UAV Thrust Decoupling and Active Wing Loading
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Solution Overview
Problem
Current UAVs face limitations in lift capabilities during takeoff and landing, payload carrying capacity, and maneuverability, especially in confined spaces, with rotor-based UAVs restricted by rotor size and winged UAVs requiring forward motion for lift and lacking vertical takeoff and landing capabilities.
Innovation Solution
A UAV design featuring a fuselage with a primary propulsion unit for lift and thrust, secondary propulsion units for orientation changes, and pivotable airfoils for adjustable lift, enabling vertical takeoff and landing, low-speed maneuverability, and high-speed flight while maintaining payload stability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If rotor-based UAVs are used for vertical takeoff and landing, then maneuverability in confined spaces is improved, but lift capability and payload capacity are limited
Solution Approach 1:
The propulsion system is divided into multiple independent rotor units that can operate independently or in combination. This segmentation allows the UAV to achieve vertical lift through multiple rotors while maintaining the ability to maneuver in confined spaces by controlling individual rotor thrust vectors.
Solution Approach 2:
The rotor system is designed to perform multiple functions: generating vertical lift for takeoff and landing, providing forward thrust for horizontal flight, and enabling maneuvering in confined spaces. This multi-functionality resolves the contradiction by making the same propulsion system adaptable to different operational requirements.
2Ease of operation
If rotor-based UAVs are used for vertical takeoff and landing, then maneuverability in confined spaces is improved, but high-speed flight capability is reduced
Solution Approach 1:
The UAV employs dynamic rotor blade pitch control and variable rotor speed capabilities that allow the system to optimize performance for different flight regimes. At low speeds, the rotors provide high thrust for maneuverability; at high speeds, the blades adjust pitch to reduce drag and increase forward velocity.
Solution Approach 2:
The propulsion system dynamically changes operational parameters including rotor speed, blade pitch angle, and thrust distribution across multiple rotors. These parameter changes enable the UAV to transition between maneuvering mode in confined spaces and high-speed flight mode as needed.
3Speed
If winged UAVs are used for high-speed flight, then speed capability is improved, but vertical takeoff and landing capability is lost
Solution Approach 1:
The lifting system is segmented into multiple independent rotor units distributed around the fuselage. This segmentation allows the UAV to generate vertical lift for takeoff and landing while also being able to tilt rotor thrust vectors for forward flight, combining the capabilities of both vertical and winged UAVs.
Solution Approach 2:
The propulsion system utilizes three-dimensional thrust vectoring capability, allowing rotors to generate force in multiple directions. This dimensional flexibility enables vertical takeoff, horizontal flight, and maneuvering in confined spaces, effectively adding the vertical dimension capability to high-speed flight performance.
4Force
If rotor size is increased to improve lift capability, then payload capacity is improved, but maneuverability in confined spaces deteriorates
Solution Approach 1:
Instead of using one or two large rotors, the lift capability is distributed across multiple smaller rotor units. This segmentation provides equivalent or superior total lift while improving maneuverability in confined spaces, as the smaller rotors can be positioned closer to the fuselage and controlled independently for precise positioning.
Solution Approach 2:
The multiple rotor configuration creates balanced thrust distribution that counteracts the weight of the UAV and payload. By distributing the anti-weight function across multiple rotors rather than concentrating it in large rotors, the system achieves both lift capability and maneuverability.
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
The design allows for heavy payload delivery over long distances in confined spaces with enhanced lift and propulsive capabilities, maintaining payload stability and protecting avionics from turbulence.
Implementation Method 1
a primary propulsion unit mounted within the duct and generating lift for upward and downward motion while the fuselage is in a substantially vertical orientation
Implementation Method 2
generating thrust for forward motion while the fuselage is in a substantially horizontal orientation
Implementation Method 3
a plurality of airfoils each having a proximal end attached at opposite sides of the fuselage, the airfoils providing lift during forward motion of the fuselage
Implementation Method 4
a plurality of secondary propulsion units generating thrust to tilt the fuselage between the substantially vertical orientation and the substantially horizontal orientation
Data Source
AI summary
An aerial vehicle, such as an unmanned aerial vehicle, includes a fuselage having a forward end, an aft end, and a duct extending between said forward end and said aft end, said duct being oriented along a longitudinal axis of said fuselage; a primary propulsion unit mounted within said duct and generating lift for upward and downward motion while said fuselage is in a substantially vertical orientation and thrust for forward motion while said fuselage is in a substantially horizontal orientation; a plurality of airfoils each having a proximal end attached at opposite sides of the fuselage, said airfoils providing lift during forward motion of said fuselage; and a plurality of secondary propulsion units generating thrust to tilt the fuselage between said substantially vertical orientation and said substantially horizontal orientation.