Integrated Flight Control Surface Sensing Without False Angle Readings
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Solution Overview
Problem
Existing flight control systems face inaccuracies in rotational position sensing due to flight control surfaces moving in orientations other than their primary axis, leading to false angle change readings.
Innovation Solution
Integration of a rotation sensor with the actuator that drives pivotal/rotational movement of the flight control surface, coupled with a controller to determine accurate flight control angles based on defined relationships between the rotational position of the actuator mount and the flight control member, using a screw-drive mechanism with a threaded shaft and nut assembly to prevent false readings.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a rotation position sensor is attached to a dedicated sensing mechanical linkage separate from the actuator, then the system can detect flight control surface angles, but false angle change readings occur when the flight control surface moves in a manner not about the primary axis of rotation
Solution Approach 1:
The patent merges the rotation sensor with the actuator assembly, specifically mounting the sensor on the actuator housing or case. This integration ensures that the sensor measures only the actuator's rotational output, which is directly coupled to the flight control surface's primary rotation axis. By combining these previously separate components, the system eliminates false readings caused by independent movements of the flight control surface that are not driven by the actuator.
2Measurement precision
If a dedicated sensing mechanical linkage is used separate from the actuator, then rotational position can be sensed, but additional mechanical linkages and components are required increasing system complexity
Solution Approach 1:
The patent integrates the rotation sensor directly into the actuator assembly, eliminating the need for separate dedicated sensing mechanical linkages. The sensor is mounted on the actuator housing and measures the rotational position of actuator components internally, thereby reducing the overall number of mechanical linkages and simplifying the system architecture while maintaining angle detection capability.
Solution Approach 2:
The actuator assembly is designed to serve multiple functions: it provides both the actuation force/movement and the rotational position sensing. By making the actuator assembly universal, the patent eliminates the need for separate dedicated sensing linkages, as the actuator itself performs both actuation and sensing functions through integrated sensors that measure its own output rotation.
3Reliability
If the rotation sensor is integrated with the actuator, then false readings are inhibited and system complexity is reduced, but the sensor must be precisely mounted on moving components of the actuator
Solution Approach 1:
The patent integrates the rotation sensor with the actuator assembly, mounting it on the actuator housing or case. This integration approach allows the sensor to be precisely positioned relative to the actuator's moving components through fixed mounting arrangements, ensuring accurate measurement while maintaining manufacturability through standardized mounting interfaces and alignment features.
Data Source
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AI summary
The present disclosure relates to rotational sensing systems for use in controlling the positions of flight control surfaces. The rotational sensing systems are integrated with actuators used to drive pivotal movement of the flight control surfaces and are configured to ensure higher accuracy in sensing angle changes and/or lack of angle changes of the flight control surfaces.