Aircraft Vortex Generator with Fluidic Muscle Actuator
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Solution Overview
Problem
Aircraft vertical tail planes and rudders generate excessive aerodynamic drag, leading to increased fuel consumption and reduced range due to the need for larger surfaces to achieve maximum yawing moment, which remains underutilized under regular conditions, and existing designs are prone to failure or costly maintenance due to complex mechanisms.
Innovation Solution
A vortex generator arrangement with a resiliently deformable airflow modification device and fluidic muscle actuators, controlled by a system that deploys and retracts the device to optimize airflow over the tail plane and rudder, reducing drag and simplifying maintenance by minimizing moving parts.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If the vertical tail plane and rudder dimensions are increased to generate maximum yawing moment, then the yawing moment capability is improved, but the aerodynamic drag increases
Solution Approach 1:
The vortex generator arrangement allows dynamic adjustment of airflow characteristics over the tail plane and rudder. By deploying vortex generators only when needed (during maneuvers requiring maximum yawing moment), the system optimizes airflow attachment and reduces drag during normal cruise conditions, eliminating the need for permanently oversized surfaces
Solution Approach 2:
The system changes the flow regime parameters over the tail plane by introducing controlled vortices. This modifies the boundary layer characteristics and pressure distribution, enabling the same surface area to generate both maximum yawing moment when needed and minimum drag during normal operation
2Adaptability or versatility
If conventional vortex generator mechanisms are used with multiple moving parts, then the airflow control capability is improved, but the reliability decreases and maintenance costs increase
Solution Approach 1:
The invention extracts and eliminates the problematic moving parts from conventional vortex generator mechanisms. The resiliently deformable flap member provides the necessary airflow control capability through elastic deformation rather than mechanical movement, removing hinges, motors, and other failure-prone components
Solution Approach 2:
The patent replaces mechanical actuation systems with a fluidic muscle actuator that uses pneumatic or hydraulic pressure to deform the flap member. This substitution eliminates mechanical wear, friction, and complex linkages while maintaining the ability to control vortex generation and airflow patterns
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 solution enhances aerodynamic performance by reducing drag, conserving fuel, and lowering maintenance costs through a more efficient and reliable vortex generator system that can be easily controlled and maintained.
Implementation Method 1
the fluidic muscle actuator is configured to apply a force to the resiliently deformable base member of an aircraft airflow modification device so as to deform it from a first state to second state or vice versa
Implementation Method 2
the resiliently deformable flap member of an aircraft airflow modification device in a first state extends through the opening when the resiliently deformable base member is in a corresponding first state
Implementation Method 3
A vortex generator arrangement with a resiliently deformable airflow modification device and fluidic muscle actuators, controlled by a system that deploys and retracts the device to optimize airflow over the tail plane and rudder
Data Source
AI summary
A vortex generator control system for a controlling an aircraft vortex generator arrangement comprising a controller configured to receive one or more deploy or retract command signals from a flight control unit and further configured to send one or more command signals to a fluid control valve, a fluid pressure sensor configured to sense one or more pressure values from an actuator of the vortex generator arrangement and to signal the pressure value(s) to the controller, wherein the fluid control valve is configured to control fluid transfer between the actuator and a reservoir in response to a command signal from the controller.