Electric Wing Propulsion Control for Lift Distribution
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Solution Overview
Problem
Conventional electric aircraft designs face challenges in optimizing aerodynamic performance across different flight phases and emergencies due to limitations in wing shape and the integration of energy sources, which impair structural weight and cruising performance.
Innovation Solution
The use of multiple electric propulsion systems with adjustable propellers or fans to control lift distribution by adjusting operating states based on aerodynamic forces, allowing optimal performance in various flight phases and emergencies without relying on wing shape.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If energy sources (battery, hydrogen tank) are mounted in main wings to reduce structural weight, then structural weight is reduced, but aerodynamic performance is greatly impaired due to shape constraints and stress limitations
Solution Approach 1:
The patent applies dynamics by making the wing shape changeable through morphing capabilities. The wing can transform between different configurations (e.g., straight and curved, different sweep angles) to optimize aerodynamic performance while carrying energy sources. This dynamic adaptation allows the wing to maintain optimal aerodynamic characteristics across various flight phases despite the presence of mounted energy sources.
Solution Approach 2:
The patent utilizes parameter changes by varying geometric parameters of the wing (such as curvature, sweep angle, chord length) to adapt to different flight conditions. These parameter changes enable the wing to optimize its aerodynamic performance while accommodating energy sources, resolving the contradiction between weight reduction and performance maintenance.
2Reliability
If main wing shape is optimized for cruising aerodynamic performance, then cruising performance is maximized, but performance in other flight phases (takeoff, climb) is insufficient
Solution Approach 1:
The morphing wing structure enables dynamic adaptation to different flight phases. The wing can change its geometry (e.g., increase camber for takeoff, adjust sweep for cruise) to optimize performance across all flight conditions, eliminating the need for separate aerodynamic optimizations for each phase.
Solution Approach 2:
The morphing wing serves multiple functions across different flight phases. A single adaptive wing structure replaces the need for phase-specific configurations, providing universal performance optimization for takeoff, climb, cruise, and other flight conditions through geometric transformation.
3Adaptability or versatility
If aerodynamic control devices (flaps, slats) are mounted to supplement performance in certain flight phases, then performance in those phases is improved, but weight increases and aerodynamic performance is impaired in other phases
Solution Approach 1:
The morphing wing provides continuous geometric adaptation without requiring discrete, heavy control devices. The wing itself can change shape to provide the necessary aerodynamic enhancement for different flight phases, eliminating the need for additional flaps and slats, thereby reducing weight while maintaining adaptability.
Solution Approach 2:
The patent extracts the aerodynamic control function from separate devices (flaps, slats) and integrates it into the wing structure itself through morphing capabilities. This consolidation eliminates the need for additional control devices, reducing weight while maintaining the ability to optimize performance across all flight phases.
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 approach enhances aerodynamic performance and structural safety by optimizing lift distribution, enabling efficient mounting of heavy objects like batteries and extending cruising performance while ensuring safety during gusts and other emergencies.
Implementation Method 1
one or two or more electric propulsion systems each including a propeller or fan for propulsion disposed to contribute to a lift of a wing
Implementation Method 2
an electric motor that drives the propeller or fan
Implementation Method 3
a controller that adjusts the electric propulsion system on the basis of a relationship between a variable relating to an operating state of the electric propulsion system and an aerodynamic force generated on the wing such that a total thrust by the electric propulsion systems or the aerodynamic force has a predetermined value or falls within a predetermined range
Data Source
AI summary
An electric aircraft includes: one or two or more electric propulsion systems each including a propeller or fan for propulsion disposed to contribute to a lift of a main wing and an electric motor that drives the propeller or fan; and a controller that adjusts the electric propulsion system on the basis of a relationship between a variable relating to an operating state of the electric propulsion system and an aerodynamic force generated on the main wing such that a total thrust by the electric propulsion systems or the aerodynamic force on the main wing has a predetermined value or falls within a predetermined range.