Dit is een Nederlandstalige bijdrage vanwege Ludo Poelaert, UGent.
In deze korte tekst wordt een inleiding tot de taal R gegeven.
U mag de tekst vrij gebruiken onder het Creative Commons CC BY 4.0 .
The CPU scheduling is the basis of multi-programming operating systems. By switching the
CPU among processes, the operating system can make the computer more productive. The
scheduler controls the way processes are managed in the operating system.
Linux supports preemptive multitasking, this means that the process scheduler decides which process
runs and when.
Balance performance across different computer configurations is one challenge in modern operating
systems.Linux has two separate process-scheduling algorithms.
If a Linux system performs similar tasks in a regular manner, it could be useful to implement
optimizations to the Linux scheduler to optimize the performance of those tasks.
In this project, we analyze and evaluate the impact of changing the kernel values on the performance
of the calculation of 8,765,4321 digits of pi using the Leibniz formula measuring the time that the
system takes to perform the calculation.
Constanza Madrigal Reyes and Ismael Lizárraga González
We study Logarithmically Spiral Trajectories and, in particular, we look for a solution to minimize the transit time of a Spacecraft propelled by a Solar Sail, while simultaneously minimizing the area of the Solar Sail, which would allow us to carry more payload on board. We start by analyzing the forces that act on the Spacecraft taking into account that its propellant is a Solar Sail; we use the studied forces to deduce the motion equations. We then solve this motion equation with a Runge-Kutta 4 method and transform the problem of minimizing time and area to a Non-linear Optimization problem. When solving the NLP we also try to minimize the relative final speed of th spacecraft with the destination planet in order to guarantee the possibility of a safe landing on its surface. The model improves when an angle parameter α (describing the angle formed by the Solar Sail with the colliding photons) is defined as a piecewise constant function and optimized whose values are optimized in every interval to minimize transit time and Area. Using the developed model to optimize the trajectory to be followed for sending from Earth to Mars a 2000kg-spacecraft propelled by a Solar Sail, subject to the condition that at trajectory start Mars and Earth were at their closest approach, and the Arrival Relative Velocity is less than 9km/s, give us a minimal transit time of 500days and a minimal area for the Solar Sail of 183158m2, meaning that the maximal payload would be 718kg. Compared with different number of partitions of α, the optimum stays stable. This gives a solid optimal trajectory and a great result for the numerical method used. Actually, waiting until the best moment to throw the Spacecraft, id est, Mars is at 1.14 radians respectively to Earth initial position, the minimal sail area 145950 m2 and, therefore, ables to transport until 978 kg of payload with the same transit time. In addition and to conclude we tried the model to optimize the inverse trajectory.
Marco Praderio Bova, Eneko Martin Martinez, & Maria dels Àngels Guinovart Llort
The contributions from conduction, convection, and radiation for an end-heated aluminum rod were quantified with experimental considerations in mind. Multiple experiments were carried out to ascertain various physical properties of the system and the aluminum rod. By applying heat-flow theory, simulations, and data-fitting techniques, the specific heat capacity, conductivity, emissivity, convective heat transfer coefficient of the system, and thermal contact resistance between the power source and aluminum rod were determined.