Flight Control Computer Quiet Climb Thrust Feedback
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current aircraft thrust control systems lack an intuitive and real-time feedback mechanism for flight crews during noise abatement procedures, particularly during takeoff and landing, which increases pilot workload and reduces safety.
Innovation Solution
The implementation of alphanumeric and graphical displays on a flight control computer that provide real-time information on automatically controlled engine thrust levels, allowing pilots to anticipate and manage engine thrust changes during quiet climb operations, with user-input parameters and graphical representations of flight paths.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If automatic thrust control is implemented during quiet climb, then flight crew workload is reduced, but real-time feedback and understanding of engine operation changes are insufficient
Solution Approach 1:
The patent implements a feedback mechanism by displaying actual engine thrust levels and quiet climb status to the flight crew in real-time. The system monitors the quiet climb phase and provides continuous information about thrust reduction status, allowing pilots to understand what the automated system is doing without manually monitoring engine parameters.
Solution Approach 2:
The flight management system acts as an intermediary between the automated thrust control system and the flight crew. It translates complex engine thrust data into simplified, intuitive displays that show the quiet climb phase status, current thrust level, and progression through the climb phase, making automated operations transparent to pilots.
2Loss of information
If manual thrust manipulation is used for noise abatement, then real-time control and understanding are maintained, but pilot attention and workload increase during critical phases
Solution Approach 1:
The system enables self-service by allowing the flight management computer to automatically manage thrust reduction and restoration during quiet climb without requiring continuous pilot intervention. The system independently monitors altitude, manages thrust transitions, and maintains compliance with noise abatement procedures, freeing pilots to focus on other critical flight parameters.
Solution Approach 2:
The system provides feedback to pilots about the automated thrust management status, showing when the aircraft is in quiet climb mode, current thrust levels, and progression through climb phases. This feedback loop maintains pilot situational awareness while eliminating the need for manual thrust manipulation.
3Reliability
If detailed thrust control information is provided to flight crew, then understanding and safety are improved, but interface complexity increases
Solution Approach 1:
The patent segments information presentation into distinct, manageable elements: quiet climb phase status (active/inactive), current thrust level indicators, altitude progression markers, and compliance status. This segmentation allows pilots to process information in discrete, understandable units rather than overwhelming them with raw engine data.
Solution Approach 2:
The interface provides localized, context-specific information about thrust control based on the current flight phase. During quiet climb, the system highlights relevant parameters (thrust reduction status, climb phase progression) while minimizing extraneous data, ensuring pilots receive appropriate information at the right time without interface clutter.
Data Source
AI summary
In accordance with an embodiment, a method includes displaying information corresponding to automatically controlled engine thrust levels during a reduced engine thrust period of flight of an aircraft. The information corresponds to one or more parameters associated with a flight control computer of the aircraft. In an alternate aspect, the displayed information includes alphanumeric information formatted in accordance with a sequential order of the automatically controlled engine thrust levels. In a further aspect, the alphanumeric information corresponds to first, second and third engine thrust levels.