapping wing is equipped with chamfering；
Further, the motor of fluttering is stepper motor；The motor is stepper motor；The propulsion electric machine is nothing
Brush motor.
The present invention provides a kind of flapping wing and fixed-wing lotus roots to close configuration aircraft, it include: body, empennage, switching mechanism,
Flapping mechanism, flapping wing, propulsion device；The body is in streamline shape, and body two sides are equipped with plate, and plate is equipped with hole；Institute
The switching mechanism stated, flapping mechanism are mounted on plate, and flapping wing is mounted on flapping mechanism；Body is arranged in the empennage
Switching mechanism described in rear portion is mounted on plate, is symmetrical set；The switching mechanism includes: L plate, articulated shaft, electricity
Machine fixed frame, motor；The articulated shaft is mounted in the bore；The L plate is equipped with hinge hole on one side, and another side is equipped with
It flutters motor fixing hole, the left and right sides for motor fixing hole of fluttering is equipped with pivoting support；The axis horizontal of the pivoting support
Setting；The L plate is arranged on plate top, and hinge hole is matched with articulated shaft；The motor is fixed through motor fixing frame
On plate, the axis of motor is connected with articulated shaft；Propulsion device fixed part is additionally provided on the empennage；The machine of fluttering
Structure includes flutter motor, rocking bar, frame of fluttering；The motor of fluttering, which is mounted on, flutters in motor fixing hole；The rocking bar
In zigzag, rocking bar is fixed on the output shaft for motor of fluttering；The frame of fluttering is in gate, the end for frame of fluttering and hinge
It is hinged to connect support；It is set on the frame of fluttering there are two traveller, traveller is arranged in parallel with pivoting support axis；Two travellers
Distance is 1-1.2 times of rocking bar diameter；The propulsion device includes propulsion electric machine, propeller；The propeller is mounted on
On the output shaft of propulsion electric machine；The propulsion electric machine is mounted on propulsion device fixed part；The end of the flapping wing is equipped with
Chamfering；The motor of fluttering is stepper motor；The motor is stepper motor；The propulsion electric machine is brushless motor.
The present invention solves the disadvantage that existing aircraft, and flapping wing aircraft and Fixed Wing AirVehicle are organically combined.
Detailed description of the invention
Fig. 1 is the main view that a kind of flapping wing of the present invention and fixed-wing lotus root close configuration aircraft；
Fig. 2 is the A-A cross-sectional view that a kind of flapping wing of the present invention and fixed-wing lotus root close configuration aircraft；
Fig. 3 is the perspective view that a kind of flapping wing of the present invention and fixed-wing lotus root close configuration aircraft；
Fig. 4 is another state stereogram that a kind of flapping wing of the present invention and fixed-wing lotus root close configuration aircraft.
Specific embodiment
Embodiment 1: a kind of flapping wing and fixed-wing lotus root close configuration aircraft
Referring to Figure 1-4, a kind of flapping wing and fixed-wing lotus root close configuration aircraft, it include: body 1, empennage 2, switching mechanism 3,
Flapping mechanism 4, flapping wing 5, propulsion device 6；
The body 1 is in streamline shape, and 1 two sides of body are equipped with plate 11, and plate 11 is equipped with hole；
The rear portion of body 1 is arranged in the empennage 2；
Propulsion device fixed part 21 is additionally provided on the empennage 2；
The switching mechanism 3 is mounted on plate 11, is symmetrical set；
The switching mechanism 3 includes: L plate 31, articulated shaft 32, motor fixing frame 33, motor 34；
The articulated shaft 32 is mounted in the bore；
The L plate 31 is equipped with hinge hole on one side, and another side is equipped with motor fixing hole of fluttering, motor fixing hole of fluttering
The left and right sides is equipped with pivoting support 311；The axis horizontal of the pivoting support 311 is arranged；
The L plate 31 is arranged on 11 top of plate, and hinge hole 311 is matched with articulated shaft 32；
The motor 34 is fixed on plate 11 through motor fixing frame 33, and the axis of motor 34 is connected with articulated shaft 32；
The motor 34 is stepper motor；
The flapping mechanism 4 includes flutter motor 41, rocking bar 42, frame 43 of fluttering；
The motor 41 of fluttering, which is mounted on, flutters in motor fixing hole；
The rocking bar 42 is in zigzag, and rocking bar 42 is fixed on the output shaft for motor 41 of fluttering；
For the frame 43 of fluttering in gate, the end for frame 43 of fluttering and pivoting support 311 are hinged；
It is set on the frame 43 of fluttering there are two traveller 431, traveller 431 is arranged in parallel with 311 axis of pivoting support, two cunnings
The distance of column 431 is 1-1.2 times of 42 diameter of rocking bar；
The motor 41 of fluttering is stepper motor；
The flapping wing 5, which is mounted on, flutters on frame 43；
The end of the flapping wing 5 is equipped with chamfering；
The propulsion device 6 includes propulsion electric machine 61, propeller 62；
The propeller 62 is mounted on the output shaft of propulsion electric machine 61；
The propulsion electric machine 61 is mounted on propulsion device fixed part 21；
The propulsion electric machine 61 is brushless motor.
In use, the motor 34 of switching mechanism 3 drives L plate 31 to rotate through articulated shaft 32, revolve flapping wing 5 around articulated shaft 32
Turn, the end of flapping wing 5 is equipped with chamfering and fits with body 1, adjusts motor 41 of fluttering, so that flapping wing 5 is in a horizontal state, aircraft is whole
Body is in Fixed Wing AirVehicle shape, and propulsion electric machine 61 drives propeller 62 to rotate, can be taken off, be landed, flare maneuver.When turn
Change planes structure 3 motor 34 through articulated shaft 32 drive L plate 31 rotate, make flapping wing 5 around articulated shaft 32 rotate, flapping wing 5 open, electricity of fluttering
Machine 41 drives rocking bar 42 to rotate, and rocking bar 42 drives two travellers 431 movement fluttered on frame 43, and flapping wing 5 is in motor 41 of fluttering
It flutters under drive, 61 stop motion of propulsion electric machine, entire aircraft is in flapping wing aircraft state.
Claims (8)
1. a kind of flapping wing and fixed-wing lotus root close configuration aircraft, it is characterised in that: it includes: body (1), empennage (2), interpreter
Structure (3), flapping mechanism (4), flapping wing (5), propulsion device (6)；The body (1) is in streamline shape, and body (1) two sides are equipped with
Plate (11), plate (11) are equipped with hole；The switching mechanism (3), flapping mechanism (4) are mounted on plate (11), flapping wing
(5) it is mounted on flapping mechanism (4)；Rear portion of empennage (2) setting in body (1).
2. a kind of flapping wing according to claim 1 and fixed-wing lotus root close configuration aircraft, it is characterised in that: the conversion
Mechanism (3) is mounted on plate (11), is symmetrical set；The switching mechanism (3) includes: L plate (31), articulated shaft
(32), motor fixing frame (33), motor (34)；The articulated shaft (32) is mounted in the bore；The L plate (31) on one side on
Equipped with hinge hole, another side is equipped with and flutters motor fixing hole (3), and the left and right sides of motor fixing hole of fluttering (3) is equipped with hinged
Support (311)；The axis horizontal of the pivoting support (311) is arranged；The L plate (31) is arranged on plate (11) top,
Hinge hole is matched with articulated shaft (32)；The motor (34) is fixed on plate (11) through motor fixing frame (33), motor
(34) axis is connected with articulated shaft (32).
3. a kind of flapping wing according to claim 2 and fixed-wing lotus root close configuration aircraft, it is characterised in that: the empennage
(2) propulsion device fixed part (21) are additionally provided on.
4. a kind of flapping wing according to claim 3 and fixed-wing lotus root close configuration aircraft, it is characterised in that: described flutters
Mechanism (4) includes flutter motor (41), rocking bar (42), frame of fluttering (43)；The motor of fluttering (41) is mounted on electricity of fluttering
On machine fixation hole (3)；The rocking bar (42) is in zigzag, and rocking bar (42) is fixed on the output shaft of motor of fluttering (41)；It is described
Frame of fluttering (43) be in gate, the end of frame of fluttering (43) and pivoting support (311) are hinged；The frame of fluttering (43)
On set there are two traveller (431), traveller (431) is arranged in parallel with pivoting support (311) axis.
5. a kind of flapping wing according to claim 4 and fixed-wing lotus root close configuration aircraft, it is characterised in that: two travellers
(431) distance is 1-1.2 times of rocking bar (42) diameter.
6. a kind of flapping wing according to claim 5 and fixed-wing lotus root close configuration aircraft, it is characterised in that: the propulsion
Device (6) includes propulsion electric machine (61), propeller (62)；The propeller (62) is mounted on the output shaft of propulsion electric machine (61)
On；The propulsion electric machine (61) is mounted on propulsion device fixed part (21).
7. a kind of flapping wing according to claim 6 and fixed-wing lotus root close configuration aircraft, it is characterised in that: the flapping wing
(5) end is equipped with chamfering.
8. a kind of flapping wing according to claim 7 and fixed-wing lotus root close configuration aircraft, it is characterised in that: described flutters
Motor (41) is stepper motor；The motor (34) is stepper motor；The propulsion electric machine (61) is brushless motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710405360.3A CN108974354A (en) | 2017-06-01 | 2017-06-01 | A kind of flapping wing and fixed-wing lotus root close configuration aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710405360.3A CN108974354A (en) | 2017-06-01 | 2017-06-01 | A kind of flapping wing and fixed-wing lotus root close configuration aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108974354A true CN108974354A (en) | 2018-12-11 |
Family
ID=64502478
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710405360.3A Pending CN108974354A (en) | 2017-06-01 | 2017-06-01 | A kind of flapping wing and fixed-wing lotus root close configuration aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108974354A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112758314A (en) * | 2020-12-15 | 2021-05-07 | 北京交通大学 | Deformable composite wing cross-medium flying submersible vehicle |
| CN114889821A (en) * | 2022-05-24 | 2022-08-12 | 深圳市人工智能与机器人研究院 | Four-wing flapping wing micro water surface aircraft and flight method |
-
2017
- 2017-06-01 CN CN201710405360.3A patent/CN108974354A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112758314A (en) * | 2020-12-15 | 2021-05-07 | 北京交通大学 | Deformable composite wing cross-medium flying submersible vehicle |
| CN114889821A (en) * | 2022-05-24 | 2022-08-12 | 深圳市人工智能与机器人研究院 | Four-wing flapping wing micro water surface aircraft and flight method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US10322814B1 (en) | Aircraft vertical stabilizer having a lift propeller and the method of using the same | |
| US10293933B2 (en) | Rotating wing assemblies for tailsitter aircraft | |
| CN107416202B (en) | Miniature flapping wing aircraft | |
| CN106043692B (en) | A kind of multiple degrees of freedom imitates bird flapping wing aircraft | |
| CN107054645B (en) | A kind of assistant deforms bionical unmanned vehicle and deformation control method | |
| CN201941975U (en) | Ornithopter simulating folding wing flapping of birds | |
| US6938853B2 (en) | Biomimetic mechanism for micro aircraft | |
| CN103482064A (en) | Bionic flapping wing air vehicle | |
| CN108860595B (en) | Flapping wing pigeon-like aircraft with passive torsion | |
| CN103552687B (en) | One flutters rotor configuration and corresponding microminiature flutters rotor driver | |
| CN104229138A (en) | Split differential tail wing control mechanism of flapping-wing micro air vehicle | |
| KR20130057222A (en) | Flight driving apparatus and ornithopter having the same | |
| EP3423351A1 (en) | Split winglet lateral control | |
| TW202136118A (en) | Rotating wing structure of flapping-wing micro aircraft respectively fixing the left actuator and the right actuator to the left and right sides of the actuator base | |
| CN108974354A (en) | A kind of flapping wing and fixed-wing lotus root close configuration aircraft | |
| CN206871360U (en) | A kind of multiple degrees of freedom flapping-wing modal with high propulsive efficiency | |
| CN210592424U (en) | Bionic butterfly flapping wing aircraft | |
| CN108528710A (en) | A kind of flapping wing matrix aerodynamic configuration of aircraft | |
| CN103552688B (en) | Flapping wing and rotary wing coupling configuration and corresponding minitype aircraft design | |
| CN201183610Y (en) | Ornithopter | |
| CN104875875A (en) | Air wing type airflow directional load transportation air vehicle | |
| CN210063360U (en) | Bionic mechanical flapping wing machine | |
| TWI572526B (en) | Miniature aircraft wings drive structure | |
| JP2023504967A (en) | Variable-span wings and related aircraft | |
| CN109911197A (en) | A kind of four-degree-of-freedom flapping wing aircraft device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181211 |