Aircraft Flight Control Actuator 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 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 universal pivot arrangements to prevent binding and ensure precise sensing.
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 sensor can detect flight control surface angle, 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 position sensor with the actuator that drives the flight control surface, eliminating the separate sensing mechanical linkage. The sensor is integrated into the actuator assembly, specifically sensing rotation of the actuator shaft or housing, which directly correlates to the flight control surface angle without being affected by non-ideal motion modes.
Solution Approach 2:
The patent uses the actuator itself as an intermediary between the flight control surface and the sensor. Instead of directly sensing the flight control surface rotation through a separate linkage, the sensor measures the actuator's rotational position, which serves as a reliable proxy for the surface angle since the actuator directly drives the surface about its primary rotation axis.
2Measurement precision
If a separate sensing mechanical linkage is used to detect flight control surface angle, then rotational position can be sensed, but the system complexity increases with additional components
Solution Approach 1:
The patent combines the sensing function with the actuator assembly, eliminating the need for a separate dedicated sensing mechanical linkage. The rotation position sensor is mounted on or integrated with the actuator, sharing the same structural platform and reducing the overall number of components required for angle detection.
Solution Approach 2:
The actuator assembly serves multiple functions: it provides the driving force for flight control surface movement and simultaneously serves as the mounting structure and reference frame for the rotation position sensor, eliminating the need for a separate sensing linkage structure.
3Measurement precision
If the rotation sensor is integrated with the actuator, then false readings are inhibited and accuracy is improved, but the integration complexity increases
Solution Approach 1:
The patent integrates the rotation position sensor directly with the actuator assembly, mounting the sensor on the actuator housing or integrating it into the actuator shaft structure. This close integration ensures that the sensor measures the actuator's rotational position directly, eliminating false readings while maintaining relatively simple implementation through standard mounting techniques.
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
Enhances sensing accuracy by inhibiting false readings and providing a compact, value-added arrangement that eliminates the need for additional sensing linkages, ensuring precise control of flight control surfaces.
Implementation Method 1
The actuator includes a threaded shaft extending along a shaft axis and a drive for rotating the threaded shaft about the shaft axis. The actuator also includes a nut assembly having a nut threadingly mounted on the threaded shaft such that rotation of the threaded shaft about the shaft axis drives axial movement of the nut assembly along the shaft axis
Implementation Method 2
The nut assembly further includes a pivot arrangement for allowing the flight control member actuator mount to pivot about a first pivot axis relative to the shaft axis as the actuator drives pivotal movement of the flight control member about the flight control pivot axis
Implementation Method 3
The system includes a rotation sensor for sensing a rotational position of the flight control member actuator mount about the first pivot axis
Data Source
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.