Redundant Flight Control Actuator System for Aircraft Safety
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Solution Overview
Problem
Aircraft systems lack effective redundancy in flight control, leading to safety risks during actuator failures, which can result in loss of control or airframe breakup and loss of life.
Innovation Solution
A redundant flight control system is implemented, featuring a pair of actuators (first and second actuators) with electric motors that convert electrical signals into mechanical movements, where if the first actuator fails, the second actuator takes over to maintain aircraft attitude control, with a pilot control generating electrical signals and a sensor detecting actuator disablement to trigger the backup.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a single actuator is used to control aerodynamic surfaces, then the device complexity is reduced, but the reliability deteriorates due to lack of redundancy during actuator failures
Solution Approach 1:
The flight control system is segmented into multiple independent actuators (first actuator and second actuator), each capable of independently controlling the aerodynamic surface. This segmentation allows the system to maintain functionality even if one actuator fails, thereby improving reliability without requiring a completely redundant complex system.
Solution Approach 2:
The system performs preliminary action by pre-configuring multiple actuators with the capability to control the same aerodynamic surface before any failure occurs. The control system is pre-programmed to detect actuator failures and automatically switch to the remaining functional actuator, ensuring continuous safe operation without requiring complex real-time decision-making during emergencies.
2Reliability
If redundant actuators are added to the flight control system, then the reliability is improved during actuator failures, but the device complexity increases
Solution Approach 1:
Multiple actuators are merged to control a single aerodynamic surface, creating a unified control system where the first actuator and second actuator work together or independently to achieve the same control objective. This merging approach provides redundancy while maintaining relatively simple system architecture compared to fully independent redundant systems.
Solution Approach 2:
Both the first actuator and second actuator are designed with universal functionality to perform the same control function on the aerodynamic surface. Each actuator can independently execute control commands, allowing the system to maintain full functionality regardless of which actuator is operational, thereby providing reliability without requiring complex specialized configurations.
3Ease of operation
If electric motors are used in actuators to convert electrical signals into mechanical movements, then the ease of operation is improved through precise control, but the use of energy increases
Solution Approach 1:
The electric motors in the actuators are designed to efficiently convert electrical energy to mechanical movement with minimal waste. The control system monitors energy consumption and optimizes actuator operation to perform only necessary control actions, allowing the system to self-regulate energy usage while maintaining precise control capability when needed.
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
Ensures safe aircraft maneuvering during actuator failures by maintaining control and preventing catastrophic events, enhancing safety and reliability.
Implementation Method 1
each of the first actuator and the second actuator comprises at least an electric motor configured to convert an electrical signal into a mechanical movement of the aerodynamic surface
Data Source
AI summary
The present invention is directed to systems and methods for redundant flight control configured for use in an aircraft. More specifically, a system is provided that includes a plurality of actuators that are configured to move a flight component of an aircraft such that one actuator is configured to move the flight component if the other actuator fails to move the flight component upon receipt of an attitude command from a pilot control.