Formation flying offers space-dependent disciplines such as astrophysics, astrodynamics, and geodesy, to name a few, the possibility of creating large spaceborne sensors from an array of small spacecraft flying in formation. This creates exciting scientific and technical opportunities as the formation could be arranged to work as, for example, an interferometer, thus providing a most unlimited angular resolution or a virtual telescope, thus unrestricted focal distances. Since the first mission including formation flying technology (EO-1) was selected by NASA, some of the challenges to realize full Formation Flying (FF) capabilities has been thought to be the definition of suitable algorithms to navigate and control FF missions.The focus of this dissertation is the design and evaluation of algorithms for navigation and control for formation flying missions. Given its importance, extensive research has been already conducted to fulfill the increase of accuracy, autonomy, and other requirements of the Guidance, Navigation, and Control (GNC) systems that derive from novel applications of formation flying missions. To centre the scope of present work, we have mainly focused in three of the present challenges: the difficulties of fusing different non-linear observations for relative navigation; the analysis and extension of behavioural algorithms for controlling a formation of spacecraft; and the design and validation of a control law for formation acquisition and formation keeping of a non-natural relative trajectory. These three interconnected topics cover a wide range of research in formation flying and embody the main algorithm components of formation flying algorithms from the observations to the navigation and to the control.The first challenge consisted, thus, in addressing the difficulties encountered by classical filters to estimate a state vector fusing common observations. We proposed several strategies to improve the robustness of these filters under non-linear conditions. Among these strategies, the modification of the residuals computation for the Unscented Kalman Filter (UKF) deserves special mention due to its excellent results and robustness against nonlinearities. A theoretical basis for these results became, thus, necessary regarding the new update equation of the UKF and has been developed subsequently in the frame of this thesis. This work has been published in Perea et al. (2007) and Perea and Elosegui (2008).The collective motion exhibited by some groups of animals has recently attracted the interest of many research groups who try to take advantage of the robustness and efficiency of natural patterns. With this aim, we have investigated the possibility of extending an interaction model that has shown emergent behaviour. In particular, the Cucker-Smale (CS) model has been extended for its application on spacecraft formation flying. Numerical simulations of the Darwin mission have proved that this strategy is suitable for loose formation keeping. Of special relevance is the low cost of the controller, specially compared to an alternative strategy, the Zero Relative Radial Acceleration Cones (ZRRAC).The problem of tight formation keeping is addressed previous publications. In these papers, we first study the relative dynamics of a virtual telescope that follows a non-natural relative trajectory driven by the position of an observed body and not by the natural forces in space. This analysis has originated the design of several controls based on different approximations of the relative dynamics. Their performances have been tested and compared through numerical simulations of the PROBA-3 mission using, first, computer based simulations, and then, a realistic platform with GNSS hardware and operational flight software in the loop. The main conclusions show that simple control definitions, as defined by the Linear Quadratic Regulator (LQR) and Linear Quadratic Regulator with the Integral term (LQRI), can fulfill stringent requirements for formation acquisition and tight formation keeping.KEYWORDS: Filering Theory; Control Theory; Guidance, Navigation and Control Systems; Formation Flying Missions / El vol de satèl.lits en formació ofereix a les disciplines de I'espai, com ara I'astrofísica, I'astrodinàmica i la geodesia, per anomenar-ne unes quantes, la possibilitat de crear grans sensors espacials a partir d'un petit grup de satèl·lits en formació. Disposar els satèl·lits per a operar com, per exemple, un interferòmetre, i per tant, oferint una resolució angular gairebe il.limitada, o com a telescopi virtual i aconseguir distàncies focals inimaginables amb un únic satèl·lit, crea grans oportunitats científiques i tècniques. Des del moment en que la NASA va seleccionar la primera missió espacial que incorporava tecnologia de vol en formació (EO-1), un dels reptes que es preveien per a realitzar autentiques missions de vol en formació es la definició d'algorismes específics per a la navegació i control dels satèl·lits.L'objectiu principal d'aquesta tesis es el disseny i avaluació d'algorismes de navegació i control apropiats per al vol de satèl·lits en formació. Donada la importancia d'aquestes missions, s'ha realitzat una extensa investigació per aconseguir acomplir amb l'increment d'objectius referents a la precisió, l'autonomia, i altres requisits del sistema de Guiat, Navegació i Control (GNC) que resulta de les noves aplicacions d'aquestes missions. El contingut d'aquesta tesis es centra en tres reptes actuals referents al sistema GNC: les dificultats de combinar diferents tipus d'observacions no lineals per a la navegació relativa; l'anàlisi i extensió d'algorismes de comportament per a controlar una formació de satèl.lits; i el disseny i la validació d'una llei de control per a l'adquisició i manteniment d'una formació en trajectòria no natural. Aquests tres temes interconnectats cobreixen una amplia àrea de recerca en el camp del vol en formació i incorpora els principals components dels algorismes de vol en formació, des de les observacions fins a la navegació i el control.