Pivoting Angled Duct VTOL Aircraft for High-Speed Transition
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Solution Overview
Problem
Existing aircraft technologies struggle to achieve efficient vertical take-off and landing (VTOL) capabilities while also supporting high-speed forward flight, with conventional designs suffering from drag and low airspeed issues.
Innovation Solution
Integration of Pivoting Angled Ducts (PADs) with Electric Ducted Rotors (EDRs), Ducted Column Assemblies (DCAs), and Ventral Control Doors (VCDs) in a streamlined fuselage, allowing for efficient transitions between VTOL and high-speed flight by rotating thrust vectors and controlling airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If helicopters use vertical take-off and landing capability, then runway requirement is eliminated, but forward flight speed and efficiency deteriorate due to severe drag
Solution Approach 1:
The patent employs dynamic tilt-rotor mechanisms that allow the rotors to change orientation from vertical (for VTOL) to horizontal (for forward flight). This dynamic reconfiguration enables the aircraft to optimize its aerodynamic characteristics for each flight regime, eliminating the drag penalties associated with fixed-configuration helicopters during forward flight while maintaining VTOL capability.
Solution Approach 2:
The aircraft integrates multiple flight modes (VTOL, transition, and high-speed forward flight) into a single platform using universal propulsion and lift systems. The tilt-rotor configuration and adjustable wing mechanisms enable the same aircraft to perform both vertical take-off/landing and efficient high-speed forward flight, eliminating the need for separate specialized aircraft.
2Adaptability or versatility
If shaft-driven tilt-rotor aircraft are used to achieve both VTOL and forward flight, then versatility is improved, but weight and complexity increase significantly
Solution Approach 1:
The patent replaces traditional shaft-driven mechanical tilt-rotor systems with electrically-driven rotor systems. This substitution eliminates complex mechanical transmission shafts, gearboxes, and associated mechanical linkages, thereby reducing weight and mechanical complexity while maintaining the ability to tilt rotors for both VTOL and forward flight operations.
Solution Approach 2:
The propulsion system is divided into independent electric motor-rotor units that can be individually controlled and tilted. This segmentation allows each rotor to be independently driven by electric motors, eliminating the need for a centralized mechanical drive shaft system and reducing overall system complexity and weight.
3Device complexity
If simpler tilt-wings or partial tilt-wing mechanisms are used, then weight and complexity are reduced, but forward airspeed remains similar to helicopters
Solution Approach 1:
The patent merges tilt-wing mechanisms with tilt-rotor propulsion systems in an integrated configuration. The wings and rotors work together as a unified system, where the tilt-wing provides aerodynamic lift and the tilted rotors provide propulsion, enabling high-speed forward flight while maintaining simplified structure compared to traditional shaft-driven systems.
4Speed
If conventional aircraft designs are used for high-speed forward flight, then speed and efficiency are improved, but runway requirement increases and VTOL capability is lost
Solution Approach 1:
The aircraft employs dynamic reconfiguration of its propulsion and lift systems, allowing transition between vertical rotor orientation for VTOL and horizontal rotor orientation for high-speed forward flight. This dynamic adaptability enables the aircraft to achieve conventional aircraft-level speeds during forward flight while retaining VTOL capability when needed.
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 solution enables aircraft to achieve improved VTOL capability combined with efficient high-speed forward flight, overcoming the limitations of prior art by optimizing thrust and lift vectors for various flight modes.
Implementation Method 1
The PADs employ electrical power from the power system to propel air
Implementation Method 2
Within each Ducted Column Assembly, the PADs rotate in unison in pitch axis to create a single vector of thrust
Implementation Method 3
During VTOL flight, the Ventral Control Doors are in the open third position, to provide left and right thrust vectoring control during substantially vertical flight
Data Source
AI summary
An aircraft that closely integrates thrust and aerodynamics to achieve VTOL flight, high speed forward flight, and smooth transitions from VTOL to forward flight. The invention combines Electric Ducted Rotors, Pivoting Angled Ducts, Ducted Column Assemblies, and Ventral Control Door assemblies for VTOL and high speed forward flight of an aircraft. In forward flight, the concept uses a plurality of Ducted Rotors arranged in columns to not only provide thrust, but also enhance aerodynamic lift. In VTOL flight and transitioning to forward flight, the PADs in a single Ducted Column Assembly rotate in unison in the pitch axis to create a single thrust vector through the Ventral Control Door Assembly, providing smooth power, controllability, and aircraft orientation throughout transition. Throughout all phases of flight, differential actuation of Electric Ducted Rotors and conventional flight controls provide control.