Aircraft Launch Bar Damping for Catapult Load Reduction
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Solution Overview
Problem
Aircraft catapult systems generate significant loads during launch, which can lead to premature wear and increased maintenance costs for aircraft components.
Innovation Solution
Incorporating a damper, such as a linear damper or torsion springs, into the launch bar or drag brace of the aircraft to reduce the forces applied during launch.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Length of moving object
If a catapult system is used to launch aircraft in limited area, then takeoff distance is reduced, but loads applied to aircraft components increase causing premature wear
Solution Approach 1:
A damper is integrated into the launch bar to provide beforehand cushioning against the high loads generated during catapult launch. The damper is positioned to absorb and dissipate shock loads before they can cause premature wear to aircraft components, thereby resolving the contradiction between achieving short takeoff distance and preventing component wear.
2Reliability
If damper is added to launch bar, then component wear is reduced, but device complexity increases
Solution Approach 1:
The damper is merged with the existing launch bar structure, integrating the load-reducing function into the already-complex catapult system rather than adding a completely separate component. This merging approach reduces component wear while minimizing the increase in overall device complexity.
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 damper effectively reduces the loads applied to the aircraft during launch, minimizing wear on components and lowering maintenance costs, while also allowing for the use of lighter and less expensive materials.
Implementation Method 1
a damper operatively coupled between the first and second portions, the damper to reduce forces applied to the launch bar at the first and second portions when the aircraft is launched by the aircraft catapult
Data Source
AI summary
Methods, systems, apparatus, and articles of manufacture to damp catapult loads on an aircraft are disclosed. An example apparatus disclosed herein includes a launch bar including a first portion and a second portion, the first portion to be releasably coupled to an aircraft catapult, the second portion to be releasably coupled to an aircraft catapult system, and a damper operatively coupled between the first and second portions, the damper to reduce longitudinal forces applied to the launch bar at the first and second portions when the aircraft is launched by the aircraft catapult.