Aircraft Door Support Assembly With Integrated Weight Compensation
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Solution Overview
Problem
Existing aircraft door assemblies lack efficient mechanisms for guiding and supporting door movements, including opening and closing, weight compensation, and emergency evacuation assistance, often requiring multiple components that complicate the system.
Innovation Solution
A support assembly for aircraft doors incorporating a forearm, links, weight compensation springs, and an emergency puller assist system (EPAS) actuator, which integrates door hinge rotation, lifting, and weight compensation functions into a single component, reducing the need for separate mechanical fittings and mechanisms.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If conventional mechanical components are used for door support, then structural simplicity is maintained, but weight compensation and operational smoothness deteriorate
Solution Approach 1:
The patent employs weight compensation springs that act as counterweights to balance the door's weight during opening and closing operations. The springs are configured to provide upward force that compensates for the gravitational force on the door, enabling smooth operation without requiring excessive actuation force and reducing the workload on the emergency puller assist system.
Solution Approach 2:
The support assembly is divided into distinct functional segments: a forearm component for primary support, link components for motion transmission, and weight compensation springs for weight balancing. This segmentation allows each component to be optimized for its specific function while working together to achieve smooth door operation.
2Reliability
If multiple links and springs are added for weight compensation, then door support performance improves, but device complexity increases
Solution Approach 1:
The forearm and link components serve multiple functions: they provide structural support, transmit motion between the door and actuation system, and work in conjunction with the springs to achieve weight compensation. This multi-functionality reduces the need for separate dedicated components for each function, thereby improving reliability without proportionally increasing complexity.
Solution Approach 2:
The patent combines the support function and weight compensation function into an integrated assembly where the forearm, links, and springs work as a unified mechanism. Rather than having separate support structures and separate weight compensation mechanisms, these functions are merged into a single coordinated system that improves reliability through functional integration.
3Productivity
If emergency puller assist system is integrated, then evacuation speed improves, but manufacturing complexity increases
Solution Approach 1:
The emergency puller assist system is integrated through the existing forearm and link mechanisms, which act as intermediaries between the actuation force and the door. This allows the EPAS to leverage the mechanical advantage already provided by the support assembly structure, enabling rapid door opening without requiring a completely separate actuation system and simplifying manufacturing.
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 integrated support assembly facilitates smooth door movement, weight compensation, and emergency evacuation by simplifying the door assembly, reducing complexity and enhancing operational efficiency.
Implementation Method 1
The support assembly may include at least one weight compensation spring. The at least one weight compensation spring may extend between and to a lower spring end and an upper spring end.
Implementation Method 2
The at least one spring may be configured to bias the door in the raised position
Implementation Method 3
The forearm is rotatably mounted to the door hinge along a first rotational axis. The at least one link is rotatably mounted to the forearm at the inner end. The at least one link is rotatable relative to the forearm about a second rotational axis.
Data Source
AI summary
A door assembly for an aircraft includes a door, a door hinge, and a support assembly rotatably mounting the door hinge to the door. The support assembly includes a forearm and at least one link. The forearm is rotatably mounted to the door hinge along a first rotational axis. The forearm extends along the first rotational axis between and to an upper end and a lower end. The at least one link extends between and to an inner end and an outer end. The at least one link is rotatably mounted to the forearm at the inner end. The at least one link is rotatable relative to the forearm about a second rotational axis. The at least one link is rotatably mounted to the door at the outer end. The at least one link is rotatable about the second rotational axis between and to a lowered position of the door and a raised position of the door.