CN113184177A - Tilt-rotor aircraft and power transmission device thereof - Google Patents
Tilt-rotor aircraft and power transmission device thereof Download PDFInfo
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- CN113184177A CN113184177A CN202110562964.5A CN202110562964A CN113184177A CN 113184177 A CN113184177 A CN 113184177A CN 202110562964 A CN202110562964 A CN 202110562964A CN 113184177 A CN113184177 A CN 113184177A
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- 230000005540 biological transmission Effects 0.000 title claims abstract description 64
- 230000008859 change Effects 0.000 abstract description 4
- 210000001015 abdomen Anatomy 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 3
- 239000004917 carbon fiber Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 238000005406 washing Methods 0.000 description 2
- 238000007792 addition Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
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Classifications
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- 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
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Wind Motors (AREA)
Abstract
The invention discloses a tilt rotor aircraft and a power transmission device thereof, relating to the field of aviation aircrafts and comprising an aircraft body, wherein the head part of the aircraft body is provided with an airflow rectifying grid cover, the tail part of the aircraft body is provided with a wind driven generator, the wind driven generator is electrically connected with a built-in power supply of the aircraft body, and the airflow rectifying grid cover is connected with an air inlet end of the wind driven generator through an airflow channel; the head of the machine body is also provided with a motor, an output shaft of the motor is connected with a propeller, and the motor is electrically connected with a built-in power supply of the machine body; the aircraft body is internally provided with an engine, and the power output end of the engine is connected with a tilt rotor power transmission box positioned at the top of the outer ends of the left and right wings of the aircraft body through an overrunning clutch. The invention has great change and obvious improvement in aspects of control, safety, energy-saving utilization and the like; combining its system performance, aircraft have produced qualitative changes and improvements.
Description
Technical Field
The invention relates to the field of aviation aircrafts, in particular to a tilt rotor aircraft and a power transmission device thereof.
Background
The tilting rotor aircraft is a rotor aircraft with unique performance, and is characterized in that two wing tips of wings of similar fixed-wing aircraft are respectively provided with a set of rotor tilting system components capable of rotating between a horizontal position and a vertical position, when the aircraft vertically takes off and lands, a rotor shaft is perpendicular to the ground, is in a flight state of a transverse helicopter, and can hover, fly forwards and backwards and fly sideways in the air. The principle is that after the tilt rotor aircraft takes off to reach a certain speed, the rotor shaft can tilt forward by 90 degrees and is in a horizontal state, the rotor is used as a tension propeller, and at the moment, the tilt rotor aircraft can fly remotely at a higher speed like a fixed-wing aircraft. The helicopter has the capabilities of vertical take-off and landing and hovering in the air of a common helicopter and the capability of high-speed cruising flight of a turboprop. The tilt rotor aircraft adopts a new thinking method to design the rotor and the overall layout of the helicopter, the design concept breaks through the category of the traditional helicopter, belongs to a rotor configuration with a new principle, is a high technology with the technical breakthrough and the spanning of the helicopter, is the revolutionary technology of the helicopter industry, and is also the inevitable result of the technical development of the helicopter.
The advanced tilt rotor aircraft which is generally accepted at present is an American eagle V-22 tilt rotor aircraft and an improved V-247, and has the main advantages of vertical take-off and landing characteristic advantages of a helicopter, and the advantages of fast flat flight, large load capacity and low oil consumption of a fixed wing aircraft; the obvious advantages make people see the development direction of the airplane.
In addition to an advanced aircraft equipped with an engine, the advanced hardware is characterized by the use of materials and aerodynamic layout, i.e., aerodynamic performance. After the aerodynamics are established, the new knowledge technology in the aspect of the pneumatic layout is also changed greatly. For example, in the sixty-seven decades of the last century, the front end face of the fixed wing of a fixed wing aircraft is changed from a U-shaped structure (as shown in fig. 1) to an approximate V-shaped structure (as shown in fig. 2), and after the shape of the end face is changed, the pressure of airflow above the fixed wing is small, and the pressure below the fixed wing is increased, so that the lift force of the aircraft is greatly improved. Although seemingly minor, the changes have made a milestone advance in the aircraft development history.
Although the tilt rotor aircraft is popularized and used in a plurality of countries at present, the tilt rotor aircraft has some defects, and data show that after the tilt rotor aircraft is equipped and used, the number of crash accidents exceeds fifty times, wherein one reason is that the aircraft is complex to operate, and the comprehensive capability of a driver is tested in an emergency scene.
For example, in a tilt rotor aircraft in the prior art, an engine is respectively installed at the outer ends of a left fixed wing and a right fixed wing, and it is difficult to keep the rotating speeds of the two engines at the same rotating speed, so that the two engines are controlled at the same rotating speed, and certain variables exist, such as changes of various components of the engines, changes of a transmission system, and the like, which may cause the rotating speeds of the two rotor engines to be different. The different rotating speeds of the left and right wing engines can cause unbalanced torque on two sides of the airplane, and accidents can be caused.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention provides the tilt rotor aircraft and the power transmission device thereof, which simplify and optimize the pneumatic layout and the power transmission device of the tilt rotor aircraft in the prior art, thereby improving the overall performance of the aircraft body and reducing the operation complexity.
The technical scheme adopted by the invention for solving the technical problems is as follows: a tilt rotor aircraft and a power transmission device thereof comprise an aircraft body; the head of the machine body is provided with an airflow rectifying grating cover, the tail of the machine body is provided with a wind driven generator, the wind driven generator is electrically connected with a built-in power supply of the machine body, and the airflow rectifying grating cover is connected with the air inlet end of the wind driven generator through an airflow channel; the head of the machine body is also provided with a motor, an output shaft of the motor is connected with a propeller, and the motor is electrically connected with a built-in power supply of the machine body. According to the aerodynamic theory: the air is viscous; although the aircraft heads in the prior art are all made into elliptical streamline shapes so as to reduce the resistance of the air to the aircraft in the flight process of the aircraft, the aircraft has too high speed in the flight process and can generate larger air resistance; the power consumption of the airplane comes from the gravity of the earth and the resistance of the airflow when the airplane flies forward. After the scheme is adopted, most of airflow generated when the airplane flies forwards can enter the airflow rectification grille cover, and is conveyed backwards to the wind driven generator at the tail part of the airplane body through the airflow channel to drive the blades of the wind driven generator to rotate, the electric quantity generated by the wind driven generator can be stored in the built-in power supply of the airplane body, and then the electric motor arranged at the head part of the airplane body is powered to drive the propeller to rotate so as to provide power for the forward flying. When the engine and the transmission system are in failure, the aircraft can be assisted to safely force to land by using the pulling force of the propeller at the head of the aircraft.
Set up the engine in the organism, the power take off end of engine is connected through freewheel clutch, drive gear, transmission shaft and is located the rotor power transmission case that verts at two wing outer end tops about the organism, and the rotor power transmission case that verts passes to the paddle with power, and when the aircraft flies before flying by the vertical lift, the rotor power transmission case that verts is in the drive of rotor tilting motor gear, forward or the back rotation, makes the paddle also forward or the back verts thereupon to realize the flight purpose.
The input shaft of rotor power transmission case verts connects the power transmission gear group that is located rotor power transmission case verts through the universal joint shaft coupling, and power transmission gear group connects the paddle fixed disk through the transmission shaft, and the paddle is connected to the paddle fixed disk.
Furthermore, a sliding sleeve bearing and a blade variable-pitch motor are arranged outside the shaft of the blade fixing disc, and blade variable pitch can be realized in the driving of the blade variable-pitch motor.
In order to guarantee the stability of paddle fixed disk, reduce and make the degree of difficulty, the tapering bearing box that the rotor power transmission case that verts set up is connected as an organic whole with the box of the rotor power transmission case that verts, and the paddle fixed disk is connected to the tapering bearing that the tapering bearing box was established.
In order to control the blade fixing disc to be capable of rotating and adjusting within the ranges of forward inclination of 85 degrees and backward inclination of 40 degrees, the airplane flies forwards and backwards; rotor power transmission case both sides fixed connection that verts gears, rotor power transmission case both sides that vert still are equipped with and vert gear connection's the rotor motor that verts, and the rotor motor's that verts output shaft can be connected with the gear engagement that verts through the gear to drive the hectare and change rotor power transmission case, use the transmission shaft as the center, do and lean forward, the hypsokinesis rotates, realize that the aircraft flies before and flies after.
The propeller is located in the front lower portion of the head end of the airplane body, the propeller is arranged in an upward inclined mode, the inclination angle between the axis line of the propeller and the horizontal line is 20 degrees, and therefore most of air flow discharged by the propeller when the airplane flies forwards is pulled to flow to the lower portion of the belly of the airplane, washing flow density under the belly is increased, and buoyancy of the airplane is further increased.
The number of the motors is a double number which is more than or equal to 2, the output shafts of the adjacent motors are opposite in rotation direction, the number of the motors is preferably 2, namely, one motor drives the connected propeller to rotate clockwise, and the other motor drives the connected propeller to rotate anticlockwise. The propellers rotate in the opposite direction to offset the yaw caused by the torque, so that the propellers on the head of the airplane pull the airplane to fly forwards. The setting has the effects of generating pulling force on the airplane, increasing the buoyancy of fluid under the belly, reducing the airflow resistance in front of the airplane, effectively improving the air resistance according to the function variable relation of 'faster speed and smaller lifting force' in airplane aerodynamics, and improving the energy-saving effect to some extent.
The airflow rectification grille cover is made of carbon fiber materials, and the increase of the weight of the airplane is small and can be ignored.
The motors all use high-speed direct current motors, and are converted into slow speed through mechanical speed change, so that driven parts are mechanically locked when the operation is stopped.
The number of the air flow channels is preferably four, and the air flow channels are respectively arranged on the left and right sides of the top and the left and right sides of the bottom of the machine body.
The invention has the beneficial effects that: through the combination innovation structure of the aspects, the conception is ingenious, and the structure is simple, the newly added aerodynamic force of the whole tilt rotor aircraft is reasonably distributed, the aerodynamic efficiency principle is met, and the aerodynamic performance is greatly improved; the control, safety, energy-saving utilization and other aspects are greatly changed and remarkably improved; combining its system performance, aircraft have produced qualitative changes and improvements.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic view of a U-shaped structure of the front end face of a fixed wing of an airplane;
FIG. 2 is a schematic view of a V-shaped structure of the front end surface of a fixed wing of an airplane;
FIG. 3 is a connection diagram of the airflow fairing cover, airflow channel, and wind turbine;
FIG. 4 is a schematic diagram of a handpiece mounted propeller configuration;
figure 5 is a schematic diagram of a tiltrotor power transmission case configuration.
The technical scheme includes that the wind power generator comprises a machine body 1, an air flow rectifying grille cover 2, a wind power generator 3, an air flow channel 4, a motor 5, a propeller 6, a tilting rotor power transmission box 7, a universal joint coupler 8, a power transmission gear set 9, a transmission shaft 10, a blade fixing plate 11, a blade 12, a sliding sleeve bearing 13, a blade variable-pitch motor 14, a taper bearing box 15, a tilting gear 16 and a rotor tilting motor 17.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Referring to fig. 3 to 5, the present embodiment provides a tiltrotor aircraft and a power transmission device thereof, including an airframe 1; the head of the machine body 1 is provided with an airflow rectification grid cover 2, the tail of the machine body 1 is provided with a wind driven generator 3, the wind driven generator 3 is electrically connected with a built-in power supply of the machine body 1, the airflow rectification grid cover 2 and the air inlet end of the wind driven generator 3 are connected through four flat tubular airflow channels 4, and the four airflow channels 4 can be arranged on two sides of the top and two sides of the bottom of the machine body 1; the head of the machine body 1 is also provided with two motors 5, the output shafts of the motors 5 are connected with a propeller 6, the steering arrangement of the two motors 5 is opposite to offset the yaw torque, and the motors 5 are electrically connected with a built-in power supply of the machine body 1. Most of airflow generated when the airplane flies forward can enter the airflow rectification grille cover 2 and is conveyed backwards to the wind driven generator 3 at the tail part of the airplane body 1 through the airflow channel 4 to drive blades of the wind driven generator 3 to rotate, electric quantity generated by the wind driven generator 3 can be stored in a built-in power supply of the airplane body 1, and then the electric quantity supplies power to the motor 5 arranged at the head part of the airplane body 1 to drive the propeller 6 to rotate so as to provide power for the forward flying. When the engine and the transmission system are in failure, the pulling force of the propeller 6 at the head of the airplane can be used for assisting the airplane to safely force to land. Wherein, the propeller 6 at the head of the machine body 1 and the blades of the wind driven generator 3 at the tail of the machine body 1 are both made of aluminum alloy or carbon fiber materials. The motor 5 casing is made of aluminum alloy to reduce weight.
Set up the engine in the organism 1, the power take off end of engine is connected through freewheel clutch, drive gear, transmission shaft and is located the rotor power transmission case 7 that verts at organism 1 left and right sides two wings outer end top, the input shaft of rotor power transmission case 7 that verts connects through universal joint coupler 8 and is located the inside power transmission gear group 9 of rotor power transmission case 7 that verts, and power transmission gear group 9 passes through transmission shaft 10 and connects paddle fixed disk 11, and paddle 12 is connected to paddle fixed disk 11. A sliding sleeve bearing 13 and a blade pitch-variable motor 14 are arranged outside the shaft of the blade fixing disc 11, and the pitch of the blades 12 can be changed under the driving of the blade pitch-variable motor 14.
In order to guarantee the stability of paddle fixed disk, reduce and make the degree of difficulty, the tapering bearing box 15 that sets up in the rotor power transmission case 7 that verts is connected as an organic whole with the box of rotor power transmission case 7 that verts, and the tapering bearing that sets up in the tapering bearing box 15 is connected paddle fixed disk 11.
In order to control the blade fixing disc to be capable of rotating and adjusting within the ranges of forward inclination of 85 degrees and backward inclination of 40 degrees, the airplane flies forwards and backwards; 7 both sides fixed connection of rotor power transmission case verts gear 16 verts, 7 both sides of rotor power transmission case verts still are equipped with the rotor motor 17 that verts that is connected with the gear 16 that verts, and the output shaft of rotor motor 17 that verts can be connected with the gear 16 meshing that verts through the gear to drive the hectare and change rotor power transmission case 7, use transmission shaft 10 as the center, do and lean forward, the hypsokinesis rotates, fly before the realization aircraft and fly with the back.
The propeller 6 is positioned at the front lower part of the head end of the machine body 1, the propeller 6 is arranged in an upward inclined mode, and the inclination angle between the axis line of the propeller 6 and the horizontal line is 20 degrees, so that most of air flow discharged by the propeller 6 when the airplane is pulled to fly forwards flows to the lower part of the belly of the airplane, the washing flow density under the belly is increased, and the buoyancy of the airplane is further increased.
The airflow rectification grille cover 2 is made of carbon fiber materials, and the increase of the weight of the airplane is small and can be ignored.
The above embodiments and drawings are only for illustrating the technical solutions of the present invention and not for limiting the present invention, and the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that changes, modifications, additions or substitutions within the spirit and scope of the present invention may be made by those skilled in the art without departing from the spirit of the present invention, and shall also fall within the scope of the claims of the present invention.
Claims (8)
1. A tilt rotor aircraft and a power transmission device thereof comprise an aircraft body; the wind driven generator is electrically connected with a built-in power supply of the machine body, and the airflow rectification grid cover is connected with the air inlet end of the wind driven generator through an airflow channel; the head of the machine body is also provided with a motor, an output shaft of the motor is connected with a propeller, and the motor is electrically connected with a built-in power supply of the machine body; the aircraft body is internally provided with an engine, and the power output end of the engine is connected with a tilt rotor power transmission box positioned at the top of the outer ends of the left and right wings of the aircraft body through an overrunning clutch.
2. The tiltrotor aircraft and the power transmission device thereof according to claim 1, wherein the input shaft of the tiltrotor power transmission case is connected to the power transmission gear set located inside the tiltrotor power transmission case through a universal joint coupler, a transmission gear and a transmission shaft, the power transmission gear set is connected to the paddle fixing disc through the transmission shaft, and the paddle fixing disc is connected to the paddle.
3. The tiltrotor aircraft and power transmission thereof of claim 2, wherein the blade mount is externally journalled with a slide bearing and a blade pitch motor.
4. The tiltrotor aircraft and the power transmission device thereof according to claim 2, wherein a taper bearing box provided in the tiltrotor power transmission case is integrally connected to a case body of the tiltrotor power transmission case, and a taper bearing provided in the taper bearing box is connected to the paddle fixing disk.
5. The tiltrotor aircraft and power transmission apparatus thereof according to any one of claims 3 or 4, wherein tilt gears are fixedly connected to both sides of the tilt rotor power transmission case, and tilt rotor motors connected to the tilt gears are further provided to both sides of the tilt rotor power transmission case.
6. The tiltrotor aircraft and power transmission thereof according to claim 1, wherein the propellers are located forwardly and downwardly of the head end of the airframe, the propellers being disposed at an upward incline; the inclination angle of the shaft axis of the propeller and the horizontal line is 20 degrees.
7. The tiltrotor aircraft and power transmission thereof as claimed in claim 1, wherein the number of said electric motors is a double number greater than or equal to 2, and the output shafts of adjacent electric motors are oppositely rotated.
8. The tiltrotor aircraft and power transmission thereof according to claim 1, wherein the number of the air flow passages is four, and the four air flow passages are provided on the top left and right sides and the bottom left and right sides of the body, respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110562964.5A CN113184177A (en) | 2021-05-17 | 2021-05-17 | Tilt-rotor aircraft and power transmission device thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110562964.5A CN113184177A (en) | 2021-05-17 | 2021-05-17 | Tilt-rotor aircraft and power transmission device thereof |
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| CN113184177A true CN113184177A (en) | 2021-07-30 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202110562964.5A Withdrawn CN113184177A (en) | 2021-05-17 | 2021-05-17 | Tilt-rotor aircraft and power transmission device thereof |
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|---|---|---|---|---|
| EP0356541A1 (en) * | 1988-08-30 | 1990-03-07 | Karl Eickmann | Vertically taking off and landing aircraft, which flies horizontally on wings which include a pipe structure and which can be pivoted from substantially vertical to horizontal position |
| CN201864038U (en) * | 2010-10-31 | 2011-06-15 | 王治岳 | Self-feeding electric air vehicle |
| CN201953579U (en) * | 2011-02-17 | 2011-08-31 | 湘电风能有限公司 | Wind driven generator fairing |
| CN202923886U (en) * | 2012-10-22 | 2013-05-08 | 夏金暑 | Plane with high safety |
| CN103590976A (en) * | 2012-08-14 | 2014-02-19 | 张金官 | Full-rotor direct-driven wind driven generator |
| CN106585976A (en) * | 2016-11-30 | 2017-04-26 | 北京航空航天大学 | Aircraft layout of tilt rotors/lift fan during high-speed long endurance |
| CN106976552A (en) * | 2017-03-17 | 2017-07-25 | 沈阳无距科技有限公司 | Tilting rotor wing unmanned aerial vehicle |
| CN108100272A (en) * | 2017-12-18 | 2018-06-01 | 赵锡军 | A kind of aircraft dynamic transfer system |
| CN109131868A (en) * | 2018-09-14 | 2019-01-04 | 沈阳无距科技有限公司 | Inclining rotary mechanism and aircraft for aircraft |
| CN112793776A (en) * | 2020-10-22 | 2021-05-14 | 彩虹无人机科技有限公司 | Rotor wing tilting system and method for unmanned tilting rotor wing machine |
-
2021
- 2021-05-17 CN CN202110562964.5A patent/CN113184177A/en not_active Withdrawn
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0356541A1 (en) * | 1988-08-30 | 1990-03-07 | Karl Eickmann | Vertically taking off and landing aircraft, which flies horizontally on wings which include a pipe structure and which can be pivoted from substantially vertical to horizontal position |
| CN201864038U (en) * | 2010-10-31 | 2011-06-15 | 王治岳 | Self-feeding electric air vehicle |
| CN201953579U (en) * | 2011-02-17 | 2011-08-31 | 湘电风能有限公司 | Wind driven generator fairing |
| CN103590976A (en) * | 2012-08-14 | 2014-02-19 | 张金官 | Full-rotor direct-driven wind driven generator |
| CN202923886U (en) * | 2012-10-22 | 2013-05-08 | 夏金暑 | Plane with high safety |
| CN106585976A (en) * | 2016-11-30 | 2017-04-26 | 北京航空航天大学 | Aircraft layout of tilt rotors/lift fan during high-speed long endurance |
| CN106976552A (en) * | 2017-03-17 | 2017-07-25 | 沈阳无距科技有限公司 | Tilting rotor wing unmanned aerial vehicle |
| CN108100272A (en) * | 2017-12-18 | 2018-06-01 | 赵锡军 | A kind of aircraft dynamic transfer system |
| CN109131868A (en) * | 2018-09-14 | 2019-01-04 | 沈阳无距科技有限公司 | Inclining rotary mechanism and aircraft for aircraft |
| CN112793776A (en) * | 2020-10-22 | 2021-05-14 | 彩虹无人机科技有限公司 | Rotor wing tilting system and method for unmanned tilting rotor wing machine |
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