Tailored Aileron Actuation Using Aerodynamic Loads and Lock Release
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Solution Overview
Problem
Traditional actuation systems for aircraft ailerons are complex, requiring power lines, hydraulic lines, and heavy actuators, which do not fit within the confined spaces of aircraft wings and result in undesirable aerodynamic effects.
Innovation Solution
A tailored aileron deployment system that utilizes aerodynamic loads and a biasing member to induce deflection, controlled by a locking assembly activated by an accelerometer, eliminating the need for mechanical actuation and reducing system complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional actuation systems with power lines, hydraulic lines, and heavy actuators are used, then reliable aileron control is achieved, but the system occupies excessive space within the confined aircraft wing and causes undesirable aerodynamic effects
Solution Approach 1:
The patent removes heavy actuators, power lines, and hydraulic lines from the wing interior, extracting only the essential control function. The aileron is controlled by aerodynamic forces acting on the control surface itself, eliminating the need for traditional mechanical actuation systems within the wing.
Solution Approach 2:
The aileron control system uses the aircraft's own aerodynamic forces to actuate the control surface. The control cable or rod transmits pilot input forces directly to the aileron, which then uses aerodynamic pressure differential to achieve the desired deflection, making the system self-actuating without external power sources.
2Ease of operation
If traditional mechanical actuation systems are used, then precise aileron deflection control is achieved, but the system complexity increases with multiple components such as actuators, cables, pulleys, and hydraulic systems
Solution Approach 1:
The patent extracts the essential control function from the complex assembly of actuators, cables, and hydraulic systems, leaving only the minimal necessary components. The control system reduces to simple mechanical linkages that transmit pilot forces directly to the aileron control hinge.
Solution Approach 2:
Instead of using powered actuators to move the aileron against aerodynamic forces, the system inverts the approach by allowing aerodynamic forces to move the aileron in response to pilot input, with the control system serving to guide and limit the movement rather than drive it.
3Ease of operation
If heavy actuators and associated plumbing are installed in the wing, then aileron actuation capability is provided, but the weight of the aircraft increases
Solution Approach 1:
The patent removes heavy actuators and associated hydraulic or electrical systems from the wing structure, extracting only the essential mechanical control function. This eliminates the need for powered actuation systems while maintaining aileron control capability through direct mechanical linkages.
Solution Approach 2:
The aileron control system uses the pilot's direct mechanical input forces combined with aerodynamic forces on the control surface to achieve actuation, eliminating the need for external power sources and heavy actuators. The system serves itself by using the aircraft's flight conditions to provide the actuation force.
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
Reduces weight, power requirements, and assembly/maintenance time while minimizing space occupation and aerodynamic disruptions by using the aircraft's natural forces to control aileron deflection.
Implementation Method 1
the aileron is locked in place in a stowed configuration and transitions to an unlocked configuration when specific gravitational forces ('G force') or centrifugal forces are recognized by an accelerometer
Implementation Method 2
when specific gravitational forces ('G force') or centrifugal forces are recognized by an accelerometer
Implementation Method 3
The control system utilizes the aerodynamic load on the aileron to induce the desired deflection of the aileron
Data Source
AI summary
A device may include a locking assembly configured for coupling with an aileron of an aircraft, the locking assembly includes a lock configured for coupling with the aileron. The locking assembly may include a lock mechanism operatively coupled with the lock and in communication with an accelerometer, where the lock mechanism is configured to transition the lock from a locked configuration to a released configuration. The lock mechanism opens the lock based on a specified acceleration measured with the accelerometer, and the lock frees the aileron to a dynamic configuration. A device may include a tailored aileron deployment system including a biasing member coupled with the aileron, in the released configuration the biasing member controls movement of the aileron in the dynamic configuration.