CN112478151A - Electric direct-drive tilt rotor aircraft - Google Patents
Electric direct-drive tilt rotor aircraft Download PDFInfo
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- CN112478151A CN112478151A CN202011419953.3A CN202011419953A CN112478151A CN 112478151 A CN112478151 A CN 112478151A CN 202011419953 A CN202011419953 A CN 202011419953A CN 112478151 A CN112478151 A CN 112478151A
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- 238000010168 coupling process Methods 0.000 claims description 8
- 238000005859 coupling reaction Methods 0.000 claims description 8
- 125000004122 cyclic group Chemical group 0.000 claims description 6
- 230000007246 mechanism Effects 0.000 description 14
- 230000000737 periodic effect Effects 0.000 description 9
- 238000000034 method Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000009977 dual effect Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
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- 238000006073 displacement reaction Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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- 230000001141 propulsive effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
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- 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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- 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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- 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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Abstract
The invention provides an electric direct-drive tilt rotor craft, which adopts an electric direct-drive rotor blade power system as a power device, wherein the rotor blade power system comprises: the electric drive assembly is used for driving the blades of the rotor blade control assembly to rotate so as to generate lift force; the rotor blade control assembly is used for adjusting the total pitch and longitudinally and periodically changing the pitch of the rotor blades; the tilting assembly is used for driving the electric drive assembly and the rotor blade control assembly to rotate; the electric drive assembly is connected with the rotor blade control assembly, a rotor blade shaft in the electric drive assembly is arranged in the center of the rotor blade control assembly, and the two rotor blade control assemblies are respectively arranged at the left end and the right end of the tilting assembly; rotor oar driving system sets up in the aircraft organism, two the rotor oar control assembly sets up respectively in controlling the wing, verts subassembly and aircraft organism fixed connection.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an electric direct-drive tilt rotor aircraft.
Background
The tilt rotor aircraft is in the two wing tip departments of similar fixed wing aircraft wing, each dress set can be at the pivoted rotor subassembly that verts between horizontal position and vertical position, when the aircraft takes off perpendicularly and lands, rotor shaft perpendicular to ground, be the horizontal formula helicopter flight state, and can hover in the air, fly around and the side, take off after reaching the certain speed at the tilt rotor aircraft, the rotor shaft can be forward or 90 jiaos of verting backward, be horizontal state, the rotor uses as pulling force screw or thrust screw, the tilt rotor can do long-range flight like fixed wing aircraft with higher speed this moment, the driving system of tilt rotor aircraft possesses the dual function of screw and rotor simultaneously promptly.
The fixed wing aircraft generally adopts propellers as a power device, the helicopter generally adopts a rotor wing as a power device, the propellers are devices which rotate in the air or water by means of blades and convert the rotating power of an engine into propulsive force, two or more blades can be connected with a hub, and the backward surface of each blade is a helicoid or a propeller similar to the helicoid; the rotor wing is an important part of the helicopter, and plays a dual role in generating lift force and pulling force in the flying process of the helicopter; the rotor is composed of a hub and a plurality of blades, the hub is arranged on a rotor shaft, the blades in the shape of slender wings are connected on the hub, but the rotor shaft of the common rotor is generally arranged along the vertical direction and cannot rotate to the horizontal direction.
Correspondingly, the tilt rotor aircraft adopts a rotor blade or a rotor blade as a power device. This patent will be applied to on the gyroplane that verts, can enough provide horizontal tension for the gyroplane that verts in order to overcome full quick-witted aerodynamic resistance and realize its high-speed flat flight, can provide vertical tension again in order to overcome earth gravitation in order to realize the gyroplane that verts VTOL and the power device definition of hovering steadily be rotor oar or oar rotor, and vertical direction can be followed to the rotor shaft of its rotor, also can rotate to the horizontal direction to distinguish with ordinary rotor.
For small and medium-sized unmanned tilt-rotor aircraft, a jet engine and a piston engine are difficult to arrange; in addition, the rotor operation mode of the traditional tilt rotor aircraft is relayed from the helicopter operation mode, and when the helicopter mode flies, longitudinal and transverse periodic variable pitch and total pitch mechanisms are all arranged, but only the longitudinal periodic variable pitch and the total pitch mechanism are needed under the actual tilt rotor aircraft helicopter state, and the additional transverse periodic variable pitch mechanism can increase the mechanism complexity, reduce the reliability and increase the weight.
Disclosure of Invention
In order to solve the problems, the invention provides an electric direct-drive tilt rotor aircraft, which aims to solve the problems of difficult power source arrangement, complex operating mechanism and the like of the traditional tilt rotor propeller aircraft; the motor is adopted for direct drive, and a novel total pitch, longitudinal periodic pitch changing mechanism and an electric tilting mechanism are designed, so that the electric tilting rotor aircraft is more suitable for small and medium-sized unmanned tilting rotor aircrafts, and is simple in structure, high in reliability and light in weight; compared with a conventional helicopter rotor system, the variable-pitch control system can realize a larger blade pitch range and meet the requirement of a tilt rotor aircraft on a large pitch in a forward flight axial flow state.
The invention provides an electric direct-drive tilt rotor craft, which adopts an electric direct-drive rotor blade power system as a power device, wherein the rotor blade power system comprises: the electric drive assembly is used for driving the blades of the rotor blade control assembly to rotate so as to generate lift force; the rotor blade control assembly is used for adjusting the total pitch and longitudinally and periodically changing the pitch of the rotor blades; the tilting assembly is used for driving the electric drive assembly and the rotor blade control assembly to rotate; the electric drive assembly is connected with the rotor blade control assembly, a rotor blade shaft in the electric drive assembly is arranged in the center of the rotor blade control assembly, and the two rotor blade control assemblies are respectively arranged at the left end and the right end of the tilting assembly; rotor oar driving system sets up in the aircraft organism, two the rotor oar control assembly sets up respectively in controlling the wing, verts subassembly and aircraft organism fixed connection.
Further, the electric drive assembly includes a motor and a rotor shaft, the rotor shaft being coupled to an output shaft of the motor.
Further, the electric drive assembly further comprises a motor speed regulator, the motor speed regulator is fixedly connected with the motor, and the motor speed regulator is used for controlling the rotation speed regulation of the motor.
Further, the electric drive assembly further comprises a coupling, and the rotor shaft and the motor are connected together through the coupling.
Furthermore, the rotor blade control assembly comprises a rack, a steering engine rocker arm, a second connecting rod, a lower torsion arm lever, a lower torsion arm support, a lower torsion arm connecting rod, an inclinator outer ring, an inclinator inner ring assembly, a first upper torsion arm, a second upper torsion arm, an upper torsion arm hoop, a first connecting rod, a blade clamp, a hub and blades; the steering engine and the lower torque arm support are fixedly connected with the rack; the steering engine, the steering engine rocker arm, the second connecting rod and the lower torsion arm lever are sequentially connected; the lower torsion arm lever is hinged with the lower torsion arm support and the lower torsion arm connecting rod at the same time, and the lower torsion arm connecting rod is hinged with the outer ring of the inclinator; the outer side of the tilter inner ring component is hinged with the tilter outer ring, and the inner side of the tilter inner ring component is connected with the rotor shaft through a spherical hinge; the tilter inner ring assembly is connected with a rocker arm of the paddle clamp through a first connecting rod; the inclinator inner ring assembly, the first upper torsion arm, the second upper torsion arm and the upper torsion arm hoop are connected in sequence; the upper torque arm hoop is fixedly connected with the rotor shaft; the paddle clamp is hinged to the hub, and the hub is hinged to the rotor shaft.
Further, the angle range of the periodic variable pitch of the blades is-20 degrees.
Furthermore, the tilting assembly comprises a tilting rudder base, a tilting steering engine, an operating rod, a tilting bearing and a tilting rod which are connected in sequence; the left end and the right end of the tilting rod are respectively fixedly connected with a pipe joint, and the pipe joints are fixedly connected with a rack of the rotor blade control assembly.
Further, the inner ring of the tilting bearing is fixedly connected with the tilting rod, and the outer ring of the tilting bearing is fixedly connected with the aircraft body.
Furthermore, the tilting rudder engine base is fixedly connected with the aircraft body and used for supporting the tilting assembly to actuate.
Furthermore, the tilting steering engine is a linear steering engine, and the actuating stroke of the tilting steering engine can enable the rotation range of the electric drive assembly and the rotor blade control assembly to reach 0-95 degrees.
The invention has the beneficial effects that: the problems that the power source of the traditional tilt rotor aircraft is difficult to arrange, the control mechanism is complex and the like are solved; the motor is adopted for direct drive, and a novel total pitch, longitudinal periodic pitch changing mechanism and an electric tilting mechanism are designed, so that the electric tilting rotor aircraft is more suitable for small and medium-sized unmanned tilting rotor aircrafts, and is simple in structure, high in reliability and light in weight; compared with a conventional helicopter rotor system, the variable-pitch propeller disclosed by the invention can realize a larger blade pitch range, and meets the requirement of a tilting rotor on a large pitch in a forward flight axial flow state.
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 embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic structural view of an electric direct-drive tiltrotor aircraft;
FIG. 2 is a schematic view of a hidden portion of a skin of an electric direct drive tiltrotor aircraft;
FIG. 3 is a schematic representation of the components of a rotor blade power system;
FIG. 4 is a schematic diagram of the components of the electric drive assembly;
figure 5 is a schematic view of a rotor blade steering assembly;
FIG. 6 is a schematic view of the tilt assembly;
FIG. 7 is a schematic view of an inner ring assembly of the recliner.
Description of reference numerals:
100-an electric drive assembly; 101-motor speed controller; 102-a motor; 103-a coupler; 104-rotor shaft; 200-a rotor-paddle steering assembly; 201-a frame; 202-lower torque arm support; 203-lower torsion arm lever; 204-lower torsion arm linkage; 205-a tilter inner ring assembly; 2051-recliner inner ring; 2052-inner ring compression ring of the inclinator; 206-a first upper torsion arm; 207-a second upper torsion arm; 208-paddle clamp; 209-hub; 210-an upper torque arm yoke; 211-a first link; 212-tilter outer ring; 213-a steering engine; 214-a second link; 215-steering engine rocker arm; 300-a tilt assembly; 301-tilting the rudder mount; 302-tilt steering engine; 303-a joystick; 304-tilt bearings; 305-a tilt lever; 306-a pipe joint; 400-aircraft airframe.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. 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. 1-3, an electric direct-drive tilt rotor craft adopts an electric direct-drive rotor blade power system as a power device, and the rotor blade power system includes an electric drive assembly 100 for driving blades of a rotor blade control assembly 200 to rotate so as to generate lift force; a rotor blade steering assembly 200 for collective pitch adjustment and longitudinal cyclic pitch variation of the rotor blades; a tilt assembly 300 for driving rotation of electric drive assembly 100 and rotor paddle manipulation assembly 200; the electric drive assembly 100 is connected to the rotor blade manipulating assembly 200, the rotor shaft 104 of the electric drive assembly 100 is disposed at the center of the rotor blade manipulating assembly 200, and the two rotor blade manipulating assemblies 200 are disposed at the left and right ends of the tilt assembly 300, respectively; rotor oar driving system sets up in aircraft organism 400, two rotor oar control assembly 200 sets up respectively in controlling the wing, verts subassembly 300 and aircraft organism 400 fixed connection.
Referring to fig. 4, the electric drive assembly 100 includes a motor governor 101, a motor 102, a coupling 103, and a rotor shaft 104; the motor speed regulator 101 is fixedly connected with the motor 102, the motor speed regulator 101 is used for controlling the rotation speed adjustment of the motor 102, and the rotor shaft 104 is connected with the motor 102 through the coupler 103 and used for transmitting the torque generated by the motor 102 to the rotor shaft 104.
Referring to fig. 5, rotor blade steering assembly 200 includes frame 201, lower torque arm mount 202, lower torque arm lever 203, lower torque arm link 204, tilter inner ring assembly 205, first upper torque arm 206, second upper torque arm 207, blade clamp 208, hub 209, upper torque arm yoke 210, first link 211, tilter outer ring 212, steering engine 213, second link 214, and steering engine rocker 215.
The number of the steering engines 213, the steering engine rocker arm 215, the second connecting rod 214 and the lower torsion arm lever 203 is two, and each steering engine 213, the steering engine rocker arm 215, the second connecting rod 214 and the lower torsion arm lever 203 are connected in sequence; the two lower torque arm levers 203 are respectively hinged with two ends of the lower torque arm support 202; the steering engine 213 is fixedly connected with the frame 201 and can drive a steering engine rocker arm 215 to rotate, the steering engine rocker arm 215 is connected with one end of a second connecting rod 214 through a joint bearing, and the other end of the second connecting rod 214 is connected with the lower torsion arm lever 203 through a joint bearing; one end of the lower torsion arm connecting rod 204 is hinged with the lower torsion arm lever 203, and the other end is hinged with the tilter outer ring 212; the outer side of tilter inner ring assembly 205 is hinged to tilter outer ring 212, and the inner side is connected to rotor shaft 104 by a spherical hinge; the tilter inner ring assembly 205, see fig. 7, is comprised of a tilter inner ring 2051, a tilter inner ring collar 2052, which are threadably connected, the outer side of the tilter inner ring collar 2052 is hinged to the tilter outer ring 212 by deep groove ball bearings, and the inner side of the tilter inner ring 2051 is ball hinged to the rotor shaft 104; first upper torsion arm 206 is connected to tilter inner ring assembly 205 via a knuckle bearing; one end of the second upper torque arm 207 is hinged to the first upper torque arm 206 and the other end is hinged to an upper torque arm clip 210, the upper torque arm clip 210 being fixedly connected to the rotor shaft 104; the paddle clamp 208 is hinged with a paddle hub 209 and is used for mounting the blades of the rotor paddle; hub 209 is hinged to rotor shaft 104, and hub 209 and rotor shaft 104 have a rotational degree of freedom therebetween to accommodate blade flapping; first link 211 has one end coupled to the swing arm of paddle clamp 208 via a knuckle bearing and the other end coupled to tilter inner ring assembly 205 via a knuckle bearing.
The connection between lower torque arm support 202, lower torque arm lever 203, lower torque arm link 204, and tilter outer ring 212 are all hinged, thereby limiting the cyclic pitch of rotor assembly 200 to only a longitudinal direction.
The components in rotor blade steering assembly 200 are designed in coordination to meet the cyclic pitch angle of the blades in the range of-20 to 20.
Referring to fig. 6, tilt assembly 300 includes tilt rudder mount 301, tilt rudder 302, operating lever 303, tilt bearing 304, tilt lever 305 and pipe joint 306. The tilting rudder base 301 is fixedly connected with the aircraft body 400 to be used as a support for actuating the tilting assembly; one end of the tilting steering engine 302 is hinged with the tilting steering engine seat 301, the other end of the tilting steering engine 302 is hinged with the operating rod 303, and the operating rod 303 is fixedly connected with the tilting rod 305; the inner ring of the tilting bearing 304 is fixedly connected with the tilting rod 305, and the outer ring of the tilting bearing 304 is fixedly connected with the aircraft body 400; tilt rod 305 is fixedly attached at both ends to coupling 306, and coupling 306 is fixedly attached to frame 201 of rotor blade steering assembly 200.
The tilting steering engine 302 is a linear steering engine, and the actuating stroke of the tilting steering engine can enable the rotating range of the electric drive assembly 100 and the rotor blade control assembly 200 to reach 0-95 degrees.
Referring to fig. 4 to 6, the specific operation process of the embodiment is as follows:
referring to fig. 4 and 5, after the motor governor 101 is powered on, the driving motor 102 rotates, the shaft coupler 103 drives the rotor shaft 104 to rotate, and the rotor shaft 104 drives the hub 209 and the blade clamp 208 hinged thereto to rotate, so as to drive the blades to rotate and generate lift force. Rotor shaft 104 drives upper torque arm yoke 210 to rotate, and first upper torque arm 206 and second upper torque arm 207 hinged to it drive tilter inner ring assembly 205 and rotor shaft 104 to rotate at a constant speed, and tilter inner ring assembly 205 and rotor shaft 104 are connected in a spherical hinge manner, so that tilter inner ring assembly 205 can rotate with rotor shaft 104 while realizing a certain angle of tilt to meet the requirement of periodic variable pitch.
Referring to fig. 5, two steering engines 213 rotate two steering engine rocker arms 215 at the same or different angles, and the steering engine rocker arms 215 drive the second connecting rods 214, the lower torsion arm levers 203, the lower torsion arm connecting rods 204, the tilter inner ring assembly 205, the first upper torsion arms 206, the second upper torsion arms 207, the paddle clamps 208, the first connecting rods 211, the tilter outer rings 212 and the first connecting rods 211 to move, so that the paddle clamps 208 finally rotate around the paddle hubs 209, and the total pitch and the longitudinal cyclic pitch of the rotor paddles are adjusted.
Referring to fig. 6, the tilt actuator 302 actuates and pushes or pulls the operating rod 303 to rotate the tilt rod 305 around the tilt bearing 304, and the pipe joint 306 fixedly connected to the tilt rod 305 drives the frame 201 to rotate, thereby driving the electric drive assembly 100 and the rotor blade control assembly 200 to rotate around the tilt bearing 304.
The invention has the beneficial effects that: the problems that the power source of the traditional tilt rotor aircraft is difficult to arrange, the control mechanism is complex and the like are solved; the motor is adopted for direct drive, and a novel total pitch, longitudinal periodic pitch changing mechanism and an electric tilting mechanism are designed, so that the tilting mechanism is more suitable for small and medium-sized unmanned tilting rotorcraft, and has the advantages of simple structure, high reliability and light weight; compared with a conventional helicopter rotor system, the variable-pitch propeller disclosed by the invention can realize a larger blade pitch range, and meets the requirement of a tilting rotor on a large pitch in a forward flight axial flow state.
Finally, it should also be noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The utility model provides an electronic rotor craft that verts that directly drives, its characterized in that adopts electronic rotor oar driving system who directly drives as power device, rotor oar driving system includes: an electric drive assembly (100) for rotating the blades of the rotor paddle steering assembly (200) to generate lift; a rotor blade steering assembly (200) for collective pitch adjustment and longitudinal cyclic pitch variation of the rotor blades; the tilting assembly (300) is used for driving the electric drive assembly (100) and the rotor blade control assembly (200) to rotate; the electric drive assembly (100) is connected with the rotor paddle manipulation assemblies (200), a rotor paddle shaft (104) in the electric drive assembly (100) is arranged at the center of the rotor paddle manipulation assemblies (200), and the two rotor paddle manipulation assemblies (200) are respectively arranged at the left end and the right end of the tilting assembly (300); rotor oar driving system sets up in aircraft organism (400), two rotor oar control assembly (200) sets up respectively in controlling the wing, verts subassembly (300) and aircraft organism (400) fixed connection.
2. An electric direct drive tiltrotor aircraft according to claim 1, wherein the electric drive assembly (100) comprises an electric motor (102) and a rotor shaft (104), the rotor shaft (104) being connected to an output shaft of the electric motor (102).
3. An electric direct drive tiltrotor aircraft according to claim 1, wherein the electric drive assembly (100) further comprises a motor governor (101), the motor governor (101) being fixedly connected to the motor (102), the motor governor (101) being adapted to control the speed regulation of the motor (102).
4. An electric direct drive tiltrotor aircraft according to claim 1, wherein the electric drive assembly (100) further comprises a coupling (103), the rotor shaft (104) and the electric motor (102) being connected together by the coupling (103).
5. The electric direct-drive tiltrotor aircraft according to claim 1, wherein the rotor blade steering assembly (200) comprises a frame (201), a steering engine (213), a steering engine rocker arm (215), a second connecting rod (214), a lower torque arm lever (203), a lower torque arm support (202), a lower torque arm connecting rod (204), a tilter outer ring (212), a tilter inner ring assembly (205), a first upper torque arm (206), a second upper torque arm (207), an upper torque arm yoke (210), a first connecting rod (211), a blade clamp (208), a hub (209) and blades; the steering engine (213) and the lower torsion arm support (202) are fixedly connected with the rack (201); the steering engine (213), the steering engine rocker arm (215), the second connecting rod (214) and the lower torsion arm lever (203) are connected in sequence; the lower torsion arm lever (203) is hinged with the lower torsion arm support (202) and the lower torsion arm connecting rod (204) at the same time, and the lower torsion arm connecting rod (204) is hinged with the outer ring (212) of the tilter; the outer side of the tilter inner ring assembly (205) is hinged with a tilter outer ring (212), and the inner side of the tilter inner ring assembly is connected with the rotor shaft (104) through a spherical hinge; the connection of the tilter inner ring assembly (205) to the swing arm of the paddle clamp (208) via a first link (211); the recliner inner ring assembly (205), the first upper torsion arm (206), the second upper torsion arm (207) and the upper torsion arm hoop (210) are connected in sequence; the upper torque arm clamp (210) is fixedly connected with the rotor shaft (104); the paddle clamp (208) is hinged to a hub (209), and the hub (209) is hinged to the rotor shaft (104).
6. An electric direct drive tiltrotor aircraft according to claim 5, wherein the cyclic pitch of the blades is in the range of-20 ° to 20 °.
7. The electric direct-drive tilt rotor aircraft according to claim 1, wherein the tilt assembly (300) comprises a tilt rudder base (301), a tilt steering engine (302), an operating lever (303), a tilt bearing (304) and a tilt lever (305) which are connected in sequence; the left end and the right end of the tilting rod (305) are respectively fixedly connected with a pipe joint (306), and the pipe joints (306) are fixedly connected with a frame (201) of the rotor blade control assembly (200).
8. An electric direct drive tiltrotor aircraft according to claim 7, wherein the inner ring of the tilt bearing (304) is fixedly connected to a tilt rod (305) and the outer ring of the tilt bearing (304) is fixedly connected to the aircraft body (400).
9. An electric direct drive tiltrotor aircraft according to claim 7, wherein the tilt rudder mount (301) is fixedly connected to the aircraft body (400) for support of actuation of the tilt assembly (300).
10. The electric direct-drive tilt rotor aircraft according to claim 7, wherein the tilt steering engine (302) is a linear steering engine, and the actuation stroke of the tilt steering engine can enable the rotation range of the electric drive assembly (100) and the rotor blade control assembly (200) to reach 0-95 degrees.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419953.3A CN112478151B (en) | 2020-12-05 | 2020-12-05 | Electric direct-drive tilting rotor craft |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011419953.3A CN112478151B (en) | 2020-12-05 | 2020-12-05 | Electric direct-drive tilting rotor craft |
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| CN112478151A true CN112478151A (en) | 2021-03-12 |
| CN112478151B CN112478151B (en) | 2023-05-02 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117446163A (en) * | 2023-12-22 | 2024-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Redundancy tilting control mechanism of tilting rotorcraft |
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|---|---|---|---|---|
| CN117446163A (en) * | 2023-12-22 | 2024-01-26 | 中国航空工业集团公司西安飞机设计研究所 | Redundancy tilting control mechanism of tilting rotorcraft |
| CN117446163B (en) * | 2023-12-22 | 2024-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Redundancy tilting control mechanism of tilting rotorcraft |
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| Publication number | Publication date |
|---|---|
| CN112478151B (en) | 2023-05-02 |
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