Closed-Wing Aircraft With Deformable Wing Portions
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Solution Overview
Problem
Existing fixed-wing aircraft designs face challenges in maneuverability, drag reduction, and adaptability during different flight stages due to the reliance on articulated control surfaces.
Innovation Solution
The proposed technology features a fixed-wing aircraft with a closed wing configuration, incorporating a deformable wing portion that elastically deforms in response to an output torque applied by an actuator arrangement. This deformation allows for maneuvering without articulated control surfaces, reducing drag and enabling lift variation at constant speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If articulated control surfaces are used for maneuvering, then control capability is improved, but drag increases
Solution Approach 1:
The wing is designed with deformable portions that can dynamically change their shape and angle of attack during flight. The deformable leading edge portion and deformable camber portion allow the wing to adapt its configuration for different flight phases, eliminating the need for separate articulated control surfaces that would increase drag.
Solution Approach 2:
The deformable wing structure serves multiple functions simultaneously: it provides maneuvering control through shape changes, maintains aerodynamic efficiency by reducing drag, and enables adaptation to different flight stages. The same deformable structure that controls angle of attack also optimizes lift-to-drag ratio, combining control and efficiency functions in one system.
2Strength
If rigid wing structure is used, then structural strength is improved, but adaptability to different flight stages deteriorates
Solution Approach 1:
The wing is divided into distinct structural portions: a rigid wing root section that maintains overall structural strength and attachment to the fuselage, and deformable sections (leading edge portion and camber portion) that can change shape. This segmentation allows the rigid parts to provide strength while the deformable parts provide adaptability for different flight stages.
Solution Approach 2:
The wing structure utilizes changes in physical parameters such as flexibility and stiffness in different regions. The deformable portions are designed with specific material properties and structural characteristics that allow controlled shape changes while the rigid portions maintain constant structural parameters, enabling the wing to adapt its geometry for takeoff, steady flight, and landing phases.
3Adaptability or versatility
If deformable wing portions are added for maneuvering, then adaptability is improved, but device complexity increases
Solution Approach 1:
The deformable leading edge portion and deformable camber portion are integrated into a unified wing structure rather than being separate components. The actuator system is merged with the wing structure itself, where the deformable portions are built-in features of the wing rather than add-on control surfaces. This merging reduces overall system complexity while maintaining adaptability for lift variation and maneuvering.
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 closed wing design enhances maneuverability and reduces drag, allowing the aircraft to be trimmed and lift to be varied, thus adapting to different flight stages such as takeoff, steady flight, and landing.
Implementation Method 1
The first deformable wing portion is arranged to elastically deform at an application of the first output torque, or first output torsional moment, to the first deformable wing portion
Implementation Method 2
The wing is arranged to provide lift in flight
Implementation Method 3
The first actuator arrangement is arranged to supply a first input torque, or first input torsional moment, to the first connector arrangement
Data Source
Figure 1a~1c
Figure 2a~3b
Figure 4a~5b
AI summary
1. A fixed-wing aircraft (10) that comprises: a fuselage (14), a closed wing (16), a first actuator arrangement (22), and a first connector arrangement (24). The closed wing (16) is coupled to the fuselage (14) and has a wingtip (18) and a first deformable wing portion (20). The first actuator arrangement (22) is arranged to supply a first input torque to the first connector arrangement (24) at an activation of the first actuator arrangement (22), the first connector arrangement (24) is arranged to apply an first output torque to the first deformable wing portion (20) at a supply of the first input torque to the connector arrangement. The first deformable wing portion (20) is arranged to elastically deform at an application of the first output torque to the first deformable wing portion (20). The closed wing (16) forms an outer support (26) at the wingtip (18) arranged to counter the first output torque.