CN106585982A - Combined type micro air vehicle driven by flapping wings - Google Patents
Combined type micro air vehicle driven by flapping wings Download PDFInfo
- Publication number
- CN106585982A CN106585982A CN201611181954.2A CN201611181954A CN106585982A CN 106585982 A CN106585982 A CN 106585982A CN 201611181954 A CN201611181954 A CN 201611181954A CN 106585982 A CN106585982 A CN 106585982A
- Authority
- CN
- China
- Prior art keywords
- wing
- flapping
- tail
- connecting rod
- air vehicle
- 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
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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
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/02—Mounting or supporting thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/06—Adjustable control surfaces or members, e.g. rudders with two or more independent movements
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention provides a combined type micro air vehicle driven by flapping wings. The combined type micro air vehicle comprises a fixed wing lifting surface, a flapping wing driving system, V-shaped tail wings and a connection rod. The fixed wing lifting surface comprises an aerofoil, a left aileron control surface and a right aileron control surface, and is mainly used for providing lifting power and rolling control required by flying of the air vehicle. The flapping wing driving system comprises the left flapping wing, the right flapping wing, a mechanism installation frame and a flapping mechanism, and is mainly used for providing thrust required by flying of the air vehicle. The V-shaped tail wings comprises the left tail wing, the right tail wing, the left tail vane and the right tail vane, and is used for providing stability as well as pitching and yaw control during flying of the air vehicle. The combined type micro air vehicle driven by the flapping wings has the advantages that flapping wing driving is adopted to replace traditional propeller driving, the propulsive efficiency of the micro air vehicle under the low Reynolds number condition can be improved, meanwhile, the lift efficiency of the whole micro air vehicle is also improved to a certain degree, and accordingly the flight performance of the micro air vehicle is improved.
Description
Technical field
The invention belongs to minute vehicle technical field, and in particular to the combined type micro air that a kind of employing flapping wing drives
Device.
Background technology
Minute vehicle is a kind of aircraft of yardstick less than 15cm, it is considered to be closely investigates on future battlefield and attacks
The important weapon hit, due to its have easy to carry, safety it is good, it is simple to operate the features such as and receive much concern.
In prior art, minute vehicle is mainly using propelling screws as propulsive mechanism.Compared with Large Scale Space Vehicle,
Minute vehicle is affected much greater by air viscosity, and this causes the low reynolds number characteristic of minute vehicle especially prominent.Receive
This impact, during conventionally employed small size propelling screws, its propulsive efficiency is substantially reduced, and directly constrains flying for minute vehicle
Row performance.Therefore, how to effectively improve the propulsive efficiency of minute vehicle, it is ensured that the flying quality of minute vehicle, be current
Problem in the urgent need to address.
The content of the invention
For the defect that prior art is present, the present invention provides the combined type minute vehicle that a kind of employing flapping wing drives,
Can effectively solving the problems referred to above.
The technical solution used in the present invention is as follows：
The present invention provides the combined type minute vehicle that a kind of employing flapping wing drives, including：Fixed-wing lifting surface, flapping wing drive
Dynamic system, vee tail and connecting rod (8)；
The front end of the connecting rod (8) is installed by the fixed-wing lifting surface；The tail end of the connecting rod (8) installs the V
Type tail；The flapping wing drive system is installed in the connecting rod (8), and is located at the fixed-wing lifting surface and the V-type
Between empennage；
Wherein, the fixed-wing lifting surface is used to produce the lift and aircraft manufacturing technology institute needed for aircraft flight
The rolling moment for needing；The fixed-wing lifting surface includes wing (1), port aileron rudder face (2) and starboard aileron rudder face (3)；The machine
The wing (1) is RECTANGULAR WINGS, and scope of its aspect ratio in 6-10, the front end of the central and described connecting rod (8) of the wing (1) are solid
Connect, and the leading edge of the wing (1) is vertical with the axis of the connecting rod (8)；The port aileron rudder face (2) and the starboard aileron
Rudder face (3) is respectively positioned at the left and right sides of the wing (1) trailing edge, the port aileron rudder face (2) and the starboard aileron rudder face (3)
It is able to be deflected around respective leading edge up and down；
Flapping wing drive system thrust required when flying before being used to provide aircraft；The flapping wing drive system includes a left side
The flutter wing (4), the right side is fluttered the wing (5), mechanism's installing rack (6) and flapping mechanism (7)；Mechanism's installing rack (6) and the connection
Bar (8) is connected, and is located between the fixed-wing lifting surface and the vee tail；The flapping mechanism (7) is fixed in the machine
On structure installing rack (6)；The wing (4) is fluttered on the left side and the right side is fluttered, and the wing (5) is symmetrically positioned in the both sides of the connecting rod (8), and
Rocking arm of fluttering with the left and right of the flapping mechanism (7) respectively is connected；
The vee tail is used to provide stability and control during aircraft flight；The vee tail includes port tailplane
(9), starboard tailplane (10), left tail vane (11) and right tail vane (12)；The port tailplane (9) and the V-shaped arrangement of the starboard tailplane (10),
Its lower edge is connected along the rear end of the connecting rod (8) direction and the connecting rod (8) respectively, the left tail vane (11) and the right side
Tail vane (12) is respectively symmetrically the trailing edge for being arranged in the port tailplane (9) and the starboard tailplane (10), and can be in respective leading edge
Lower deflection.
Preferably, the angular range that the port aileron rudder face (2) and the starboard aileron rudder face (3) are deflected up and down is ± 40 °
Within.
Preferably, within the angular range that the left tail vane (11) and the right tail vane (12) are deflected up and down is ± 40 °.
Preferably, the flapping wing drive system is positioned at the position of the 40%-60% of total length before and after minute vehicle.
The combined type minute vehicle that the employing flapping wing that the present invention is provided drives has advantages below：
(1) present invention drives the type of drive for replacing traditional propeller to drive as minute vehicle using flapping wing,
Under low reynolds number environment, flapping wing is improve micro- under low reynolds number environment with the pneumatic efficiency higher than traditional propeller
The propulsive efficiency of type aircraft；
(2) wing is fluttered in addition to it can produce thrust and drive aircraft and advance, itself can also produce certain lift, and
During fluttering, the air that can be ordered about above flows backward, so as to lift the lift efficiency of fixed-wing, thus using this multiple
Box-like layout, can lift the lift efficiency of whole minute vehicle to a certain extent.
Description of the drawings
The dimensional structure diagram of the combined type minute vehicle that Fig. 1 is driven for the employing flapping wing that the present invention is provided；
The top view of the combined type minute vehicle that Fig. 2 is driven for the employing flapping wing that the present invention is provided.
Specific embodiment
In order that technical problem solved by the invention, technical scheme and beneficial effect become more apparent, below in conjunction with
Drawings and Examples, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein only to
The present invention is explained, is not intended to limit the present invention.
For small size propeller under low reynolds number environment the low problem of propulsive efficiency, the present invention using flapping wing replacement
A kind of driving means of the traditional propeller as minute vehicle, there is provided the combined type minute vehicle that employing flapping wing drives.
According to aerodynamic result of study, under the conditions of low reynolds number, flapping wing has higher drive efficiency, thus adopts flapping wing
Drive and replace propeller to drive the performance that can improve minute vehicle.
With reference to Fig. 1 and Fig. 2, the combined type minute vehicle of the employing flapping wing driving that the present invention is provided, including fixed-wing liter
Power face, flapping wing drive system, vee tail and connecting rod 8.The front end of connecting rod 8 is installed by fixed-wing lifting surface；The tail of connecting rod 8
End is installed by vee tail；Flapping wing drive system is installed in connecting rod 8, and is located between fixed-wing lifting surface and vee tail, is led to
Often before and after minute vehicle between the 40%-60% of total length, particular location need to by related aerodynamic analysis and test come
It is determined that.Thus constitute whole aircraft.Hereinafter each part is discussed in detail respectively：
(1) fixed-wing lifting surface
Fixed-wing lifting surface is used to produce the rolling needed for the lift and aircraft manufacturing technology needed for aircraft flight
Torque；Fixed-wing lifting surface includes wing 1, port aileron rudder face 2 and starboard aileron rudder face 3；Wing 1 is square that wing section is certain aerofoil profile
The shape wing, scope of its aspect ratio in 6-10, the central authorities of wing 1 and the front end of connecting rod 8 are connected, and leading edge and the connection of wing 1
The axis of bar 8 is vertical；Port aileron rudder face 2 and starboard aileron rudder face 3 are respectively positioned at the left and right sides of 1 trailing edge of wing, port aileron rudder face 2
It is able to be deflected around respective leading edge up and down with starboard aileron rudder face 3, range of deflection angles is within ± 40 °.
(2) flapping wing drive system
Flapping wing drive system thrust required when flying before being used to provide aircraft；Flapping wing drive system include a left side flutter the wing 4,
The right side is fluttered the wing 5, mechanism's installing rack 6 and flapping mechanism 7；Mechanism's installing rack 6 is connected with connecting rod 8, and is located at fixed-wing lifting surface
And vee tail between；Flapping mechanism 7 is fixed on mechanism's installing rack 6；The wing 4 is fluttered on a left side and the right side is fluttered, and the wing 5 is symmetrically positioned in connecting rod
8 both sides, and rocking arm of fluttering with the left and right of flapping mechanism 7 respectively is connected.
(3) vee tail
Vee tail is used to provide stability and control during aircraft flight；Vee tail includes port tailplane 9, starboard tailplane
10th, left tail vane 11 and right tail vane 12；10 V-shaped arrangement of port tailplane 9 and starboard tailplane, its lower edge is respectively along 8 direction of connecting rod and company
The rear end of extension bar 8 is connected, and left tail vane 11 and right tail vane 12 are respectively symmetrically the trailing edge for being arranged in port tailplane 9 and starboard tailplane 10, and energy
Deflected around respective leading edge up and down, range of deflection angles is within ± 40 °.
The combined type minute vehicle that the employing flapping wing that the present invention is provided drives, its flight theory is：
Fixed-wing lifting surface is mainly for generation of the lift needed for aircraft flight, while the port aileron rudder by its trailing edge
The differential deflection of face 2 and starboard aileron rudder face 3 provides the rolling moment needed for aircraft manufacturing technology；Flapping wing drive system is mainly used
Required thrust when flying before aircraft is provided；Vee tail is mainly used in providing stability and control during aircraft flight,
Pitching moment aircraft manufacturing technology needed for can be provided when left tail vane 11 and the linkage deflection of right tail vane wherein, when left tail vane
11 and the yawing needed for aircraft manufacturing technology can be provided during the differential deflection of right tail vane；Fixed-wing lifting surface, flapping wing drive
Dynamic system and vee tail are fixed together by connecting rod 8, so as to constitute whole aircraft.
In sum, the combined type minute vehicle that the employing flapping wing that the present invention is provided drives has advantages below：
(1) present invention drives the type of drive for replacing traditional propeller to drive as minute vehicle using flapping wing,
Under low reynolds number environment, flapping wing is improve micro- under low reynolds number environment with the pneumatic efficiency higher than traditional propeller
The propulsive efficiency of type aircraft；
(2) wing is fluttered in addition to it can produce thrust and drive aircraft and advance, itself can also produce certain lift, and
During fluttering, the air that can be ordered about above flows backward, so as to lift the lift efficiency of fixed-wing, thus using this multiple
Box-like layout, can lift the lift efficiency of whole minute vehicle to a certain extent.
The above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, under the premise without departing from the principles of the invention, some improvements and modifications can also be made, these improvements and modifications also should
Depending on protection scope of the present invention.
Claims (4)
1. the combined type minute vehicle that a kind of employing flapping wing drives, it is characterised in that include：Fixed-wing lifting surface, flapping wing drive
Dynamic system, vee tail and connecting rod (8)；
The front end of the connecting rod (8) is installed by the fixed-wing lifting surface；The tail end of the connecting rod (8) installs the V-type tail
The wing；The flapping wing drive system is installed in the connecting rod (8), and is located at the fixed-wing lifting surface and the vee tail
Between；
Wherein, the fixed-wing lifting surface is used to produce needed for the lift and aircraft manufacturing technology needed for aircraft flight
Rolling moment；The fixed-wing lifting surface includes wing (1), port aileron rudder face (2) and starboard aileron rudder face (3)；The wing (1)
For RECTANGULAR WINGS, scope of its aspect ratio in 6-10, the front end of the central and described connecting rod (8) of the wing (1) are connected, and institute
The leading edge for stating wing (1) is vertical with the axis of the connecting rod (8)；The port aileron rudder face (2) and the starboard aileron rudder face (3)
The left and right sides of the wing (1) trailing edge, the port aileron rudder face (2) and the starboard aileron rudder face (3) difference energy are located at respectively
It is enough to be deflected around respective leading edge up and down；
Flapping wing drive system thrust required when flying before being used to provide aircraft；The flapping wing drive system includes that a left side is fluttered
The wing (4), the right side are fluttered the wing (5), mechanism's installing rack (6) and flapping mechanism (7)；Mechanism's installing rack (6) and the connecting rod (8)
It is connected, and is located between the fixed-wing lifting surface and the vee tail；The flapping mechanism (7) is fixed in mechanism's peace
Shelve on (6)；The wing (4) is fluttered on the left side and the right side the is fluttered wing (5) is symmetrically positioned in both sides of the connecting rod (8), and respectively
With the left and right of the flapping mechanism (7) flutter rocking arm be connected；
The vee tail is used to provide stability and control during aircraft flight；The vee tail include port tailplane (9),
Starboard tailplane (10), left tail vane (11) and right tail vane (12)；The port tailplane (9) and the V-shaped arrangement of the starboard tailplane (10), under which
Edge is connected along the rear end of the connecting rod (8) direction and the connecting rod (8) respectively, the left tail vane (11) and the right tail vane
(12) trailing edge for being arranged in the port tailplane (9) and the starboard tailplane (10) is respectively symmetrically, and can be inclined up and down around respective leading edge
Turn.
2. the combined type minute vehicle that employing flapping wing according to claim 1 drives, it is characterised in that the port aileron
Within the angular range that rudder face (2) and the starboard aileron rudder face (3) are deflected up and down is ± 40 °.
3. the combined type minute vehicle that employing flapping wing according to claim 1 drives, it is characterised in that the left tail vane
(11) and within the angular range that deflects up and down of the right tail vane (12) is ± 40 °.
4. the combined type minute vehicle that employing flapping wing according to claim 1 drives, it is characterised in that the flapping wing drives
Dynamic system is positioned at the position of the 40%-60% of total length before and after minute vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611181954.2A CN106585982A (en) | 2016-12-20 | 2016-12-20 | Combined type micro air vehicle driven by flapping wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611181954.2A CN106585982A (en) | 2016-12-20 | 2016-12-20 | Combined type micro air vehicle driven by flapping wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106585982A true CN106585982A (en) | 2017-04-26 |
Family
ID=58600054
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611181954.2A Pending CN106585982A (en) | 2016-12-20 | 2016-12-20 | Combined type micro air vehicle driven by flapping wings |
Country Status (1)
| Country | Link |
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| CN (1) | CN106585982A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109094777A (en) * | 2017-06-21 | 2018-12-28 | 北京航空航天大学 | A kind of flapping wings type can be changed wing unmanned plane |
| CN110510109A (en) * | 2019-09-20 | 2019-11-29 | 仿翼(北京)科技有限公司 | Electromagnetic steering engine and aircraft |
| CN110758731A (en) * | 2019-10-22 | 2020-02-07 | 北京航空航天大学 | Fixed wing flapping wing combined type aircraft |
| CN111017207A (en) * | 2019-12-16 | 2020-04-17 | 北京航空航天大学 | Flapping mechanism of combined type aircraft |
| WO2020143738A1 (en) * | 2019-01-11 | 2020-07-16 | 魏朝阳 | Differential variable-load flapping wing and operation method thereof |
| CN112078791A (en) * | 2020-09-10 | 2020-12-15 | 哈尔滨工业大学（深圳） | Flapping wing aircraft |
| CN112319801A (en) * | 2020-11-24 | 2021-02-05 | 北京航空航天大学 | Flapping-effect-based large high-mobility hovering flapping-wing aircraft |
| CN112339991A (en) * | 2020-11-05 | 2021-02-09 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
| WO2022078258A1 (en) * | 2020-10-12 | 2022-04-21 | 汉王科技股份有限公司 | Flapping wing aircraft |
| CN116674747A (en) * | 2023-08-03 | 2023-09-01 | 西南石油大学 | Flexible flapping wing and ducted propeller hybrid-driven simulated baton floating aircraft |
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| FR565853A (en) * | 1923-05-07 | 1924-02-05 | Aircraft without engine powered by flapping wings | |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109094777A (en) * | 2017-06-21 | 2018-12-28 | 北京航空航天大学 | A kind of flapping wings type can be changed wing unmanned plane |
| WO2020143738A1 (en) * | 2019-01-11 | 2020-07-16 | 魏朝阳 | Differential variable-load flapping wing and operation method thereof |
| CN110510109A (en) * | 2019-09-20 | 2019-11-29 | 仿翼(北京)科技有限公司 | Electromagnetic steering engine and aircraft |
| CN110758731A (en) * | 2019-10-22 | 2020-02-07 | 北京航空航天大学 | Fixed wing flapping wing combined type aircraft |
| CN110758731B (en) * | 2019-10-22 | 2021-01-26 | 北京航空航天大学 | Fixed wing flapping wing combined type aircraft |
| CN111017207B (en) * | 2019-12-16 | 2021-01-05 | 北京航空航天大学 | Flapping mechanism of combined type aircraft |
| CN111017207A (en) * | 2019-12-16 | 2020-04-17 | 北京航空航天大学 | Flapping mechanism of combined type aircraft |
| CN112078791A (en) * | 2020-09-10 | 2020-12-15 | 哈尔滨工业大学（深圳） | Flapping wing aircraft |
| WO2022078258A1 (en) * | 2020-10-12 | 2022-04-21 | 汉王科技股份有限公司 | Flapping wing aircraft |
| CN112339991A (en) * | 2020-11-05 | 2021-02-09 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
| CN112339991B (en) * | 2020-11-05 | 2023-01-03 | 江西洪都航空工业股份有限公司 | Aircraft tail structure for stability and drag enhancement |
| CN112319801A (en) * | 2020-11-24 | 2021-02-05 | 北京航空航天大学 | Flapping-effect-based large high-mobility hovering flapping-wing aircraft |
| CN116674747A (en) * | 2023-08-03 | 2023-09-01 | 西南石油大学 | Flexible flapping wing and ducted propeller hybrid-driven simulated baton floating aircraft |
| CN116674747B (en) * | 2023-08-03 | 2023-10-20 | 西南石油大学 | Flexible flapping wing and ducted propeller hybrid-driven simulated baton floating aircraft |
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Application publication date: 20170426 |