Automatic Landing Gear Bay Door Closing Under Takeoff Delay
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Solution Overview
Problem
The movement of landing gear and its bay door in aircraft during take-off causes drag and increases workload for pilots, particularly in situations like one engine inoperative (OEI), leading to delayed retraction and increased drag, which affects aircraft performance.
Innovation Solution
An aircraft system with a controller that automatically initiates the closing of the landing gear bay door based on predetermined criteria, such as in-flight status or delay in receiving a retraction command, to minimize drag and reduce pilot workload.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If the landing gear bay door is manually controlled by the pilot during take-off, then the pilot has full control over the retraction timing, but the workload increases and response time may be delayed in critical situations
Solution Approach 1:
The system enables self-service operation by automatically controlling the landing gear bay door retraction based on flight parameters. The controller monitors climb rate, altitude, and engine status, then autonomously initiates door closing without pilot intervention, reducing workload while ensuring timely execution
Solution Approach 2:
The system implements feedback control by continuously monitoring flight parameters (climb rate, altitude, engine status) and using this information to determine the optimal moment for door retraction. The controller adjusts the retraction timing based on real-time feedback from flight conditions
2Reliability
If the landing gear and bay door remain extended during take-off, then safety is maintained for ground operations, but aircraft drag increases and performance deteriorates
Solution Approach 1:
The system performs preliminary action by automatically initiating the bay door closing sequence based on predetermined flight criteria (climb rate threshold, altitude threshold). This ensures the door is retracted at the optimal time for performance while maintaining safety margins through conservative threshold settings
Solution Approach 2:
The system uses parameter changes in flight conditions (climb rate, altitude, engine status) as triggers for door retraction. When parameters indicate the aircraft has safely established climb, the system transitions the door from open to closed position, optimizing performance
3Productivity
If automatic door closing is initiated, then drag is reduced and performance improves, but the system complexity increases
Solution Approach 1:
The controller is designed with multi-functionality, serving both as the automatic door control system and as part of the existing flight management system. By reusing existing sensors and flight data infrastructure, the patent minimizes additional system complexity while achieving automatic door retraction functionality
Solution Approach 2:
The patent merges the automatic door control functionality with the existing flight management and engine control systems. The controller integrates door retraction logic with climb rate monitoring and engine status detection, combining multiple functions into a unified control architecture
4Reliability
If the bay door is opened early during take-off, then the landing gear can be retracted, but drag increases during the critical climb phase
Solution Approach 1:
The system implements dynamic control by adjusting the door retraction timing based on real-time flight conditions. Rather than using a fixed timeline, the controller continuously evaluates climb rate and altitude to determine the optimal retraction moment, adapting to varying take-off performance scenarios
Data Source
AI summary
An aircraft system for an aircraft is disclosed including a controller. The controller is configured, during a take-off procedure, to initiate automatic closing of a landing gear bay door of the aircraft from an open position towards a closed position, on the basis of a determination that a predetermined door-closing criterion has been met and a command to retract a landing gear has not been received, the landing gear being arranged to retract into a landing gear bay to be at least partially covered by the landing gear bay door when the landing gear bay door is in the closed position.