Flapping-Wing Flight Control Using Drive Motion Error Feedback
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Solution Overview
Problem
Conventional UAVs with flapping wings experience delays in detecting and correcting for disturbances due to inherent lag in closed feedback systems, leading to instability and control issues, particularly in environments with rapid changes.
Innovation Solution
A flight control system that includes a controller to send control signals to drive units, receive feedback on actual motion, and compare it to demanded motion to determine and correct errors in real-time, using encoders to monitor and compensate for displacement errors in drive units.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a closed feedback loop is used to detect and correct disturbances, then the UAV can be stabilized, but the system exhibits hysteresis and lag because the attitude must change to a threshold level before correction can begin
Solution Approach 1:
The controller performs preliminary action by detecting motion errors in the drive unit before they translate into significant attitude changes. By monitoring drive unit position feedback and comparing it to commanded position, the system identifies disturbances at their source and applies corrective signals proactively, preventing the need to wait for attitude threshold violations.
Solution Approach 2:
The system replaces traditional mechanical attitude-based feedback with an electronic control-based feedback mechanism. Instead of relying on mechanical attitude changes to trigger correction, the system uses electronic sensors and controllers to detect drive unit position errors and generate corrective signals, eliminating mechanical lag and hysteresis.
2Power
If conventional rotor-based thrust generators are used, then the UAV can generate lift, but the rotational inertia of the rotors adversely affects the ability to react rapidly to disturbances
Solution Approach 1:
The system transitions from static, high-inertia rotor assemblies to dynamic, low-inertia flapping wing mechanisms driven by oscillating drive units. The wings can rapidly change their flapping motion in response to control signals, enabling quick disturbance rejection while maintaining lift generation capability through controlled flapping motion.
Solution Approach 2:
The system changes the fundamental operating parameters of the thrust generation mechanism by replacing continuous rotation with oscillatory motion. This parameter change from rotational to oscillatory movement fundamentally alters the inertial characteristics, enabling rapid response to disturbances while preserving the ability to generate necessary lift forces.
Data Source
AI summary
A flight control system (20) comprising: • at least one drive unit (4); • at least one wing (5) operatively connected to the at least one drive unit; and • a controller (21) configured to: • send a control signal to the at least one drive unit to operate the at least one drive unit through a demanded motion; • receive a feedback signal indicative of the actual motion of the at least one drive unit; and • compare the actual motion to the demanded motion to determine a motion error of the at least one drive unit.