Aileron Actuation Using APU Power for Aircraft Roll Control
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Solution Overview
Problem
Larger aircraft wing designs with improved aerodynamic performance increase payload capacity and flight range but complicate manual control for pilots, as they require more effort to manage flight control surfaces effectively.
Innovation Solution
The implementation of a system that includes a wing actuator coupled to an aileron, an alternate power unit, a control wheel position sensor, and a flight control computer, which converts pilot input into control signals to control the aileron through a differential linkage, allowing for automated control of aircraft roll operations.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If larger aircraft wing designs are used to improve aerodynamic performance, then payload capacity and flight range are improved, but manual control difficulty increases
Solution Approach 1:
The patent replaces the purely mechanical manual control system with an automated flight control system that uses sensors to detect control wheel position and actuators to automatically adjust flight control surfaces. This substitution of mechanical direct control with an automated control system resolves the contradiction by maintaining the benefits of large wing designs while eliminating the increased manual control difficulty through automation.
Solution Approach 2:
The flight control system performs self-service by automatically sensing the pilot's control inputs through control wheel position sensors and autonomously actuating the flight control surfaces via wing actuators and aileron actuators. This self-service capability allows the system to manage its own control operations without requiring direct mechanical intervention, thereby resolving the manual control difficulty while preserving aerodynamic performance.
2Ease of operation
If automated control systems are implemented to reduce pilot workload, then ease of operation is improved, but device complexity increases
Solution Approach 1:
The automated control system is segmented into distinct functional modules: control wheel position sensors for detection, flight control computers for processing, wing actuators for power transmission, and aileron actuators for surface control. This segmentation allows each component to perform a specific function independently, reducing overall system complexity while maintaining automated control capabilities that ease pilot workload.
Solution Approach 2:
The flight control system incorporates multi-functional components that serve multiple purposes. For example, the control wheel position sensors not only detect control inputs but also provide feedback for system monitoring. The wing actuators serve both as power transmission elements and as control actuators. This multi-functionality reduces the number of separate components needed, thereby reducing device complexity while maintaining ease of operation.
3Measurement precision
If differential linkage is used to convert actuator movement into aileron control, then control precision is improved, but device complexity increases
Solution Approach 1:
The differential linkage acts as an intermediary mechanism between the wing actuator and the aileron. It converts the linear or rotational movement of the actuator into the precise angular movement required for aileron control. This intermediary mechanism provides the necessary motion transformation and control precision while keeping the overall system manageable through its specialized function, thereby resolving the contradiction between control precision and device complexity.
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 system reduces pilot workload by enabling precise control of aircraft roll operations, enhancing safety and efficiency by automating the control of flight control surfaces, even in situations where hydraulic systems fail or are non-responsive.
Implementation Method 1
a differential linkage coupled to the wing actuator and the aileron, the differential linkage to convert first movement of the wing actuator into second movement to control the aileron
Implementation Method 2
a valve spring coupled to the mode selector valve, the valve spring to adjust the mode selector valve from the active position to a block position
Data Source
AI summary
Systems, methods, and apparatus for controlling aircraft roll operations are disclosed. An example system includes a wing actuator coupled to an aileron of an aircraft, an alternate power unit (APU), a control wheel position sensor to measure a control wheel position of a control wheel of the aircraft, a flight control computer (FCC) coupled to the APU and the control wheel position sensor, the FCC to invoke the APU to provide power to the wing actuator, and transmit a control signal to the wing actuator, the control signal to invoke the wing actuator to control the aileron based on the control wheel position, and a differential linkage coupled to the wing actuator and the aileron, the differential linkage to convert first movement of the wing actuator into second movement to control the aileron, the first movement of the wing actuator based on the control wheel position.