CN103693194A - Tilting four-rotor-wing aircraft - Google Patents
Tilting four-rotor-wing aircraft Download PDFInfo
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- CN103693194A CN103693194A CN201310691329.2A CN201310691329A CN103693194A CN 103693194 A CN103693194 A CN 103693194A CN 201310691329 A CN201310691329 A CN 201310691329A CN 103693194 A CN103693194 A CN 103693194A
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Abstract
The invention provides a tilting four-rotor-wing aircraft, comprising a body, main tilting rotor wings, auxiliary tilting rotor wings, an end-piece, main wings and auxiliary wings, wherein the end-piece is mounted at the tail part of the body; two main wings are mounted at the two sides of the body, respectively; two auxiliary wings are mounted at the two sides of the end-piece, respectively; each main tilting rotor wing is mounted at one end, far away from the body, of each main wing; each auxiliary tilting rotor wing is mounted at one end, far away from the end-piece, of each auxiliary wing; the main tilting rotor wings and the auxiliary tilting rotor wings are capable of rotating in the axial direction of the wings; the end-piece is capable of rotating in the axial direction of the body. The carrying capability of an existing tilting rotor wing aircraft is improved; the controllability of the aircraft at the take-off and landing stages is improved; the safety performance of flying is improved; the internal carrying space of the aircraft is expanded; the forward flight performance of the aircraft is improved; a control vane surface is omitted, so that the structure is light and simple (simplified).
Description
Technical field
The present invention is a kind of aircraft, belongs to airmanship field.
Background technology
Tiltrotor aircraft is a kind of aircraft of can vertical takeoff and landing, again can high-performance cruise flight.Tilting rotor,, by the verting of rotor, regulates the state of flight of aircraft: during vertical takeoff and landing, rotor axis direction upwards produces lift; Before while flying, rotor axis direction produces forward pulling force.
Existing tiltrotor aircraft is mainly two tilting rotors of sending out.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 guaranteeing, under the constant prerequisite of resultant lift, can not to provide neatly actuating force (moment); Two tilting rotors must be arranged near fuselage centroid position, cause airframe structure shorter, and inner space is limited.
CN103072688A has announced a kind of quadrotor that verts, this aircraft is installed the rotor steering hardware that carries rotor on four fixed wings, when rotor steering hardware verts, drive rotor to rotate, realize the conversion flying before the level of aircraft with vertical lift pattern.It has adopted aircraft rear end rotor lower than the way of 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, in this way can not make rear end rotor 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: a kind of quadrotor that verts, 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 respectively two sides of fuselage, two auxiliary wings are arranged on respectively two sides of rear, 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 be along wing axial-rotations, rear can be 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 be controlled separately.
The invention has the beneficial effects as follows: the carrying capacity that improves existing tiltrotor aircraft; Improve the handling of its landing stage; Improve the safety performance of flight; Increase its inner delivery space; Before improving it, fly performance; 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 a kind of landing-front transformation condition schematic diagram that flies of the quadrotor that verts.
Before a kind of quadrotor that verts of Fig. 3, fly view.
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.
The specific embodiment
As shown in the figure.A kind of quadrotor that verts, 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 be along the axial-rotation of wing 5, and auxiliary tilting rotor 3 can be along the axial-rotation of wing 6.When aircraft takeoff, the rotor of main tilting rotor 2 and auxiliary tilting rotor 3, makes aircraft obtain power upwards upward during rotor wing rotation.When aircraft need to fly forward, main tilting rotor 2 turns over 90 degree forward with auxiliary tilting rotor 3, makes the rotor of main tilting rotor 2 and auxiliary tilting rotor 3 forward, makes aircraft obtain power forward during rotor wing rotation.While flying forward due to aircraft, auxiliary tilting rotor 3 easily falls into the wake zone of main tilting rotor 2, make the rear 4 can be along fuselage 1 axial-rotation, when normal flight, make rear 4 90-degree rotations, make an auxiliary tilting rotor 3 be positioned at the top of aircraft, an auxiliary tilting rotor 3 is positioned at the below of aircraft, thereby makes two auxiliary tilting rotors 3 all avoid the wake zone of main tilting rotor 2, has guaranteed the safety of aircraft flight.
Rear 4 at main tilting rotor 2 rears increases by two auxiliary tilting rotors 3 that size is less, the utilization of auxiliary tilting rotor 3, thus can provide certain lift to improve carrying capacity; The revolving rotative speed, hand of rotation, tilt angle and can control separately of each main tilting rotor 2 and each auxiliary tilting rotor 3.In the landing stage, main tilting rotor 2 lift remain unchanged, and auxiliary tilting rotor 3 provides actuating force (moment) by the variation of tilt angle and rotating speed, thereby improves road-holding property; Main tilting rotor 2 front, auxiliary tilting rotor 3 after aerodynamic arrangement can use longer fuselage, thereby increased inner space.That is to say that the size of main tilting rotor 2 is greater than the size of auxiliary tilting rotor 3.
In order further to promote the carrying capacity of aircraft, 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 axis are vertically upward.Now, main tilting rotor 2 can provide main lift, and auxiliary tilting rotor 3 provides auxiliary lifting, and provides operating effort (moment) by the variation of gyroplane rotate speed and rotor tilt angle.
Landing as shown in Figure 2-front transformation condition that flies.Now, rotatable rear 4 is horizontality, and main tilting rotor 2 and auxiliary tilting rotor 3 axis vert 90 °, and axis by the level that is converted to vertically upward of floating state forward.
As shown in Figure 3, fly state.Now, rotatable rear 4 half-twists, are vertical state, and main tilting rotor 2 and auxiliary tilting rotor 3 axis horizontal forward, that is to say, during aircraft horizontal flight, auxiliary wing becomes an angle of 90 degrees with host wing.Auxiliary tilting rotor 3 is outside main tilting rotor 2 wake effect districts.
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 respectively two sides of fuselage (1), two auxiliary wings (6) are arranged on respectively 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 be along wing (5 with auxiliary tilting rotor (3), 6) axial-rotation, rear (4) can be along fuselage (1) axial-rotation.
2. aircraft according to claim 1, is characterized in that: during horizontal flight, 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: rotative speed, tilt angle and the hand of rotation of each main tilting rotor (2) and each auxiliary tilting rotor (3) can be controlled 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 |
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| CN103693194A true CN103693194A (en) | 2014-04-02 |
| CN103693194B CN103693194B (en) | 2015-11-18 |
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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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Cited By (13)
| 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 |
| 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 |
| CN106494614A (en) * | 2016-10-28 | 2017-03-15 | 清华大学 | Aircraft |
| CN107757912A (en) * | 2017-03-03 | 2018-03-06 | 珠海磐磊智能科技有限公司 | Power set, aircraft and flying vehicles control method |
| CN108698685A (en) * | 2016-02-22 | 2018-10-23 | 深圳市大疆创新科技有限公司 | Unmanned vehicle and its rack, external member, assemble method and operating method |
| CN108803643A (en) * | 2018-06-19 | 2018-11-13 | 成都纵横自动化技术有限公司 | Flight control method, device, flight controller and compound rotor aircraft |
| CN110466752A (en) * | 2019-08-07 | 2019-11-19 | 深圳市道通智能航空技术有限公司 | A kind of control method and tilting rotor wing unmanned aerial vehicle of tilting rotor wing 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 |
| US10696391B2 (en) | 2017-11-16 | 2020-06-30 | Textron Innovations Inc. | Extended range quad tiltrotor aircraft |
| US10752352B2 (en) | 2017-12-07 | 2020-08-25 | Textron Innovations Inc. | Dual rotor propulsion systems for tiltrotor aircraft |
| EP3630603A4 (en) * | 2017-05-22 | 2021-03-03 | Karem Aircraft, Inc. | Evtol aircraft using large, variable speed tilt rotors |
| CN112498678A (en) * | 2020-11-30 | 2021-03-16 | 鹏城实验室 | Carrier-based vertical take-off and landing unmanned aerial vehicle and flight method |
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Cited By (23)
| 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 |
| CN108698685B (en) * | 2016-02-22 | 2021-11-02 | 深圳市大疆创新科技有限公司 | Unmanned aerial vehicle, frame, kit, assembly method and operation method thereof |
| US11427319B2 (en) | 2016-02-22 | 2022-08-30 | SZ DJI Technology Co., Ltd. | Foldable multi-rotor aerial vehicle |
| CN108698685A (en) * | 2016-02-22 | 2018-10-23 | 深圳市大疆创新科技有限公司 | Unmanned vehicle and its rack, external member, assemble method and operating method |
| 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 |
| CN106494614A (en) * | 2016-10-28 | 2017-03-15 | 清华大学 | Aircraft |
| 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 |
| CN107757912A (en) * | 2017-03-03 | 2018-03-06 | 珠海磐磊智能科技有限公司 | Power set, aircraft and flying vehicles control method |
| EP3630603A4 (en) * | 2017-05-22 | 2021-03-03 | Karem Aircraft, Inc. | Evtol aircraft using large, variable speed tilt rotors |
| KR20230005442A (en) * | 2017-05-22 | 2023-01-09 | 오버에어, 인코퍼레이티드 | Evtol aircraft using large, variable speed tilt rotors |
| US11964755B2 (en) | 2017-05-22 | 2024-04-23 | Overair, Inc. | Tilt actuator for aircraft |
| JP7466963B2 (en) | 2017-05-22 | 2024-04-15 | オーバーエアー インコーポレイテッド | Large variable-speed tilt rotor eVTOL aircraft |
| KR102627083B1 (en) * | 2017-05-22 | 2024-01-18 | 오버에어, 인코퍼레이티드 | Evtol aircraft using large, variable speed tilt rotors |
| KR102483971B1 (en) | 2017-05-22 | 2023-01-02 | 오버에어, 인코퍼레이티드 | Evtol aircraft using large, variable speed tilt rotors |
| KR20220075239A (en) * | 2017-05-22 | 2022-06-07 | 오버에어, 인코퍼레이티드 | Evtol aircraft using large, variable speed tilt rotors |
| US10696391B2 (en) | 2017-11-16 | 2020-06-30 | Textron Innovations Inc. | Extended range quad tiltrotor aircraft |
| US10752352B2 (en) | 2017-12-07 | 2020-08-25 | Textron Innovations Inc. | Dual rotor propulsion systems for tiltrotor aircraft |
| CN108803643A (en) * | 2018-06-19 | 2018-11-13 | 成都纵横自动化技术有限公司 | Flight control method, device, flight controller and compound rotor 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 |
| CN110466752A (en) * | 2019-08-07 | 2019-11-19 | 深圳市道通智能航空技术有限公司 | A kind of control method and tilting rotor wing unmanned aerial vehicle of tilting rotor wing 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 |
| CN112498678A (en) * | 2020-11-30 | 2021-03-16 | 鹏城实验室 | Carrier-based vertical take-off and landing unmanned aerial vehicle and flight method |
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| CN103693194B (en) | 2015-11-18 |
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