Rotary Actuator Integration for Thinner Aircraft Control Surfaces
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Solution Overview
Problem
Aircraft control surface systems face limitations in reducing wing thickness and achieving optimal aerodynamic performance due to the spatial requirements and aerodynamic penalties of linear actuators, which necessitate a more efficient and compact solution for controlling control surfaces.
Innovation Solution
An electronically controlled rotary actuator system is integrated within the aerodynamic aircraft structure, utilizing a hydraulic pump and electric motor system to move control surfaces with variable pressure, reducing the need for external space and enhancing aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Volume of moving object
If linear actuators are used to control control surfaces, then the control surface can be moved to desired positions, but the wing thickness cannot be reduced and aerodynamic performance is penalized due to the space required for the actuator
Solution Approach 1:
The patent replaces the traditional linear actuator mechanical system with a rotary actuator system that uses hydraulic or electric rotation to achieve control surface movement. This substitution eliminates the need for a linear mechanical push-pull mechanism, allowing the actuator to be mounted in a rotary configuration that occupies less space within the wing structure, thereby enabling reduced wing thickness while maintaining control surface positioning capability
Solution Approach 2:
The patent transitions from linear actuation (one-dimensional movement) to rotary actuation (rotational movement around an axis). This dimensional change allows the actuator to be integrated into the wing structure in a different spatial orientation, reducing the volume required along the wing thickness dimension while preserving the ability to move the control surface through mechanical linkage
2Manufacturing precision
If linear actuators are used in aircraft, then control surfaces can be positioned accurately, but non-value-added structural space is required for spatial integration of system equipment
Solution Approach 1:
The patent replaces the space-intensive linear actuator mechanical system with a compact rotary actuator system. The rotary mechanism, driven by hydraulic motors or electric motors with gear reductions, achieves the same control surface positioning accuracy through rotational motion converted to linear motion at the control surface hinge, thereby reducing the volume required for actuator integration within the aircraft structure
Solution Approach 2:
The patent integrates the rotary actuator components (motor, gear train, shafts) in a nested or compact arrangement within the wing or fuselage structure. The counterbalancing mechanism and drive train are arranged in a space-efficient configuration that fits within the existing structural envelope, minimizing the non-value-added space required while maintaining positioning accuracy
3Ease of operation
If linear actuators are used, then control surface movement is achieved, but aerodynamic performance is penalized
Solution Approach 1:
The patent replaces linear actuators with rotary actuators that can be positioned more optimally within the wing structure. This substitution allows for better aerodynamic fairing of the actuator housing and surrounding structures, reducing drag and improving airflow over the wing. The rotary actuator configuration enables cleaner integration with the aerodynamic surface, eliminating the need for protruding linear actuator components that create aerodynamic penalties
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 allows for thinner wing designs with improved aerodynamic performance, reduced drag, and increased safety through dual-energy actuation, enabling efficient control surface movement and backup functionality in case of hydraulic system failure.
Implementation Method 1
A hydraulic pump sends hydraulic fluid into the rotary actuator at variable pressure
Implementation Method 2
An electric motor system operates to cause the hydraulic pump to send the hydraulic fluid into the rotary actuator
Data Source
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AI summary
A method and apparatus for positioning a control surface (210). A desired position (320) for the control surface (210) associated with an aerodynamic aircraft structure (212) is identified. The control surface (210) is moved to the desired position (320) using an electronically controlled rotary actuator system (208) located inside of the aerodynamic aircraft structure (212), wherein a shape (216) of the aerodynamic aircraft structure (212) with the electronically controlled rotary actuator system (208) has a desired aerodynamic performance (220).