Landing Gear Wheel Motor Control for Taxiing and Tight Maneuvering
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Solution Overview
Problem
Aircrafts have high fuel consumption during ground movements due to reliance on main engines for taxiing and maneuvering, and existing electric motor systems disrupt pilot habits, making control uncomfortable.
Innovation Solution
A motorizing device with an electric motor connected to the landing gear wheels and an electronic control unit that transforms pilot control signals into motor control signals, implementing control laws for speed and maneuverability, allowing smooth control of aircraft movements along straight and curved paths.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the main engine is used for ground movements (taxiing and maneuvering), then the aircraft can move on the ground, but fuel consumption increases significantly
Solution Approach 1:
The patent divides the control system into two distinct control laws: a first control law for taxiing operations and a second control law for maneuvering operations. This segmentation allows the system to optimize control characteristics for each specific ground operation, reducing overall energy consumption while maintaining pilot comfort through operation-specific control strategies
Solution Approach 2:
The patent implements dynamic control by switching between different control laws based on the operational phase (taxiing vs. maneuvering). The electronic control unit dynamically adjusts control parameters and characteristics to match the current ground operation, enabling energy-efficient operation while adapting to varying pilot comfort requirements across different operational contexts
2Ease of operation
If a single control law is used for all ground movements, then the control system is simple, but the pilot experiences discomfort due to broken habits
Solution Approach 1:
The electronic control unit dynamically selects and applies different control laws based on the current operational mode detected from control interface signals. This dynamic adaptation allows the system to provide pilot-familiar control characteristics for each operation type without requiring permanent structural complexity, as the system adapts its behavior rather than its physical structure
Solution Approach 2:
The patent changes control parameters and characteristics based on the operational phase. The first control law uses parameters optimized for taxiing stability, while the second control law uses parameters optimized for maneuvering precision. This parameter adaptation maintains pilot comfort across different operations without requiring fundamentally different hardware systems
3Productivity
If high speed is used for straight movements, then taxiing efficiency increases, but control precision for maneuvering decreases
Solution Approach 1:
The patent segments the ground operation into taxiing phase and maneuvering phase, applying different control strategies to each. During taxiing, the first control law prioritizes speed and efficiency for straight-line movements. During maneuvering, the second control law prioritizes precision and control for curved trajectories, thus resolving the conflict between speed and precision through operational segmentation
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 efficient control of aircraft speed and maneuverability on the ground, reducing fuel consumption and enhancing pilot comfort by optimizing movement dynamics based on aircraft center of gravity and landing gear track.
Implementation Method 1
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 (L) to drive said rotating wheel
Implementation Method 2
an electronic control unit (3) connected on the one hand to the motor (2) to control it and on the other hand to a control interface (4) from which the pilot of the aircraft can transmit control signals which the electronic control unit (3) is arranged to transform into motor control signals
Data Source
AI summary
The invention relates to a motorizing device (1) for moving an aircraft (A) provided with a landing device (L) having wheels (W) on the ground, the motorizing 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 for driving 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 control interface (4) from which the aircraft pilot can transmit control signals which the electronic control unit (3) is arranged to transform into motor control signals, characterized in that the control unit is arranged to implement a first control law having determined dynamics to promote an aircraft movement speed and a second control law having dynamics to promote aircraft manoeuvrability.