Aircraft Arresting Hook Vertical Damper Actuator
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Solution Overview
Problem
Conventional arresting hook systems for aircraft, particularly those used on short runways like aircraft carriers, face challenges with large moment forces due to offset pivot axes, leading to increased system weight and complexity, and lack efficient damping mechanisms for arrestment loads.
Innovation Solution
The proposed arresting hook system incorporates a trapeze deployment assembly and a hook deployment assembly with a vertical damper actuator, decoupling the VDA from the trapeze assembly and mounting it via a trunnion, which reduces weight and complexity while improving damping kinematics and cable engagement performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of operation
If conventional arresting hook systems use offset pivot axes to enable deployment, then the hook can be positioned for cable engagement, but large moment forces are generated increasing system weight and complexity
Solution Approach 1:
The patent extracts the damping function from the traditional trapeze assembly and places it in a separate vertical damper actuator (VDA) that is pivotally coupled to the aircraft structure. This separation removes the harmful moment forces from the trapeze assembly, reducing its weight and complexity while maintaining hook deployment capability.
Solution Approach 2:
The arresting hook system is divided into distinct functional segments: the trapeze deployment assembly for positioning, the hook deployment assembly for cable engagement, and the vertical damper actuator for damping arrestment loads. This segmentation allows each component to be optimized independently, reducing overall system complexity.
2Reliability
If the vertical damper actuator is integrated with the trapeze assembly, then damping function is provided, but system weight and complexity increase
Solution Approach 1:
The damping function is extracted from the trapeze assembly and implemented in a separate vertical damper actuator that is pivotally coupled to the aircraft structure. This extraction maintains the damping reliability while reducing the weight and complexity of the trapeze assembly by removing the integrated damper mechanism.
3Shape
If the arresting hook system is stowed within the outer mold line, then aerodynamic profile is maintained, but deployment mechanism becomes more complex
Solution Approach 1:
The arresting hook system is designed to nest within the aircraft's outer mold line when in the stowed position. The trapeze deployment assembly and hook deployment assembly are arranged to fit within the available space, maintaining the aerodynamic profile while enabling deployment through the defined mechanism.
4Ease of operation
If offset pivot axes are used for hook deployment, then cable engagement is achieved, but large moment forces are generated
Solution Approach 1:
The vertical damper actuator is extracted from the trapeze assembly and pivotally coupled to the aircraft structure, separating the damping function from the deployment mechanism. This reduces the moment forces on the trapeze assembly while maintaining cable engagement capability through the hook deployment assembly.
Solution Approach 2:
The vertical damper actuator serves as an intermediary between the aircraft structure and the hook deployment assembly, absorbing moment forces through its damping mechanism while allowing the trapeze assembly to perform its positioning function with reduced load.
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
This design reduces the system's weight and complexity, enhances damping efficiency, and improves cable engagement performance, allowing for effective deceleration of aircraft on short runways with reduced moment forces and increased design flexibility.
Implementation Method 1
The VDA is to dampen arrestment loads when the hook deployment assembly is in the deployed position
Data Source
AI summary
Methods, apparatus, systems, and articles of manufacture are disclosed. An example arresting hook system for an aircraft includes a linkage assembly defining a trapeze deployment assembly of the arresting hook system, a pivot assembly to pivotally couple a hook shank to a primary pivot joint of an aft body, a vertical actuator coupled to a forward body and a frame of the aircraft to move the arresting hook system between a stowed position and an intermediate position, and a vertical damper actuator (VDA) including a cylinder and a piston. The cylinder pivotally coupled to the frame of the aircraft via a VDA pivot joint, the VDA to rotate relative to the frame of the aircraft, the piston having an end operatively coupled to the pivot assembly, the VDA to move the arresting hook system between the intermediate position and a deployed position.