MULTIROTOR AERIAL VEHICLE WITH TILTABLE ROTOR

Abstract

A VTOL (vertical take-off and landing) rotorcraft with distributed propulsion system having the capability to convert to airplane flight. The rotorcraft includes a fuselage, a tail boom or tail fin, a pair of wings, a pair of transversally extended forward pivotable rotor booms, a plurality of forward proprotor mounted to the pivotable rotor booms, a plurality of rear lift rotor mounted to the tail boom, and a stabilizer mounted on the tail boom or tail fin. The proprotor and lift rotor can be open rotor or ducted rotor design. The proprotors in a first configuration and lift rotors provide thrust vector for VTOL (vertical take-off and landing) flight. Moreover, the proprotors in a second configuration provide the forward propulsive thrust in airplane flight.

Claims

1. A multirotor vehicle adapted for both VTOL (vertical take-off and landing) and horizontal airplane flight comprising: a longitudinally extended fuselage; a longitudinally extended tail boom, said tail boom is coupled to the rear end of said fuselage; a symmetric pair of transversely extended wings, each of said wings having a proximal end coupled to said fuselage; a symmetric pair of transversely extended tiltable rotor booms, each of said rotor booms associated to an actuator having a proximal end coupled to said fuselage; a symmetric pair of vertically extended pylons, each of said pylons having an upper end coupled to the distal end from each of said wings, and each of said pylons having a lower end coupled to the distal end from each of said tiltable rotor boom; a plurality of proprotor, said plurality of proprotor is coupled to said tiltable rotor booms; a plurality of lift rotor, said plurality of lift rotor is coupled to said tail boom; a symmetric pair of vertical and horizontal stabilizer, each of said vertical and horizontal stabilizer having a horizontal airfoil with the proximal end coupled to said tail boom, and each of said vertical and horizontal stabilizer having a horizontal airfoil with the distal end coupled to the vertical airfoil; a symmetric pair of ailerons, said ailerons associated to an actuator are coupled to said wings; a symmetric pair of rudders, said rudders are coupled to the vertical airfoil of said vertical and horizontal stabilizer; a symmetric pair of elevators, said elevators associated to an actuator are coupled to the horizontal airfoil of said vertical and horizontal stabilizer; a symmetric pair of jet nozzles, said jet nozzles associated to a motor fan are coupled to said vertical and horizontal stabilizer.

2. A multirotor vehicle as set forth in claim 1, wherein said plurality of proprotor can have blades with variable collective pitch capability.

3. A multirotor vehicle as set forth in claim 1, wherein said plurality of proprotor in the VTOL configuration and plurality of lift rotor can have the axis of rotation canted from the vertical axis to direct rotor burst trajectory away from critical flight components and passenger.

4. A multirotor vehicle as set forth in claim 1, wherein said pair of tiltable rotor booms can tilt on the pitch axis to orient the thrust vector of said plurality of proprotor vertically downward in VTOL flight, diagonally downward and aftward in partial wing borne flight, and horizontally aftward in airplane flight.

5. A multirotor vehicle as set forth in claim 1, wherein said plurality of proprotor in the VTOL flight configuration and said plurality of lift rotor provide the vertical thrust vector to hover, fly up, fly down, fly forward, fly backward, fly sideway and change yaw heading.

6. A multirotor vehicle as set forth in claim 1, wherein said plurality of proprotor in airplane flight configuration provides the thrust for horizontal flight and said wings provide the lift force to maintain airborne.

7. A multirotor vehicle as set forth in claim 1, wherein said pair of ailerons, said pair of rudders and said pair of elevators provide the flight control for pitch, roll and yaw during airplane flight.

8. A multirotor vehicle as set forth in claim 1, wherein said jet nozzles provide the lateral thrust to correct yaw motion.

9. A multirotor vehicle adapted for both VTOL (vertical take-off and landing) and horizontal airplane flight comprising: a longitudinally extended fuselage; a longitudinally extended tail fin, said tail fin is coupled to the rear end of said fuselage; a symmetric pair of transversely extended wings, each of said wings having a proximal end coupled to said fuselage; a symmetric pair of transversely extended tiltable rotor booms, each of said rotor booms associated to an actuator having a proximal end coupled to said fuselage; a symmetric pair of vertically extended pylons, each of said pylons having an upper end coupled to the distal end from each of said wings, and each of said pylons having a lower end coupled to the distal end from each of said tiltable rotor boom; a plurality of ducted proprotor, said plurality of ducted proprotor is coupled to said tiltable rotor booms; a plurality of ducted lift rotor, said plurality of ducted lift rotor is coupled to said tail fin; a symmetric pair of vertical and horizontal stabilizer, each of said vertical and horizontal stabilizer having a horizontal airfoil with the proximal end coupled to said tail fin, and each of said vertical and horizontal stabilizer having a horizontal airfoil with the distal end coupled to the vertical airfoil; a symmetric pair of ailerons, said ailerons associated to an actuator are coupled to said wings; a symmetric pair of rudders, said rudders are coupled to the vertical airfoil of said vertical and horizontal stabilizer; a symmetric pair of elevators, said elevators associated to an actuator are coupled to the horizontal airfoil of said vertical and horizontal stabilizer; a symmetric pair of jet nozzles, said jet nozzles associated to a motor fan are coupled to said vertical and horizontal stabilizer.

10. A multirotor vehicle as set forth in claim 9, wherein said plurality of ducted proprotor can have blades with variable collective pitch capability.

11. A multirotor vehicle as set forth in claim 9, wherein said plurality of ducted proprotor in the VTOL configuration and plurality of ducted lift rotor can have the axis of rotation canted from the vertical axis to direct rotor burst trajectory away from critical flight components and passenger.

12. A multirotor vehicle as set forth in claim 9, wherein said pair of tiltable rotor booms can tilt on the pitch axis to orient the thrust vector of said plurality of ducted proprotor vertically downward in VTOL flight, diagonally downward and aftward in partial wing borne flight, and horizontally aftward in airplane flight.

13. A multirotor vehicle as set forth in claim 9, wherein said plurality of ducted proprotor in the VTOL flight configuration and said plurality of ducted lift rotor provide the vertical thrust vector to hover, fly up, fly down, fly forward, fly backward, fly sideway and change yaw heading.

14. A multirotor vehicle as set forth in claim 9, wherein said plurality of ducted proprotor in airplane flight configuration provides the thrust for horizontal flight and said wings provide the lift force to maintain airborne.

15. A multirotor vehicle as set forth in claim 9, wherein said pair of ailerons, said pair of rudders and said pair of elevators provide the flight control for pitch, roll and yaw during airplane flight.

16. A multirotor vehicle as set forth in claim 9, wherein said jet nozzles provide the lateral thrust to correct yaw motion.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Regarding the invention disclosure, the feature and advantage of the invention are particularly pointed and distinctly claimed in the claims. Detailed description and methods are given to provide further comprehension of the functionality of the invention. It should be observed that three mutual orthogonal directions X, Y, and Z are shown in some of the FIGURES. The first direction X is said to be longitudinal, and the forward side is referenced to be positive. Rotational movement around the longitudinal axis is said to be roll. The second direction Y is said to be transverse, and the port side is referenced to be positive. And the Y plane is referenced as centerline of the vehicle. Rotational movement around the transverse axis is said to be pitch. Finally, the third direction Z is said to be vertical, and the up side is referenced to be positive. Rotational movement around the vertical axis is said to be yaw. Furthermore, the direction of motion or rotation is shown in hollow arrow and force vector is shown in solid arrow.

[0011] FIG. 1 is a perspective view of the multirotor vehicle in according to an embodiment of the present invention during VTOL flight.

[0012] FIG. 2 is a top plane view from the embodiment of FIG. 1.

[0013] FIG. 3 is a perspective view of the multirotor vehicle in according to an embodiment transitioning between different flight configurations.

[0014] FIG. 4 is a perspective view of the multirotor vehicle in according to an embodiment of the present invention during airplane flight.

[0015] FIG. 5 is a top plane view from the embodiment of FIG. 4.

[0016] FIG. 6 is a perspective view of the multirotor vehicle in according to a second embodiment of the present invention during VTOL flight.

[0017] FIG. 7 is a perspective view of the multirotor vehicle in according to a second embodiment of the present invention during airplane flight.

DETAILED DESCRIPTION OF THE EMBODIMENTS

[0018] Advantageously, VTOL (vertical take-off and landing) vehicle can operate without a long runway. However, VTOL flight requires significantly higher energy than the energy required for a fixed wing aircraft to maintain forward flight. Therefore, the usefulness of VTOL vehicle is limited to short range flight. Modern VTOL vehicle is commonly designed with electrical power plant. In order to reduce the weight of electrical energy storage, an efficient VTOL vehicle can convert to airplane configuration for long range forward fight. In the disclosure of the invention, the technical term rotary wing is referred as rotor, and a rotary wing dedicated to generate lift is referred as lift rotor. Moreover, the technical term proprotor is referred as the rotary wing capable of operating both as an airplane-style propeller and helicopter-style rotor. Moreover, the term symmetric is used to describe a component, feature, or element which is symmetrical with respecting to median plane of the rotorcraft. It is further understood that the terms includes, including, comprises, comprising, couples, coupled, mounts, and mounted, when used herein, specify the presence of stated features, components and elements, without the further detail on the method of mechanical interconnexion. In addition, it is also understood that the singularity form a, an, and the used throughout the description are intended to includes plural forms as well, unless the context clearly specifies otherwise.

[0019] As shown in FIGS. 1 to 2, multirotor aerial vehicle from embodiment 100 in VTOL flight configuration. FIG. 1 shows a perspective view of the embodiment 100. The multirotor vehicle 100 comprises of the fuselage 101, the tail boom 102, the wings 103, the tiltable rotor booms 104, the pylons 105, a plurality of forward proprotor 106, a plurality of tail lift rotor 107, the vertical and horizontal stabilizer 108, the ailerons 109, the rudders 110, the elevators 111, and the jet nozzles 112. The longitudinally extended fuselage 101 is coupled together with the longitudinally extended tail boom 102. The proximal ends of the transversely extended symmetric wings 103 are coupled to the upper portion of the fuselage 101. Naturally, the center of the wing's lift force is positioned near the center of gravity of the vehicle along the longitudinal direction. The proximal ends of the transversely extended symmetric tiltable rotor booms 104 are coupled to the lower portion of the fuselage 101. The distal ends of the wings 103 and the distal ends of the tiltable rotor booms 104 are coupled together by the pylons 105 to form the box aerostructure. The 103 wings are provided with the ailerons 109. Each tiltable rotor boom 104 is provided with a plurality of forward proprotor 106, positioned side by side along the transverse axis. Embodiment 100 is an example having two proprotors 106 on each of the rotor booms 104, but not limited to two proprotors 106. The tiltable rotor booms 104 are shown in the VTOL flight configuration. The tiltable rotor booms 104 is associated to an actuator to tilt up and down to change the proprotors 106 thrust vector relative to the fuselage 101. The tail boom 102 is provided with a plurality of lift rotors 107, positioned tandemly along the longitudinal axis. Embodiment 100 is an example having two lift rotors 107 on the tail boom 102, but not limited to two lift rotors 107. A practical application can have a combination of a total of four, six, eight or ten proprotors 106 and two, four or six lift rotor 107. The proprotor 106 might have fixed pitch or variable pitch blade to achieve optimal operational efficiency for both VTOL flight and airplane flight. The vertical and horizontal stabilizer 108 is coupled to the tail boom 102. The vertical and horizontal stabilizer 108 is provided with the rudders 110, and elevators 111. The vertical and horizontal stabilizer 108 might have hinged trim tabs to tune the heading, levelling, speed and attitude of the vehicle. Moreover, the vertical and horizontal stabilizer 108 is provided with the jet nozzles 112.

[0020] FIG. 2 shows a top plane view of the multirotor aerial vehicle from embodiment 100 in VTOL flight configuration. One possible combination of the rotational direction of the proprotors 106 and lift rotors 107 are shown in hollow arrows.

[0021] FIG. 3 shows perspective view of the multirotor aerial vehicle from embodiment 100 transitioning to different flight configurations.

[0022] FIG. 4 shows a perspective view of the multirotor aerial vehicle from embodiment 100 in airplane flight configuration.

[0023] FIG. 5 shows a top plane view of the multirotor aerial vehicle from embodiment 100 in airplane flight configuration.

[0024] The multirotor aerial vehicle in VTOL configuration from embodiment 100 in different flight configurations is shown in FIG. 3. The operation in different flight configurations is described in the following section. The multirotor vehicle 100 has four proprotors 106 and two lift rotors 107 to operate in VTOL flight (thrust borne flight). The tiltable rotor booms 104 to pitch the proprotors 106 to direct the thrust vector vertically. An example of the direction of the rotation of the proprotors are shown by the hollow arrow in FIG. 2. As a result of the counter-rotation nature, the torque effect is net zero for each pair of lift rotors 107, each pair of starboard side proprotors 106 and port side proprotors 106 operating at the same power setting. Naturally, the four proprotors 106 and two lift rotors 107 provide the thrust vector during VTOL flight for taking-off, landing, hovering, and flying vertically. The effective maneuvering thrust vectors are shown in solid arrow and the direction of travel is shown in hollow arrow in FIG. 3. Moreover, the modulation of the power setting of the proprotors 106 and lift rotors 107 creates a desirable torque effect to assist the vehicle to change yaw heading. The axis of the rotation of the proprotors 106 and lift rotors 107 may be canted from the vertical axis to minimize the damage resulting from a blade failure event (commonly referred as rotor burst). In detail, the canted orientating allows rotor burst trajectory to avoid impacting the fuselage 101, adjacent propulsion component and flight critical component. In the event of a failure of one of the proprotors 106 or lift rotors 107, the unbalanced yawing motion can be counted by the jet nozzles 112. The jet nozzles 112 associated by a motor fan provides a thrust vector in the longitudinal direction against the rotor boom 102 to create a corrective yawing torque moment acting on the multirotor vehicle 100. The lateral thrust vectors along the transverse direction of the jet nozzles 112 are shown in FIG. 3. The propulsive thrust of the jet nozzles 112 is not affected by the propwash of the lift rotors 107. In order to transition from VTOL flight (thrust borne flight) to airplane flight (wing borne flight), the tiltable rotor boom 104 tilts from VTOL flight configuration to airplane flight configuration. Firstly, the tiltable rotors boom 104 tilts the orientation of the proprotors 106 thrust vector between vertical and horizontal direction. Meanwhile, the thrust vector of the proprotors 106 has a vertical component to lift the vehicle and a horizontal component to repel the vehicle. Consequently, the power setting of the proprotors 106 also increased to produce higher thrust. Beneficially, the wings 103 is not affected by the downwash flow of the proprotors 106. Therefore, undisturbed air flow interacts with the wings 102 to generate airfoil lift force. The vehicle is known to be in partial wing borne flight due to the sum of the airborne lift force is contributed by the wings 103, proprotors 106 and lift rotors 107. As the vehicle gains higher forward speed in levelled flight, the wing lift force increases and overall thrust lift force decreases. This process allows a smooth transition from thrust borne flight to wing borne flight. Finally, upon reaching the desired cruise speed, the flight is fully transition to airplane flight when all the airborne lift force is provided by the wings 103. Moreover, the tiltable rotor booms 104 tilt the proprotors 106 to the airplane flight configuration to direct the thrust vector horizontally and the proprotors 106 continue to propel the vehicle throughout the forward flight. Moreover, lift rotors 107 become unpowered and the blade of the lift rotors 107 are stowed in parallel with the longitudinal axis to reduce aerodynamic drag. In airplane flight, the actuatable ailerons 109, rudders 110, and elevators 111 provide the flight control capability to steer the vehicle in the pitch, roll and yaw axis. Finally, vertical and horizontal stabilizer 108 provides directional stability during airplane flight and might have hinged trim tabs to tune the heading, levelling, speed and attitude of the vehicle.

[0025] As shown in FIGS. 6 to 7, multirotor aerial vehicle from embodiment 200. FIG. 6 shows a perspective view of the embodiment 200 in VTOL flight configuration. The multirotor vehicle 200 comprises of the fuselage 201, the blended tail fin 202, the wings 203, the tiltable rotor booms 204, the pylons 205, a plurality of forward ducted proprotor 206, a plurality of ducted tail lift rotor 207, the vertical and horizontal stabilizer 208, the ailerons 209, the rudders 210, the elevators 211, and the jet nozzles 212. The longitudinally extended fuselage 201 is coupled together with the longitudinally extended tail fin 202. The tail fin 202 is blended with the fuselage 201 for aerodynamic benefit. The proximal ends of the transversely extended symmetric wings 203 are coupled to the upper portion of the fuselage 201. Naturally, the center of the wing's lift force is positioned near the center of gravity of the vehicle along the longitudinal direction. The proximal ends of the transversely extended symmetric tiltable rotor booms 204 are coupled to the lower portion of the fuselage 201. The distal ends of the wings 203 and the distal ends of the tiltable rotor booms 204 are coupled together by the pylons 205 to form the box aerostructure. The 203 wings are provided with the ailerons 209. Each tiltable rotor boom 204 is provided with a plurality of forward ducted proprotor 206, positioned side by side along the transverse axis. Embodiment 200 is an example having two ducted proprotors 206 on each of the rotor booms 204, but not limited to two proprotors 206. The tiltable rotor booms 204 are shown in the VTOL flight configuration. The tiltable rotor booms 204 is associated to an actuator to tilt up and down to change the proprotors 206 thrust vector relative to the fuselage 201. The tail fine 202 is provided with a plurality of ducted lift rotors 207, positioned tandemly along the longitudinal axis. Embodiment 200 is an example having two ducted lift rotors 207 on the tail fin 202, but not limited to two ducted lift rotors 207. A practical application can have a combination of a total of four, six, eight or ten proprotors 206 and two, four or six lift rotor 207. The ducted proprotor 206 might have fixed pitch or variable pitch blade to achieve optimal operational efficiency for both VTOL flight and airplane flight. The duct offers protection and containment for the rotating blade of ducted proprotor 206 and ducted lift rotor 207. The vertical and horizontal stabilizer 208 is coupled to the tail fin 202. The vertical and horizontal stabilizer 208 is provided with the rudders 210, and elevators 211. The vertical and horizontal stabilizer 208 might have hinged trim tabs to tune the heading, levelling, speed and attitude of the vehicle. Moreover, the vertical and horizontal stabilizer 208 is provided with the jet nozzles 212.

[0026] FIG. 7 shows a perspective view of the embodiment 200 in airplane flight configuration. The function and operation of the multirotor aerial vehicle in VTOL and airplane flight from embodiment 200 is exactly the same as embodiment 100. The embodiment 200 is an alternative configuration of the embodiment 100 with the duct wrapped around the proprotors and lift rotors. The ducted proprotors 106 and ducted lift rotors 107 is advantageous for the higher propulsive efficient and lower operational noise. Moreover, the ducted proprotors 106 and ducted lift rotor 107 configuration protects the rotating blades from striking a foreign body and contains any departing blade in a rotor burst event.

[0027] Naturally, there are numerous variations, modifications and alternative configurations which may be made hereto without departing from the scope of the disclosure invention. It should be understood that the embodiments are for illustrative and explanatory purpose and it is not conceivable to identify exhaustively all possible embodiments. In particular, it is important to observe that the invention as described relates in particular to a multirotor aerial vehicle with specific positioning of the forward tiltable rotors and rear fixed rotors secured to the vehicle. Contrary to a handful examples of multirotor VTOL vehicle design, this invention has either tiltable rotor nor lift rotors coupled to the wing. The absence of disruption by nacelle and rotor propwash over the clean wing is beneficial for decreasing noise and improving lift performance. Moreover, the lift characteristic of the clean wing has minimized impact by rotor propwash during transition between thrust born flight and wing born flight. The tiltable rotor can be achieved by tiltable boom, tiltable nacelle pod or tiltable rotor hub. In addition, the single actuation of the rotor booms allows to convert between thrust borne flight and wing borne flight. The distal end of the rotor boom is mechanical coupled to the distal end of the wing to create the box aerostructure is an option. The box aerostructure benefits from an improvement of structural strength, fatigue strength and load carrying strength. Nevertheless, the invention is applicable to any multirotor vehicle of arbitrary weight, such as a light drone to a large tonnage vehicle.