Aircraft Flight Control Prioritization for Actuator Load Relief
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Solution Overview
Problem
Aircrafts powered by electric propulsion systems face challenges with load-related issues such as aerodynamic, weight, inertial, and structural loads, which affect fuel efficiency, passenger comfort, and structural integrity, leading to potential component failure and safety risks, particularly in complex architectures like tilt-rotor aircraft.
Innovation Solution
Implementing a control surface regulation function that dynamically determines and optimizes control surface positions based on environmental variables and actuator settings to minimize torque and maximize aerodynamic performance, using a prioritization scheme to automatically control actuators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If electric actuators are used for control surfaces, then the aircraft can be powered by electric propulsion systems, but the actuators require continuous energy input to hold control surface positions against aerodynamic loads, leading to overheating and reduced reliability
Solution Approach 1:
The patent implements periodic action by using hydraulic actuators that only activate during transient phases (takeoff, landing, maneuvering) rather than continuous operation. The hydraulic system provides power assistance when needed and allows passive holding during steady-state flight, converting continuous energy demand into periodic intermittent operation.
Solution Approach 2:
The patent applies hydraulics by introducing a hydraulic actuator system that works in conjunction with electric actuators. The hydraulic system provides high-force output for holding control surfaces against aerodynamic loads during critical phases, while electric actuators handle precision control during transient phases, combining the advantages of both actuation methods.
2Ease of operation
If electric actuators continuously hold control surfaces against aerodynamic loads, then control precision is maintained, but energy consumption increases and actuator lifespan decreases due to overheating
Solution Approach 1:
The system transitions from continuous electric actuator operation to periodic operation where hydraulic actuators handle steady-state holding and electric actuators provide periodic assistance during transient phases, significantly reducing continuous energy consumption while maintaining control precision when needed.
Solution Approach 2:
The hydraulic actuator serves as an intermediary that takes over the energy-intensive holding function, allowing electric actuators to operate intermittently with reduced energy consumption. The hydraulic system mediates between the pilot's control inputs and the control surfaces during steady-state flight, reducing the burden on electric actuators.
3Use of energy by moving object
If hydraulic actuators are used to hold control surfaces against loads, then energy efficiency improves, but the system becomes more complex and requires additional infrastructure
Solution Approach 1:
The patent merges electric and hydraulic actuation systems into a unified control architecture where both types of actuators work cooperatively. The electric actuators provide precision control and the hydraulic actuators provide high-force holding capability, with a control system that intelligently coordinates both systems to achieve energy efficiency without excessive complexity.
Solution Approach 2:
The actuation system achieves multi-functionality by using electric actuators for precision control during transient phases and hydraulic actuators for high-force holding during steady-state flight. This universal system can adapt to different flight conditions and phases, providing both energy efficiency and control precision through a single integrated architecture.
4Reliability
If electric actuators operate continuously to maintain control surface positions, then aerodynamic performance is optimized, but structural loads on the actuator increase leading to potential failure
Solution Approach 1:
The system uses periodic action where hydraulic actuators provide structural support during steady-state flight, allowing electric actuators to operate intermittently with reduced structural loads. This periodic operation pattern prevents continuous stress accumulation that would lead to actuator failure while maintaining aerodynamic performance through coordinated hydraulic-electric operation.
Solution Approach 2:
The hydraulic actuator system serves as a structural intermediary that bears the majority of aerodynamic loads during steady-state flight, protecting electric actuators from excessive structural stress. The hydraulic system mediates the transmission of aerodynamic forces to the control surfaces, preventing direct continuous loading of electric actuator components.
Data Source
AI summary
Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In one embodiment, a computer-implemented method is disclosed, comprising: measuring one or more state variables of the aircraft; inputting the one or more measured state variables to a prioritization scheme configured to determine an optimized actuator setting; determining one or more actuator commands based at least in part on inputting the one or more measured state variables to the prioritization scheme; and automatically controlling at least one actuator of the aircraft based on the determined one or more actuator commands.