Hybrid Actuation System for Aircraft Flight Control Surfaces
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Solution Overview
Problem
Current aircraft flight control systems face inefficiencies due to the need for large, powerful hydraulic actuators that consume excessive engine power, especially during non-peak aerodynamic conditions, leading to reduced aircraft performance and increased weight.
Innovation Solution
A hybrid power actuation system that employs a hydraulic actuator during non-peak conditions and switches to a combination of hydraulic and electric actuators during peak conditions, optimizing power usage and reducing actuator size and weight by activating the electric actuator only when necessary.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If large, powerful hydraulic actuators are used to move flight control surfaces during all flight conditions, then the control surface can be moved during peak aerodynamic conditions, but excessive engine power is consumed during non-peak conditions and aircraft weight increases
Solution Approach 1:
The system dynamically switches between different actuator configurations based on flight conditions. During non-peak conditions, only the electric actuator is used. During peak conditions, the hydraulic actuator is activated to provide additional power. This dynamic adaptation resolves the contradiction by matching actuator power output to actual flight requirements, reducing unnecessary engine power consumption while maintaining flight control reliability when needed.
Solution Approach 2:
The flight control system employs a hybrid actuation system with both electric and hydraulic actuators that can function independently or together. The electric actuator handles normal operations, while the hydraulic actuator provides backup and peak power capability. This multi-functionality ensures reliability is maintained across all flight conditions without requiring the hydraulic system to operate continuously, thus reducing engine power consumption during non-peak conditions.
2Force
If hydraulic actuators are used for all flight control operations, then sufficient power is available for peak aerodynamic conditions, but aircraft weight and hydraulic system size increase
Solution Approach 1:
The actuation system is segmented into two independent actuators: an electric actuator for normal operations and a hydraulic actuator for peak conditions. This segmentation allows the aircraft to carry the lighter electric actuator as the primary system, reducing overall weight, while the hydraulic actuator serves as a supplemental component only activated when high force is required, thus resolving the weight-force contradiction.
Solution Approach 2:
The system changes the power source parameter from exclusively hydraulic to a hybrid electric-hydraulic configuration. By switching the primary actuation mode to electric (which is lighter) and using hydraulic power only when high force parameters are required, the system reduces aircraft weight while maintaining the capability to generate sufficient actuator force during peak aerodynamic conditions.
3Weight of moving object
If electric actuators are used instead of hydraulic actuators, then aircraft weight and system volume are reduced, but reliability decreases due to electronics operating in harsh environments and regenerative effects on the power system
Solution Approach 1:
The system incorporates a hydraulic actuator as a pre-prepared backup and support system for the electric actuator. This 'cushioning' arrangement ensures that if the electric actuator fails or encounters regenerative effects, the hydraulic actuator is already in place to take over and maintain flight control reliability, thus resolving the reliability concern while keeping the primary system lightweight and electric.
Solution Approach 2:
The hydraulic actuator serves as an intermediary backup system that mediates between the electric actuator and the flight control surface. When the electric actuator operates in harsh environments and reliability is compromised, the hydraulic actuator intervenes to provide reliable actuation. This intermediary arrangement allows the system to benefit from the weight reduction of electric actuators while maintaining the reliability assurance of hydraulic systems.
4Reliability
If three independent hydraulic systems are used for redundancy, then flight control reliability is improved, but aircraft weight and system complexity increase
Solution Approach 1:
The system extracts and removes two of the three hydraulic systems, retaining only one hydraulic system to support the electric actuator. This extraction reduces hydraulic system complexity and aircraft weight while maintaining adequate reliability through the hybrid configuration. The single hydraulic system serves as a backup and peak-power source, providing sufficient redundancy without the complexity of three independent hydraulic systems.
Data Source
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AI summary
Methods and apparatus for controlling aircraft flight control surfaces are disclosed. An example apparatus includes a flight control surface controller to move a control surface (202) of an aircraft to a target position via at least one of a first actuator (204) or a second actuator (206) associated with the control surface based on a command input received by the flight control surface controller. The flight control surface controller to: obtain a flight characteristic of the aircraft; compare the flight characteristic to a flight characteristic threshold; in response to a first comparison result, cause the first actuator to move the control surface to the target position based on the command input without moving the second actuator; and in response to a second comparison result, cause the first actuator and the second actuator to move the control surface to the target position based on the command input.