Aircraft Wing Actuator Arm Alignment for Drag Reduction
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Solution Overview
Problem
Conventional aircraft wing actuators for flight control surfaces, especially those at the trailing edge, require large fairings due to their non-parallel alignment with the flight path, which reduces aerodynamic efficiency.
Innovation Solution
An actuator arm with a longitudinal axis aligned with the flight path, allowing non-planar movement through pivotal connections in multiple planes, reducing the size and aerodynamic impact of the fairing needed to cover the actuator.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If the actuator longitudinal axis is made perpendicular to the hinge line for simple planar operation, then the actuator mechanism is simplified, but the fairing size increases significantly reducing aerodynamic efficiency
Solution Approach 1:
The actuator arm is enabled to move from a single planar dimension to multiple dimensions by incorporating pivotal connections that allow rotation in both the first plane (perpendicular to hinge line) and second plane (parallel to hinge line). This multi-planar movement capability allows the actuator longitudinal axis to be aligned with the line of flight while still actuating the control surface, thereby reducing fairing size and aerodynamic drag without sacrificing actuation functionality
Solution Approach 2:
The invention changes the movement parameters of the actuator arm by introducing rotational freedom in multiple planes through pivotal connections. This parameter change enables the actuator to achieve both the simplified alignment with the line of flight and the necessary control surface actuation, resolving the contradiction between mechanism simplicity and aerodynamic efficiency
2Object-affected harmful factors
If the actuator longitudinal axis is aligned with the line of flight to reduce fairing size, then aerodynamic efficiency is improved, but the actuator connection arrangement becomes more complex requiring multi-plane pivotal connections
Solution Approach 1:
The actuator arm is enabled to move from a single planar dimension to multiple dimensions by incorporating pivotal connections that allow rotation in both the first plane (perpendicular to hinge line) and second plane (parallel to hinge line). This multi-planar movement capability allows the actuator longitudinal axis to be aligned with the line of flight while still actuating the control surface, thereby reducing fairing size and aerodynamic drag without sacrificing actuation functionality
Solution Approach 2:
The actuator arm with multi-plane pivotal connections serves multiple functions: it maintains alignment with the line of flight for aerodynamic efficiency, enables control surface actuation through first plane rotation, and accommodates the geometric relationship between the control surface hinge line and flight path through second plane rotation. This multi-functionality resolves the contradiction by making the connection arrangement capable of handling both aerodynamic and actuation requirements
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 minimizes the fairing size, enhancing the aerodynamic performance of the aircraft wing by allowing the actuator arm to move in multiple planes while maintaining efficient operation of the flight control surfaces.
Implementation Method 1
the first pivotal connection and/or second pivotal connection allows rotary movement of the actuator arm in a first plane and second plane
Data Source
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AI summary
The present invention relates to the provision of an improve aircraft wing and flight control surface. More particularly, the invention seeks to provide a flight control surface with an actuator with an improved aerodynamic fairing. The aircraft comprises a swept aircraft wing (12). The aircraft wing comprises a movable flight control surface with a hinge line (X) non-perpendicular to the line of flight of the aircraft, and an actuator arm (20) configured to actuate the flight control surface. The actuator arm (20) comprises a longitudinal axis (Y) substantially aligned with the line of flight, the actuator arm (16) extending at least partially from an outer surface of the aircraft wing (12), and a fairing (18) arranged on the outer surface of the aircraft wing to at least partially cover the actuator arm (16). Aligning the actuator arm with the line of flight of the aircraft may allow for an improved fairing to be provided.