Rotatable Lateral Wings for Electric Aircraft Ground Maneuverability
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Solution Overview
Problem
Current aircraft architectures, such as the cylindrical fuselage with two lateral wings, face challenges in optimizing aerodynamics, stability, compactness, flight speed, short-distance takeoff and landing capabilities, and useful load, leading to inefficient use of propulsion power and passenger comfort issues.
Innovation Solution
An aircraft design featuring a central wing with pivoting lateral wings, where the wings pivot between deployed and folded positions, incorporating aerodynamic control surfaces, hydrofoils for water operations, and electric propulsion, with specific geometric and angular characteristics to optimize lift distribution and reduce drag, allowing for adaptable flight phases and compact ground operations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If the wingspan is increased to improve lift and reduce takeoff/landing distance, then the aircraft can take off and land over shorter distances, but the aircraft becomes harder to park and maneuver on the ground
Solution Approach 1:
The patent implements rotatable lateral wings that can change their span dynamically. During flight, the wings are extended to maximum span for optimal lift and aerodynamic efficiency. During ground operations, the wings are rotated to a folded position, reducing the span to a fraction of the extended length. This dynamic reconfiguration allows the aircraft to have both long wingspan benefits during flight and compact dimensions during ground handling, directly resolving the contradiction between takeoff/landing performance and ground maneuverability.
2Object-generated harmful factors
If the fuselage size is reduced to decrease drag and improve aerodynamic efficiency, then the drag is reduced and fuel consumption decreases, but the passenger comfort and cabin layout become compromised
Solution Approach 1:
The patent divides the traditional fuselage-wings configuration into a blended wing body design where the fuselage and wings are integrated. The lateral wings are positioned such that they blend into the fuselage structure, creating a more aerodynamic shape with reduced drag. This segmentation and integration approach allows the aircraft to maintain a compact fuselage for low drag while providing sufficient cabin volume through the blended design, improving both aerodynamic efficiency and passenger comfort.
3Weight of moving object
If the empty weight is reduced to improve fuel efficiency and increase useful load ratio, then the propulsion power is used more efficiently for transporting passengers, but the structural integrity and safety margins may be compromised
Solution Approach 1:
The patent employs composite materials in the construction of the blended wing body structure. These advanced composite materials provide high strength-to-weight ratios, allowing the aircraft to achieve reduced empty weight while maintaining or even improving structural integrity. The composite structures enable the aircraft to carry less empty weight without compromising safety margins, directly improving fuel efficiency and useful load ratio while ensuring reliability.
4Device complexity
If the lateral wings are made fixed to simplify the structure and reduce complexity, then the device complexity is reduced, but the adaptability for different flight phases and operations is limited
Solution Approach 1:
The patent implements rotatable lateral wings that can dynamically adjust their configuration based on flight phase requirements. The wings are equipped with rotation mechanisms allowing them to transition between extended and folded positions, and between different angular orientations. This dynamic capability provides adaptability for various flight phases including takeoff, cruise, landing, and ground operations, while the rotation mechanism is designed to be relatively simple, minimizing the increase in device complexity.
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 design enhances aerodynamic efficiency, stability, and compactness, enabling faster flight speeds, shorter takeoff and landing distances, and improved passenger comfort while optimizing propulsion power usage and reducing drag, thus addressing the limitations of existing aircraft architectures.
Implementation Method 1
two lateral wings (2, 2') pivoting on the central wing (1) about respective axes of rotation (3, 3')
Implementation Method 2
at least two hydrofoils (6, 6') below the central wing (1) and which are retractable in the said central wing (1)
Data Source
AI summary
An aircraft includes a central wing accommodating passengers and/or freight and two lateral wings that pivot on the central wing about respective axes of rotation. The various wings obey the following geometric characteristics: 0.3×Long<Larg<Long, 0.11×Long<Haut<0.25×Long, Env>1.4×Long, wherein Larg being the distance between the two axes, Long being the length of the central wing, Haut being the height of the central wing, Env being the wingspan of the aircraft. The axes of rotation are inclined by an angle relative to the vertical axis of the aircraft such that the lateral pivot from rear to front and vice versa so as to come closer to, or deploy on either side from, the fuselage.