Wing Airflow Deflection for Vortex-Induced Aircraft Lift
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Solution Overview
Problem
Existing missiles lack scalability and efficient operation, particularly in terms of payload capacity and energy efficiency, as they rely on conventional lift mechanisms that require high energy expenditure and are not easily adaptable.
Innovation Solution
The missile design incorporates a wing structure with converging profile surfaces that generate a support vortex through air flow management, allowing for energy-efficient flight and scalability by using a deflection element to direct air flow parallel to the wing, creating a low-turbulence air film that induces lift with minimal energy expenditure.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If conventional lift mechanisms are used, then the missile can achieve flight, but energy consumption is high
Solution Approach 1:
The patent replaces conventional mechanical rotor-based lift systems with a vortex-induced lift mechanism. Air is conveyed through channels in the missile body to generate controlled vortices along the wings, which produce lift through aerodynamic effects rather than mechanical rotor action. This substitution significantly reduces energy consumption while maintaining flight stability.
Solution Approach 2:
The patent employs pneumatic systems to convey air through internal channels and generate vortices. Air inlets draw in atmospheric air, which is then directed through flow channels to vortex-generating openings on the wings. This pneumatic approach enables efficient lift generation without the high energy expenditure of conventional mechanical systems.
2Speed
If rotor-based systems are used, then lift can be generated, but speed is limited
Solution Approach 1:
The patent extracts and eliminates the rotor mechanism entirely from the lift generation system. By removing the rotating components, the design achieves higher speeds without the mechanical limitations and complexity of rotor-based systems. Lift is generated solely through aerodynamic vortices produced by the pneumatic system.
Solution Approach 2:
Instead of using rotating blades to generate lift (conventional approach), the patent inverts the approach by using stationary wings with air-conveyed vortices. The lift is generated by the interaction of conveyed air with the wing surfaces, creating sustained vortex flow that produces lift without mechanical rotation.
3Adaptability or versatility
If conventional missile designs are used, then basic flight is possible, but payload scalability is limited
Solution Approach 1:
The patent creates a universal missile platform where the vortex-based lift system can accommodate various payload configurations. The modular wing design with distributed air inlets and vortex openings allows the same basic structure to support different payload sizes and types, enabling scalability from small to large payloads without fundamental design changes.
Solution Approach 2:
The patent incorporates dynamic adjustment capabilities in the air conveyance system, allowing flow rates and vortex intensities to be adjusted based on payload weight and flight conditions. This dynamic adaptability enables the same missile design to optimize performance across a range of payload configurations.
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 enables efficient and stable flight operations with reduced energy consumption, allowing for scalable payload capacity and precise control of the missile, similar to a helicopter, while achieving high speeds without the limitations of rotor-based systems.
Implementation Method 1
The air conveying device is designed and arranged to convey air from the air inlet opening (7) to the air outlet opening (8) in such a way that a support vortex (24) is generated
Implementation Method 2
creating a low-turbulence air film that induces lift with minimal energy expenditure
Implementation Method 3
Viewed in section, the wing is bounded by two profile surfaces, namely the first profile surface (4) and the second profile surface (5)
Data Source
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AI summary
The invention relates to an aircraft (1). Said aircraft 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 further relates to a method for operating an aircraft (1).