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Konstruktion av en enkel flygplanssimulator

A simple flight simulator has been built up, using an analog computer to simulate the aircraft dynamics. The dynamics model used, does not represent any particular aircraft. It is nevertheless representative of a large group of conventional aircraft. Simulations clearly show an increased ease in handling the flight simulator, if the pilot has flying experience. This indicates a similarity between

Simulering av styrsystem för tankfartyg

The main purpose of this investigation was to compare, by simulations, the ability of an adaptive regulator and a PID-regulator to keep a ship on desired course with small rudder deflections. Manual steering in confined waters of the simulated ship was also performed. Recordings of delivery tests from real ships were compared to simulations. The non-linear mathematical model of the ship, which was

Duala regulatorer

Our task has been to compare the ability of three different regulators to control some single-input single-output systems with unknown parameters. The regulators were a minimal variance regulator, the Self-TUning REgulator STURE and an active suboptimally dual regulator. No simulations with the minimal variance regulator are shown since it turned out that it performs as STURE on systems with const

A nonlinear dynamical model and control of the feed water system on a turbine tanker

In this report we present a non-linear mathematical model of the feed water system onboard a 250 000 ton dwt turbine tanker in the Kockum Hull 540-series (Esso Dalriada). Well-known relations from the theory of fluid mechanics give the main part of the model. A few equations are approximations of the manufacturer's data curves. The most important dynamical equations embrace acceleration of the

Undersökning av regulatorer for normalaccelerationen hos ett flygplan

This work is dealing with airplane control. The work is based on the JACC conference from 1970, where the time domain specifications on the step response of the normal acceleration n^z (perpendicular to the longitudinal direction of the airplane) and its derivative are given, so that all step responses shall entirely lie within the specifications with a probability of at least 85%. The system is