CN114802737B - Rotary wing aircraft with tilting mechanism driven by flexible steel wire - Google Patents
Rotary wing aircraft with tilting mechanism driven by flexible steel wire Download PDFInfo
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- CN114802737B CN114802737B CN202210452535.7A CN202210452535A CN114802737B CN 114802737 B CN114802737 B CN 114802737B CN 202210452535 A CN202210452535 A CN 202210452535A CN 114802737 B CN114802737 B CN 114802737B
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- 230000007246 mechanism Effects 0.000 title claims abstract description 49
- 229910000831 Steel Inorganic materials 0.000 title claims abstract description 45
- 239000010959 steel Substances 0.000 title claims abstract description 45
- 238000009434 installation Methods 0.000 claims description 2
- 230000000712 assembly Effects 0.000 claims 1
- 238000000429 assembly Methods 0.000 claims 1
- 238000006243 chemical reaction Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 3
- 238000013461 design Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 241000566150 Pandion haliaetus Species 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000033001 locomotion Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Classifications
-
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a rotary wing aircraft with a tilting mechanism driven by flexible steel wires to rotate, which comprises a tail rotor, a fuselage, wings, rotary wings, a tilting tower and a tilting rotor mechanism, wherein the tail rotor is arranged at the tail part of the fuselage; the rotor is mounted on the pitch tower. The rotary wing aircraft has simple integral mechanism and low cost; the tilting is more flexible, and the aircraft mobility is higher.
Description
Technical Field
The invention relates to the technical field of rotorcraft, in particular to a rotorcraft with a tilting mechanism driven by flexible steel wires to rotate.
Background
XV-3 is a tiltrotor aircraft principle verification machine of Bei Erzhi helicopter company, and is mainly used for verifying the principle of the tiltrotor aircraft, has simpler design, adopts the existing technology and components at the time, and only produces two frames. A piston engine installed at the back of the cabin is used as power to drive two pairs of rotors installed at wing tips. The rotor blade is similar to a helicopter blade, has smaller torsion and relatively larger rotor diameter, and is not suitable for being used as a propeller for flat flight of a fixed-wing aircraft. The landing gear is a skid type. XV-3 performance index is not high, and maximum speed is close to that of a helicopter.
In 11 years from the first flight of XV-3 frame 1 in 8 in 1955 to the crash of XV-3 frame 2 in 5 in 1966, a large number of wind tunnel tests, ground and flight tests are carried out by using XV-3, so that the tilting rotor principle can be applied to a vertical take-off and landing conveyor, the technical advantages of the tilting rotor principle are verified, and a data foundation is provided for the following XV-15 and V-22 plans.
The fuselage structure of XV-15 is basically that of a conventional fixed-wing aircraft, but lift at hover and thrust at cruise are provided by low disk load rotors at the wing tips. The rotor and the turboshaft engine can tilt, so that the rotor can be converted from a vertical position of a helicopter flight mode to a horizontal position of a fixed-wing aircraft flight mode. When flying in a normal fixed-wing aircraft, the control plane is mainly used for controlling the aircraft. The transverse shaft system connected with the two pairs of rotors ensures the rotation speed synchronization of the two pairs of rotors; the switching system interconnecting shaft is used for guaranteeing tilting synchronization of the rotor shaft.
V-22 is a rotor tilting system component which is arranged at two wing tips of a wing of a similar fixed-wing aircraft and can rotate between a horizontal position and a vertical position, when the aircraft vertically takes off and lands, a rotor shaft is vertical to the ground, is in a state of flying a horizontal helicopter, and can hover in the air, fly back and forth and fly sideways; after the tiltrotor aircraft takes off and reaches a certain speed, the rotor shaft can tilt forward by 90 degrees to form a horizontal state, the rotor is used as a tension propeller, and the tiltrotor aircraft can remotely fly at a higher speed like a fixed-wing aircraft.
The V-22 has a turning rotor propulsion device at two ends of the wing, each comprising a Lawster-Ai Lisen T406 turbine shaft engine and a rotor comprising three blades, the whole propulsion device can turn around the wing shaft from upward to forward and can be fixed in the required direction, thus generating upward lifting force or forward thrust. This conversion process is typically completed in tens of seconds. When the V-22 propulsion device is vertically upwards, lift force is generated, the helicopter can vertically take off, land or hover, and the control system can change the magnitude of the lift force on the rotor wing and the inclined direction of the lift force of the rotor wing so as to enable the aircraft to keep or change the flight state. After taking off, the propulsion device can be rotated to a horizontal position to generate forward thrust, and the propulsion device can fly by relying on wings to generate lift like a fixed-wing propeller plane. At this time, the two pairs of ailerons at the rear edge of the main wing can ensure the transverse operation of the aircraft, and the rudder hinged on the end plate type vertical tail wing and the elevator on the horizontal tail wing can change the flight direction and the flight height by virtue of the steering engine.
Similar to V-22 in general. The most critical part, V-280 vs. V-22 core lifting, is a change of the core mechanical principle, and in the age V-22, the engine rotates synchronously along with the rotation of the rotor, so that the transmission conversion problem with the propeller (the traditional helicopter has serious power loss in the part and is one of the most fragile parts), but because two large engines are rotated to enable the V-22 to perform conversion between the fly-vertical lifting mode, a plurality of difficulties exist, such as the effect that the exhaust gas of the engine influences the efficiency of the rotor when blowing to the ground, and the deck is destroyed by the high-temperature exhaust gas. Let alone the V-22 engine switching mechanism has also presented several problems. The V-280 engine is not moving, but only the method of rotating the rotor, and the problems of engine rotation are avoided although transmission conversion is added.
The research of XV-3 and XV-15 makes the V-22 'hawk' tiltrotor aircraft possible, but the technology is limited at the time, and a series of problems such as complex structure, high cost, low safety and the like exist. The two engines of the V-22 osprey tiltrotor aircraft equipment are connected by drive shafts to a common central gearbox so that one engine can power both propellers in the event of an engine failure. Either engine can power both propellers through the wing drive shaft. When stored on the ground or an amphibious attack ship, the V-22 hawk tiltrotor aircraft can fold the rotor and the short wing back after rotating in 90 seconds, and the wing rotates to be aligned with the front and back of the fuselage. The occupied area of the aircraft is greatly reduced. These designs are very complex. And also because the structure is too complex. The failure rate of V-22 osprey tiltrotor aircraft has remained high. V-280 improves V-22, and multistage ball screw is adopted to realize tilting, but the problems of high noise and vibration and the like still exist. In summary, the following steps are:
1. V-22 has low reliability and safety. The reliability directly influences the safety. V-22 proprotors are indeed "pitched" during short take-off and landing, vertical take-off and landing, hovering, transitional flight, etc., but they do not deflect alone, but instead rotate with the rotation of the nacelle. Thus, the exact name of the model should be a helicopter "using pitch-over-motor technology". Therefore, the V-22 accident rate is high and the safety is low.
2. V-280 is much more noisy and vibrating. V-280 has the characteristics of vertical take-off and landing and high-speed cruising, and is realized through a tilting mechanism. The tilting mechanism is realized through a multi-stage ball screw, and is in line contact, relatively large in gap and relatively large in noise and vibration.
3. The tilting mechanisms of XV-3, XV-15 and the subsequent V-22 and V-280 are complex, and the mechanism has high manufacturing requirements and high cost.
In summary, most of the existing tilting mechanisms have complex structure, large vibration and noise, high design cost and high manufacturing cost, and part of the schemes have problems of safety and reliability. Therefore, the problem of vibration and noise can be solved on the premise of simple structure, the cost is reduced, and the safety is ensured.
Disclosure of Invention
The invention aims to provide a rotary wing aircraft with a tilting mechanism driven by flexible steel wires, which solves the problems of complex structure, higher cost, low safety and larger vibration and noise of the traditional tilting mechanism.
In order to achieve the above object, the present invention provides the following solutions: the invention provides a rotary wing aircraft with a tilting mechanism driven by flexible steel wires to rotate, which comprises tail paddles, an aircraft body, wings, rotary wings, a tilting tower and a tilting rotor mechanism, wherein the tail paddles are arranged at the tail part of the aircraft body, two wings are symmetrically arranged at two sides of the aircraft body, the tilting rotor mechanism and the tilting tower are arranged at the outer side end parts of the wings, the tilting rotor mechanism comprises an electric push rod assembly, flexible steel wires and pulleys, a cylinder seat of the electric push rod assembly is fixed on the aircraft body, one end of each flexible steel wire is connected with a telescopic end of the electric push rod assembly, the other end of each flexible steel wire bypasses the pulleys and is connected with a mounting seat of the tilting tower, and the tilting rotor mechanism is used for driving the tilting tower to perform angle adjustment relative to a horizontal line; the rotor is mounted on the tilt tower.
Preferably, the aircraft further comprises a tilting housing fixed to the outer end of the wing, and the tilting rotor mechanism and the tilting tower are mounted on the tilting housing.
Preferably, two ends of the mounting seat of the tilting tower are assembled on the tilting shell through bearings, and the mounting seat of the tilting tower can rotate relative to the tilting shell; the rotor is assembled on a driving shaft which is arranged on the tilting tower and perpendicular to the mounting seat.
Preferably, the electric push rod assembly comprises an electric push rod I and an electric push rod II, cylinder bases of the electric push rod I and the electric push rod II are both fixed on the same side of the machine body, a flexible steel wire I is connected to a telescopic end of the electric push rod I, and the other end of the flexible steel wire I winds on a left bearing moving ring of a mounting base of the tilting tower after bypassing a pulley I; the telescopic end of the second electric push rod is connected with a second flexible steel wire, and the other end of the second flexible steel wire bypasses the second pulley and then is wound on the right bearing moving ring of the mounting seat of the tilting tower.
Compared with the prior art, the invention has the following beneficial technical effects:
1. the principle of the invention is that the electric push rod is connected with the steel wire, the motor controls the electric push rod to stretch and retract, thereby driving the steel wire to move, and the other side of the steel wire is wound on the mounting seat of the tilting tower. When the steel wire rope moves under the drive of the telescopic rod, the mounting seat also rotates along with the steel wire rope, so that the whole rotor wing part is driven to rotate. The whole mechanism is very simple and the cost is low.
2. When the tilting rotor mechanism of the invention tilts, two electric push rods are respectively arranged at two sides to control the tilting of the rotor wings at one side of the tilting rotor mechanism, and the tilting of the two rotor wings is independent, so that the tilting is more flexible and the aircraft mobility is higher.
3. The invention adopts the flexible steel wire to realize tilting, has no gap in the rope movement process, stable operation, no redundant gear and other mechanisms, and small vibration and noise.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a state diagram of an aircraft rotor in helicopter mode;
FIG. 2 is a state diagram of the aircraft rotor in cruise mode;
FIG. 3 is a component view of a tiltrotor mechanism;
the wind turbine comprises a tail rotor, a fuselage, a wing, a rotor wing, a tilting shell 5, a tilting tower, a tilting rotor wing mechanism 7, a pulley, an electric push rod 9 and a flexible steel wire 10.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention aims to provide a rotary wing aircraft with a tilting mechanism driven by flexible steel wires, which solves the problems of complex structure, higher cost, low safety and larger vibration and noise of the traditional tilting mechanism.
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.
As shown in fig. 1-3, the present embodiment provides a novel tilt rotor aircraft using flexible steel wires to drive rotors to rotate, which comprises a tail rotor 1, a fuselage 2, wings 3, rotors 4, a tilt housing 5, a tilt tower 6 and a tilt rotor mechanism 7.
When the aircraft vertically takes off and lands, the rotor shaft is vertical to the ground and is in a state of flying by a horizontal helicopter, as shown in fig. 1.
The two tilting rotor mechanisms 7 of the tilting rotor aircraft can swing at an angle of-5 degrees to 105 degrees and can hover in the air, fly back and forth and fly sideways; after the tiltrotor aircraft takes off to reach a certain speed, the rotor shaft can tilt forward by 90 degrees to form a horizontal state, the rotor 4 is used as a tension propeller, and at the moment, the tiltrotor aircraft can fly remotely at a higher speed like a fixed-wing aircraft, and the figure 2 is shown.
The main tilting mechanism is fig. 3. Mainly comprises a tilting rotor mechanism 7, a pulley 8, an electric push rod 9 and a flexible steel wire 10. Wherein the electric push rod 9 is positioned on the part of the fuselage 2, and the flexible steel wire 10 is positioned on the part of the wing 3.
One end of the flexible steel wire 10 is connected with an electric pole, and the other end is wound on the tilting mechanism. The electric push rod 9 stretches out and draws back under the control of the motor, drives the flexible steel wire 10 to move, and the flexible steel wire 10 passes through the direction changes of a plurality of pulleys such as the pulley 8 and finally drives the flexible steel wire 10 wound around the tilting rotor mechanism 7 to move, so that tilting of the rotor 4 is realized. And controlling the motion of the two electric poles to realize tilting in different directions.
Specifically, the outer end of wing 3 is mounted with a tilt rotor mechanism 7 and a tilt tower 6, tilt rotor mechanism 7 comprises an electric push rod assembly, a flexible steel wire 10 and a pulley 8, rotor 4 is mounted on tilt tower 6, tilt housing 5 is fixed at the outer end of wing 3, tilt rotor mechanism 7 and tilt tower 6 are mounted on tilt housing 5.
Two ends of the mounting seat of the tilting tower 6 are assembled on the tilting shell 5 through bearings, and the mounting seat of the tilting tower 6 can rotate relative to the tilting shell 5; rotor 4 is mounted on a drive shaft on pitch tower 6 arranged perpendicular to the mount. The electric push rod assembly comprises an electric push rod I and an electric push rod II, cylinder seats of the electric push rod I and the electric push rod II are fixed on the same side of the machine body 1, a flexible steel wire I is connected to the telescopic end of the electric push rod I, and the other end of the flexible steel wire I winds a left bearing ring of a mounting seat of the tilting tower 6 after bypassing the pulley I; the telescopic end of the second electric push rod is connected with a second flexible steel wire, and the other end of the second flexible steel wire winds around the second pulley and then winds on the right bearing moving ring of the installation seat of the tilting tower 6.
The tilting mechanism comprises a tilting rotor mechanism 7, a pulley 8, an electric push rod 9 and a flexible steel wire 10, and has simple structure and low cost compared with the existing tilting mechanism; unlike available rotor tilting, the present invention has two electric push rods 9 to control the rotor 4 to tilt separately, so that the tilting is flexible and the aircraft has high mobility; the invention mainly adopts the flexible steel wire 10 to control tilting, runs stably, has no clearance problem of gear transmission and other structures, and greatly reduces vibration and noise.
It should be noted that it will be apparent to those skilled in the art that the present invention is not limited to the details of the above-described exemplary embodiments, but may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.
The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.
Claims (3)
1. The utility model provides a flexible steel wire drives rotary wing aircraft that tilting mechanism rotated which characterized in that: the self-adaptive tilting rotor mechanism comprises a tail rotor, a fuselage, wings, rotors, a tilting tower and a tilting rotor mechanism, wherein the tail rotor is arranged at the tail part of the fuselage, two wings are symmetrically arranged at two sides of the fuselage, the tilting rotor mechanism and the tilting tower are arranged at the outer side end parts of the wings, the tilting rotor mechanism comprises an electric push rod assembly, a flexible steel wire and a pulley, a cylinder seat of the electric push rod assembly is fixed on the fuselage, one end of the flexible steel wire is connected with a telescopic end of the electric push rod assembly, the other end of the flexible steel wire bypasses the pulley and then is connected with a mounting seat of the tilting tower, and the tilting rotor mechanism is used for driving the tilting tower to perform angle adjustment relative to a horizontal line; the rotor wing is arranged on the tilting tower;
The electric push rod assembly comprises an electric push rod I and an electric push rod II, cylinder bases of the electric push rod I and the electric push rod II are fixed on the same side of the machine body, a flexible steel wire I is connected to a telescopic end of the electric push rod I, and the other end of the flexible steel wire I winds a left bearing moving ring of an installation base of the tilting tower after bypassing a pulley I; the telescopic end of the second electric push rod is connected with a second flexible steel wire, and the other end of the second flexible steel wire winds on a right bearing moving ring of the mounting seat of the tilting tower after bypassing the second pulley;
when the rotorcraft tilts, two electric push rods in the electric push rod assemblies are respectively arranged on two sides to control the tilting of the rotor wings on the side of the rotorcraft, and the tilting of the two rotor wings is independent.
2. The rotary wing aircraft with tilting mechanism rotated by flexible steel wire according to claim 1, wherein: the wing tilting device further comprises a tilting shell, wherein the tilting shell is fixed at the outer side end part of the wing, and the tilting rotor mechanism and the tilting tower are installed on the tilting shell.
3. The rotary wing aircraft with the tilting mechanism rotated by the flexible steel wire according to claim 2, wherein: the two ends of the mounting seat of the tilting tower are assembled on the tilting shell through bearings, and the mounting seat of the tilting tower can rotate relative to the tilting shell; the rotor is assembled on a driving shaft which is arranged on the tilting tower and perpendicular to the mounting seat.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210452535.7A CN114802737B (en) | 2022-04-27 | 2022-04-27 | Rotary wing aircraft with tilting mechanism driven by flexible steel wire |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210452535.7A CN114802737B (en) | 2022-04-27 | 2022-04-27 | Rotary wing aircraft with tilting mechanism driven by flexible steel wire |
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| CN114802737A CN114802737A (en) | 2022-07-29 |
| CN114802737B true CN114802737B (en) | 2024-04-16 |
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Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008085195A2 (en) * | 2006-08-15 | 2008-07-17 | Abe Karem | Improved wing efficiency for tilt-rotor aircraft |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| JP2012111475A (en) * | 2010-11-28 | 2012-06-14 | Kenta Yasuda | Vertical takeoff and landing unmanned aircraft by wing-rotor |
| CN102632994A (en) * | 2012-05-05 | 2012-08-15 | 扬州大学 | Tilt rotor aircraft |
| CN103466087A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Nacelle tilting mechanism for tilt rotor aircraft |
| CN104768848A (en) * | 2012-07-27 | 2015-07-08 | 乔纳森·黑塞尔巴尔斯 | Vertical-takeoff aircraft |
| CN105711830A (en) * | 2016-05-10 | 2016-06-29 | 左建章 | Rotor-wing craft with two tilting flaps with balanced axial vector |
| CN106184736A (en) * | 2016-08-29 | 2016-12-07 | 天津中翔腾航科技股份有限公司 | The compound aircraft that a kind of fixed-wing forms with many rotors |
| KR20170118383A (en) * | 2016-04-15 | 2017-10-25 | 한국산업기술대학교산학협력단 | Aerial vehicle |
| CN108372930A (en) * | 2018-03-14 | 2018-08-07 | 长沙市云智航科技有限公司 | The component that verts for manned more rotor flying vehicles |
| CN210971521U (en) * | 2019-10-22 | 2020-07-10 | 深圳悟空飞行器有限公司 | Front and back rotor wing synchronous tilting and hanging disc type rotor wing aircraft |
| JP2021123322A (en) * | 2020-02-06 | 2021-08-30 | 有限会社エーエムクリエーション | Electric aircraft |
| CN114313251A (en) * | 2022-03-03 | 2022-04-12 | 天津斑斓航空科技有限公司 | Combined type aircraft active tilting structure and aircraft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7427047B2 (en) * | 2004-05-10 | 2008-09-23 | Omid Saeed Tehrani | Powered aircraft including inflatable and rotatable bodies exhibiting a circular cross-section perpendicular to its rotation axis and in order to generate a lift force |
| KR101125870B1 (en) * | 2011-07-29 | 2012-03-28 | 한국항공우주연구원 | The tiltrotor aircraft |
| US10071801B2 (en) * | 2013-08-13 | 2018-09-11 | The United States Of America As Represented By The Administrator Of Nasa | Tri-rotor aircraft capable of vertical takeoff and landing and transitioning to forward flight |
| FR3065440B1 (en) * | 2017-04-24 | 2019-06-07 | Fly-R | VERTICAL LANDING AIRCRAFT RHOMBOEDRICAL VESSEL |
| ES2917775T3 (en) * | 2017-06-26 | 2022-07-11 | Acc Innovation Ab | Rotor Flying Vehicle |
| WO2021034640A1 (en) * | 2019-08-16 | 2021-02-25 | Textron Systems Corporation | Separated lift-thrust vtol aircraft with articulated rotors |
-
2022
- 2022-04-27 CN CN202210452535.7A patent/CN114802737B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008085195A2 (en) * | 2006-08-15 | 2008-07-17 | Abe Karem | Improved wing efficiency for tilt-rotor aircraft |
| CN101423117A (en) * | 2008-12-05 | 2009-05-06 | 北京航空航天大学 | Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder |
| JP2012111475A (en) * | 2010-11-28 | 2012-06-14 | Kenta Yasuda | Vertical takeoff and landing unmanned aircraft by wing-rotor |
| CN102632994A (en) * | 2012-05-05 | 2012-08-15 | 扬州大学 | Tilt rotor aircraft |
| CN104768848A (en) * | 2012-07-27 | 2015-07-08 | 乔纳森·黑塞尔巴尔斯 | Vertical-takeoff aircraft |
| CN103466087A (en) * | 2013-08-23 | 2013-12-25 | 中国航空工业集团公司西安飞机设计研究所 | Nacelle tilting mechanism for tilt rotor aircraft |
| KR20170118383A (en) * | 2016-04-15 | 2017-10-25 | 한국산업기술대학교산학협력단 | Aerial vehicle |
| CN105711830A (en) * | 2016-05-10 | 2016-06-29 | 左建章 | Rotor-wing craft with two tilting flaps with balanced axial vector |
| CN106184736A (en) * | 2016-08-29 | 2016-12-07 | 天津中翔腾航科技股份有限公司 | The compound aircraft that a kind of fixed-wing forms with many rotors |
| CN108372930A (en) * | 2018-03-14 | 2018-08-07 | 长沙市云智航科技有限公司 | The component that verts for manned more rotor flying vehicles |
| CN210971521U (en) * | 2019-10-22 | 2020-07-10 | 深圳悟空飞行器有限公司 | Front and back rotor wing synchronous tilting and hanging disc type rotor wing aircraft |
| JP2021123322A (en) * | 2020-02-06 | 2021-08-30 | 有限会社エーエムクリエーション | Electric aircraft |
| CN114313251A (en) * | 2022-03-03 | 2022-04-12 | 天津斑斓航空科技有限公司 | Combined type aircraft active tilting structure and aircraft |
Non-Patent Citations (3)
| Title |
|---|
| 不断发展的倾转旋翼机;蔡汝鸿;;直升机技术;20050628(第02期);第49-53页 * |
| 无人倾转旋翼机飞行控制系统设计;马文辉;中国优秀硕士学位论文全文数据库 (工程科技Ⅱ辑);20180331;第C031-254页 * |
| 独具特色的倾转旋翼机技术;张广林;;现代军事;20021231(第09期);第40-42页 * |
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| CN114802737A (en) | 2022-07-29 |
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