Aircraft Vane Array Yaw Control via Air Channeling
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Solution Overview
Problem
Aircrafts face a challenge in generating yawing moment control power without compromising their ability to generate pitching and rolling moment control power, as conventional blade spoilers reduce air flow effectiveness for these axes.
Innovation Solution
An air flow channeling yaw control device comprising a vane array and actuator that redirects air flow over the wing, allowing for independent control of yaw, pitch, and roll moments by deploying and retracting vanes to create channels and side forces.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If blade spoilers are used to generate yawing moment control power, then yaw control is improved, but pitching moment and rolling moment control power are reduced
Solution Approach 1:
The aircraft control surface is divided into functionally independent segments: traditional spoilers for pitch/roll control and a separate yaw control device with channeling vanes. This segmentation allows each component to perform its specific function without interfering with the others, resolving the contradiction between yaw control effectiveness and pitch/roll control power.
Solution Approach 2:
The yaw control device introduces an intermediary mechanism (channeling vanes and vane array) that redirects airflow to generate yawing moments through side forces. This intermediary approach creates yaw control through a different physical mechanism than traditional spoilers, preventing the loss of pitch and roll control authority.
2Ease of operation
If a fixed yaw control device is deployed, then yaw control is provided, but aerodynamic efficiency is reduced due to continuous presence
Solution Approach 1:
The yaw control device is designed with movable, deployable components that can dynamically adjust their configuration. The channeling vanes and vane array can be retracted into the wing when not needed and deployed only when yaw control is required, allowing the aircraft to maintain optimal aerodynamic efficiency during normal flight while providing yaw control capability when needed.
Solution Approach 2:
The yaw control device can be retracted into the wing structure when not in use, effectively discarding its aerodynamic presence to maintain efficiency. When yaw control is needed, the device is deployed and then recovered back into the wing after use, minimizing its impact on overall aerodynamic performance.
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
Enables aircraft to generate yawing moment control power while maintaining or enhancing pitching and rolling moment control power, with the device being retractable for aerodynamic efficiency and deployable only when necessary.
Implementation Method 1
The plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over the leading edge of the wing through channels created by the plurality of vanes
Implementation Method 2
The blade spoiler is configured to spoil a flow of air, generating a drag force at a moment arm to rotate about the yaw axis
Data Source
AI summary
An air flow channeling yaw control device includes a vane cover, a vane array, and an actuator. The vane array includes a plurality of vanes, each of the plurality of vanes comprising a first edge and a second edge, the first edge being hingedly coupled to the vane cover and the second edge being hingedly coupled to a wing of an aircraft. The wing includes a leading edge and a trailing edge. The actuator is configured to move the plurality of vanes from a retracted position into a deployed position. The plurality of vanes, when moved into the deployed position, are configured to direct a flow of air flowing over the leading edge of the wing through channels created by the plurality of vanes. The plurality of vanes, when moved into the retracted position, are configured to retract within the wing.