CN103693194B - One can be verted quadrotor - Google Patents
One can be verted quadrotor Download PDFInfo
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- CN103693194B CN103693194B CN201310691329.2A CN201310691329A CN103693194B CN 103693194 B CN103693194 B CN 103693194B CN 201310691329 A CN201310691329 A CN 201310691329A CN 103693194 B CN103693194 B CN 103693194B
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Abstract
One can be verted quadrotor, comprise fuselage, main tilting rotor, auxiliary tilting rotor, rear, host wing, auxiliary wing, rear is arranged on the afterbody of fuselage, two host wings are arranged on two sides of fuselage respectively, two auxiliary wings are arranged on two sides of rear respectively, host wing is provided with main tilting rotor away from one end of fuselage, auxiliary wing is provided with auxiliary tilting rotor away from one end of rear, main tilting rotor and auxiliary tilting rotor can along wing axial-rotations, and rear can along fuselage axial-rotation.Improve the carrying capacity of existing tiltrotor aircraft; Improve the handling of its landing stage; Improve the safety performance of flight; Increase its inner carrying space; Performance is flown before improving it; Save primary control surface, make structure relaxed (simplified structure).
Description
Technical field
The present invention is a kind of aircraft, belongs to airmanship field.
Background technology
Tiltrotor aircraft be a kind of can vertical takeoff and landing, again can the aircraft of high speed cruise flight.Tilting rotor, verting namely by rotor, regulates the state of flight of aircraft: during vertical takeoff and landing, and rotor axis direction upwards produces lift; Before when flying, rotor axis direction produces pulling force forward.
Existing tiltrotor aircraft is mainly two tilting rotors.Two tiltrotor aircrafts have some shortcomings: due to fuselage arrangement restriction, rotor diameter is less, causes its carrying capacity limited; In the landing stage, two tilting rotors are ensureing, under the prerequisite that resultant lift is constant, to provide actuating force (moment) neatly; Two tilting rotors must be arranged near fuselage centroid position, cause airframe structure shorter, inherent space constraints.
CN103072688A discloses one and can to vert quadrotor, the rotor steering hardware carrying rotor installed by this aircraft on four fixed wings, when rotor steering hardware verts, drive rotor rotational, before realizing the level of aircraft, fly the conversion with vertical lift pattern.Which employs the way of aircraft rear end rotor lower than front end rotor height to avoid the wake zone of front end rotor, because the diff-H of aircraft front and back end rotor can not be too large, rear end rotor in this way can not be made to avoid the wake zone of front end rotor completely, still there is large risk.
Summary of the invention
In order to overcome the defect of existing tiltrotor aircraft design, the present invention proposes four tiltrotor aircrafts of the rotatable distortion of a kind of rear.
The present invention realizes the technical scheme that its function adopts: one can be verted quadrotor, comprise fuselage, main tilting rotor, auxiliary tilting rotor, rear, host wing, auxiliary wing, rear is arranged on the afterbody of fuselage, two host wings are arranged on two sides of fuselage respectively, two auxiliary wings are arranged on two sides of rear respectively, host wing is provided with main tilting rotor away from one end of fuselage, auxiliary wing is provided with auxiliary tilting rotor away from one end of rear, main tilting rotor and auxiliary tilting rotor can along wing axial-rotations, rear can along fuselage axial-rotation.
Preferably: during horizontal flight, auxiliary wing and host wing are at an angle of 90.
Preferably: the size of main tilting rotor is greater than the size of auxiliary tilting rotor.
Preferably: the below of main tilting rotor and auxiliary tilting rotor is provided with inlet channel.
Preferably: the rotative speed of each main tilting rotor and each auxiliary tilting rotor, tilt angle and hand of rotation can control separately.
The invention has the beneficial effects as follows: the carrying capacity improving existing tiltrotor aircraft; Improve the handling of its landing stage; Improve the safety performance of flight; Increase its inner carrying space; Performance is flown before improving it; Save primary control surface, make structure relaxed (simplified structure).
Accompanying drawing explanation
Fig. 1 is a kind of vertical takeoff and landing view of the quadrotor that verts.
Fig. 2 is that a kind of landing-front of the quadrotor that verts flies transformation condition schematic diagram.
View is flown before a kind of quadrotor that verts of Fig. 3.
Reference numeral title is as follows: 1, fuselage; 2, main tilting rotor; 3, auxiliary tilting rotor; 4, rear; 5, host wing; 6, auxiliary wing; 7, inlet channel.
Detailed description of the invention
As shown in the figure.One can be verted quadrotor, comprise fuselage 1, main tilting rotor 2, auxiliary tilting rotor 3, rear 4, host wing 5, auxiliary wing 6, rear 4 is arranged on the afterbody of fuselage 1, two host wings 5 are arranged on two sides of fuselage 1, two auxiliary wings 6 are arranged on two sides of rear 4, host wing 5 is provided with main tilting rotor 2 away from one end of fuselage 1, auxiliary wing 6 is provided with auxiliary tilting rotor 3 away from one end of rear 4, main tilting rotor 2 can along the axial-rotation of wing 5, and auxiliary tilting rotor 3 can along the axial-rotation of wing 6.When aircraft takeoff, the rotor of main tilting rotor 2 and auxiliary tilting rotor 3, makes aircraft acquisition power upwards upward during rotor wing rotation.When aircraft needs to fly forward, main tilting rotor 2 turns over 90 degree forward with auxiliary tilting rotor 3, and the rotor making main tilting rotor 2 and auxiliary tilting rotor 3, makes aircraft acquisition power forward forward during rotor wing rotation.Due to aircraft fly forward time, auxiliary tilting rotor 3 easily falls into the wake zone of main tilting rotor 2, make rear 4 can along fuselage 1 axial-rotation, rear 4 90-degree rotation is made when normal flight, an auxiliary tilting rotor 3 is made to be positioned at the top of aircraft, an auxiliary tilting rotor 3 is positioned at the below of aircraft, thus makes two auxiliary tilting rotors 3 all avoid the wake zone of main tilting rotor 2, ensure that the safety of aircraft flight.
Increase the less auxiliary tilting rotor 3 of two sizes at the rear 4 at main tilting rotor 2 rear, the utilization of auxiliary tilting rotor 3, certain lift can be provided thus improve carrying capacity; Each main tilting rotor 2 and each auxiliary tilting rotor 3 revolve rotative speed, hand of rotation, tilt angle can control separately.In the landing stage, main tilting rotor 2 lift remains unchanged, and auxiliary tilting rotor 3 provides actuating force (moment) by the change of tilt angle and rotating speed, thus improves road-holding property; Main tilting rotor 2 can use longer fuselage in front, the auxiliary posterior aerodynamic arrangement of tilting rotor 3, thus increases inner space.That is the size of main tilting rotor 2 is greater than the size of auxiliary tilting rotor 3.
In order to promote the carrying capacity of aircraft further, the below of main tilting rotor 2 and auxiliary tilting rotor 3 is provided with inlet channel 7.
Landing state as shown in Figure 1.Now, rotatable rear 4 is horizontality, and main tilting rotor 2 and auxiliary tilting rotor 3 axes normal are upwards.Now, main tilting rotor 2 can provide prevailing lift, and auxiliary tilting rotor 3 provides auxiliary lifting, and provides operating effort (moment) by the change of gyroplane rotate speed and rotor tilt angle.
Landing as shown in Figure 2-front flies transformation condition.Now, rotatable rear 4 is horizontality, and main tilting rotor 2 and auxiliary tilting rotor 3 axis vert 90 °, and axis is horizontal forward by being converted to vertically upward of floating state.
Before fly state as shown in Figure 3.Now, rotatable rear 4 half-twist is vertical state, and forward, that is, during aircraft horizontal flight, auxiliary wing becomes an angle of 90 degrees with host wing for main tilting rotor 2 and auxiliary tilting rotor 3 axis horizontal.Auxiliary tilting rotor 3 is in outside main tilting rotor 2 wake effect district.
Claims (5)
1. the quadrotor that can vert, it is characterized in that: comprise fuselage (1), main tilting rotor (2), auxiliary tilting rotor (3), rear (4), host wing (5), auxiliary wing (6), rear (4) is arranged on the afterbody of fuselage (1), two host wings (5) are arranged on two sides of fuselage (1) respectively, two auxiliary wings (6) are arranged on two sides of rear (4) respectively, host wing (5) is provided with main tilting rotor (2) away from one end of fuselage (1), auxiliary wing (6) is provided with auxiliary tilting rotor (3) away from one end of rear (4), main tilting rotor (2) and auxiliary tilting rotor (3) can along wings (5, 6) axial-rotation, rear (4) can along fuselage (1) axial-rotation.
2. aircraft according to claim 1, is characterized in that: during horizontal flight, and auxiliary wing (6) and host wing (5) are at an angle of 90.
3. aircraft according to claim 1, is characterized in that: the size of main tilting rotor (2) is greater than the size of auxiliary tilting rotor (3).
4. aircraft according to claim 1, is characterized in that: the below of main tilting rotor (2) and auxiliary tilting rotor (3) is provided with inlet channel (7).
5. aircraft according to claim 1, is characterized in that: the rotative speed of each main tilting rotor (2) and each auxiliary tilting rotor (3), tilt angle and hand of rotation can control separately.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310691329.2A CN103693194B (en) | 2013-12-17 | 2013-12-17 | One can be verted quadrotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310691329.2A CN103693194B (en) | 2013-12-17 | 2013-12-17 | One can be verted quadrotor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103693194A CN103693194A (en) | 2014-04-02 |
| CN103693194B true CN103693194B (en) | 2015-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201310691329.2A Expired - Fee Related CN103693194B (en) | 2013-12-17 | 2013-12-17 | One can be verted quadrotor |
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| CN (1) | CN103693194B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3486168A1 (en) * | 2017-11-16 | 2019-05-22 | Bell Helicopter Textron Inc. | Extended range quad tiltrotor aircraft |
Families Citing this family (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105035319A (en) * | 2015-07-27 | 2015-11-11 | 江阴市翔诺电子科技有限公司 | Novel vertical take-off and landing air vehicle and control method thereof |
| CN105366046A (en) * | 2015-12-15 | 2016-03-02 | 江苏艾锐泰克无人飞行器科技有限公司 | Fixed-wing air vehicle and control method in vertical posture |
| EP3971084A1 (en) * | 2016-02-22 | 2022-03-23 | SZ DJI Technology Co., Ltd. | Aéronef multi-rotor pliable |
| CN106043686A (en) * | 2016-07-18 | 2016-10-26 | 四川傲势乐翼科技有限公司 | Vertical take-off and landing fixed wing aircraft |
| CN106494614B (en) * | 2016-10-28 | 2018-08-28 | 清华大学 | Aircraft with Horizontal Take-off and Landing and VTOL function |
| CN107757912B (en) * | 2017-03-03 | 2022-01-14 | 珠海磐磊智能科技有限公司 | Power device, aircraft and aircraft control method |
| US10351235B2 (en) | 2017-05-22 | 2019-07-16 | Karem Aircraft, Inc. | EVTOL aircraft using large, variable speed tilt rotors |
| US10752352B2 (en) | 2017-12-07 | 2020-08-25 | Textron Innovations Inc. | Dual rotor propulsion systems for tiltrotor aircraft |
| CN108803643B (en) * | 2018-06-19 | 2021-08-20 | 成都纵横自动化技术股份有限公司 | Flight control method and device, flight controller and composite wing aircraft |
| CN110466752B (en) * | 2019-08-07 | 2021-11-26 | 深圳市道通智能航空技术股份有限公司 | Control method of tilt rotor unmanned aerial vehicle and tilt rotor unmanned aerial vehicle |
| CN110562448A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | Tailstock type unmanned aerial vehicle |
| CN112498678B (en) * | 2020-11-30 | 2023-04-11 | 鹏城实验室 | Carrier-based vertical take-off and landing unmanned aerial vehicle and flight method |
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| US3181810A (en) * | 1961-02-27 | 1965-05-04 | Curtiss Wright Corp | Attitude control system for vtol aircraft |
| US6227481B1 (en) * | 1999-08-06 | 2001-05-08 | Bell Helicopter Textron, Inc. | Method and apparatus for controlling force fights in a rotating shaft |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN203638093U (en) * | 2013-12-17 | 2014-06-11 | 南京航空航天大学 | Tiltable four-rotor aircraft |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2010096104A1 (en) * | 2008-10-03 | 2010-08-26 | Bell Helicopter Textron Inc. | Method and apparatus for aircraft sensor and actuator failure protection using reconfigurable flight control laws |
| US20110001020A1 (en) * | 2009-07-02 | 2011-01-06 | Pavol Forgac | Quad tilt rotor aerial vehicle with stoppable rotors |
-
2013
- 2013-12-17 CN CN201310691329.2A patent/CN103693194B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3181810A (en) * | 1961-02-27 | 1965-05-04 | Curtiss Wright Corp | Attitude control system for vtol aircraft |
| US6227481B1 (en) * | 1999-08-06 | 2001-05-08 | Bell Helicopter Textron, Inc. | Method and apparatus for controlling force fights in a rotating shaft |
| CN102126553A (en) * | 2010-01-12 | 2011-07-20 | 北京航空航天大学 | Vertically taking off and landing small unmanned aerial vehicle |
| CN203638093U (en) * | 2013-12-17 | 2014-06-11 | 南京航空航天大学 | Tiltable four-rotor aircraft |
Non-Patent Citations (1)
| Title |
|---|
| "倾转旋翼机模型及仿真";唐亮;《四川兵工学报》;20121031;第33卷(第10期);全文 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3486168A1 (en) * | 2017-11-16 | 2019-05-22 | Bell Helicopter Textron Inc. | Extended range quad tiltrotor aircraft |
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| Publication number | Publication date |
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| CN103693194A (en) | 2014-04-02 |
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