Wing Air Outlet Gap and Deflector for Vortex Lift Generation
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Solution Overview
Problem
Existing aircraft designs face challenges in scalability and efficient operation, particularly in generating lift while minimizing energy consumption and maximizing stability, especially when it comes to varying payload capacities.
Innovation Solution
The aircraft features a wing design with a lower first profiled surface and an upper second profiled surface that converge at an aerofoil transition point, incorporating an air delivery apparatus that creates a support vortex by deflecting air through an air outlet gap, allowing for efficient lift generation and energy-efficient flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If traditional lift generation methods are used, then sufficient lift is achieved, but energy consumption increases
Solution Approach 1:
The patent introduces a deflecting element as an intermediary component between the air outlet opening and the free stream. This deflecting element guides the jet flow to create a support vortex that indirectly generates lift through vortex-induced pressure differences, rather than relying solely on direct jet thrust. The intermediary vortex structure enables more efficient lift generation with reduced energy consumption.
Solution Approach 2:
The patent utilizes pneumatic principles by employing jet flows and vortex dynamics to generate aerodynamic forces. The air delivery apparatus creates controlled air streams that form vortices, leveraging fluid dynamics and pressure differentials to produce lift. This pneumatic approach replaces or supplements traditional mechanical or direct-thrust lift generation methods, achieving lower energy consumption.
2Adaptability or versatility
If aircraft design is optimized for specific payload, then efficiency is improved, but scalability to different payloads is limited
Solution Approach 1:
The patent employs dynamic control of the deflecting element and air delivery apparatus to adapt the vortex strength and characteristics to different payload conditions. By dynamically adjusting the jet flow parameters and deflecting element position, the aircraft can optimize its lift generation efficiency for varying payloads, maintaining high productivity across different operating conditions rather than being fixed for a specific payload configuration.
Solution Approach 2:
The patent utilizes parameter changes in the jet flow (velocity, volume, direction) and deflecting element geometry to adapt the vortex-induced lift to different payload requirements. By changing these parameters, the same basic design can efficiently operate across a range of payload capacities, achieving both scalability and operational efficiency without requiring completely different aircraft configurations.
3Use of energy by moving object
If support vortex is generated using air delivery apparatus, then energy consumption decreases, but device complexity increases
Solution Approach 1:
The air delivery apparatus is designed to serve multiple functions: it provides primary thrust, generates the support vortex for efficient lift, and can be adjusted for different operating conditions. This multi-functionality reduces the need for separate dedicated vortex-generating components, thereby limiting the increase in device complexity while achieving lower energy consumption through vortex-induced lift.
Solution Approach 2:
The patent merges the lift generation function with the thrust generation function by using the same air delivery apparatus to create both forward motion and the support vortex. The deflecting element integrates the vortex generation into the existing jet flow path, combining multiple aerodynamic functions into a unified system. This merging approach achieves energy-efficient lift without proportionally increasing 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 configuration enables the aircraft to operate with low energy consumption, achieve high stability, and be scalable in terms of payload capacity by utilizing a support vortex that is generated with less energy than traditional lift methods, allowing for efficient and stable flight operations.
Implementation Method 1
an air delivery apparatus (11), which is provided and designed for sucking air through the at least one air inlet opening (7) and for discharging the intake air through the at least one air outlet opening (8)
Implementation Method 2
the at least one air outlet opening (8) is overlapped at least in part by a deflecting element (15) which, together with the second profiled surface (5), delimits an air outlet gap (16)
Data Source
AI summary
The invention relates to an aircraft (1). Said aircraft (1) is characterized by a wing (2) which, viewed in section, is delimited on one side by a first profiled surface (4), which is at the bottom when the aircraft (1) is operated as intended, and on the other side by an upper second profiled surface (5), which merges at an aerofoil transition point (6) with the first profiled surface (4), wherein the first profiled surface (4) surrounds at least one air inlet opening (7), and the second profiled surface (5) surrounds at least one air outlet opening (8), and the aircraft (1) comprises a drive apparatus (12) with an air delivery apparatus (1), which is provided and designed for sucking air through the at least one air inlet opening (7) and for discharging the intake air through the at least one air outlet opening (8), wherein the at least one air outlet opening (8) is overlapped at least in part by a deflecting element (15) which, together with the second profiled surface (5), delimits an air outlet gap (16) which is flow-connected to the air outlet opening (8). The invention also relates to a method for operating an aircraft (1).