Aircraft Landing Gear Control System with Decoupled Door and Gear Actuation
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Solution Overview
Problem
Current aircraft landing gear control systems require pilots to manually initiate both landing gear retraction and extension during high-workload phases of flight, leading to potential delays and increased drag and noise, as well as risk of damage from extended gear exposure.
Innovation Solution
An aircraft control system with a user interface and landing gear controller that allows pilots to manually input separate requests for landing gear bay door and landing gear position changes, enabling earlier retraction after take-off and closer to landing, using sensors to determine aircraft status and unlock mechanical locks for controlled operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the landing gear is extended during flight, then the risk of gear damage increases, but the drag and noise increase as well
Solution Approach 1:
The system allows the landing gear bay door to be opened in advance of the actual gear retraction operation. The door can be opened when the aircraft reaches a predetermined altitude or speed threshold, creating a time buffer that allows the gear to be retracted earlier without increasing drag or noise exposure during flight.
2Object-generated harmful factors
If the landing gear is retracted earlier after take-off, then drag and noise are reduced, but the risk of gear damage from exposure increases
Solution Approach 1:
The landing gear bay door is opened before the gear is actually retracted. By decoupling these two operations and allowing the door to open at an earlier stage (based on altitude or speed thresholds), the system enables earlier gear retraction while maintaining protection against damage through controlled door timing.
Solution Approach 2:
The landing gear bay door acts as an intermediary protective element between the external environment and the landing gear. By controlling the door's opening and closing timing independently from the gear retraction operation, the door provides a protective barrier that allows earlier gear retraction without exposing the gear to damaging conditions.
3Device complexity
If a single user interface is used for both door and gear control, then device complexity is reduced, but the ease of operation during high-workload phases deteriorates
Solution Approach 1:
The control system segments the control functions for the landing gear bay door and the landing gear itself, allowing each to be controlled independently through the same physical interface. This segmentation enables clearer, more intuitive operation during high-workload phases by allowing pilots to focus on one operation at a time without confusion about which component is being controlled.
Data Source
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Figure 3(a)~4
AI summary
Disclosed is an aircraft control system (100) configured to be operably connected to at least one landing gear and at least one landing gear bay door of an aircraft (400). The system comprises: a user interface (10) operable by a user to manually input first and second requests; and a landing gear controller (20) communicatively coupled to the user interface. The controller is configured, in use, to: receive, from the user interface, a first indication indicative of user-operation of the user interface to input the first request, and to initiate movement of the landing gear bay door from a closed position to an open position on the basis of the first indication without initiating movement of the landing gear between an extended position and a retracted position; and receive, from the user interface, a second indication indicative of user-operation of the user interface to input the second request, and to initiate movement of the landing gear between the extended position and the retracted position on the basis of the second indication.