• Bolsa de mestrado no valor de R$940,00 por mês durante 2 anos;
• Aulas de teoria no ITA ministradas em inglês por especialistas russos do renomado Moscow Aviation Institute (MAI);
• Aulas de laboratórios (em inglês) no MAI no com duração de 3 a 4 semanas;
• Disciplinas especializadas em propulsão líquida

• Ter diploma em engenharia mecânica, aeronáutica, mecatrônica ou aeroespacial, obtido preferencialmente nos últimos 2 anos
• Apresentar currículum vitae, preparado preferencialmente na plataforma Lattes do CNPq;
• Apresentar cópia de diploma(s) obtido(s);
• Apresentar histórico(s) escolar(es);

Complementar a formação de engenheiros graduados em diferentes áreas (aeronáutica, mecânica, civil, elétrica, eletrônica, química, metalurgia, materiais, etc.) com conhecimentos técnico-científicos especializados na área de engenharia aeroespacial, focalizando especificamente o segmento de foguetes de sondagem e de veículos lançadores de satélites, assim como formar e consolidar o senso interdisciplinar que norteia o desenvolvimento destes aparatos.

O curso se insere no contexto do Curso de Pós-Graduação em Engenharia Aeronáutica e Mecânica (PG-EAM) e atende às normas da CAPES relativas a Mestrado Profissionalizante, conforme Portaria CAPES no 080, de 16 de Dezembro de 1998, estando devidamente regulamentado pelo ITA no que concerne à avaliação de disciplinas, contagem de créditos, elaboração e defesa do trabalho final.

As atividades são ministradas por professores do ITA, por especialistas do IAE e professores do MAI, compreendendo aulas teóricas, práticas laboratoriais e computacionais, seminários, trabalho em equipe e trabalho individual no final do curso.

Durante o curso, os alunos têm à disposição as seguintes facilidades: apostilas e livros técnicos, salas de aulas com equipamento de projeção multimídia, laboratórios, sala de estudos e microcomputadores individuais para revisão das aulas, treinamento em softwares e elaboração de trabalhos.

Fase constituída de módulos de disciplinas direcionadas à Área de Concentração, atendendo as necessidades de capacitação profissional de empresas parceiras no Programa.

Fase constituída por um “Estágio Profissionalizante”, que compreende a execução, em ambiente profissional, de projetos em times multidisciplinares, coordenados por profissionais da empresa parceira e conjuntamente orientados por professores do Corpo Docente do ITA, visando a produção da dissertação de mestrado profissionalizante exigida pelo Programa.

• ME-710: Theory and Calculation of Liquid-propellant Rocket Engines I
• ME-711: Theory and Calculation of Liquid-propellant Rocket Engines II
• ME-715: Theory and Calculation of Liquid-propellant Rocket Engine Turbopumps I
• ME-716: Theory and Calculation of Liquid-propellant Rocket Engine Turbopumps II
• MP-780: Design of Liquid-propellant Rocket Engine Chambers I
• MP-781: Design of Liquid-propellant Rocket Engine Chambers II
• MP-785: Design of Liquid-propellant Rocket Engine Turbopumps I
• MP-786: Design of Liquid-propellant Rocket Engine Turbopumps II
• MP-735: Automatic Control of Liquid-propellant Rocket Engines I
• MP-736: Automatic Control of Liquid-propellant Rocket Engines II
• MT-720: Manufacture and Assembly of Liquid-propellant Rocket Engines I
• MT-721: Manufacture and Assembly of Liquid-propellant Rocket Engines II

• Projeto final
• Dissertação

ME-710: Theory and Calculation of Liquid-propellant Rocket Engines I (60 horas-aula, 3,5 créditos máximo)
Section 1. Reasons of LRE design parameters. Choosing the propelant, chamber pressure and nozzle outlet pressure. Engines with the pressurized propellant feeding system and their limitation. Means to improve pressurized feed systems. Engines with the turbopamp feeding system without the generator gas after-burning. Specific impulse losses owing to turbopump driving. Engines with the generator gas after-burning. Power balance of turbopump and chamber pressure limitation. Block-schemes of LRE and their calculation. Section 2. Gasgenerators of LRE: requirements, classification, tipes. Gasenerators based on propellant catalyzation and thermal decomposition. Two-component generators of gas. Efficiency of different gases for a turbine driving. Section 3. Set-up of operational processes in combustion chamber and their description (propellant mixing, gasification, burning etc.).Principle configuration of chamber and work process organization. Internal cooling of chamber walls by a wall layer. Mixing head and injector dispositions on a head.. Screen cooling. Energy efficiency of combustion chamber and estimation of expected efficiency. The chamber gasdynamical calculation Building-up of the chamber contour and supersonic part of a nozzle.
Bibliografia:

ME-711: Theory and Calculation of Liquid-propellant Rocket Engines II (60 horas-aula, 3,5 créditos máximo)
Section 4. Injectors: types and characteristics. Spray cone and propellant flow distribution. Theory and calculation of liquid and gaseous jet injectors. Theory and calculations of centrifugal injectors. Two-component injectors, their types and special features. Section 5. Equations of boundary layer and the rout of their solution. Calculated relations for convective heat flow, and different factors influence. The wall layer and film screen as methods to decrease a heat flow into a chamber wall. Heat flow calculation under film screen protection. Radiative heat flow and its calculation. Heat flow distribution along chamber. Flowing cooling, basic relations and steps of calculation.Effect different factors on the wall cooling. Section 6. General information about phenomenon of instability in combustion chamber. Hydraulic and chamber mechanism of pressure oscillations. Characteristics of instability. Methods to prevent instability.
Bibliografia:

ME-715: Theory and Calculation of Liquid-propellant Rocket Engines Turbopumps I (60 horas-aula, 3,5 créditos máximo)
Section 1. Turbomachine definition. Classification of turbomachines. Basic properties of turbomachines. Parameters of blade cascades. Kinematic relations of turbomachines. Euler’s equation for turbomachines. Forces acting on the blade profile in the axial blade cascade. Relation between the momentum acting on the radial turbomachine impeller with Coriolis inertia force momentum. Kinematic reaction degree and its influence on the specific turbomachine parameters. Taking into account three-dimensional character of flow in blade profiling along the radius. Similarity of turbomachines. Losses in turbomachines. Classification of the main loss types. Thermodynamic relations and using thermodynamic diagrams in turbomachine process examination. Efficiency coefficients of turbomachines. Section 2. Centrifugal pumps with axial screw inducer. Outline. Suction inlet. The axial screw inducer and centrifugal impeller. Theoretical head of the screw-centrifugal pump with taking into account the finite number of blades. Discharge casing. Circular diffuser without vanes. Vane circular diffuser, its profiling. Volute casing. Conical diffuser. Losses in the volute casing and conical diffuser. Hydraulic efficiency of the pump. Leakage losses in the pump. Dynamic radial sealing (impeller) calculation. Disk friction losses in pumps. Efficiency coefficients structure in the pump. Energetic characteristics of the centrifugal and screw-centrifugal pump. Theoretical characteristics. Actual characteristics. Efficiency- flow rate characteristic. Power – flow rate characteristic. Complete pump characteristic. Axial and diagonal pumps, outline, operation range. Basics of axial pump profiling. Screw-inducer pump. Energetic characteristics of the screw-inducer pump. Cavitation in pumps. Basic relations of pump cavitation modes. Cavitation stall characteristic. Cavitation coefficients. Conditions of pump operation without cavitation stall. Influence of physical properties of propellant components on cavitation. Application of booster pumps in LPRE feed systems. Pump similarity. Pump specific speed. Pressure pulsation and hydraulic vibration of centrifugal pumps.
Bibliografia:

ME-716: Theory and Calculation of Liquid-propellant Rocket Engines Turbopumps II (60 horas-aula, 3,5 créditos máximo)
Section 3. Turbine types. The turbine stage. Basic concepts and relations. Representation of real processes of turbine in the thermal diagram. Turbine similarity. Turbine specific speed coefficient. Expansion of gas in convergent vane cascades with an oblique section. Expansion of gas in vane cascades and nozzles with an expanding channel and oblique section. Profiling of nozzle cascades under subsonic and supersonic gas velocities. Conditions of rotor cascade flow choking. Height and width of nozzle and rotor cascade. Admission degree. Optimal axial gap determination. Fixed circular (nozzle) cascades. Working impeller of the radial – axial flow (inward-flow) turbine. Circular efficiency of the turbine stage. Coefficient of circular work of the turbine stage. Losses of turbine stage connected with the working medium leakage. Turbine disk friction losses. Losses connected with partial admission. Mechanical losses. Dependence of the effective efficiency on kinematical parameters. Determination of the optimal admission degree and optimal relation between circular velocity and absolute velocity in one-stage impulse turbines. Multistage reaction turbine. Multistage impulse turbine. Impulse turbine with pressure stages. Impulse turbine with velocity stages. Single-rim multistage impulse partial-admission turbines. Birotatory turbines. Energy turbine characteristics and methods of their obtaining. Calculation of the turbine characteristics. Selection of parameters and order of calculation of turbines. Selection of the turbine type. Calculation of the autonomous turbine. Calculation of the prechamber turbine. Axial turbine blade profiling along the radius. Particularities of the radial turbine calculation. Section 4. Selection of key turbopump unit (TPU) parameters of the feed system with autonomous or prechamber turbine. Operation of pumps and turbines within the feed system regulation. Requiered head of the feed system Fuel flow control modes of the feed system with turbopumps. Pump control. Turbine control. Choosing of control modes for TPU regulation. Stability of pump operation in the feed system. Team-work of pumps in the feed system. Axial and radial forces in TPU. Axial force in the pump and in the turbine. Axial force in a dynamic radial sealing (impeller). Radial force in the pump and in the turbine. Link of TPU weight with hydrodynamic parameters of the feed system. Turbopump unit efficiency. TPU specific mass and specific power of turbopump units.
Bibliografia:

MP-780: Design of Liquid-propellant Rocket Engines Chambers I (60 horas-aula, 3,5 créditos máximo)
Section 1. The chamber and gasgenerator subsystems of the engine. Purpose, structure of parameters, General scheme of designing. Stages of designing the engine of flying apparatus, specific peculiarities. Section 2. The contents of technical task for working out the chamber and gasgenerator. The stages of designing. Analysis of initial data and parameters, defining peculiarities of load application of chambers. The maximum level of the pressure in the combustion chamber as a facture of load application. Section 3. Principles of designing strength schemes of casing. Strength schemes with independently working and fixed casings. Schemes of fixed casings: longitudinal, screw and point. Concept of spaced and frequent ties. Designing performance of different schemes of ties. Geometrical parameters and their coordination. Merits and drawbacks of different schemes of ties. Peculiarities of strength schemes of casings with shaped tubes Section 4. Hydraulic scheme of cooling duct/ Branched and unbranched schemes. Peculiarities of hydraulic estimation. Collectors of inlet and outlet coolants, demands for them, geometrical correlations between bores, calculation of the strength. Peculiarities of calculation of outer cooling, criteria and limits. construction materials. Section 5. The principle of segmentation of casings securing coaxiality of sections. Definition of positions of real axes of the nozzle, axes of casings. Securing coaxiality of the chamber and casing of the heavier than air aircraft. The strength of the casing elements. Load carrying capacity (graphical method). Local strength. Belts of hang-up, their designation and main demands. Variants of construction of belts hang-ups and their comparative analyses. Nuzzle outlets with radiation cooling, peculiarities of calculating cooling, variants of construction. Connections of outlets with the casing. Construction of chamber fitting. Estimation of their strength.
Bibliografia: [1] Baulin V.I. ,Volodin N.V. et. al., “Construction and designing of LRE”, textbook for aviation professions, Machinebuilding. Moscow. 1989. [2] Vasiletv A.P. Kudryavtsev V.M. et. al., “Fundamentals of the theory and calculation of LRE” in two volumes, textbook for rocket specialized fields. Higher school publishing house. 1993. [3] Gahun G.G., Doubenets S.A. et. al., Atlas of LRE, Part 1, “Construction of combustion chambers” MAI. 1968.

MP-781: Design of Liquid-propellant Rocket Engines Chambers II (60 horas-aula, 3,5 créditos máximo)
Section 6. Demands for the construction of mixing heads. Classification of mixing heads according to their type, according to their position, according to the type of their inner bottom, according to their strength scheme. Section 7. Loading, applied to the elements of their mixing head. Behavior of elements of mixing heads under the pressure of loading. Construction and schematic ways of securing stiffness and strength of mixing heads. Section 8. Construction of the fuel nozzle, peculiarities of calculation, geometrical parameters. Ways of connection with bottoms. Anti-detonation walls, dctectors. The eleeent of mixing heads. Form and construction of outer bottoms, definitionthe wall thikness Section 9. Calculation of the nozzle block on local strength. Peculiarites of calculation using limiting condition. Calculation of temporary stress conditioning of the nozze block. Calculation of the strength of outer bottom and curvitude of gas ducts. Section 10. Manufacturing of cases: assembly, soldering and sealing of case elements. Manufacturing of spheres, air intake cones, flanges. Assembly of elements of mixing heads. The main demands to materials used, solders and data multiplexers. Performing onepiece joints of different materials. Tests on the strength and free from leakage soldered and sealing connections. Demands to the control tests.
Bibliografia: [1] Doubenets S.A. "Calculation of jackets of LRE combustion chambers for strength" M. MAI 1960, 73 pp. [2] Doubenets S.A., Homyakov A.M. “Construction and designing of engines of flying appapatus”. M. 1989. [3] Dobrovolsky M.V. “Liquid jet engines”, “Fundamentals of design”, textbook. M. Machine-building 1968.

MP-785: Design of Liquid-propellant Rocket Engines Turbopumps I (60 horas-aula, 3,5 créditos máximo)
Section 1. General information of LRE Turbopumps. Typical requirements for Turbopumps development. Generalised diagram of the Turbopumps designing. Formulation of the optimal design problems. Section 2. Classification of the layout configurations. The main factors defining selection of the layout configurations. The main variants of layout configurations. Section 3. Centrifugal and impeller pumps. Axial and radial-axial turbines. Section 4. Seal classification and requirements. Annular and labyrinth seals. Seals with floating rings and segments seals. Hydrodynamic seals. Gasket, muff and brush seals. Face contact and hydrostatic seals.
Bibliografia:

MP-786: Design of Liquid-propellant Rocket Engines Turbopumps II (60 horas-aula, 3,5 créditos máximo)
Section 5. Rolling bearings in Turbopumps. Rotor support dampers. Hydrodynamic and hydrostatic bearings and thrust bearings. Design of Lubrication systems and Cooling systems at in Turbopumps bearings. Section 6. Detachable and nondetachable connections. Centering of housings. Seals for housing connections. Section 7. Classification of loads influencing the Turbopumps structural elements.Axial forcees in the centrifugal pumps and turbines of Turbopumps. Methods of the axial force decreasing. Balance device. Radial forces in Turbopumps and vtyhods of their decreasing. Inertial loads influencing in Turbopumps and mrthods of theis decreasing. Section 8. Strength of the turbine blades and disks. Paticularities of disk calculations for radial turbines and centrifugal pumps. Blade oscillations. Turbopumps rotor oscillations. Calculation of the oscillation critical frequencies for the Turbopumps rotor as a system with the complicated distribution of masses and rigidities. Ways of preventing of the Turbopumps rotor critical modes.
Bibliografia:

MP-735: Automatic Control of Liquid-propellant Rocket Engines I (60 horas-aula, 3,5 créditos máximo)
Section 1. Main scheme solutions of LRE. Connection cyclograme work of LRE with flight program of the vehicle. Static characteristic of LRE as subject of control. Placement of the regulators. Examples of fulfillment modern LRE and their control systems. The classification of control systems. Traditional and perspective control systems of LRE. Section 2. Static hydraulic characteristic of the pipe lines. Filling hydraulic pipe lines by propellant components. Hydraulic shock in pipe lines. Gas – liquid volumes with separated gaseous volume, with pressured gaseous volume, with two-phase gas-liquid medium. Filling and empting of the mixture heads Section 3. The processes of transformation propellant in the combustion chambers and gas generators. Main admittances in process of dynamical equations preparation. Scheme moving of the gaseous and liquid flows in the process of transformation. Section 4. Static characteristics of the pumps and turbines. Gaseous and hydraulic turbines. The consideration of the cavitations phenomena in pumps. The equations of the head and circular moment for non stationary regimes. The equation of the rotor’s turbo pumps rotation. The movement’s equation of the turbo pump.
Bibliografia: [1] A.P.Babkin, S.P.Belov, N.B.Rutovsky, E.V. Soloviov, "The basis of the theory automatically controls of rocket engine devices", Moscow, Mashinostroenie, 1988 (in Russian) [2] A.A.Kozlov, V.N.Novikov, E.V.Soloviov, "Feed and control systems of LRED", Moscow, Mashinostroenie, 1988 (in Russian).

MP-736: Automatic Control of Liquid-propellant Rocket Engines II (60 horas-aula, 3,5 créditos máximo)
Section 5. Units of the automatic and control. Valves, reductors, throttles. Regulators of mass flow direct and non direct action. Equations of the mass flow regulator. Hydrodynamic forces in the mobile parts of regulators. The stability of the regulator’s work in the hydraulic system. Section 6. Quality valuation of the transitional processes in the closed control systems. Stability of linear control systems. Criteria of the stability. The peculiarities of the dynamical properties of control system with take in consideration non linear characteristics its elements. Section 7. The peculiarities of the pulse regime LRE of small thrust as executive unit control systems regarding center of mass of the vehicle. Imitation models of LRESth. Connection accuracy and economic work reactive control system regarding center of mass.
Bibliografia: [1] B.F.Glicman. "Automatic control of LRE", Moscow, Mashinostroenie, 1974 (in Russian). [2] E.N.Beliaev,V.K.Chvanov, V.V.Chervakov. "Mathematical simulation of the working process in LRE", Moscow, MAI, 1999.(in Russian)

MT-720: Manufacture and Assembly of Liquid-propellant Rocket Engines I (60 horas-aula, 3,5 créditos máximo)
Introduction. Some information about the main stages in the development of space-rocket engineering. The role of the technological science. Special technology of engine manufacturing. Specific features of aerospace production. The structure of the technological process. The concept of technological effectiveness of constructions. The criteria of technological efficiency. Selection of design and technological solutions. The role of technology in the provision of reliability of engines. Designing of the technological processes of manufacturing parts and units of engines. Specific features of manufacturing parts and unit of liquid-propellant rocket engines (LRE). Some general information and requirements imposed on LRE. Design and technological solution for their parts and units. Methods of manufacturing work-pieces of LRE parts. Cold and hot molding. Casting. Methods of machining and physicochemical treatment.
Bibliografia: