Trailing-Rotor Fixed-Wing Aircraft Layout for Stall Control
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Solution Overview
Problem
Existing aircraft designs with tilt rotors face challenges in stability and control during stall conditions, particularly when horizontal lift surfaces stall out, and require improved performance and efficiency in takeoff and landing with smaller footprints.
Innovation Solution
The aircraft configuration includes a forward swept and fixed wing with trailing edge mounted tilt rotors, a canard, and a T-tail, where the T-tail's horizontal plane is higher than the wing plane, enhancing stability and control during stall conditions and improving efficiency in transitions between hover and cruise modes.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If tilt rotors are mounted on the trailing edge of the wing, then the aircraft can achieve vertical takeoff and landing capability, but the aircraft loses stability and control when horizontal lift surfaces stall out
Solution Approach 1:
The patent positions the horizontal stabilizer in the T-tail configuration at a higher vertical dimension, above the main wing's stall region. This spatial relocation allows the stabilizer to operate in cleaner airflow even when the main wing stalls, maintaining pitch control authority during stall conditions while preserving VTOL capability through trailing edge rotor mounting
2Device complexity
If the horizontal stabilizer is positioned at the same level as the main wing, then the structure is simpler, but the stabilizer becomes ineffective when the main wing stalls out
Solution Approach 1:
The T-tail configuration elevates the horizontal stabilizer to a higher vertical plane above the main wing. This dimensional relocation ensures the stabilizer remains in undisturbed airflow during wing stall conditions, maintaining control effectiveness without significantly increasing overall structural complexity
Solution Approach 2:
The patent separates the horizontal stabilizer from the main wing structure into an independent T-tail assembly. This segmentation allows the stabilizer to function independently of the main wing's aerodynamic state, ensuring continued control authority even when the wing stalls
3Adaptability or versatility
If the aircraft uses conventional takeoff and landing methods, then the operating envelope is limited, but the aircraft requires larger footprints and airports
Solution Approach 1:
The aircraft integrates multiple flight modes (VTOL, hover, cruise) into a single platform through the trailing edge rotor mounting system. This multi-functionality allows the aircraft to operate from locations without traditional runways while maintaining efficient cruise performance, expanding the operating envelope without increasing footprint 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 configuration maintains better control and stability during stall conditions, allows for efficient vertical takeoff and landing, and expands the operating envelope, enabling faster and slower flight speeds with reduced power consumption and increased flight range.
Implementation Method 1
the T-tail's horizontal plane is higher than the wing plane, enhancing stability and control during stall conditions
Implementation Method 2
trailing edge mounted tilt rotors... allows for efficient vertical takeoff and landing
Data Source
AI summary
An aircraft that includes a canard having a leading edge and a trailing edge, a forward swept and fixed wing having a trailing edge, and a plurality of tilt rotor submodules, a dovetail, and a T-tail. The plurality of tilt rotor submodules are coupled to the trailing edge of the forward swept and fixed wing. The dovetail is attached to an underside of a fuselage. The T-tail is located above the dovetail. A horizontal plane of the T-tail is at a height that is higher than a horizonal plane of the forward swept and fixed wing.