Aircraft Automatic Guidance Management During Engine Failure
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Solution Overview
Problem
During a complete engine failure in flight, aircraft autopilot and flight director systems face challenges in maintaining guidance, especially in altitude hold or climbing modes, due to insufficient engine thrust, requiring manual disconnection and potential loss of autothrottle control, which can be time-consuming and risky.
Innovation Solution
An automatic method and system that detects engine failure and adjusts the aircraft's guidance configuration to a compatible mode, disengages autothrottle, and manages the engagement and disengagement of autopilot and flight director systems to ensure stable and safe descent, while avoiding lower flight routes and terrain obstacles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the autopilot and flight director are used in altitude hold or climbing modes during complete engine failure, then guidance functionality is maintained, but insufficient engine thrust causes guidance failure and system incompatibility
Solution Approach 1:
The system performs preliminary detection of engine failure conditions and proactively switches guidance modes before the autopilot or flight director fails. The control system monitors engine parameters and, upon detecting complete failure, automatically transitions from incompatible modes (altitude hold, climbing) to compatible modes (descent with reduced thrust), preventing guidance failure rather than reacting after it occurs.
Solution Approach 2:
The guidance mode is made dynamic and adaptive based on engine thrust availability. The system continuously adjusts the operational state of guidance systems, switching between different mode configurations depending on whether engine thrust is sufficient or insufficient. This dynamic adaptation ensures that the autopilot and flight director operate only in modes compatible with current engine performance conditions.
2Reliability
If pilots manually disconnect autopilot and flight director during TEFO events, then incompatible guidance modes are avoided, but response time increases and pilot workload increases
Solution Approach 1:
The system performs self-diagnosis and self-correction by automatically detecting engine failure conditions and autonomously switching guidance modes without requiring pilot intervention. The control system monitors its own operational state and takes corrective action by disengaging incompatible guidance systems or transitioning to compatible modes, thereby serving itself and eliminating the need for manual pilot response.
Solution Approach 2:
The system implements continuous feedback monitoring of engine parameters and guidance system status. When engine failure is detected, the feedback loop triggers automatic mode switching logic that disengages incompatible guidance systems. This closed-loop control ensures that the guidance configuration continuously adapts to engine performance conditions, providing real-time compatibility assurance without pilot involvement.
3Ease of operation
If the autothrottle remains engaged during complete engine failure, then thrust control is maintained, but the system cannot manage failed engines and requires deactivation
Solution Approach 1:
The system extracts or separates the autothrottle function from the failed engine management system. Upon detecting complete engine failure, the control system automatically disengages the autothrottle from attempts to control failed engines, isolating the malfunctioning component while preserving the integrity of the overall control system. This extraction prevents the unreliable autothrottle from compromising further control functions.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
Enables immediate and automatic adaptation of the aircraft's guidance configuration during engine failure, reducing pilot workload and ensuring safe operation by maintaining reliable autopilot and flight director functionality, even in critical modes, and preventing collisions or terrain hazards.
Implementation Method 1
The aircraft is generally provided with a dynamic air turbine of the RAT type ('Ram Air Turbine'), making it possible to supply a certain amount of power to the control systems of the aircraft. It includes propellers deployed on the exterior of the fuselage, which are set in rotation under the effect of the displacement of the aircraft and drive the said turbine.
Data Source
AI summary
A method and system for managing automatic guidance of an aircraft during a complete engine failure. Said system includes means for monitoring engines so as to be able to detect a complete failure of the engines; means for detecting whether the aircraft is in flight; means for detecting whether the aircraft is in a different guidance mode from a guidance mode configured to make the aircraft descend with a reduced engine thrust and a fixed speed; and control means for automatically bringing guidance means of the aircraft into a guidance configuration compatible with the situation associated with the complete failure of the engines.