Box Wing eVTOL Airframe for Compact Lift and Stable Transition
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Solution Overview
Problem
The design of airframes for electric vertical take-off and landing (EVTOL) aircrafts is critical for achieving both vertical and horizontal flight characteristics, particularly in terms of propulsion placement and stability, which existing designs have not adequately addressed.
Innovation Solution
Aircraft design featuring a fuselage with modular box wing airfoils and an electric powerplant, incorporating lower propulsion devices for vertical lift and upper propulsion devices for horizontal thrust, with mechanisms for rotating thrust vectors and modular wings for varying flight characteristics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional airframe designs are used for EVTOL aircraft, then structural simplicity is maintained, but aerodynamic efficiency and stability are insufficient for both vertical and horizontal flight
Solution Approach 1:
The aircraft airframe is segmented into distinct functional modules: a fuselage module, a box wing module with separate lifting surfaces, and a propulsion module. This segmentation allows each component to be optimized for its specific function while maintaining overall structural integrity for both vertical and horizontal flight stability
Solution Approach 2:
The box wing structure merges the upper and lower lifting surfaces with the fuselage through integrated booms and connector surfaces, creating a unified aerodynamic structure that improves stability without requiring separate support structures
2Adaptability or versatility
If propulsion devices are positioned for optimal vertical lift, then vertical take-off capability is achieved, but horizontal flight thrust and stability are compromised
Solution Approach 1:
The propulsion devices are designed with dynamic positioning capabilities, allowing them to rotate and reposition between a vertical orientation for lift during take-off and a horizontal orientation for thrust during forward flight. This dynamic adaptability enables a single propulsion system to serve both flight modes effectively
Solution Approach 2:
The propulsion devices are designed as multi-functional units that can perform both vertical lift generation and horizontal thrust production. By incorporating rotational mechanisms, the same propulsion devices serve dual purposes across different flight phases, reducing the need for separate specialized systems
3Volume of moving object
If wingspan is reduced for compactness, then aircraft size is minimized, but aerodynamic efficiency and lift generation are reduced
Solution Approach 1:
The box wing design employs curved connector surfaces joining the upper and lower lifting surfaces, creating smooth aerodynamic transitions that reduce drag and improve lift efficiency. The curved geometry optimizes airflow patterns around the wing structure, maintaining aerodynamic performance in a compact configuration
Solution Approach 2:
The box wing structure utilizes composite construction with multiple lifting surfaces and connector surfaces that work together as an integrated aerodynamic system. This composite structure maximizes lift generation per unit of wingspan by distributing aerodynamic loads across multiple surfaces
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
Enhances aerodynamic efficiency and reduces wingspan requirements while maintaining lift, enabling seamless transitions between vertical take-off and horizontal flight, with improved stability and safety features.
Implementation Method 1
at least one propulsion device movable between a first configuration wherein a thrust vector of the at least one propulsion device is directed substantially vertically downward and a second configuration wherein the thrust vector of the at least one propulsion device is directed substantially horizontally rearward
Implementation Method 2
a first lifting surface having a first root portion located proximate the at least one boom, and a first tip portion located distally from the first root portion
Data Source
AI summary
An aircraft frame includes a fuselage, at least one boom and a wing structure including a first lifting surface having a first root portion located proximate the at least one boom and a first tip portion where at least a portion of the first tip portion is located forwardly from at least a portion of the first root portion, a second lifting surface having a second root portion located proximate the fuselage, and a second tip portion located spaced from the first tip portion where at least a portion of the second tip portion is located rearwardly from at least a portion of the second root portion, and a connector surface extending between the first and second tip portions.