Rotor Torque Vectoring for VTOL Wing Actuation
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Solution Overview
Problem
Existing VTOL aircraft rely on heavy and complex tilt wing actuators to change the angle of thrust, which increases weight, reduces efficiency, and adds mechanical complexity, limiting maneuverability and safety.
Innovation Solution
The use of cyclic control of rotors to generate torque and adjust the angle of wings relative to the fuselage, eliminating the need for separate tilt actuators and simplifying the aircraft by integrating rotor torque for wing and rotor tilting, allowing for independent control of roll, pitch, and yaw without conventional control surfaces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If heavy tilt wing actuators are used to change the angle of thrust, then the aircraft can achieve VTOL capability, but the weight increases and efficiency reduces
Solution Approach 1:
The patent combines the functions of the rotor system and tilt actuator into a single integrated system. The rotor blades perform both propulsion and tilting functions by varying their pitch angle cyclically, eliminating the need for separate heavy tilt actuators. This merging of functions directly reduces aircraft weight while maintaining VTOL capability.
Solution Approach 2:
The rotor blades are designed to perform multiple functions: they provide thrust for forward flight, generate vertical lift for hover and takeoff, and control the tilting motion through cyclic pitch variation. This multi-functionality eliminates the need for dedicated tilt actuators, reducing overall system weight and complexity.
2Adaptability or versatility
If heavy tilt wing actuators are used to change the angle of thrust, then the aircraft can achieve VTOL capability, but the mechanical complexity increases
Solution Approach 1:
The patent merges the tilt actuation mechanism into the rotor system itself. The cyclic pitch control mechanism, already necessary for rotor operation, is used to control both the thrust vector angle and the tilting motion. This integration eliminates separate tilt actuators and their associated mechanical linkages, reducing overall system complexity.
Solution Approach 2:
The rotor system serves itself by using its own cyclic pitch control mechanism to perform both propulsion and tilting functions. The rotor blades generate the necessary torques for tilting through their own pitch variations, eliminating the need for external tilt actuators and their complex mechanical systems.
3Weight of moving object
If cyclic control of rotors is used to generate torque for wing tilting, then weight and complexity are reduced, but control precision requirements increase
Solution Approach 1:
The patent employs feedback control mechanisms to monitor and adjust the cyclic pitch variations of the rotor blades. Sensors detect the actual tilt angle and thrust vector position, and the control system continuously adjusts the pitch control inputs to achieve the desired precision. This feedback loop compensates for the increased control complexity by providing real-time correction.
Solution Approach 2:
The system uses dynamic control of rotor blade pitch angles to achieve precise tilting. By continuously varying the pitch angle throughout the rotor rotation cycle, the system can generate the exact torques needed for precise positioning. This dynamic control approach provides fine-grained adjustment capability that meets the precision requirements.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach reduces weight and complexity, enhances maneuverability, and improves efficiency by utilizing existing rotor propulsion systems to change thrust direction, enabling smoother transitions between vertical and horizontal flight modes.
Implementation Method 1
cyclic control of a rotor to generate torque around an axis of rotation of a wing
Implementation Method 2
rotor to generate torque around an axis of rotation of a wing
Implementation Method 3
redirecting the thrust generated by the rotor and changing the angle of the wing with respect to the fuselage
Data Source
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AI summary
An aircraft is configured with a propulsion system having a rotor with both cyclic and collective control, and an axis of rotation about which the propulsion system rotates with respect to the fuselage. A control system is configured to use torque generated through cyclic control of the rotor to reposition the propulsion system around the axis of rotation without the need for an independent actuator mechanism to rotate the propulsion system, thus reducing the weight and mechanical complexity of the aircraft. The control system may also utilize the torque provided by one or more rotors to position one or more wings with respect to the airflow over the aircraft, exerting torque on the aircraft to control the direction of the aircraft.