Actuator Control System Failure Protection for Electromechanical Actuators
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Solution Overview
Problem
Conventional failure protection systems for flight control systems with hydraulic actuators are not fully suitable for electromechanical actuators, particularly in unmanned air vehicles, due to differences in functionality, with electromechanical actuators being more prone to jamming in safety-critical positions.
Innovation Solution
An actuator control system and method that integrates a failure protection system with servo monitor, command monitor, and loop closure functionalities, specifically designed for electromechanical actuators, where these functions are arranged and located to optimize performance and redundancy within the flight control system, including the actuator stage to handle potential faults.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional failure protection systems designed for hydraulic actuators are used with electromechanical actuators, then the system structure can be maintained, but the reliability and suitability for electromechanical actuators deteriorates due to functional differences and jamming susceptibility
Solution Approach 1:
The patent applies local quality by implementing actuator-specific failure protection configurations. The system distinguishes between hydraulic and electromechanical actuator types and applies different monitoring and protection strategies tailored to each actuator type's characteristics, particularly addressing the jamming susceptibility of electromechanical actuators through specialized detection mechanisms.
Solution Approach 2:
The system changes operational parameters based on actuator type. It monitors different parameters for electromechanical actuators (such as position, velocity, and current) compared to hydraulic actuators, and adjusts protection thresholds and response strategies according to the specific actuator type to optimize reliability.
2Reliability
If redundancy and conventional failure protection functions are implemented, then system reliability improves, but device complexity increases due to additional monitoring and protection mechanisms
Solution Approach 1:
The patent implements multi-functional monitoring apparatus that can perform multiple failure protection functions (servo monitoring, command monitoring, loop closure) within a single integrated system. This universal approach reduces overall system complexity by consolidating redundant functions into unified monitoring and protection mechanisms that serve multiple purposes simultaneously.
Solution Approach 2:
The system merges multiple failure protection functions into integrated monitoring apparatus. The servo monitor, command monitor, and loop closure functions are combined into a unified failure protection system that shares common hardware and software resources, reducing the total number of separate components while maintaining comprehensive protection coverage.
3Adaptability or versatility
If electromechanical actuators are used instead of hydraulic actuators, then system adaptability improves for unmanned air vehicles, but reliability deteriorates due to increased jamming in safety-critical positions
Solution Approach 1:
The system performs preliminary detection of potential jamming conditions through continuous monitoring of actuator position, velocity, and current parameters. By detecting anomalies before complete jamming occurs, the system can trigger preventive actions such as switching to backup actuators or initiating recovery procedures, thereby maintaining reliability despite the use of electromechanical actuators.
Solution Approach 2:
The patent implements feedback mechanisms that continuously monitor actuator performance parameters and provide real-time information to the failure protection system. This feedback enables the system to detect jamming conditions, assess their severity, and respond appropriately by isolating faulty actuators or activating redundancy, thereby compensating for the lower inherent jamming resistance of electromechanical actuators.
Data Source
AI summary
An actuator control system for coupling to one or more flight control computers (FCCs); comprising: apparatus for controlling an aerodynamic control surface in response to commands received from one or more FCCs, and, integrated with the controlling apparatus, a failure protection system comprising apparatus arranged to provide at least one of the following functionalities: a servo monitor functionality, a command monitor functionality, and a loop closure functionality. Thus, in the overall flight control system, some or all of the elements of the failure protection system are located in the actuator control stage.