CN106986005B - Tilting structure of oil-driven tilting rotary wing aircraft - Google Patents
Tilting structure of oil-driven tilting rotary wing aircraft Download PDFInfo
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- CN106986005B CN106986005B CN201710198177.0A CN201710198177A CN106986005B CN 106986005 B CN106986005 B CN 106986005B CN 201710198177 A CN201710198177 A CN 201710198177A CN 106986005 B CN106986005 B CN 106986005B
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- 230000005540 biological transmission Effects 0.000 claims abstract description 57
- 230000007246 mechanism Effects 0.000 claims abstract description 30
- 230000008878 coupling Effects 0.000 claims description 11
- 238000010168 coupling process Methods 0.000 claims description 11
- 238000005859 coupling reaction Methods 0.000 claims description 11
- 210000003050 axon Anatomy 0.000 claims description 3
- 238000000034 method Methods 0.000 description 7
- 230000008569 process Effects 0.000 description 5
- 230000007547 defect Effects 0.000 description 4
- 230000033001 locomotion Effects 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 241001631457 Cannula Species 0.000 description 2
- 241000272184 Falconiformes Species 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000002360 explosive Substances 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 238000005406 washing Methods 0.000 description 2
- 241000566150 Pandion haliaetus Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
- B64C13/24—Transmitting means
- B64C13/38—Transmitting means with power amplification
- B64C13/50—Transmitting means with power amplification using electrical energy
- B64C13/504—Transmitting means with power amplification using electrical energy using electro-hydrostatic actuators [EHA's]
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Automation & Control Theory (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- General Details Of Gearings (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention relates to the field of spacecraft power machinery, and provides a tilting structure of an oil-driven tilting rotor aircraft, which comprises a transmission shafting, an L-shaped commutator, a transmission bearing group, a tilting bearing group and an electric push rod, wherein the transmission shafting is connected with the transmission bearing group; the transmission shaft system is arranged in the wing and is used for transmitting power; the L-shaped commutator comprises a driving bevel gear and a driven bevel gear, the output end of a transmission shafting is connected with the driving bevel gear, and the driving bevel gear is meshed with the driven bevel gear; the driven bevel gear is connected with the propeller pitch-changing structure; the transmission bearing group supports the drive bevel gear to rotate at a high speed in the fixed flange; the tilting bearing group supports the L-shaped commutator to tilt around the outer circle of the fixed flange under the driving of the electric push rod; the transmission shaft system is coaxial with the rotation center of the L-shaped commutator. The invention solves the problem of large-load and large-range endurance of the electric propeller aircraft, is suitable for the tilting mechanism of a small and medium unmanned aerial vehicle, and has the advantages of light weight, simple structure, modularized design, simple assembly and easy disassembly and assembly.
Description
Technical Field
The invention relates to the field of spacecraft power machinery, in particular to a tilting structure of an oil-actuated tilting rotor aircraft.
Background
Tilting rotor: in the form of an airplane, the airplane can generate lift upwards through a propeller to fly like a rotor wing of a helicopter; the propeller can also be tilted to a horizontal position for fixed wing flight.
In the aspect of tilting mechanism, as the existing active tilting rotorcraft, the V22 hawk acts similarly, but the engine of the tilting mechanism tilts along with the propeller, so that the transmission is simple, but the tilting mechanism is too complex. V22 causes overlarge wing end load because the engine tilts along with the propeller, and high requirements are put on the performance of the engine and the operation of a pilot, so that the safety performance is slightly poor; v280 is expected to relieve the technical problem of V22, but cannot be thoroughly solved, is difficult to transplant on a small and medium-sized unmanned aerial vehicle sensitive to space and weight due to the current structure, and cannot improve the flying performance by further increasing the aspect ratio.
The future U.S. V280 scheme is huge in structure, suitable for large-scale transport, not suitable for small and medium-sized unmanned aerial vehicles sensitive to weight and size, and can not be added with tilting winglets outside a tilting mechanism, which are helpful for improving the performance of the aircraft.
The existing electric tilting rotorcraft is limited by batteries in the aspects of loading and voyage, and before the battery energy storage is greatly broken through, the defects cannot be thoroughly solved in a short period of time.
Although the scheme of synchronous tilting of the propeller and the winglet is developed in the domestic middle industry, the unmanned aerial vehicle belongs to a light and small electric unmanned aerial vehicle, is limited by a battery, and cannot be compared with the same type of aircraft driven by an oil engine in load and voyage.
The invention is based on solving the tilting problem of a small and medium-sized oil-actuated tilting rotorcraft, the transmission problem and improving the flying performance by adding winglets.
Disclosure of Invention
The invention aims to overcome the defects of the prior art, and provides a tilting structure of an oil-actuated tilting rotorcraft, which mainly solves three practical engineering problems:
1. controllable tilting of the propeller. The propeller needs to be stopped and driven for a long time at the vertical position and the horizontal position; different from a light electric tilting rotor aircraft, the electric propeller has strong explosive force, can switch states in a short time, and rapidly overcomes the inertia of the aircraft by virtue of the explosive force of the electric propeller and the control of a self-driving instrument, and is switched from one flight state to another flight state. An oil-actuated tiltrotor aircraft is typically a large aircraft that requires slow tilting and cocking movements between two positions at precise linear speeds to avoid stall. The invention solves the basic tilting action problem primarily.
2. And the transmission problem of the propeller in the tilting mechanism. The engine or the motor of the large-sized active tilting rotor wing conveyor and the small-sized electric tilting rotor wing unmanned aerial vehicle are both positioned at the propeller, and the transmission structure is simple. The scheme is almost free from design defects of the small electric tilting rotor unmanned aerial vehicle, and the small electric tilting rotor unmanned aerial vehicle has the inherent defects that the electric unmanned aerial vehicle cannot carry a large load and cannot travel for a long time. The solution of placing the engine under the propellers at both ends of an oil-operated tiltrotor aircraft like a hawk simplifies the transmission, but increases the moment of inertia of the whole aircraft, belonging to the position of the worst roll stability of the aircraft, which presents challenges both for the overall performance of the engine and for the operating skills of the pilot. The present invention will provide a solution in which the engine does not have to follow the tilting of the propeller, even without having to be fixed in the vicinity of the propeller.
3. The tilting mechanism can expand the problems related to the winglet. Tiltrotor aircraft is a collection of advantages of fixed wing aircraft and helicopter aircraft, and is a compromise between the design disadvantages of both. Depending on the location of the tilting mechanism and engine, future U.S. V280 tiltrotor aircraft have increased aspect ratios over V22 osprey, but winglets have not been able to be added to increase aspect ratios. The stall speed and the safety and reliability of the aircraft are limited when the aircraft is in the maximum range. The invention provides a technical scheme of externally hung winglets for the tilting rotor unmanned aerial vehicle, thereby improving the flight performance as a whole.
The invention relates to a tilting structure of an oil-driven tilting rotor aircraft, which comprises a transmission shafting, an L-shaped commutator, a transmission bearing group, a tilting bearing group, a fixed flange and an electric push rod, wherein the transmission shafting is provided with a plurality of transmission shaft groups;
the transmission shaft is arranged in the wing and is used for transmitting power; the output end of the transmission shaft system is connected with the input end of the L-shaped commutator; the output end of the L-shaped reverser is connected with the propeller pitch-changing structure;
the fixed flange is fixedly connected with the fuselage or the wing; the outer circle of the fixed flange axon is provided with a tilting bearing group, the tilting bearing group is provided with the L-shaped commutator, and the L-shaped commutator is driven by the electric push rod to be supported by the tilting bearing group and rotate around the outer circle of the fixed flange at a low speed according to the rotation direction of the bearing; the inner hole of the fixed flange is provided with the transmission bearing group, and the transmission shaft is constrained and supported by the transmission bearing group and rotates at a high speed in the fixed flange according to the rotation direction of the bearing;
the transmission shaft system is coaxial with the rotation center of the L-shaped commutator.
Further, the L-shaped commutator comprises a driving bevel gear and a driven bevel gear, the output end of the transmission shafting is connected with the driving bevel gear, and the driving bevel gear is meshed with the driven bevel gear; and the driven bevel gear is connected with the propeller pitch-changing structure.
Furthermore, the L-shaped reverser is a three-section steering transmission mechanism formed by two couplings.
Further, the L-shaped reverser is a flexible coupling.
Furthermore, a tubular plugging mechanism is arranged on one side of the L-shaped reverser, which corresponds to the tilting winglet, and a cannula is correspondingly arranged on the tilting winglet, and the L-shaped reverser is locked by an anti-drop pin after being plugged with the tilting winglet.
Further, the shape of the interface of the tubular plugging mechanism is round, elliptic or polygonal.
Further, the number of the tubular plugging mechanisms is 2 or more.
Further, the electric push rod is hydraulically driven or driven by a steering engine connecting rod.
The beneficial effects of the invention are as follows:
1. the tilting mechanism suitable for the small and medium unmanned aerial vehicle is light in weight, simple in structure, modular in design, simple in assembly, easy to assemble and disassemble, and suitable for transporting maneuver after packing;
2. the method is suitable for the tilting rotor aircraft of the oil engine, and solves the problem of large-load and large-range endurance of the electric propeller aircraft;
3. the tilting winglet interface can avoid the situation that wings like V22 hawks and V280 block the downward washing airflow of a propeller in a large area when tilting, provide a lift force with a large attack angle in the process of switching tilting into flat flight, and provide a differential pressure lift force with a large aspect ratio in the process of flat flight.
Drawings
Fig. 1 is a schematic view of a tilt structure of an oil-actuated tilt rotor aircraft according to an embodiment of the present invention in a vertical take-off and landing state.
Fig. 2 is a schematic structural view of a tilt structure of an oil-actuated tilt-rotor aircraft in a fixed-wing flat-flight state according to an embodiment of the present invention.
Fig. 3 is a schematic overall structure of a tilt structure of an oil-actuated tilt rotor aircraft according to an embodiment of the present invention.
Fig. 4 is a schematic view of a tubular plugging mechanism.
Fig. 5 shows a schematic view of a three-joint steering transmission mechanism formed by two couplings.
In the figure: the device comprises a 1-wing, a 2-tilting winglet, a 3-electric push rod, a 4-L-shaped commutator, a 5-propeller pitch structure assembly, a 6-tilting bearing group, a 7-transmission bearing group, an 8-driving bevel gear, a 9-driven bevel gear, a 10-transmission shafting, an 11-fixed flange and a 12-anti-falling pin.
Detailed Description
Specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be regarded as being isolated, and they may be combined with each other to achieve a better technical effect. In the drawings of the embodiments described below, like reference numerals appearing in the various drawings represent like features or components and are applicable to the various embodiments.
As shown in fig. 1-4, the tilting structure of the oil-actuated tilting rotor aircraft according to the embodiment of the invention comprises a transmission shaft system 10, an L-shaped commutator 4, a transmission bearing group 7, a tilting bearing group 6, a fixed flange 11 and an electric push rod 3;
the transmission shafting 10 is arranged in the wing 1 and is used for transmitting power; the output end of the transmission shaft system 10 is connected with the input end of the L-shaped commutator 4; the output end of the L-shaped reverser 4 is connected with a propeller pitch-changing structure 5;
the fixed flange 11 is fixedly connected with the fuselage or the wing 1; the outer circle of the axon of the fixed flange 11 is provided with a tilting bearing group 6, the tilting bearing group 6 is provided with the L-shaped commutator 4, and the L-shaped commutator 4 is supported by the tilting bearing group 6 under the drive of the electric push rod 3 and rotates around the outer circle of the fixed flange 11 at a low speed according to the rotation direction of the bearing; the inner hole of the fixed flange 11 is provided with the transmission bearing group 7, and the transmission shaft system 10 is constrained and supported by the transmission bearing group 7 and rotates at a high speed in the fixed flange 11 according to the rotation direction of the bearing;
the transmission shaft system 10 is coaxial with the rotation center of the L-shaped commutator 4.
The L-shaped commutator 4 can adopt a driving bevel gear-driven bevel gear structure, the output end of the transmission shaft system 10 is connected with the driving bevel gear 8, and the driving bevel gear 8 is meshed with the driven bevel gear 9; the driven bevel gear 9 is connected with the propeller pitch structure 5.
The L-shaped reverser 4 can also select a three-section steering transmission mechanism formed by two couplings to replace a bevel gear pair transmission mode. The L-shaped commutator 4 may also be a flexible coupling.
The L-shaped reverser 4 is provided with a tubular plugging mechanism on one side corresponding to the tilting winglet 2, the tilting winglet 2 is correspondingly provided with a cannula, and the L-shaped reverser 4 is locked by an anti-falling pin 12 after being connected with the tilting winglet 2. The shape of the interface of the tubular plugging mechanism is round, elliptic or polygonal. The number of the tubular plugging mechanisms can be 2 or more.
The electric push rod 3 is driven by hydraulic or steering engine connecting rod.
In practical application, as shown in fig. 1-2, the propeller pitch structure assembly 5 is mounted on an L-shaped commutator 4, and the L-shaped commutator 4 rotates along an axis under the drive of an electric push rod 3, so as to realize the switching between vertical take-off and landing and tilting and leveling. The extension size of the electric push rod 3 can be subjected to high-precision servo control according to design requirements, so that a propeller posture adjustment curve of the aircraft from vertical take-off and landing to horizontal flight of the fixed wing is fitted.
The tilting mechanism drives the propeller to tilt, so that the thrust direction of the propeller is changed, and the power of the propeller is transmitted by a power shaft in the wing 1. As shown in fig. 3, the power is transmitted by the transmission shaft system 10, and is transmitted to the driven bevel gear 9 through the driving bevel gear 8 in the L-shaped commutator 4, and the driven bevel gear 9 directly transmits the power to the propeller pitch structure assembly 5. Wherein the transmission bearing group 7 supports the bevel gear 8 to rotate in the fixed flange 11 at high speed so as to transmit the rotation power required by the propeller; the tilting bearing group 6 supports the L-shaped commutator 4 to tilt around the outer circle of the fixed flange 11 at a low speed under the drive of the electric push rod 3. Wherein the rotational speed of the transmission shaft 10 is 4000rpm when the tilting operation is performed, and the rotational speed is 1rpm when the tilting operation is completed by 90 ° rotameter in 15 seconds. The latter is only 1/4000 of the former, and the influence of the dragging motion generated by tilting is negligible.
The L-shaped reverser 4 is provided with 2 tubular plugging mechanisms which can be plugged and unplugged rapidly, as shown in fig. 4, the corresponding positions of the tilting winglets 2 are provided with cannulas, and after the two are plugged, the cannulas are locked by the anti-falling pins 12 to prevent vibration falling off in the flying process.
The invention has the following characteristics:
1. the L-shaped commutator 4 doubles as a design feature of the tilting mechanism. The key point of the design is that the input shaft of the L-shaped commutator 4 is coaxial with the rotation center of the tilting mechanism, and the output end which is vertical to 90 degrees is tilted under the pushing of the electric push rod 3. According to the existing structure, the scheme that the hydraulic push rod drives the tilting, the steering engine connecting rod drives the tilting, and even the servo motor drives the L-shaped reverser 4 through a gear to realize the tilting can be derived, and the scheme belongs to the simple modification based on the design characteristics of the L-shaped reverser 4 and the tilting mechanism;
2. in the inner and outer concentric transmission structure of the fixed flange 11, the L-shaped commutator 4 performs tilting motion around the fixed flange 11 through the tilting bearing group 6, and the coaxial drive bevel gear 8 is supported by the transmission bearing group 7 inside the fixed flange 11 and transmits power inside. The key point of the structure is the structure of the inner and outer bearing sets of the fixed flange 11, and the structure belongs to the protection point of the invention. The modulus, pressure angle and helix angle of the gear are changed in the design, which belongs to the simple modification of the invention; under the support of the inner and outer bearing structures of the fixed flange 11, the internal transmission can be changed into the steering transmission of a plurality of universal couplings, as shown in figure 5, the bevel gear transmission pair can be replaced by a three-joint steering transmission mechanism formed by two couplings; the steering transmission mechanism formed by two or more couplings can also be replaced by a single flexible coupling to realize steering transmission;
3. the fixed feature of the tilting winglet 2 on the L-shaped commutator 4 is the protection point of the invention. The plug interfaces between the two can be round, oval, rectangular or even polygonal, the length of the interfaces can be long and short and thick because of different loads, and even the number of the plug interfaces is increased to more than two, and the plug interfaces are simply modified; in addition, the pin structure can be derived from a cotter pin to form pins with other shapes, or a fairing with various shapes is added on the outer side, and the simple modification is realized only by adding and tilting the fixed plug-in interface of the winglet 2 on the outer side of the L-shaped commutator 4, which belongs to the protection of the invention.
The beneficial effects of the invention are as follows:
1. the tilting mechanism suitable for the small and medium unmanned aerial vehicle is light in weight, simple in structure, modular in design, simple in assembly, easy to assemble and disassemble, and suitable for transporting maneuver after packing;
2. the method is suitable for the tilting rotor aircraft of the oil engine, and solves the problem of large-load and large-range endurance of the electric propeller aircraft;
3. the tilting winglet interface can avoid the situation that wings like V22 hawks and V280 block the downward washing airflow of a propeller in a large area when tilting, provide a lift force with a large attack angle in the process of switching tilting into flat flight, and provide a differential pressure lift force with a large aspect ratio in the process of flat flight.
Although a few embodiments of the present invention have been described herein, those skilled in the art will appreciate that changes can be made to the embodiments herein without departing from the spirit of the invention. The above-described embodiments are exemplary only, and should not be taken as limiting the scope of the claims herein.
Claims (3)
1. The tilting structure of the oil-driven tilting rotorcraft is characterized by comprising a transmission shaft system, an L-shaped commutator, a transmission bearing group, a tilting bearing group, a fixed flange and an electric push rod;
the transmission shaft is arranged in the wing and is used for transmitting power; the output end of the transmission shaft system is connected with the input end of the L-shaped commutator; the output end of the L-shaped reverser is connected with the propeller pitch-changing structure;
the fixed flange is fixedly connected with the fuselage or the wing; the outer circle of the fixed flange axon is provided with a tilting bearing group, the tilting bearing group is provided with the L-shaped commutator, and the L-shaped commutator is driven by the electric push rod to be supported by the tilting bearing group and rotate around the outer circle of the fixed flange at a low speed according to the rotation direction of the bearing; the inner hole of the fixed flange is provided with the transmission bearing group, and the transmission shaft is constrained and supported by the transmission bearing group and rotates at a high speed in the fixed flange according to the rotation direction of the bearing;
the transmission shaft system is coaxial with the rotation center of the L-shaped commutator;
the L-shaped commutator comprises a driving bevel gear and a driven bevel gear, the output end of the transmission shafting is connected with the driving bevel gear, and the driving bevel gear is meshed with the driven bevel gear; the driven bevel gear is connected with the propeller pitch-changing structure;
a tubular plugging mechanism is arranged on one side of the L-shaped reverser, which corresponds to the tilting winglet, and a cannula is correspondingly arranged on the tilting winglet, and the L-shaped reverser is locked by an anti-falling pin after being plugged with the tilting winglet; the number of the tubular plugging mechanisms is 2 or more;
the shape of the interface of the tubular plugging mechanism is round, elliptic or polygonal;
the electric push rod is hydraulically driven or driven by a steering engine connecting rod.
2. The tiltrotor aircraft tilter structure of claim 1, wherein the L-shaped commutator is a three-joint steering gear formed by two couplings.
3. The tilter structure of claim 1, wherein the L-shaped commutator is a flexible coupling.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710198177.0A CN106986005B (en) | 2017-03-29 | 2017-03-29 | Tilting structure of oil-driven tilting rotary wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710198177.0A CN106986005B (en) | 2017-03-29 | 2017-03-29 | Tilting structure of oil-driven tilting rotary wing aircraft |
Publications (2)
| Publication Number | Publication Date |
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| CN106986005A CN106986005A (en) | 2017-07-28 |
| CN106986005B true CN106986005B (en) | 2024-02-13 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710198177.0A Active CN106986005B (en) | 2017-03-29 | 2017-03-29 | Tilting structure of oil-driven tilting rotary wing aircraft |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN209567080U (en) * | 2019-01-25 | 2019-11-01 | 深圳市旗客智能技术有限公司 | rotary wing drone |
| CN109911179B (en) * | 2019-03-13 | 2022-11-04 | 南京灵龙旋翼无人机系统研究院有限公司 | Propulsion type rotary wing aircraft capable of vertically taking off and landing and flying at high speed and control method thereof |
| CN109911178A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
| CN115717980A (en) * | 2022-11-23 | 2023-02-28 | 中国航空工业集团公司哈尔滨空气动力研究所 | Small-size tilt rotor aircraft wind tunnel test model driving device |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1458030A (en) * | 2003-05-26 | 2003-11-26 | 韩培洲 | Horizontal and vertical take-off and landing plane with tilted front rotary wing |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
| CN101973398A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Tilt rotation driving mechanism for tilt rotation nacelle of tilt rotor craft |
| CN203332392U (en) * | 2013-03-27 | 2013-12-11 | 南京傲翼伟滕自动化科技有限公司 | Tiltable-rotation type fixed-wing unmanned aerial vehicle |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7594625B2 (en) * | 2003-01-23 | 2009-09-29 | Bell Helicopter Textron Inc. | Proprotor blade with leading edge slot |
| US7861967B2 (en) * | 2008-04-25 | 2011-01-04 | Abe Karem | Aircraft with integrated lift and propulsion system |
-
2017
- 2017-03-29 CN CN201710198177.0A patent/CN106986005B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1458030A (en) * | 2003-05-26 | 2003-11-26 | 韩培洲 | Horizontal and vertical take-off and landing plane with tilted front rotary wing |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
| CN101973398A (en) * | 2010-09-30 | 2011-02-16 | 南京航空航天大学 | Tilt rotation driving mechanism for tilt rotation nacelle of tilt rotor craft |
| CN203332392U (en) * | 2013-03-27 | 2013-12-11 | 南京傲翼伟滕自动化科技有限公司 | Tiltable-rotation type fixed-wing unmanned aerial vehicle |
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| CN106986005A (en) | 2017-07-28 |
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