This paper presents experiences in using several model checking tools to verify properties of a critical real time embedded system. The tools we tested are Lesar, SMV, Prover Plug In for SCADE and Uppaal. The application is the landing gear control system of a military aircraft, developed by Dassault Aviation. The property to be verified states that the gear must be down in at most 14 seconds. ...

This paper contains numerical analysis of brake system for heavy (mass m=6400[kg]) transport car. Analysis was performed in order to correct existing non optimal brakes in mentioned car. Analysis was based on results of the brake system dynamic tests made in Landing Gear Laboratory Institute of Aviation in Warsaw, Poland. Authors describe analytical process which led to generate results for new...

Computational results for an 18%-scale, semi-span Gulfstream aircraft model are presented. Exa Corporation’s lattice Boltzmann PowerFLOW® solver was used to perform time-dependent simulations of the flow field associated with this high-fidelity aircraft model. The simulations were obtained for free-air at a Mach number of 0.2 with the flap deflected at 39o (landing configuration). We focused on...

The shimmy phenomenon is a self-excited limit cycle oscillation occurring in many physical rolling systems, particularly in aircraft nose landing gears (NLG). This paper presents a new active damping controller developed in the context of the European DRESS (“Distributed and Redundant Electro-mechanical nose gear Steering System”) project for avoiding the shimmy oscillation. The controller base...

In this paper, an active control structure used piezoelectric stack actuator is built to suppress vibration due to internal incentive in gear transmission. Because the gear system is timevariant and unknown, an offline modeling technique is unable to tracking the changes in the secondary path, an adaptive filter algorithm used online secondary path modeling method is proposed to the active vibr...