Подготовил: Головкин А.А. СМ12-41 Proton (UR-500 - Universal rocket, "Proton-K", "ProtonM") is a heavy-class launch vehicle designed to launch automatic spacecraft into Earth orbit and further into outer space. It is capable of launching cargoes up to 3.3 tons into geostationary orbit. Developed in 1961-1967 in a subdivision of the Khrunichev State Research and Production Space Center, which was part of VN Chelomey's OKB-52. The original two-stage version of the Proton carrier (UR-500) became one of the first carriers of the medium-heavy class, and the three-stage Proton-K the heavy one. The Proton launch vehicle was the launch vehicle for all Soviet and Russian orbital stations Salyut-DOS and Almaz, modules of the Mir and ISS stations, the planned manned spacecraft TKS and L-1 / Zond (Soviet lunar flight program ), as well as heavy satellites for various purposes and interplanetary stations. The missile was developed both in combat versions: a global orbital and intercontinental ballistic missile (12,000 km) for hitting a superpowerful thermonuclear warhead (power - 150 megatons) of especially important targets anywhere in the world, and in the version of a carrier rocket for heavy satellites. “Proton-M” is a heavy rocket Head part: Upper stage + spacecraft Starting weight: Third stage Kilo Kilo Lagrange point Rocket height Second stage Kilo Low space orbit First stage It is 1.5 times more than the mass of the ISS Head fairing Head fairing Head fairing Payload Head fairing Payload Payload Payload Oxygen tank Kerosene tank Upper stage Oxidizer tank (N2O4) Oxidizer tank (N2O4) Engines Oxidizer tank (N2O4) Fuel tank Fuel tank Fuel tank Fuel tank Oxidizer tank (N2O4) Engines Engines Engines Engines Engines Oxidizer tank (N2O4) Proton Oxidizer tank (N2O4) Oxidizer tank (N2O4) Oxidizer tank (N2O4) Fuel tank Fuel tank Fuel tank Engines Engines Engines Oxidizer tank (N2O4) Fuel tank Fuel tank Engines Engines Proton-M Oxidizer tank (N2O4) Fuel tank Oxidizer tank (N2O4) Fuel tank Engines Engines Proton-K Proton-K with upper stage Characteristic Name ДМ-2 ДМ-2М ДМ-03 On Earth 3,2 In Space 2,3 2,2 Fuel Sintin+liquid oxygen Sintin+liqui Sintin+liquid d oxygen oxygen Unsymmetrical dimethylhydrazine Fuel reserve 15,1 15,1 18,7 до 20 Main engine 11Д58М 11Д58С 11Д58М / 11Д58МДФ 14Д30 Thrust in vacuum 8,5 8,5 8,5 2 Specific impulse 360 361 361 / 367 329 Number of engine starts Up to 5 Up to 5 Up to 5 Up to 8 2,4 2,5 2,95 Weight Payload mass in GSO Start of operation «Proton-K» 3,245 «Бриз-М» «Proton-М» (third stage) 1982 1994 2,35 2,5 3,44 3,7 2007 1999 PayLoad=40T PayLoad=30T Proton-M PayLoad=35T PayLoad=45T Payload Rocket Numbers The First flight of launches per y. Width Starting weight LEO GTO GSO Diametr Success Price of ful launch flights ProtonM 2001 8—12 (109) 46° 705 23 6,35 3,25 4,35 90 65—70[ Zenit 3SL 1999 4—5 (36) 0° 473 13,7 6,06 2,6 4,15 91 80 Ariane 5 ECA 2002 6 (74) 5° 780 20 10 5,4 97,2 220 Delta IV Heavy 2004 1 (12) 35° и 28° 732 23 10,75 6,57 5,1 97,56 265 Delta IV M+(5,4)[ 2009 2—3 (8) 35° и 28° 399 13,5 5,5 3,12 5,1 97,56 170 2003 2 (2) 419 13,49 4,88 2,63 5,4 97 160 541 18,8 6,86 3,90 5,4 97 190 549 22,8 5,5—8,3 5,2 98,86 62 Atlas V 521 Atlas V 551 Falcon 9 FT Falcon Heavy 2006 2015 35° и 28° 35° и 1 (3) 28° 35° и 18—26 (92) 28° 2018 1—2 (3) 28° 1421 63,8 8,0— 26,7 5,2 100 90—150 H-IIB 2009 2 (5) 30° 531 19 8 5,1 100 182 CZ-3B 1996 4 (22) 28° 426 11,2 5,1 4,2 91 50—70 2
