Swiveling Vane Flow Control for Aircraft Lift Augmentation
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Solution Overview
Problem
Current aircraft designs face challenges in achieving improved short takeoff and landing (STOL) performance due to limitations in lift generation, particularly in environments without sophisticated runways, as existing technologies struggle to efficiently control engine exhaust flow and maximize lift using the Coanda Effect.
Innovation Solution
A system and method that utilize swiveling vanes in fluid ejection orifices to direct and rotate the flow of compressed fluid over the aircraft's lifting surfaces, enhancing lift generation by suppressing flow separation and optimizing the attachment of the exhaust stream to the surface, thereby increasing lift and reducing the required runway length for takeoff.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If engine exhaust flow is directed over the lifting surface using fixed vanes, then lift generation is enhanced through Coanda Effect attachment, but the system cannot adapt to varying operational conditions and maintains optimal flow attachment
Solution Approach 1:
The patent applies the Dynamics principle by implementing vanes that can rotate about their longitudinal axes to change the flow direction dynamically. The vanes are positioned at different longitudinal locations along the exhaust stream and can be independently rotated to different angles. This allows the system to adapt to varying operational conditions (such as different flight phases, speeds, and altitudes) by adjusting the flow attachment angle, thereby resolving the contradiction between adaptability and complexity through controlled dynamic adjustment rather than complete system redesign.
Solution Approach 2:
The patent applies the Segmentation principle by dividing the exhaust stream into multiple segments and controlling each segment independently through separately positioned vanes. Each vane operates at a specific longitudinal location and can be rotated to a specific angle to control the local flow direction. This segmentation allows targeted adaptation to different operational conditions without requiring complex centralized control, thus balancing adaptability with manageable system complexity.
2Force
If compressed fluid is ejected through fluid ejection orifices to enhance lift, then flow separation is suppressed and lift generation is improved, but engine bleed requirements increase
Solution Approach 1:
The patent applies the Local quality principle by positioning fluid ejection orifices at specific locations where flow separation is most likely to occur. The vanes are strategically placed at different longitudinal positions along the exhaust stream to target specific flow attachment zones. This localized approach ensures that compressed fluid is ejected only where needed to suppress flow separation and enhance lift, rather than uniformly across the entire exhaust stream, thereby reducing the total quantity of compressed fluid required while maintaining effective lift generation.
Solution Approach 2:
The patent applies the Self-service principle by utilizing the engine's own exhaust stream as the primary flow control medium. The system directs the existing exhaust gases over the lifting surface using the vanes, and only supplements with compressed fluid from engine bleed when necessary for flow separation suppression. This self-service approach maximizes the use of already-available exhaust flow, minimizing the additional compressed fluid quantity required while still achieving enhanced lift.
3Reliability
If vanes are used to direct exhaust stream attachment, then lift augmentation is maintained across varying flight conditions, but the system complexity and control requirements increase
Solution Approach 1:
The patent applies the Dynamics principle by implementing rotatable vanes that can adjust their angle dynamically based on operational conditions. Each vane rotates about its longitudinal axis to change the flow direction locally. This dynamic capability ensures reliable lift augmentation across varying flight conditions (takeoff, landing, cruise, etc.) while keeping the control mechanism relatively simple - each vane is independently rotatable without requiring complex interconnections or centralized control systems.
Solution Approach 2:
The patent applies the Segmentation principle by dividing the flow control function into multiple independent vane segments positioned at different longitudinal locations. Each vane can be controlled independently to optimize flow attachment at its specific location. This segmentation distributes the control complexity across multiple simple, independent units rather than requiring one complex centralized control mechanism, thereby maintaining reliable lift augmentation while managing overall system complexity through modular independence.
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 system effectively enhances lift generation, providing robust STOL capabilities across a range of operational conditions with reduced engine bleed requirements, improving aircraft performance and efficiency by maintaining lift augmentation during takeoff, landing, and varying flight conditions.
Implementation Method 1
Recent military campaigns, for example, have demonstrated an increased need for improved short takeoff and landing (STOL) performance to allow aircraft to operate in environments where sophisticated airports and other landing facilities may not be available. In particular, it is desirable to create aircraft that are able to takeoff and/or land even on relatively short runways with even better STOL performance than current designs.
Implementation Method 2
A system and method that utilize swiveling vanes in fluid ejection orifices to direct and rotate the flow of compressed fluid over the aircraft's lifting surfaces, enhancing lift generation by suppressing flow separation and optimizing the attachment of the exhaust stream to the surface
Implementation Method 3
The flow direction is rotated in a span-wise direction over the lifting surface by swiveling the vanes periodically. The vanes can also deflect a constant blowing jet to a given angle. The vanes can rotate the flow direction depending on the operational condition.
Data Source
AI summary
A system and method for robust lift generation through flow separation suppression are presented. A fluid flow is ejected over a lifting surface from a fluid ejection orifice, and a flow direction of the fluid flow over the lifting surface is directed using a plurality of vanes configured in the fluid ejection orifice. The flow direction is rotated in a span-wise direction over the lifting surface by swiveling the vanes.