CN105292460A - Tilt-rotor based on combination of four rotor wings and fixed wing - Google Patents
Tilt-rotor based on combination of four rotor wings and fixed wing Download PDFInfo
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- CN105292460A CN105292460A CN201510660016.XA CN201510660016A CN105292460A CN 105292460 A CN105292460 A CN 105292460A CN 201510660016 A CN201510660016 A CN 201510660016A CN 105292460 A CN105292460 A CN 105292460A
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Abstract
The invention discloses a tilt-rotor based on combination of four rotor wings and a fixed wing. The tilt-rotor is structurally characterized in that a first rotor wing, a second rotor wing, a third rotor wing and a fourth rotor wing are divided into two groups which are respectively symmetrically mounted on the two sides of a tilt-rotor body by two shafts; (1, 2) is a front motor group; (3, 4) is a rear motor group; a middle wing is horizontally mounted on the tilt-rotor body and is vertical to the tilt-rotor body; backswept wings on the two sides are respectively mounted on the two sides of the middle horizontal wing at a backswept angle of 50 degrees. According to the tilt-rotor disclosed by the invention, the four rotor wings and the fixed wing are enabled to share a set of power system to realize vertical takeoff and landing, hovering and cruise level flying; the front and rear tilting motor groups (1, 2) and (3, 4) share a set of tilting device to realize synchronous tilting by a tilting drive shaft, thereby simplifying a tilting structure and improving the operability and stability of the tilt-rotor.
Description
Technical field
The present invention relates to airplane design technology, be specially a kind of tiltrotor aircraft based on four rotors and fixed-wing compound.
Background technology
Taking off and landing and be subject to the restriction in place all to a great extent due to Fixed Wing AirVehicle, often need specific runway for taking off and landing, and it can not hover aloft, not perform some specific aerial missions.
All can not there is verting forward or backward in tradition quadrotor four rotors, on the one hand, when it flies and does before realizing level, require that two gyroplane rotate speeds being in front fuselage reduce, and be in back body two gyroplane rotate speeds increases, produce lift difference because front and back end gyroplane rotate speed is different like this, and then inevitably cause fuselage to produce luffing, fly before making aircraft level to influence each other with vertical lifting; On the other hand, traditional quadrotor limits due to its Design Mechanism, is difficult to reach cruising speed higher as fixed wing.
Tiltrotor aircraft has the advantage of cyclogyro and fixed wing aircraft simultaneously, when vertical takeoff and landing, provides to raising force by rotor, when cruising flight, provides lift by the fixed wing being fixed on fuselage.Existing tiltrotor aircraft mostly is diaxon and verts, as the MV-22 of the U.S., more unstable during very limited and two rotary-wing flight of the load carrying ability of aircraft when the shortcoming of this type of tiltrotor is vertical takeoff and landing.Meanwhile, existing tiltrotor is verted complicated in mechanical structure and process of verting is dangerous.Exactly because above-mentioned shortcoming makes the application of tiltrotor aircraft be extremely restricted.
Summary of the invention
For the above shortcoming or deficiency, the invention provides a kind of tiltrotor aircraft based on four rotors and fixed-wing compound, four rotors and fixed-wing are organically combined, realize the function of vertical takeoff and landing, hovering and cruising level flight, and anteversion and retroversion rotating motor group shares a set of control setup that verts to be verted physical construction and to vert control process by the transmission shaft that the verts simplification that realizes verting, and improves flight stability and the aircraft load carrying ability of tiltrotor.
The present invention is achieved through the following technical solutions: a kind of tiltrotor aircraft based on four rotors and fixed-wing compound, comprises four motors, transmission shaft is verted in fuselage, outside, both sides swept wing, wingtip, vertical tail, the horizontal wing in stage casing, fuselage interior are verted transmission shaft, transmission gear, aileron and tailplane, it is characterized in that: nosing is verted by outside, and transmission shaft is symmetrical installs the first motor and the second motor, middle fuselage is by the horizontal wing in erection of main beam stage casing, back body is verted by outside, and transmission shaft is symmetrical installs the 3rd motor and the 4th motor, fuselage interior is longitudinally installed fuselage interior and to be verted transmission shaft and transmission gear, the described outside transmission shaft that verts is linked together by two transmission gears and the fuselage interior transmission shaft that verts, back body installs tailplane and vertical tail, swept wing is installed with the sweepback angle of 50 ° symmetry respectively in horizontal wing both sides, stage casing, both sides swept wing installs aileron respectively, both sides swept wing end installs wingtip.
First, second, third, fourth electric motor mounting structure of the present invention is the same; Described first, second, third, fourth parameter of electric machine is the same, and adjacent direction of motor rotation is contrary between two.
First motor of the present invention, the second motor, the 3rd motor, the 4th motor by two outsides vert transmission shaft respectively symmetry be arranged on fuselage both sides, a set of rotor respectively installed by first, second, third, fourth motor.
Of the present inventionly control fuselage interior by reclining device and to vert drive axis thus drive the outside transmission shaft that verts that the first motor, the second motor, the 3rd motor, the 4th motor in synchrony are verted; Front and back group of motors shares a set of structure of verting, and realizes synchronously verting.
Four rotors of the present invention and fixed-wing share a set of engine installation, are four rotor mode when vertical takeoff and landing or hovering, control aircraft with four rotor flying control system; When switching to fixed-wing pattern, control aircraft with fixed-wing flight control system.
When aircraft switches to fixed-wing mode process by four rotors, it is 0 ° to 45 ° that first, second, third, fourth motor synchronously tilts forward angle by control system of verting with the drive mechanism that verts, and is still now four rotor master modes; When first, second, third, fourth motor in synchrony tilts forward angle when being greater than 45 °, Automatic control of single chip microcomputer switches to fixed-wing master mode, two groups of motors vert to level attitude to preamble immediately, then controlling aircraft flight attitude in fixed-wing mode, is now fixed-wing master mode.
When aircraft is four rotor mode, controlled the flight attitude of aircraft by the differential controlling first, second, third, fourth motor; And when aircraft is fixed-wing pattern, controlled the flight attitude of aircraft by level of control empennage, vertical tail, aileron.
When receiver receives control signal, microcomputer control system produces four rotors and fixed-wing tilt control signal automatically according to instruction, drives the steering wheel system of verting that first, second, third, fourth motor is verted.
Advantage of the present invention is: make four rotors and fixed-wing share a set of power system and realize vertical takeoff and landing, hovering and cruising level flight, anteversion and retroversion rotating motor group (1,2) (3,4) share a set of reclining device and realize synchronously verting by the transmission shaft that verts, and simplify vert structure and improve road-holding property and the stability of tiltrotor with this.
accompanying drawing illustrates:
Fig. 1 is structural representation of the present invention.
Fig. 2 is motor cabinet structural representation of the present invention.
Fig. 3 is aircraft lateral plan of the present invention.
In Fig. 1,1,2,3,4 be respectively first, second, third, fourth motor, 5,6 is fuselage, and 7,8 for verting transmission shaft outside, 9,13 is both sides swept wing, 10 is wingtip, and 11 is vertical tail, and 12 is the horizontal wing in stage casing, 14 to vert transmission shaft for fuselage interior, 15,16 is transmission gear, and 17,18 is aileron, and 19 is tailplane.
Detailed description of the invention
Describe the present invention below in conjunction with accompanying drawing; Shown in figure 1, Fig. 2 and Fig. 3, the present invention is a kind of tiltrotor aircraft based on four rotors and fixed-wing compound, fuselage 5,6 leading portion is verted by outside, and transmission shaft 8 is symmetrical installs first, second motor, fuselage 5,6 stage casing is by the horizontal wing 12 in erection of main beam stage casing, being verted by outside in fuselage 5,6 rear end, transmission shaft 7 is symmetrical installs the 3rd, the 4th motor, fuselage 5,6 is inner longitudinally to be installed fuselage interior and to vert transmission shaft 14 and transmission gear 15,16, and tailplane 19 and vertical tail 11 are installed in fuselage 5,6 rear end.Swept wing 9,13 is installed with the sweepback angle of 50 ° symmetry respectively in horizontal wing 12 both sides, stage casing, and both sides swept wing 9,13 installs aileron 17,18 respectively, and both sides swept wing 9,13 end installs wingtip 10.
In the present invention, four motors 1,2,3,4 are fixed on outside by motor cabinet as shown in Figure 2 and vert on transmission shaft 7,8, and front motor group (1,2) is the same with rear motor group (3,4) motor used, and adjacent direction of motor rotation is contrary between two.The outside transmission shaft 7,8 that verts is connected by gear 15,16 and fuselage interior transmission shaft 14 and forms the whole drive mechanism that verts, when vert drive axis time drive before and after two groups of motor in synchrony vert.
Principle of work of the present invention is: when aircraft vertical landing of the present invention, and vertically upward, adjacent two direction of motor rotation make moment of torsion of cancelling out each other to first, second, third, fourth rotor on the contrary, produces lift upwards; When aircraft does pitching or travels forward, the rotating speed of front motor group (1,2) and rear motor group (3,4) is different.As aircraft forward time, the rotating speed of front motor group (1,2) rises, and the rotating speed of rear motor group (3,4) rises; When aircraft needs adjustment course angle, the first, the 3rd gyroplane rotate speed rises simultaneously (or decline), and the second, the 4th gyroplane rotate speed declines simultaneously (or rising); When aircraft do move to the left or to the right time, the first, the 4th gyroplane rotate speed rises (or decline), and second, third gyroplane rotate speed declines (or rising).
When aircraft cruises motion with fixed-wing pattern, first, second, third, fourth motor in synchrony tilts forward 90 ° as shown in Figure 3, produce lift by fuselage and wing, then control flight attitude with elevating rudder, yaw rudder, aileron, tailplane, vertical tail.
The tiltrotor aircraft of four rotors of the present invention and fixed-wing compound designs the tiltrotor aircraft being shared a set of engine installation by four rotors and fixed-wing, four rotors and fixed-wing are organically combined, realize vertical takeoff and landing, hovering and equal at a high speed the function flown, and anteversion and retroversion rotating motor group shares a set of control setup that verts to be verted physical construction and to vert control process by the transmission shaft that the verts simplification that realizes verting, and improves flight stability and the aircraft load carrying ability of tiltrotor.
Claims (6)
1., based on a tiltrotor aircraft for four rotors and fixed-wing compound, comprise four motors, transmission shaft is verted in fuselage, outside, both sides swept wing, wingtip, vertical tail, the horizontal wing in stage casing, fuselage interior are verted transmission shaft, transmission gear, aileron and tailplane, it is characterized in that: nosing is verted by outside, and transmission shaft is symmetrical installs the first motor and the second motor, middle fuselage is by the horizontal wing in erection of main beam stage casing, back body is verted by outside, and transmission shaft is symmetrical installs the 3rd motor and the 4th motor, fuselage interior is longitudinally installed fuselage interior and to be verted transmission shaft and transmission gear, the described outside transmission shaft that verts is linked together by two transmission gears and the fuselage interior transmission shaft that verts, back body installs tailplane and vertical tail, swept wing is installed with the sweepback angle of 50 ° symmetry respectively in horizontal wing both sides, stage casing, both sides swept wing installs aileron respectively, both sides swept wing end installs wingtip.
2. a kind of tiltrotor aircraft based on four rotors and fixed-wing compound according to claim 1, is characterized in that: described first, second, third, fourth electric motor mounting structure is the same with parameter, and adjacent direction of motor rotation is contrary between two.
3. a kind of tiltrotor aircraft based on four rotors and fixed-wing compound according to claim 1, is characterized in that: a set of rotor respectively installed by described first, second, third, fourth motor.
4. a kind of tiltrotor aircraft based on four rotors and fixed-wing compound according to claim 1 or 3, it is characterized in that: four rotors and fixed-wing share a set of engine installation, be four rotor mode when vertical takeoff and landing or hovering, control aircraft with four rotor flying control system; When switching to fixed-wing pattern, control aircraft with fixed-wing flight control system.
5. a kind of tiltrotor aircraft based on four rotors and fixed-wing compound according to claim 4, it is characterized in that: when aircraft switches to fixed-wing mode process by four rotors, it is 0 ° to 45 ° that first motor, the second motor, the 3rd motor, the 4th motor synchronously tilt forward angle by vert control system and the drive mechanism that verts, and is still now four rotor master modes; When the first motor, the second motor, the 3rd motor, the 4th motor in synchrony tilt forward angle when being greater than 45 °, Automatic control of single chip microcomputer switches to fixed-wing master mode, two groups of motors vert to level attitude to preamble immediately, then controlling aircraft flight attitude in fixed-wing mode, is now fixed-wing master mode.
6. a kind of tiltrotor aircraft based on four rotors and fixed-wing compound according to claim 5, it is characterized in that: when aircraft is four rotor mode, by control the first motor, the second motor, the 3rd motor, the 4th motor differential control the flight attitude of aircraft; And when aircraft is fixed-wing pattern, controlled the flight attitude of aircraft by level of control empennage, vertical tail, aileron.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510660016.XA CN105292460A (en) | 2015-10-14 | 2015-10-14 | Tilt-rotor based on combination of four rotor wings and fixed wing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510660016.XA CN105292460A (en) | 2015-10-14 | 2015-10-14 | Tilt-rotor based on combination of four rotor wings and fixed wing |
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| CN105292460A true CN105292460A (en) | 2016-02-03 |
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| CN201510660016.XA Pending CN105292460A (en) | 2015-10-14 | 2015-10-14 | Tilt-rotor based on combination of four rotor wings and fixed wing |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN105775128A (en) * | 2016-02-22 | 2016-07-20 | 武汉智能鸟无人机有限公司 | Flight vehicle |
| CN105905291A (en) * | 2016-06-04 | 2016-08-31 | 刘海涛 | Multi-rotor craft with tilting rotors |
| CN106379525A (en) * | 2016-12-01 | 2017-02-08 | 北京猎鹰无人机科技有限公司 | Wing connected unmanned plane |
| CN106585951A (en) * | 2016-12-09 | 2017-04-26 | 上海圣尧智能科技有限公司 | Folding structure and aircraft |
| CN106956773A (en) * | 2017-04-07 | 2017-07-18 | 南昌航空大学 | Tilting rotor formula VUAV and its control method |
| CN107323653A (en) * | 2017-08-21 | 2017-11-07 | 山东蜂巢航空科技有限公司 | One kind vertical lift tilting rotor wing unmanned aerial vehicle and its control method |
| CN107963209A (en) * | 2017-11-17 | 2018-04-27 | 沈阳无距科技有限公司 | Tandem wing tilting rotor wing unmanned aerial vehicle |
| CN108327906A (en) * | 2018-01-31 | 2018-07-27 | 北京临近空间飞行器***工程研究所 | A kind of morphing aircraft |
| CN108482668A (en) * | 2018-05-24 | 2018-09-04 | 深圳智航无人机有限公司 | Tilting type vertically taking off and landing flyer |
| CN108639332A (en) * | 2018-06-12 | 2018-10-12 | 中国科学院工程热物理研究所 | The compound multi-modal flight control method of three rotor wing unmanned aerial vehicles |
| CN108750081A (en) * | 2018-06-05 | 2018-11-06 | 中国人民解放军国防科技大学 | Tilting four-rotor-wing deformable aircraft |
| CN110155317A (en) * | 2019-05-13 | 2019-08-23 | 中国人民解放军国防科技大学 | Oil-electricity hybrid vertical take-off and landing fixed-wing aircraft |
| CN110267876A (en) * | 2017-05-08 | 2019-09-20 | 田瑜 | More rotor lift body aircrafts with tilting rotor |
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2015
- 2015-10-14 CN CN201510660016.XA patent/CN105292460A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105775128A (en) * | 2016-02-22 | 2016-07-20 | 武汉智能鸟无人机有限公司 | Flight vehicle |
| CN105752345A (en) * | 2016-03-18 | 2016-07-13 | 西安交通大学 | Large load long duration multifunctional aircraft for operation |
| CN105905291A (en) * | 2016-06-04 | 2016-08-31 | 刘海涛 | Multi-rotor craft with tilting rotors |
| CN106379525A (en) * | 2016-12-01 | 2017-02-08 | 北京猎鹰无人机科技有限公司 | Wing connected unmanned plane |
| CN106585951A (en) * | 2016-12-09 | 2017-04-26 | 上海圣尧智能科技有限公司 | Folding structure and aircraft |
| CN106956773A (en) * | 2017-04-07 | 2017-07-18 | 南昌航空大学 | Tilting rotor formula VUAV and its control method |
| CN110267876A (en) * | 2017-05-08 | 2019-09-20 | 田瑜 | More rotor lift body aircrafts with tilting rotor |
| CN110267876B (en) * | 2017-05-08 | 2024-02-02 | 上海峰飞航空科技有限公司 | Multi-rotor lifting body aircraft with tiltrotor |
| CN107323653A (en) * | 2017-08-21 | 2017-11-07 | 山东蜂巢航空科技有限公司 | One kind vertical lift tilting rotor wing unmanned aerial vehicle and its control method |
| CN107963209A (en) * | 2017-11-17 | 2018-04-27 | 沈阳无距科技有限公司 | Tandem wing tilting rotor wing unmanned aerial vehicle |
| CN107963209B (en) * | 2017-11-17 | 2020-03-20 | 沈阳无距科技有限公司 | Tandem wing rotor unmanned aerial vehicle that verts |
| CN108327906A (en) * | 2018-01-31 | 2018-07-27 | 北京临近空间飞行器***工程研究所 | A kind of morphing aircraft |
| CN108482668A (en) * | 2018-05-24 | 2018-09-04 | 深圳智航无人机有限公司 | Tilting type vertically taking off and landing flyer |
| CN108750081A (en) * | 2018-06-05 | 2018-11-06 | 中国人民解放军国防科技大学 | Tilting four-rotor-wing deformable aircraft |
| CN108639332A (en) * | 2018-06-12 | 2018-10-12 | 中国科学院工程热物理研究所 | The compound multi-modal flight control method of three rotor wing unmanned aerial vehicles |
| CN110155317A (en) * | 2019-05-13 | 2019-08-23 | 中国人民解放军国防科技大学 | Oil-electricity hybrid vertical take-off and landing fixed-wing aircraft |
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| C06 | Publication | ||
| PB01 | Publication | ||
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Application publication date: 20160203 |