VTOL Aircraft Tail Control Surfaces Wake Avoidance
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Solution Overview
Problem
In electrically propelled vertical take-off and landing (VTOL) aircraft, maintaining aircraft integrity during flight and ensuring safe landing is challenging due to the limitations of control surfaces in adjusting attitude effectively.
Innovation Solution
The design incorporates a VTOL aircraft with a fuselage, lift components affixed to booms, and a tail with vertically and horizontally projecting elements positioned outside the wake of the lift components, enhancing stability and control through a unique configuration of control surfaces and flight controller systems.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If control surfaces are positioned in conventional locations on the aircraft, then the aircraft structure is simplified, but the control surfaces are interfered with by the wake from lift components reducing effectiveness
Solution Approach 1:
The control surfaces are repositioned from conventional two-dimensional planar locations to a three-dimensional configuration where they extend laterally beyond the booms and are positioned in the wake-free zone. This spatial relocation in another dimension allows the control surfaces to operate without interference from the lift component wakes while maintaining structural integration.
Solution Approach 2:
The boom structure serves as an intermediary element that positions the control surfaces in the optimal location outside the wake region. The boom acts as a mechanical mediator that extends the control surfaces laterally to the wake-free zone while maintaining their aerodynamic effectiveness and structural connection to the fuselage.
2Reliability
If control surfaces are positioned outside the wake from lift components, then control effectiveness is improved, but the aircraft structure becomes more complex
Solution Approach 1:
The control surfaces are merged with the boom structure to form an integrated assembly. The control surfaces extend laterally from the booms, combining the structural function of the boom with the aerodynamic function of the control surfaces. This merging reduces the need for separate mounting structures and simplifies the overall aircraft configuration while achieving wake-free positioning.
Solution Approach 2:
The boom structure serves multiple functions: it supports the lift components vertically, provides lateral extension to position control surfaces in the wake-free zone, and acts as a structural backbone for the control surface assembly. This multi-functionality reduces the need for additional separate structures, thereby reducing overall device complexity while achieving improved flight stability.
3Reliability
If vertically projecting elements form angles and sweep angles, then flight dynamics and stability are optimized, but manufacturing precision requirements increase
Solution Approach 1:
The vertically projecting elements are designed with specific geometric parameters including angle relative to the longitudinal plane and sweep angle relative to the lateral plane. These parameter changes optimize the aerodynamic performance and flight dynamics by controlling the interaction with airflow and positioning the elements in wake-free zones. The defined angular parameters provide clear manufacturing specifications that balance performance optimization with manufacturability.
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 improves the aircraft's ability to maintain stability and control during flight, ensuring safe landing by positioning control surfaces to avoid interference from lift components and optimizing flight dynamics.
Implementation Method 1
The plurality of vertically projecting elements are positioned outside of the wake from the at least a lift component while the aircraft is engaged in conventional flight
Data Source
AI summary
In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.