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Projeto Otimizado De Um Veículo Lançador De Satélites Baseado Em Propelentes Híbridos

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Projeto Otimizado De Um Veículo Lançador De Satélites Baseado Em Propelentes Híbridos UNIVERSIDADE DE BRASÍLIA FACULDADE DE TECNOLOGIA DEPARTAMENTO DE ENGENHARIA MECÂNICA PROJETO OTIMIZADO DE UM VEÍCULO LANÇADOR DE SATÉLITES BASEADO EM PROPELENTES HÍBRIDOS PEDRO LUIZ KALED DA CÁS ORIENTADOR: CARLOS ALBERTO GURGEL VERAS DISSERTAÇÃO DE MESTRADO EM CIÊNCIAS MECÂNICAS BRASÍLIA/DF: MARÇO – 2013 1 UNIVERSIDADE DE BRASÍLIA FACULDADE DE TECNOLOGIA DEPARTAMENTO DE ENGENHARIA MECÂNICA OTIMIZAÇÃO E PROJETO DE UM MICRO LANÇADOR DE SATÉLITES BASEADO EM PROPELENTES HÍBRIDOS PEDRO LUIZ KALED DACÁS DISSERTAÇÃO SUBMETIDA AO DEPARTAMENTO DE ENGENHARIA MECÂNICA DA FACULDADE DE TECNOLOGIA DA UNIVERSIDADE DE BRASÍLIA COMO PARTE DOS REQUISÍTOS NECESSÁRIOS PARA A OBTENÇÃO DO GRAU DE MESTRE EM CIÊNCIAS MECÂNICAS APROVADA POR: _________________________________________________ Profo Carlos Alberto Gurgel Veras (Orientador) _________________________________________________ Profº José Alexander Araújo, PhD (ENM-UnB) (Examinador Interno) _________________________________________________ •Luiz Eduardo Vergueiro Loures da Costa, DSc (IAE) (Examinador Externo) BRASÍLIA/DF, 10 DE ABRIL DE 2013 2 FICHA CATALOGRÁFICA KALED DA CÁS, PEDRO LUIZ Otimização e Projeto de um Micro Lançador de Satélites Baseado em Propelentes Híbridos [Distrito Federal] 2013. xvii, 145p., 210 x 297 mm (ENM/FT/UnB, Mestre, Ciências Mecânicas, 2013). Dissertação de Mestrado – Universidade de Brasília. Faculdade de Tecnologia. Departamento de Engenharia Mecânica. 1.Projeto Aeroespacial 2.Otimização Genética 3.Propulsão Híbrida 4. Projeto Multidissplinar I. ENM/FT/UnB II. Título (série) REFERÊNCIA BIBLIOGRÁFICA KALED DA CÁS, P. L. (2013). Otimização e Projeto de um Micro Lançador de Satélites Baseado em Propelentes Híbridos. Dissertação de Mestrado em Tecnologia Ciências Mecânicas, PublicaçãoENM.DM-206A/2013, Departamento de Engenharia Mecânica, Universidade de Brasília, Brasília, DF, 145p. CESSÃO DE DIREITOS AUTOR: Pedro Luiz Kaled Da Cás. TÍTULO: Otimização e Projeto de um Micro Lançador de Satélites Baseado em Propelentes Híbridos GRAU: Mestre ANO: 2013 É concedida à Universidade de Brasília permissão para reproduzir cópias desta dissertação de mestrado e para emprestar tais cópias somente para propósitos acadêmicos e científicos. O autor reserva outros direitos de publicação e nenhuma parte dessa dissertação de mestrado pode ser reproduzida sem autorização por escrito do autor. ____________________________ Pedro Luiz Kaled Da Cás Super Quadra Sul 106 Bloco C Apartametno 602, Asa Sul. 70345-030 Brasília – DF – Brasil. 3 CONTENTS 1.1 A Launcher for Brazil ................................................................................................ 13 1.2 Motivation ................................................................................................................. 15 1.2.1 A Simpler alternative.......................................................................................... 16 1.4 Objective ................................................................................................................... 17 1.5 Methodology ............................................................................................................. 17 1.6 Dissertation Structure ................................................................................................ 18 2-MARKET AND MISSION .............................................................................................. 20 2.Market Analysis ........................................................................................................... 20 2.1.1 Buyers ................................................................................................................. 20 2.1.2 New entrants ....................................................................................................... 22 2.1.3 Suppliers ............................................................................................................. 23 2.1.4 Competing technologies ..................................................................................... 24 2.2 Size and Behavior of the Market ............................................................................... 25 2.2.1 Mass Range ........................................................................................................ 25 2.2.2 Orbital Range ..................................................................................................... 27 2.2.3 The market in Brazil ........................................................................................... 28 2.2.4 Future Forecast ................................................................................................... 29 2.3 Direct Competitors .................................................................................................... 30 2.3.1 Scorpius .............................................................................................................. 30 2.3.2 Neptune 5 and 9 .................................................................................................. 32 2.3.3 Virgin Galactic Small Launcher ......................................................................... 35 2.4 Mission Definition ..................................................................................................... 35 2.4.1 Orbit and Payload ............................................................................................... 35 2.4.2 Expected Market Share ...................................................................................... 38 2.5 Conclusion ................................................................................................................. 44 4 3- THEORY, OPTIMIZATION AND BALLISTICS ........................................................ 45 3.1 Ballistic Module ........................................................................................................ 45 3.1.1 Numerical integration ......................................................................................... 49 3.1.2 Propellants .......................................................................................................... 50 3.2 Design Module .......................................................................................................... 54 3.2.1 Construction Material Selection ......................................................................... 54 3.2.2 Materials Sleeted for Analysis. .......................................................................... 57 3.2.3 Wall Thickness and Material quality considerations. ........................................ 58 3.3 DESIGN MODULE; MASS MODEL .................................................................. 59 3.3.1 Fairing, Satellite Adaptor and Guidance systems .............................................. 60 3.3.2 Pressurization Subsystem. .................................................................................. 61 3.3.3 PROPELLANT TANKS, UNSTIFFENED SHELLS........................................ 66 3.3.4 PROPELLANT TANKS, STIFFENED SHELLS ............................................. 69 3.3.5 DRY BAYS AND COMPARTMENTS ............................................................ 70 3.3.6 COMBUSTION CHAMBER ............................................................................. 71 3.3.7 CIRCUNFERENCIAL FRAMES ...................................................................... 73 3.3.8 NOZZLE ............................................................................................................ 76 3.4 Complete mass of the stages ..................................................................................... 77 3.4.1 Dry Bays ............................................................................................................. 77 4.4.2 Propellant loading............................................................................................... 78 3.4.4 Oxidizer tank ...................................................................................................... 78 3.4.5 Combustion chamber and Nozzle ....................................................................... 79 3.4.6 Pressurization system ......................................................................................... 79 3.4.7 Combined mass estimate for the stages. ............................................................. 79 3.5 ROCKET FLIGHT LOADINGS .............................................................................. 80 3.6 VELOCITY MODULE ............................................................................................. 85 3.7 INTEGRATED LAUNCHER SIMULATION CODE ............................................. 88 5 3.8 SETTING OF OPTIMIZATION ALGORITHM...................................................... 89 3.8.1 Setting the Design Space. ................................................................................... 89 3.8.2 Design of Experiments ....................................................................................... 91 3.9 OPTIMIZATION ALGORITHM ............................................................................. 93 3.9.1 Adaptive Range Multi-Objective Genetic Algorithm (ARMOGA) ................... 94 3.9.2 Downhill SIMPLEX Algorithm (SIMPLEX) .................................................... 96 4.9.3 ARMOGA-SIMPLEX hybrid ............................................................................ 97 4-RESULTS AND DISCUSSION .................................................................................... 101 4.1 Design of Experiments ...........................................................................................
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