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Maniobras Orbitales. Puesta En Órbita Objetivos

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Maniobras Orbitales. Puesta En Órbita Objetivos Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Comunicaciones por Satélite Curso 2008-09 Maniobras orbitales. Puesta en órbita Ramón Martínez Rodríguez-Osorio Miguel Calvo Ramón Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 1 Objetivos • Conocer la necesidad y los fundamentos de la maniobras orbitales que realiza un satélite • Introducir los principios que rigen el lanzamiento y puesta en órbita de un satélite • Conocer las principales familias de lanzadores y su capacidad de lanzamiento Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 2 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 1 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Índice • Maniobras orbitales – Ecuaciones básicas – Clasificación • Transferencias coplanarias y no coplanarias • Maniobras no impulsivas • Puesta en órbita – Fases de puesta en órbita. Transferencia de Hohmann – Lanzadores – Bases de lanzamiento – Ventana de lanzamiento – Estadísticas • Ejemplo: Misión de lanzamiento Inmarsat-4 (F2) Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 3 Maniobras orbitales • Funcionamiento nominal del satélite – Corrección de la posición de un satélite para mantener la órbita dentro de unos márgenes – Durante el lanzamiento, si se emplea una órbita de aparcamiento – Contrarrestar el efecto de las perturbaciones – Subsistema de propulsión del satélite – Maniobras de de-orbitación al final de la vida útil – Los propulsantes más empleados son líquidos y sólidos • Lanzamiento de un satélite – Puesta en órbita en sucesivas maniobras – Corrección de errores de inyección Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 4 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 2 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Ecuaciones básicas • Maniobra orbital → Cambio de velocidad y energía v2 µ µ + − = − 2 r 2a { { { Energía Energía Energía cinética potencial total • Velocidad de escape: µ 2µ < velíptica < 2µ r r v = escape r µ vcircular = • Velocidad asintótica: r 2µ µ v = v = parab r ∞ r 2µ v > hiperb r Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 5 Ecuación del cohete • Maniobra orbital → Requiere propulsión y gasto de combustible – En órbita, propulsante del subsistema de propulsión del satélite – En lanzamiento, propulsión del lanzador • Cambios de velocidad tangenciales – El cambio de velocidad en un ápside, sólo afecta al otro ápside contrario • Impulso específico: es el período en segundos por el cual 1 kg de masa de propelente producirá un empuje de 1 kg de fuerza • Ecuación del cohete (ecuación de Tsiolkovski, 1903): ⎛ ∆V ⎞ ⎛ M ⎞ M = M exp⎜− id ⎟ ∆V = I g ln⎜ 0 ⎟ b 0 ⎜ ⎟ id sp 0 ⎜ ⎟ ⎝ Isp g0 ⎠ ⎝ Mb ⎠ M0 = M p + M S + M f = M p + Mb { { { { { Masa inicial Masa del Masa de la Masa de la Masa del vehículo después del cohete propulsante estructura carga útil de consumir el propulsante Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 6 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 3 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Impulso específico ISP • ISP: es la relación entre el empuje y la velocidad de salida del propulsante F : empuje (N) F I = g : aceleración de la gravedad anivel del suelo (m/s2) sp qg 0 0 q : velocidad de escape del propulsante (m/s) – Se mide en “segundos” – Es característico de cada propulsante – Depende de la presión ambiente (diferenciar entre el Isp a nivel el mar y en espacio) – Es necesario tener en cuenta pérdidas por reacción química, tobera, respirador, etc. Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 7 Transferencias coplanarias • No se modifica el plano orbital, sólo su orientación – ∆v debe estar contenido dentro del plano orbital – Si se quiere un único impulso, ambas órbitas deben intersectarse 2 2 ∆v = vF + vI − 2vFvI cosα α: ángulo que forman vF y vI v senα senβ = F 2 2 β: ángulo que forman vI y el impulso ∆v vF + vI − 2vF vI cosα • Si se necesitan varios impulsos: ∆v = ∆v1 + ∆v2 +...+ ∆vN = Velocidad característica • Transferencia de Hohmann • Transferencia bielíptica Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 8 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 4 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Transferencia de Hohmann • Circular a circular – Dos impulsos tangenciales entre dos órbitas circulares y coplanarias – La velocidad característica sólo depende de la relación entre los radios inicial y final ∆v 2λ λ −1 1 RF 2 ∆v = vI + −1 siendo λ = 1+ λ λ λ RI Órbita Órbita elíptica 0.55 final RF de transferencia 0.54 Órbita 0.53 inicial I v/v 0.52 ∆ R I 0.51 ∆v1 0.5 0.49 10 15.6 20 50 100 λ Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 9 Transferencia bielíptica • Circular a circular – Maniobra de tres impulsos – Mejora la transferencia de Hohmann para λ>15.6 ∆v 2 1ª Órbita elíptica 2ª Órbita elíptica de transferencia de transferencia 0.55 Órbita 0.53 final RF 0.51 1 v / v Órbita ∆ inicial 0.49 Hohmann bielliptic r = r 3 H bielliptic r = 2 r R 0.47 3 H I bielliptic r = 4 r 3 H biparabolic ∆v 1 0.45 10 r r 20 2r 50 4r 100 P H H H r /r 2 1 ∆v3 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 10 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 5 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Transferencias no coplanarias • Cambio en la orientación de la órbita (1) Órbita final α ∆v = 2vsen 2 v ∆v α v Órbita inicial Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 11 Transferencias no coplanarias • Cambio en la orientación de la órbita (2) – El vector impulso no está en el plano orbital inicial – Mayor cantidad de combustible que coplanarias – Se realiza en el apogeo orbital –El vector ∆v es perpendicular al plano orbital inicial – Efecto de la inclinación (vi=vf) vi α ∆v ∆v = 2v sen α : ángulo formado por los dos planos i 2 v – Cambio en la inclinación f • Se produce en el plano ecuatorial en uno de los nodos para no modificar Ω i − i ∆v = 2vsen F I 2 – Cambio en la ascensión recta • Fuera del plano ecuatorial ∆Ω ∆v = 2v seni sen 2 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 12 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 6 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Transferencias no coplanarias • Maniobra en un único impulso – Se realiza el cambio de plano y velocidad en el apogeo de forma simultánea – Mayor ahorro que con Hohmann y cambio de plano – Usado en la puesta en órbita 2 2 ∆V = VA +Vs − 2VAVs cosi ⎛V sin i ⎞ ϑ = sin−1⎜ s ⎟ ⎝ ∆V ⎠ Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 13 Maniobras no impulsivas Disminución • Propulsión iónica apogeo – Alternativa a los sistema químicos – Bajo empuje, pero alto impulso específico 1 – Basada en la aceleración electrostática de un 2 combustible ionizado (Xenon) 3 • Maniobras aeroasistidas – Se aprovecha la resistencia atmosférica para Resistencia modificar el apogeo atmosférica – Misiones interplanetarias • Maniobras con ayuda gravitatoria (fly-by) – Aumento de la energía mecánica al pasar cerca de un planeta por cambio en la velocidad – Aceleración de sondas interplanetarias Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 14 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 7 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Maniobras en GEO • Mantener la posición nominal en cinturón GEO – ±0.1 º deriva E-O (longitud): cambia el semieje mayor y la excentricidad • Cambio del periodo – ±0.1º deriva N-S (latitud): cambia la inclinación • Cambio en el plano orbital (costosas) – Evitar derivas hacia 75.3ºE y 255.3ºE (eje menor del geoide) • Deorbitación al final de vida útil – Reducción de basura espacial – Elevar la altura de la órbita GEO en 160 km – Incremento de 6 m/s en cuatro impulsos sucesivos en puntos opuestos de la órbita Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 15 Fases de Puesta en Órbita (GEO) r1 = 6578Km h2 = 35786Km r2 = 42164Km r1 3.99×105 r vgeo = 2 42164 = 3.076Km s (r + r ) a = 1 2 = 24371Km 2 ⎛ 2 1 ⎞ v = k⎜ − ⎟ =1.598Km s h1 = 200Km A ⎜ ⎟ ⎝ r2 a ⎠ ⎛ 2 1 ⎞ 5⎛ 1 ⎞ v1 = k⎜ − ⎟ = 3.99×10 ⎜ ⎟ ⎛ 2 1 ⎞ ⎝ r a ⎠ ⎝ ()6378+ 200 ⎠ vP = k⎜ − ⎟ =10.244Km s ⎝ r1 a ⎠ = 7.788Km s Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 16 Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo 8 Comunicaciones por Satélite (5º curso) ETSI de Telecomunicación. Dpto. de Señales, Sistemas y Universidad Politécnica de Madrid Radiocomunicaciones Puesta en órbita ∆v = 1.47 km/s GTO: va=1634 m/s Órbita geoestacionaria (GEO) (v=3074 m/s) rap=42164 km Órbita de transferencia elíptica (GTO) a=(rap+rp)/2 Órbita circular de aparcamiento (h~200-600 km) r =6578 km Para h=200 km: v=7788m/s p GTO: vp=10250 m/s ∆v = 2.46 km/s Comunicaciones por Satélite. Curso 2008-09. ©Ramón Martínez, Miguel Calvo CSAT 17 Lanzamiento del INSAT-4A (83ºE) Propulsion • 440 Newton Liquid Apogee Motor (LAM) with Mono Methyl Hydrazine (MMH) as fuel and Mixed Oxides of Nitrogen (MON-3) as oxidiser for orbit raising Fuente: http://www.isro.org/insat-4a/insatpage2.htm Comunicaciones por Satélite.
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