Aircraft Tail Electrical Interlock System
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Solution Overview
Problem
Existing systems for the tail section of large cargo transport aircraft face challenges such as difficulty in opening and closing under windy conditions, potential for unlatching during flight, costly and time-consuming manual inspections, and risk of over-rotation, which can lead to damage and accidents.
Innovation Solution
An electrical interlock and indication system that prevents operation of the latch/lock actuation system without a tail support, inhibits over-rotation, and detects latch pin retraction failures, using a tail support that communicates with the latching and locking functions to reduce deflection loads and ensure safe operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If a caster-type strut is used to support the tail section, then the tail section can be supported during loading and unloading, but the strut provides minimal ability to hold the tail section open and has limited or no braking capability under windy conditions
Solution Approach 1:
The patent replaces the purely mechanical caster-type strut with an electrical interlock system that uses electrical signals to control latch pin actuation. The system uses a tail support device with electrical controls to prevent unintended unlatching and to provide controlled opening/closing operations, substituting mechanical passive support with active electrical-controlled mechanical support.
Solution Approach 2:
The patent implements feedback control through the electrical interlock system that monitors tail section position and support device status. The system uses sensors and electrical signals to provide feedback about the tail section state, enabling controlled operation and preventing over-rotation or unintended opening under various conditions including windy conditions.
2Adaptability or versatility
If latches are arranged to allow in-flight deflections to cause unlatching, then the tail section can accommodate flight movements, but unexpected unlatching can cause catastrophic accidents during flight
Solution Approach 1:
The patent replaces the passive mechanical latch arrangement with an electrical interlock system that actively controls latch pin actuation. The electrical system prevents unintended unlatching by requiring specific conditions to be met before allowing latch release, while still allowing controlled opening during ground operations. This substitution eliminates the harmful effect of in-flight deflection-induced unlatching while maintaining operational flexibility.
Solution Approach 2:
The patent applies preliminary anti-action by using the electrical interlock system to prevent unintended unlatching before it can occur. The system proactively blocks the latch release mechanism under flight conditions, counteracting the potential harmful effect of deflection forces that could cause accidental unlatching. The electrical control acts in advance to prevent the harmful action rather than reacting after damage occurs.
3Ease of manufacture
If manual visual inspection is used to detect faults in latch pins and hinges, then the inspection can be performed with simple equipment, but the inspection is time consuming and may involve hours or days of time
Solution Approach 1:
The patent replaces manual visual inspection with an electrical interlock system that includes sensors and monitoring capabilities. The system automatically detects the status of latch pins, hinges, and other tail section components through electrical signals and sensor feedback, eliminating the need for time-consuming manual inspections. The electrical system provides continuous monitoring and can detect faults without requiring physical access to difficult-to-reach components.
Solution Approach 2:
The patent implements self-service inspection through the electrical interlock system that automatically monitors and detects faults in tail section components. The system performs its own inspection function through integrated sensors and monitoring circuits that continuously check the status of latches, hinges, and support structures, eliminating the need for external manual inspection operations and reducing maintenance time significantly.
4Adaptability or versatility
If the tail section is totally disconnected from the fuselage and placed on a cart, then the tail section can be moved independently, but the system is time consuming and requires special equipment to hold the tail section
Solution Approach 1:
The patent makes the tail support device universal by integrating multiple functions into a single system. The electrical interlock system provides both the support function and the control function, allowing the same device to support the tail section during loading/unloading and to control its opening/closing operations. This eliminates the need for separate special equipment and reduces overall system complexity while maintaining mobility and operational flexibility.
Data Source
AI summary
An electrical interlock and indication system for use with an aircraft having a hinged tail section is provided. The interlock and indication system prevents operation of a latch/lock actuation system of the hinged tail section unless a tail support is engaged to the tail section, inhibits over rotation of the hinged tail section, and detects retraction failures of latch pins located in the hinged tail section.