Aircraft Control Surface Actuators With Force-Torque Control
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Solution Overview
Problem
Existing aircraft actuator control systems face inefficiencies in handling external gusts and fast flight maneuvers due to rigid position control, leading to high loads on control surfaces and actuators, and are not optimally suited for nonlinear conditions.
Innovation Solution
A device and method implementing force/torque control for actuators driving aerodynamic control surfaces, allowing flexible response to gusts and faster control dynamics, with processors and sensors managing setpoint forces and torques, and virtual limits to prevent mechanical overload.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If rigid position control is used for actuators, then control precision is maintained, but high loads occur on control surfaces and actuators during gusts and fast maneuvers
Solution Approach 1:
The patent changes the control parameter from position to force/torque. Instead of rigidly controlling actuator position, the system now controls the force/torque output of the actuator. This allows the control surface to respond more flexibly to external gusts and maneuvers, reducing the loads transmitted to the actuator while maintaining adequate control authority through force-based actuation.
2Reliability
If conservative design is applied to position-controlled actuators, then stability is ensured, but nonlinear actuators are not optimally utilized
Solution Approach 1:
The patent transitions from static conservative design to dynamic force control. By controlling actuators based on force/torque requirements rather than fixed position limits, the system can dynamically adapt to varying flight conditions. This allows nonlinear actuators to operate in their optimal performance range while maintaining stability through active force regulation rather than conservative mechanical design margins.
3Ease of operation
If position control is used, then control authority is maintained, but response speed is limited during fast maneuvers
Solution Approach 1:
The patent changes the controlled parameter from position to force/torque, which fundamentally alters the control dynamics. Force control allows for faster response because it directly actuates the control surface without the inertial and frictional constraints that limit position-controlled systems. The control authority is maintained through sufficient force/torque capability, while response speed improves due to the more direct actuation mechanism.
Data Source
AI summary
The invention relates to a device and to a method for the open and closed control of n actuators An, n=1, 2, . . . , N, where N≥1, which drive aerodynamic control surfaces of an aircraft. The proposed device includes a first interface at which, by manually inputting of a pilot into an input means, predefinitions SVPilot for controlling the actuators An are generated and made available and/or a second interface at which, by means of an automatic flight controller of the aircraft, predefinitions SVAutoPilot for controlling the actuators An are generated and made available, a unit, which on the basis of predefinitions SVPilot and/or SVAutoPilot per actuator An, determines a reference variable FAn,setpoint, for controlling the actuator An, wherein the reference variable FAn,setpoint specifies a setpoint force or a setpoint torque, and per actuator An a force/torque controller REGn for performing closed control of the actuator An on the basis of the assigned reference variable FAn,setpoint and a force/torque FAn generated by the actuator An as a closed-control variable which is determined by a sensor device S1n, which is respectively present at or in the actuator An or in the drivetrain of the respective actuator An.