Dynamic recurrent fuzzy neural network-based adaptive sliding control for longitudinal automatic carrier landing system

Design of Air-Wake Rejection Control for Longitudinal Automatic Carrier Landing Cyber-Physical System

Ship motion effects on landing impact loads V/STOL landing on aircraft carrier

The global maritime operating environment of U.S. Naval Aviation assets necessitates their prolonged exposure to severe corrosive environments. The resulting corrosion damage on flight critical structural components has a significant adverse impact on fleet readiness and total ownership costs. To address these issues, NAVAIR has initiated a multiyear research program to investigate and quantify the fatigue life reduction due to corrosion on high- strength steels, and to develop models and metrics to implement actionable maintenance criteria for corrosion damage. The service component selected for analysis and testing was the F/A-18C/D arresting shank (P/N 74A480617). Five arresting shanks that were rejected for depot-level rework due to excessive corrosion damage were shipped by the Boeing Co. in Mesa, Arizona, to NAVAIR for inspection. Of the five, three were selected for fatigue testing due to the severity of the corrosion present and their overall condition. The three arresting shanks that were tested all exhibited a significant degree of fatigue resistance to fleet induced corrosion damage. This would imply that improvements in service life intervals for arresting shanks may be possible if the corrosion-fatigue damage resistance can be adequately characterized. All three shanks that were tested exhibited critical fatigue failures due to fretting at the hook end. As a result, fretting fatigue should be considered the primary fatigue failure mode for service-damaged arresting shanks.

Analysis and Testing of Fleet Corroded F/A-18C/D Arrestment Shanks

When a carrier-based aircraft is in arrested landing on deck, the impact loads on landing gears and airframe are closely related to landing states. The distribution and extreme values of the landing loads obtained during life-cycle analysis provide an important basis for buffering parameter design and fatigue design. In this paper, the effect of the multivariate distribution was studied based on military standards and guides. By establishment of a virtual prototype, the extended Fourier amplitude sensitivity test (EFAST) method is applied on sensitivity analysis of landing variables. The results show that sinking speed and rolling angle are the main influencing factors on the landing gear’s course load and vertical load; sinking speed, rolling angle, and yawing angle are the main influencing factors on the landing gear’s lateral load; and sinking speed is the main influencing factor on the barycenter overload. The extreme values of loads show that the typical condition design in the structural strength analysis is safe. The maximum difference value of the vertical load of the main landing gear is 12.0%. This research may provide some reference for structure design of landing gears and compilation of load spectrum for carrier-based aircrafts.

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Mingbo Tong

Papers

Analysis of Global Sensitivity of Landing Variables on Landing Loads and Extreme Values of the Loads in Carrier-Based Aircrafts