Aircraft Landing Gear Drive Control for Zero-Speed Braking
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Solution Overview
Problem
Current aircraft landing gear drive systems face challenges in maintaining control, particularly when moving forward at low speeds, uphill, or across slopes, leading to difficulties in parking and potential damage, and lack effective control over speed transitions from forward to zero speed.
Innovation Solution
A control system with a controller and control unit that provides torque commands and braking inputs to the landing gear drive system, allowing for smooth transitions from forward motion to zero speed, including regenerative braking, and offering additional power settings for enhanced maneuverability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If the controller provides zero forwards driving torque when moved to zero speed setting, then the aircraft can be stopped, but the aircraft cannot maintain zero speed on slopes
Solution Approach 1:
The control unit acts as an intermediary between the controller setting and the drive system, automatically selecting between torque provision and braking application based on the current situation. When the controller is in zero speed setting, the control unit determines whether to provide zero torque or apply braking torque based on whether the aircraft is moving, ensuring reliable speed maintenance without requiring the pilot to understand multiple operating modes.
2Force
If the drive system provides maximum forwards torque, then the aircraft can move up hill, but the system cannot control low speed forward motion
Solution Approach 1:
The control system dynamically adjusts its behavior based on the controller setting and aircraft speed. In forward motion settings, the system provides torque proportional to the controller position for power. When the controller is moved to zero speed setting, the system automatically transitions to providing zero torque and applying braking, enabling precise low-speed control and stopping without requiring the pilot to manually modulate torque.
3Device complexity
If the zero setting provides zero torque, then the drive system is simple, but the aircraft cannot slow down to zero speed from forward motion
Solution Approach 1:
The control unit automatically determines when braking is needed based on the controller setting and current aircraft speed, without requiring pilot intervention. When the controller is in zero speed setting and the aircraft is moving, the control unit automatically applies braking torque to slow the aircraft to zero speed, making the system self-regulating and eliminating the need for complex pilot maneuvers.
4Power
If the drive system is oversized to handle hill climbing, then the aircraft can move effectively uphill, but the system cannot provide precise low speed control
Solution Approach 1:
The control system segments the operating modes into distinct settings: forward motion settings for power delivery and zero speed setting for stopping. This segmentation allows the drive system to be optimized for high power output while the control logic handles low-speed precision through automatic braking intervention, eliminating the need for an oversized drive system with reduced low-speed control capability.
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 controlled speed management from forward to zero speed, reducing the risk of damage and improving parking precision, while providing additional power for challenging terrain, ensuring smooth and efficient aircraft movement.
Implementation Method 1
a speed sensor for sensing an aircraft taxi speed and for providing an indication of the aircraft taxi speed to the control unit
Implementation Method 2
the control unit provides a braking command to apply a braking torque to the wheel to slow rotation of the wheel while the aircraft taxi speed is above zero
Data Source
Figure 1~2a
Figure 2b~3
Figure 4~5
AI summary
The invention provides a control system 200 for controlling a landing gear drive system 72 for driving rotation of an aircraft wheel, comprising a control panel 40 with a controller 20 having a forward motion setting 23, 28, 24 30 and a zero speed setting 27, a control unit 60 for receiving a control input 41 from the controller, and for providing a torque command 71, 81 to be applied to the wheel, and a speed sensor 50 for sensing an aircraft taxi speed and for providing an indication of the aircraft taxi speed 51 to the control unit, wherein, when the controller is moved from the forward motion setting to the zero speed setting, the control unit provides a torque command 71 to the drive system to provide zero forwards driving torque to the wheel, and a braking command 81 to apply a braking torque to the wheel. The invention provides other control systems, an aircraft, methods of controlling an aircraft landing gear drive system and a control panel.