Study of Earth-to-Jupiter transfers with gravity assist at Mars using the C3 matching technique
Visualitza/Obre
REPORT_211.pdf (3,732Mb) (Accés restringit)
BUDGET_223.pdf (637,4Kb) (Accés restringit)
ANNEX_144.pdf (1,423Mb) (Accés restringit)
Estadístiques de LA Referencia / Recolecta
Inclou dades d'ús des de 2022
Cita com:
hdl:2117/188188
Tipus de documentTreball Final de Grau
Data2016-06-22
Condicions d'accésAccés restringit per decisió de l'autor
Tots els drets reservats. Aquesta obra està protegida pels drets de propietat intel·lectual i
industrial corresponents. Sense perjudici de les exempcions legals existents, queda prohibida la seva
reproducció, distribució, comunicació pública o transformació sense l'autorització del titular dels drets
Abstract
Space exploration arouses a great interest in the scientific community and, each time, it is intended to deal with more complex and ambitious missions. Nowadays, the computing power allows modelling accurate force fields and improving the design of interplanetary trajectories. In the pursuit of the reduction of mission costs, gravity-assisted trajectories have been extensively used in recent years. This work was aimed to study the C3matching technique and it was applied to a concrete case: Earth-to-Jupiter trajectories using Mars as a flyby body. There is no literature about this possibility so it was worth investigating it.The simplified method of patching conicsand the two-body model were used and it was studied the application of small impulses at the limits of the sphere of influence of Mars in order to connect the trajectory from Earth to Mars with the transfer from Mars to Jupiter. Some tolerances were set about the minimum acceptable distance between the two trajectories and about the minimum acceptable error between the time of flight computed and that predicted at the beginning. Results under these tolerances were found and the technique was validated. However, a high impulse was required at the closest point to Mars so it was thought to apply deep space maneuvers to enter at a different point of the sphere of influence, in order to achieve an unpowered passage at Mars. Since the latest was out of scope, it was set as future lines of this work
Descripció
The objective of the proposed work is the investigation of a technique called "C3 matching" due to Williams (1990) and Longuski & Williams (1991) and implemented for the first time in the STOUR code of JPL.The technique consists in patching gravity assist trajectories by matching the magnitude of the incoming v_infinity (hyperbolic excess speed with respect to the specific swing-by planet) with the outgoing v_infinity aiming at an unpowered (i.e., not propelled) gravity assist. The two velocity vectors are solutions of two distinct Lambert problems. For the specific application, the C3 matching (C3 is the square of the hyperbolic excess speed) is sought at Mars, flyby body of a trajectory from Earth to Jupiter. For given Earth departure and Mars encounter dates, varying the Jupiter arrival dates yields different values of C3 on leaving Mars (C3 curve). Some of these values coincide with the C3 value of the trajectory that approaches Mars. The matching suggests that an unpowered gravity assist with Mars may exist. Such opportunity shall be investigated by allowing small impulsive correction maneuvers at the sphere of influence of Mars aiming at connecting (with continuity both in position and in velocity) the resulting hyperbola branches relative to Mars. This part of the work requires implementation of appropriate orbital mechanics formulas for the continuity requirement.
MatèriesOuter space--Exploration, Gravity, Space flight to Jupiter, Espai exterior -- Exploració, Gravetat, Vol espacial a Júpiter
TitulacióGRAU EN ENGINYERIA EN TECNOLOGIES AEROESPACIALS (Pla 2010)
Fitxers | Descripció | Mida | Format | Visualitza |
---|---|---|---|---|
REPORT_211.pdf | 3,732Mb | Accés restringit | ||
BUDGET_223.pdf | 637,4Kb | Accés restringit | ||
ANNEX_144.pdf | 1,423Mb | Accés restringit |