Aircraft Control System Switching Between Surface and Thrust Laws
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing aircraft control systems face challenges in efficiently switching from a control law that relies solely on control surface deflection angles to one that also utilizes engine thrust, leading to slower motion responses when control surfaces malfunction, necessitating appropriate switching between these control laws to maintain stable flight.
Innovation Solution
An aircraft control system that includes a control unit capable of switching between two control laws: one controlling deflection angles of control surfaces and another controlling both deflection angles and engine thrust, with a detection unit for identifying control surface malfunctions and a calculation unit determining necessary deflection angles and rates of change to decide on law switching.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the control surface/thrust integrated flight control law is used to control flight by controlling deflection angles of control surfaces and engine thrust, then the aircraft can maintain stable flight when control surfaces malfunction, but the motion response of the aircraft becomes slower
Solution Approach 1:
The system dynamically switches between the reconfigurable flight control law (for fast response) and the control surface/thrust integrated flight control law (for reliability) based on real-time assessment of flight safety requirements. This dynamic adaptation allows the system to optimize motion response while maintaining stable flight capability when needed.
Solution Approach 2:
The system changes the control parameters by switching between two distinct control laws. The reconfigurable flight control law uses only control surface deflection angles, while the control surface/thrust integrated flight control law adds engine thrust control. This parameter change enables the system to balance response speed and stable flight capability based on malfunction severity.
2Speed
If the reconfigurable flight control law is used to control flight by controlling deflection angles of control surfaces, then the motion response remains fast, but the system cannot maintain stable flight when control surfaces are severely damaged
Solution Approach 1:
The system continuously monitors flight conditions and control surface status, providing feedback to the switching necessity judgment unit. This feedback mechanism enables real-time assessment of whether to switch from the fast-response reconfigurable flight control law to the more reliable control surface/thrust integrated flight control law, ensuring stable flight is maintained when control surfaces are severely damaged.
Solution Approach 2:
The switching necessity judgment unit acts as an intermediary that evaluates flight safety requirements and determines when to transition between control laws. This intermediary component bridges the gap between the fast-response reconfigurable flight control law and the reliable control surface/thrust integrated flight control law, enabling appropriate switching to maintain both speed and stability.
3Reliability
If switching from the reconfigurable flight control law to the control surface/thrust integrated flight control law is performed too early, then stable flight is ensured, but flight control efficiency decreases due to slower response
Solution Approach 1:
The system performs preliminary assessment of flight safety requirements through the switching necessity judgment unit before deciding to switch control laws. This preliminary action ensures that switching to the control surface/thrust integrated flight control law occurs only when truly necessary, preventing premature switching that would reduce flight control efficiency while still ensuring stable flight capability when needed.
4Productivity
If switching from the reconfigurable flight control law to the control surface/thrust integrated flight control law is delayed, then flight control efficiency is maintained, but the aircraft may lose stable flight capability when control surfaces are severely damaged
Solution Approach 1:
The continuous feedback mechanism in the switching necessity judgment unit monitors control surface status and flight conditions, enabling timely detection of severe damage. This feedback ensures that switching to the control surface/thrust integrated flight control law occurs at the appropriate moment, maintaining flight control efficiency while preventing loss of stable flight capability when control surfaces are severely damaged.
Data Source
AI summary
A control system of an aircraft includes a computer that controls flight based on either a flight control law that controls flight by controlling the deflection angles of control surfaces or a control surface/thrust integrated flight control law that controls flight by controlling the deflection angles of the control surfaces and engine thrust, and a control surface failure/damage detection device. If malfunctioning of the control surface(s) is detected, the deflection angles and the rates of change of the deflection angles of the control surfaces are calculated based on the detection result, and the necessity of switching from the flight control law to the control surface/thrust integrated flight control law is judged by judging whether or not the calculated deflection angles or rates of change of the deflection angles exceed an acceptable range of change.