Aircraft Control Feedback for Gust Disturbance Compensation
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Solution Overview
Problem
Existing aircraft control systems struggle to maintain proper control during disturbances such as gusts, which can lead to instability and inaccurate navigation.
Innovation Solution
An aircraft control system that includes a target instruction value calculation unit, a reference velocity calculation unit, a relative velocity calculation unit, an estimated disturbance quantity calculation unit, and a correction target instruction value calculation unit, which work together to calculate and correct the target instruction value based on estimated disturbances, ensuring stable and accurate flight control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional navigation control is used, then the aircraft can be controlled under normal conditions, but the control accuracy deteriorates when disturbances such as gusts occur
Solution Approach 1:
The control system calculates the difference between actual velocity and reference velocity to estimate disturbance quantities, then feeds this information back to correct the target instruction value. This feedback mechanism enables the system to adapt to disturbances such as gusts and maintain control accuracy under varying flight conditions.
Solution Approach 2:
The patent introduces an intermediary disturbance estimation mechanism that acts as a mediator between the velocity calculation unit and the target instruction value calculation unit. By calculating disturbance quantities based on velocity differences and using these as correction inputs, the system effectively isolates and compensates for harmful external factors.
2Reliability
If disturbance compensation is added to improve control accuracy, then the system becomes more complex
Solution Approach 1:
The disturbance compensation function is merged into the existing velocity calculation and target instruction value calculation processes. The disturbance estimation is performed by utilizing the velocity difference information that is already available in the control loop, and the correction is applied within the existing calculation framework, avoiding the need for separate complex compensation subsystems.
Solution Approach 2:
The control system performs self-diagnosis and self-correction by autonomously estimating disturbance quantities from its own velocity measurements and automatically adjusting its target instruction values. This self-service capability allows the system to maintain stability without requiring external intervention or complex additional hardware.
Data Source
AI summary
An aircraft control system includes a target instruction value calculation unit configured to acquire a target instruction value to set an aircraft in a target state, a reference velocity calculation unit configured to input, to a reference model in which a reference velocity corresponding to a reference value of an aircraft velocity is set uniquely as an output value according to an input value, a value based on the target instruction value as the input value. A relative velocity calculation unit is configured to calculate a relative velocity of the aircraft to a target position. An estimated disturbance quantity calculation unit is configured to calculate an estimated disturbance quantity acting on the aircraft, based on a difference between the relative and reference velocities, and a correction target instruction value calculation unit is configured to correct the target instruction value, based on the estimated disturbance quantity calculated at a previous time.