• resistenza viscosa o attrito
• resistenza parassita
• resistenza indotta
• resistenza di pressione
• resistenza d'interferenza
• resistenza aerodinamica
• residence and transit time of the propellants
• requisiti di lancio
• recovery system
• razzo a propulsione liquida
• radial and longitudinal moment of inertia
• punto di separazione
• progetto STERN
• prestazione di volo
• pressure drag
• portanza
• ponderazione del vento
• planform
• pitch
• perturbing effects
• perturbazione
• perturbation
• parasitic drag
• paracadute principale e pilota
• ossigeno liquido LOX
• oscillazione dell'asse verticale
• Open Rocket
• offset della camera di combustione
• numero di Reynolds
• nose cone
• normal force
• non homogeneous second order diff. eq.
• non costanti
• natural frequency
• Montecarlo analysis
• momento dissipativo
• momento d'inerzia longitudinale e radiale
• momento correttivo
• Mobile Rocket Base (MORABA)
• Mobile Raketenbasis (MORABA)
• mission specifications
• metodo empirico
• metodo Datcom
• metodo analitico
• materiali fibrorinforzati a matrice polimerica
• margini di volo
• margini di sicurezza
• margine di stabilità
• Mandell
• Malewicki
• main and drogue chute
• Mach
• liquid propellant rocket
• liquid oxigen LOX
• lift
• leading and trailing edge
• launch tower tilting analysis
• launch site
• launch requirements
• launch angle
• landing area
• lancio verticale
• laminar and turbulent boundary layer
• Kiruna
• Jorgensen
• interference drag
• instabilità di combustione
• induced drag
• impact velocity
• imbardata
• hot gaseous jet damping
• horizontal wind
• groundtrack
• gravity turn
• Glass Reinforced Plastic (GRP)
• German Aerospace Center (DLR)
• Galejs
• frequenza naturale
• free turbulence
• forza normale
• forza assiale
• flutter delle ali
• flusso subsonico supersonico e transonico
• flight performance
• flight margin
• flight events
• Fehskens
• eventi di volo
• Euler equations for the rigid body
• ethanol
• etanolo
• Esrange Space Center
• Esa
• equazioni di Eulero per il corpo rigido
• equazione differenziale del second'ordine
• empirical method
• elliptical fin
• elevation angle
• effetti perturbativi
• disturbo dell'assetto
• dissipazione del getto di gas caldi
• dispersion analysis
• disallineamento delle superfici aerodinamiche di
• disallineamento della spinta propulsiva
• dinamica rotazionale
• Deutsches Zentrum für Luft- und Raumfahrt e.V.
• descend velocity
• derivate aerodinamiche
• Datcom method
• damping ratio
• damping moment
• cylindrical body
• culmination velocity
• crosswind
• corretta apertura
• corrective moment
• correct deployment
• corpo cilindrico
• control fins
• cono di naso
• configurazione con tre o quattro impennaggi
• combustion instability
• combustion chamber offset
• coefficienti aerodinamici
• coda
• clipped delta fin
• Centro Spaziale Esrange
• centro di pressione
• centro di gravità o massa
• centro aerodinamico
• center of pressure
• center of gravity or mass
• Catia
• Carbon Fiber Reinforced Polymer (CFRP)
• Caporaso
• burnout velocity
• bordo d'attacco e d'uscita
• boat tail
• Bengen
• beccheggio
• Base Razzi Mobile (MORABA)
• Barrowman
• banderuola segnavento
• ballistic trajectory
• axial force
• attitude disturbance
• ASTOS
• area di atterraggio
• apogeo
• apogee
• Ansys Fluent
• angolo di lancio
• angolo di elevazione
• angolo di attacco
• angle of attack
• analytical method
• analisi statistica
• analisi Montecarlo
• analisi della dispersione
• analisi dell'inclinazione della torre di lancio
• Allen
• ali di controllo
• ala ellittica
• ala aerodinamica
• ala a delta
• Agenzia Spaziale Tedesca (DLR)
• aeroelasticity
• aeroelasticità
• aerodynamic surfaces misalignment
• aerodynamic stability
• aerodynamic drag
• aerodynamic derivatives
• aerodynamic coefficients
• aerodynamic center
• active and passive attitude control system
• accoppiamento del moto di rollio
• resonance
• Reynolds number
• risonanza
• Rocksim
• roll
• rolling motion coupling
• rollio
• rotational dynamics
• rotazione per gravità
• safety margin
• second order system
• semiapertura alare
• semispan
• separation point
• sistema del second'ordine
• sistema di controllo attivo e passivo dell'asset
• sistema di recupero
• sito di lancio
• SMART Rockets Project (SPR)
• Società Spazio Svedese (SSC)
• Solidworks
• sopra e sottovento
• specifiche di missione
• stability margin
• statistical analysis
• STERN project
• Stine
• strato limite laminare e turbolento
• streamlined fin
• subsonic transonic and supersonic flow
• superficie alare
• Swedish Space Corporation (SSC)
• tasso di smorzamento
• Technische Universitat Dresden
• tempo di residenza e transito propellente
• three- or four-fins configuration
• thrust misalignment
• traccia a terra
• traiettoria balistica
• transition
• transizione
• turbolenza libera
• Università Tecnica Dresda
• up- and downwind
• velocità alla culminazione
• velocità allo spegnimento del motore
• velocità di discesa
• velocità di impatto
• vento di traverso
• vento orizzontale
• vertical axis oscillation
• vertical launch
• vetroresina (GRP)
• viscous drag or friction
• weathercock
• wind weighting
• wings flutter
• Wolfram Mathematica
• yaw
• stabilità aerodinamica

Scope of this thesis is the analysis and validation of the aerodynamics of the SMART rocket from the point of view of both the aerodynamic stability and trajectory. The rocket summarizes the contribution of the Technical University (Technische Universitat) Dresden to the STudentische Experimental-RaketeN (STERN) program, promoted by the German Space Administration (DLR). In the first part of this work, all the possible disturbances commonly affecting the rocket during its atmospheric flight are modeled in an analytical fashion. These include thrust vector misalignments and offsets, combustion instabilities, fins misalignments and presence of wind. Then these perturbing terms are considered inside properly defined models able to provide the response of the vehicle in terms of the time evolution of its vertical axis deflection with respect to the velocity direction, i.e. the time profile of the angle of attack. In this way the aerodynamic stability of the any uncontrolled rocket could be possibly studied from both the static and dynamic point of view. The previous models are applied to the actual state of the SMART rocket and the most critical types of disturbance are identified with the related safety margins. Subsequently a design procedure is developed to define a new aerodynamics able to extend the most critical of the previous margins. This procedure is based on the study of the most important quantities related to the aerodynamic stability problem as a function of a properly defined set of geometrical parameters. These parameters are directly related with the aerodynamic shape of the rocket fins. The optimum which results in the best compromize between the vehicle response to all the previous disturbances is so evaluated and considered in the subsequent trajectory validation. This is realized by means of the ASTOS software, a powerful mission and system analysis and optimization program funded by the European Space Research and Technology Center (ESA/ESTEC). This program has been used both to verify the previous analytical response regarding the vehicle aerodynamic stability and to validate the trajectory of the updated configuration of the SMART rocket. Both 3 dof and 6 dof vertical and non-vertical analysis with and without perturbations have been simulated. The results are compared with those provided by dedicated analytical models whenever is possible. In conclusion the updated configuration obtained from the analytical design results to be the optimum one able to satisfy the imposed requirements in terms of minimum altitudes and maximum culmination velocities with any type of disturbance.