Oblique Flying Wing Control With Yaw-Pitch-Roll Decoupling
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Solution Overview
Problem
Oblique flying wing aircraft face unique stability and handling challenges due to aerodynamic and inertial couplings, which existing control methods struggle to effectively address.
Innovation Solution
A robust control method involving an angular velocity controller with a dense plant matrix and specific transfer function is used to decouple yaw, pitch, and roll rate axes, allowing for independent adjustment of each axis through control effectors, thereby improving stability and handling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If conventional control methods are used for oblique flying wing aircraft, then the control system is simpler, but the aircraft exhibits poor stability and handling due to aerodynamic and inertial couplings
Solution Approach 1:
The control system segments the coupled aircraft dynamics into three independent rotational axes (roll, pitch, yaw) through decoupling control. Each axis is controlled independently by dedicated control effectors, transforming the complex coupled system into manageable separate control channels while maintaining overall stability.
Solution Approach 2:
The control system dynamically adjusts control parameters including angular velocity errors, moment commands, and control effector deflections to compensate for aerodynamic and inertial couplings. By changing these parameters in real-time based on actual versus reference angular velocities, the system achieves stable handling despite the inherently coupled physics of oblique flying wing configuration.
2Measurement precision
If a dense plant matrix with all non-zero components is used in the angular velocity controller, then the control accuracy improves, but the processing requirements increase
Solution Approach 1:
The control system extracts and processes only the essential angular velocity error information (difference between reference and actual angular velocities) rather than processing the entire dense state vector. This extraction of critical parameters maintains control precision while reducing computational burden by focusing only on the most relevant feedback signals.
Solution Approach 2:
The system uses a dense plant matrix that includes all possible coupling terms (excessive action) but only actively processes and responds to the specific angular velocity errors that matter for stability (partial action). This allows the controller to maintain high precision through the complete matrix while avoiding unnecessary computation of terms that do not contribute to the immediate control objective.
Data Source
AI summary
A robust control method for an oblique flying wing aircraft includes computing an angular velocity error between a reference angular velocity and an actual angular velocity and computing a moment command with an angular velocity controller based at least in part on the angular velocity error. The angular velocity controller decouples two or more of a yaw rate axis, a pitch rate axis, and a roll rate axis of the asymmetric aircraft for the moment command.