Electrically Activated Landing Gear Control System
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Conventional mechanically driven aircraft landing gear systems are heavy due to numerous mechanical components and hydraulic tubing, which increases weight and reduces efficiency.
Innovation Solution
An electrically activated landing gear control system with a processing module, proximity sensors, and electrically activated valves, utilizing a high integrity, modular control architecture to minimize mechanical components and optimize sequencing, featuring a dual channel architecture for high availability and dispatchability.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mechanically driven landing gear systems are used, then reliable control of landing gear extension and retraction is achieved, but aircraft weight increases significantly due to numerous valves and hydraulic tubing
Solution Approach 1:
The patent replaces the conventional mechanical/hydraulic control system with an electrically activated system. Electrically activated valves replace traditional hydraulic valves, and electrical signaling replaces mechanical linkages and hydraulic tubing. This substitution dramatically reduces the number of mechanical components and hydraulic tubing required, thereby reducing aircraft weight while maintaining reliable control of landing gear extension and retraction through electrical actuation.
Solution Approach 2:
The patent extracts and eliminates unnecessary mechanical components from the landing gear control system. By removing numerous valves and extensive hydraulic tubing in favor of electrically activated valves and electrical signaling, the system achieves weight reduction while preserving the essential function of controlling landing gear extension and retraction.
2Ease of operation
If numerous valves and hydraulic tubing are used, then complete control of all landing gear components is achieved, but device complexity increases
Solution Approach 1:
The patent substitutes electrical control mechanisms for mechanical control components. Electrically activated valves with electrical solenoids replace traditional hydraulic valves controlled by mechanical linkages. This substitution reduces device complexity by eliminating numerous mechanical components while maintaining complete control capability over all landing gear components through electrical signaling and control logic.
Solution Approach 2:
The electrically activated valves serve multiple functions that previously required separate mechanical components. A single electrically activated valve can control multiple aspects of landing gear operation through electrical control signals, reducing the overall number of components needed while maintaining comprehensive 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
The system reduces aircraft weight by minimizing mechanical components, improves landing gear sequencing, and enhances system performance, dispatchability, and availability through electronic control of valves.
Implementation Method 1
The command signals may be sent to remote power distribution units and data concentrator units to energize or de-energize solenoid coils of the electrically activated valves
Data Source
Figure 1
AI summary
An electrically activated landing gear control system is provided. A processing module of landing gear control system is provided with landing gear control system software that receives data relating to the position of a landing gear lever. Proximity sensors positioned at landing gear and wheel well areas of the aircraft are coupled for communication with the processing module. The proximity sensors provide the landing gear control system software with position data relating to the landing gear. The landing gear control software converts the data received from the landing gear lever and the data received from the proximity sensors to command signals to control electrically activated valves associated with landing gear components. The command signals may be sent simultaneously to remote power distribution units and remote data concentrator units to energize or de-energize solenoid coils of the electrically activated valves.