Breakover Rotorcraft Seat Frame for Emergency Pilot Extraction
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Solution Overview
Problem
In helicopters or rotorcraft, damaged side doors can prevent the removal of an injured or disabled pilot, necessitating alternative access methods.
Innovation Solution
A convertible seat frame structure with fixed and pivoting frame members connected by a bushing assembly, allowing the seat to transition from a default fixed configuration to a breakover configuration where the pivoting frame members can rotate rearward, enabling pilot removal through the cockpit rear.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If the seat frame structure is fixed in the default configuration, then the structural stability and ease of operation are improved, but the adaptability in emergency situations deteriorates
Solution Approach 1:
The seat frame structure incorporates pivoting frame members that can rotate between a default configuration (providing stability) and a breakover configuration (providing adaptability for emergency removal). The coupling pin assembly allows controlled transition between these states, enabling the structure to adapt to different operational requirements while maintaining structural integrity in each state.
2Adaptability or versatility
If the coupling pin assembly is made retractable to enable breakover configuration, then the adaptability is improved, but the device complexity increases
Solution Approach 1:
The coupling pin assembly utilizes spring-loaded mechanisms that automatically extend or retract based on the position of the control lever. The springs provide the necessary force to move the coupling pins without requiring additional actuators or complex control systems, thereby enabling breakover capability while minimizing device complexity.
3Ease of operation
If the pivoting frame members are allowed to rotate freely for breakover, then the ease of operation in emergencies is improved, but the reliability under normal conditions deteriorates
Solution Approach 1:
The coupling pin assembly is designed to preemptively prevent unintended rotation of the pivoting frame members by extending the coupling pins into the fixed frame members under normal conditions. This preliminary locking action ensures the seat remains securely fixed during routine operations, while allowing controlled rotation when the control lever is deliberately actuated to retract the coupling pins.
Data Source
AI summary
A seat frame structure for a rotorcraft or other vehicle operator seat is convertible between non-breakover and breakover configurations. The structure includes fixed frame members mounted to the cabin floor (e.g., via floor tracks) and pivoting frame members for supporting the operator seat, the pivoting and fixed frame members connected by a bushing assembly. The seat frame structure includes a tilt controller with coupling pins extending into the fixed frame members, locking the structure into the non-breakover configuration. A control lever mounted to the seat frame structure controls the coupling pins via connecting cables; the occupant of the seat may, via the control lever, transition the seat frame structure to the breakover configuration by retracting the coupling pins into the pivoting frame members, enabling rearward rotation of the pivoting frame members (e.g., at least 80 degrees, or contact with the cabin floor).