Universal Aircraft Controller with Auto-Identifying Program Selection
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Solution Overview
Problem
Aircraft control systems require multiple unique controllers for different aircraft assemblies, leading to complexity and increased costs for operators and manufacturers.
Innovation Solution
A controller unit with a processor and computer-readable medium that identifies and selects the appropriate program code to control various aircraft assemblies by connecting to different controller slots in an electronics bay, allowing a single controller to manage multiple types of assemblies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple unique controllers are used for different aircraft assemblies, then each assembly can be controlled with a specialized controller, but the overall system complexity and cost increase
Solution Approach 1:
The controller unit is designed with a universal interface that can connect to multiple different aircraft assemblies (landing gear, brakes, steering, etc.). The controller contains multiple program codes corresponding to different assemblies, allowing a single controller to perform multiple specialized functions that previously required separate dedicated controllers for each assembly type.
Solution Approach 2:
The controller dynamically changes its operational parameters by selecting different program codes based on which aircraft assembly is connected. The processor identifies the connected assembly and loads the appropriate program code, allowing the same hardware controller to adapt its control behavior to match the specific requirements of each different assembly type.
2Adaptability or versatility
If multiple unique controllers are used for different aircraft assemblies, then each assembly has dedicated control capability, but maintenance and operational costs increase
Solution Approach 1:
The controller unit is designed with a universal interface that can connect to multiple different aircraft assemblies (landing gear, brakes, steering, etc.). The controller contains multiple program codes corresponding to different assemblies, allowing a single controller to perform multiple specialized functions that previously required separate dedicated controllers for each assembly type.
Solution Approach 2:
Instead of manufacturing multiple physical controllers, the invention uses software copying - the same hardware controller is used repeatedly with different program codes loaded into its memory. Each program code is a digital copy of control logic that can be stored and executed on the same physical controller, eliminating the need to manufacture multiple identical hardware units.
3Device complexity
If a single controller is used for multiple aircraft assemblies, then the number of controllers is reduced, but the controller must identify and select the correct program code for each assembly
Solution Approach 1:
The controller implements an identification system that detects which aircraft assembly is connected to the controller slot. The processor receives feedback signals from the connected assembly and uses this information to automatically select and load the appropriate program code from its stored memory, ensuring the correct control logic is applied without manual intervention.
Solution Approach 2:
The controller automatically performs the identification and program code selection process without requiring external assistance. When an aircraft assembly is connected, the controller self-identifies the assembly type through its detection system, automatically retrieves the corresponding program code from its stored memory, and configures itself to control that specific assembly, eliminating the need for manual setup or expert intervention.
Data Source
Figure 1A
Figure 1B~2
Figure 3
AI summary
A controller unit (100) for an aircraft control system includes an interface (105) that is electrically connectable to a controller slot of an electronics bay (420) of the aircraft control system, a processor (106) coupled to the interface, and a tangible non-transitory computer-readable medium (110) having instructions stored thereon that, in response to execution by the processor, cause the processor to perform various operations. The various operations include identifying, by the processor, a first aircraft assembly in electrical communication with the controller slot of the electronics bay, identifying, by the processor, a first program code stored on the tangible non-transitory computer-readable medium corresponding to the first aircraft assembly, and selecting, by the processor, the first program code to control the first aircraft assembly.