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Projecte llegit

Títol: Cálculo de la trayectoria para un orbitador lunar


Director/a: CASTAN PONZ, JOSÉ ANTONIO

Departament: DEGD

Títol: Cálculo de la trayectoria para un orbitador lunar

Data inici oferta: 16-02-2021     Data finalització oferta: 16-10-2021



Estudis d'assignació del projecte:
    GR ENG SIS TELECOMUN
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Paraules clau:
Trayectoria, Orbitador, Lunar
 
Descripció del contingut i pla d'activitats:
Aspectos a tratar: Órbitas, problema de los dos cuerpos,
maniobras orbitales, sistemas de empuje
 
Overview (resum en anglès):
In this work, the idea promoted by NASA to put a space station around the Moon has been studied. To be able to do this, first its make a review of Kepler¿s laws and of the classical mechanics defined by Newton on gravitational attraction. Later, the different mechanisms to perform orbital maneuvers have been investigated, both between two coplanar orbits and for orbits with different inclination. For coplanar orbits, the Hohmann transfer orbit has been analyzed, which presents the best option energetically, also it is analyzed more direct transfers such as parabolic and hyperbolic. It was studied also the rocket¿s equation developed by Tsiolkovski and how affects the burning of fuel in the generation of thrust.

With all this in mind, we have developed some calculations of which is the best way for NASA¿s platform to go to its correct positioning on the Moon. By Hohmann¿s method, two paths have been seen depending on the engine chosen; With a liquid fuel engine you can reach the Moon with a fuel consumption of 8 tons after 3 days, and with an electric engine, on the other hand, you need more than 50 days to accelerate and be able to achieve your optimal speed, but the good thing is that its fuel consumption is around 680 kg of xenon.

The parabolic orbit presents a good alternative if you want to carry a manned mission, with a consumption of 8.68 tons you can reach the Moon in 38 hours. Hyperbolic is a too expensive option that would only be considered if the mission could require a lot of haste in its development.

As for positioning, NASA¿s proposal has been seen and it has been studied the optimal path to adjust the orbit in its right place. For doing that it was analyzed a transfer with two ignitions, 89º and 1º respectively. Then, it will need a third ignition in order to define the orbit as the high elliptical it was planned. Both shape and orientation of this platform is guided by the idea of maintaining good communications with the Earth and with a future base located on the surface of the Moon.

For the orbit maintenance it has been studied an experiment done in Monte Carlo. The objective was to predict the perturbations the platform will suffer during a life period of 15 years. It has been analyzed following two algorithms and in which point of the orbit it may take place the ignitions.


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