Landing Gear Drive Control for Taxi Speed and Maneuverability
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Solution Overview
Problem
Current aircraft ground movement systems, which rely on main engine propulsion or tow vehicles, result in high fuel consumption and pilot discomfort due to unfamiliar control dynamics during taxiing and maneuvering.
Innovation Solution
A motorization system comprising electric motors connected to the aircraft's landing gear, controlled by an electronic unit and a pilot interface with adjustable speed controls, allowing for smooth and efficient ground movement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the main engine is used to move the aircraft on the ground, then the aircraft can move at high speed, but fuel consumption increases significantly
Solution Approach 1:
The patent divides the ground movement function into two distinct modes: high-speed taxiing using the main engine, and low-speed maneuvering using an auxiliary electric motor. This segmentation allows each subsystem to operate in its optimal performance range, with the electric motor handling energy-intensive low-speed operations and the main engine reserved for high-speed movement, thereby reducing overall fuel consumption.
Solution Approach 2:
The patent introduces an auxiliary electric motor as an intermediary device between the pilot's control inputs and the aircraft's ground movement. This electric motor serves as a mediator that handles the energy-demanding maneuvering tasks, allowing the main thermal engine to operate more efficiently or remain idle during low-speed operations, thus reducing fuel consumption while maintaining the capability for high-speed movement when needed.
2Use of energy by moving object
If an auxiliary electric motor is used for ground movement, then fuel consumption is reduced, but the pilot experiences discomfort due to unfamiliar control dynamics
Solution Approach 1:
The patent implements dynamic control characteristics that adapt to different flight phases. The electronic control unit modifies the relationship between pilot control inputs and motor response based on whether the aircraft is in taxiing or maneuvering mode. This dynamic adjustment ensures that the control system provides familiar and intuitive response characteristics to the pilot, maintaining ease of operation and comfort while utilizing the energy-efficient electric motor for ground movement.
3Productivity
If the control system provides high acceleration for quick movement, then productivity increases, but the aircraft becomes difficult to control during maneuvering
Solution Approach 1:
The patent employs dynamic control characteristics that automatically adjust acceleration and speed parameters based on the selected operational mode. In taxiing mode, the system permits higher acceleration for efficient ground movement, while in maneuvering mode, it limits acceleration and maximum speed to enable precise control. This dynamic adaptation allows the system to optimize productivity during transit while ensuring controllability during positioning operations.
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
The system enables aircraft to move on the ground with reduced fuel consumption and enhanced pilot comfort by allowing precise control of speed and maneuverability, improving overall ground handling efficiency.
Implementation Method 1
an electric motor (2) having an output shaft provided with means for its rotational connection to the wheels (W) of the front landing gear (L) to drive said wheels (W) in rotation
Data Source
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AI summary
The invention relates to a propulsion device (1) for moving an aircraft (A) on the ground having a landing device (L) comprising wheels (W), the propulsion device comprising at least one electric motor (2) having an output shaft provided with means for its rotational connection to at least one of the wheels (W) of the landing device to drive said wheel in rotation, and an electronic control unit (3) connected on the one hand to the motor to control it and on the other hand to a piloting interface (4) from which the pilot of the aircraft can emit control signals which the electronic control unit (3) is arranged to transform into motor piloting signals,characterized in that the control unit is arranged to implement a first control law having a specific dynamic to favor a certain aircraft speed and a second control law having a dynamic that favors aircraft maneuverability.