Heavy Launchers by Alain Souchier president Association Planète Mars France EMC11 Neuchâtel, 1 Octobre 2011

Content Heavy launchers of the past World heavy and semi heavy launchers NASA heavy launcher Space X proposals Russian heavy and semi heavy launchers Chinese heavy and semi heavy launcher European capabilities Heavy launchers missions

Heavy launchers of the past Saturn – flights t Energya 1987 – flights 88 t + Shuttle 1981 – flights t N – flights 95 t

World heavy and semi heavy launchers LEO payload comparisons SLS t Delta 4H 24t HII B 16,5t Rus-M 23-50t In green: projects or development USA Europe Japan Russia China India A5ECB 21-23t Proton 20t GSLV Mk2 Mk3 5t 10t A6 13t Atlas 5 18t Angara 4-35t Liberty 21t t 25-50t Long March Chinese HLLV t Falcon 9 Heavy 53t

US NASA heavy launcher Configuration frozen summer 2011: 8.4 m diameter core (identical to ET) with 3 SSME/RS25, 5 segments boosters Payload with boosters and central core: 70t Payload with second stage (J2X) and 5 SSMEs: 130t Operations requested starting in 2017 (unmanned) and 2021 (manned) Devt costs: 12 B$ Docs. NASA

US NASA heavy launcher The selected configuration remains close to the old Ares 5 RS25 = SSME shuttle engine in an expandable version Poussée 225 t vacuum thrust Specific impulse 453 s J2X engine 130 t thrust (later versions) Boosters with 5 segments (4 for the shuttle) 130 t payload version Docs. NASA

Space X proposals

Beginning of 2011, Space X has proposed to fly the Falcon 9 Heavy as soon as Falcon 9 Heavy lower composite is an assembly of 3 Falcon 9 first stages (27 engines). The central core engines as well as the boosters engines are fed from the booster tanks at lift off and during the mission first part. When the boosters tanks are empty the boosters are shut off and jettisonned. The central core then operates on its own tanks which are still full at separation. This operating mode is called « cross feeding ». This concept has been known for a long time but has never been applied. It is probably the reason why the payload given by Space X has grown from 32 t mid 2010 (preceding chart) to 54 t beginning of 2011.

Experience on large multiengines propulsion bays: - Soyouz: 5 turbopumps and 20 chambers on the first stage; very good reliability -N1 lunar launcher: 30 engine on the first stage; 4 failures on 4 launches -Ariane 4: 8 Viking engines on the first stage; very good reliability -Saturn 1 and 1 B: 8 H1 engines on the first stage; very good reliability but few flights Space X proposals

After Falcon 9 Heavy: Space X proposals Space X foresees the development of 2 new engines: The 600 t Merlin 2 and the 70t LOX/LH2 Raptor. One Merlin 2 replaces the 9 Merlin 1 on the Falcon 9 and in a cluster is the basis for a heavy launcher family Falcon X, Falcon X Heavy and Falcon XX.

Space X future engines Merlin 2 J-2X Propellant LOX/RP LOX/LH2 Thrust (vac) [klbf] 1, Isp (vac) [sec] T/W [lbf/lbm] Merlin 2 LOX/RP GG cycle Raptor LOX/LH2 SC cycle

Angara family 2014 ? RD 190 LOX/kéro staged combustion t thrust engine

Angara family cryo upper stages Isayev KVD1 RD56M 7.4 t thrust H2/O2 staged combustion engine

Rus M family First stage and boosters powered by the 150/170 t thrust NK33 LOX/kero engine (N1 lunar rocket) From 6 to 50 t in LEO Upper stage powered by four 10 t thrust RD0146 LOX/LH2 engine Launch from Vostochny 2015 ?

Long March 5 family Heavy launcher Chinese heavy and semi heavy launchers

Long March 5 Diameteer 2,25 m 1 YF 100 (120t) LOX/kero Diameter 3,35 m 2 YF 100 (120t) LOX/kero Diameter5 m 2 YF 77 (50t) LOX/LH2 Diametrer 5 m 2 YF 75D LOX/LH2 Diameter 3,35 m 1 YF 75D LOX/LH2 and CZ5- DY with 6 boosters (next chart) 10 to 25 t LEO - 6 to 14t GTO 2015 ?

China Heavy version of the Long March 5 6 boosters LOX/kero each with 2 YF thrust engines 5 m diameter LOX/LH2 central core with 4 YF thrust engines 50 t LEO payload

China Two different versions of the heavy launcher To the left with LOX/kero boosters (YF-650 engines), LOX/Kero first stage (4x YF-650) and cryo upper stage (2x YF-220) To the right solid propellants boosters, cryo first stage (5 x YF-220) and cryo second stage (1x YF-220) The Long March 5 et the heavy launcher

Heavy chinese launcher engines Ground thrust Vacuum thrust Ground specific impulse Vacuum specific impulse Chamber pressure Mixture ratio Oxydiser flowrate Propellant flowrate Area ratio

LOX/Kero 700 t engine: staged combustion cycle LOX/LH 200 t engine: gaz generator cycle Heavy chinese launcher engines

Chine Chinese Moon programme: heavy launcher use

A5 ECA VULCAIN 2 A5 ECB VULCAIN 2 (+rallumage) A5 ECB VULCAIN 2 MPS2 A5 ECB VEDA MPS2 A5 H620 Ø 8m 5 VULCAIN 2 4 MPS A5 ECB VULCAIN 2 3EPC 4 MPS1 A5 H620 Ø 8m 5 VULCAIN 2 2 MPS 4 SRB (US) A5 H920 5 VULCAIN 2 2 MPS 4 SRB(US) No launch pad modifications Launch pad modifs Production facilities modifs International cooperation LEO payload in tonnes Increasing modifications Ariane 5 growth potential for space exploration European capabilities (1) A5 ECB VULCAIN 2 4 MPS1 A5 H Ø 9,8m 5 VULCAIN 2 6 MPS Limit for manned moon or NEO asteroids missions Limit for human Mars missions

European capabilities (2) Examples of heavy launchers derived from Ariane 5 For 541C and 543C: production synergy with the basic Ariane 5

European capabilities (3) Till more than 100 t in LEO Ariane 5SH Examples of heavy launchers derived from Ariane 5

A5L4p H620 4 EAP 80t A5L6Pp H EAP 4SRB 110t A5L4Pp H620 2 EAP 2SRB 100t A5L+6Pp H745 2EAP 4SRB 130t Désignation Central Core Boosters LEO payload A5L++6Pp H920 2EAP 4SRB 140t Lift off with 4SRB + 5 Vulcain EAP ignition at SRB shut off European capabilities (4) Example of US Europe cooperation SRB US

European capabilities (5) Budgetary capabilities Russie

Martian exploration – 3 launches (Mars Direct) to – 7 launches (NASA DRA 5) Lunar exploration – 1 launch NEO asteroids exploration – 1 to 2 launches Defense against NEO asteroids – 1 to x launches New geostationary missions (antenna farms, Earth observation more secure than in SSO, solar power stations,…) Heavy launches may be linked to semi heavy launches for example to launch the crew Heavy launchers missions examples

Questions around Falcon 9 Heavy Space X proposals - What are the budgetary sources for the launcher development? - A 5,2 m diameter fairing is far too small for 50 t payloads. Space X is now presenting versions with a 8 m diameter fairing. - Cross feeding is not so easy to develop (transition for the central core engines from one tank to an other) - The 27 engine configuration enables an « engine out » capability if the monitoring system is very efficient in detecting anomalies before it is too late which may lead to a complicated monitoring system. - In some cases engines present catastrophic failures (fire, explosion) which propagate to the other engines or propulsion bay equipments which cannot be dealt with the engine out capability. This failure mode probability is no more neglectible in a 27 engines configuration. This failure rate may be evaluated at 1 or 2 on 1000 which means 3 to 6 % on a 27 engines configuration to which other failure modes have to be added The impressive Falcon 9 Heavy 27 engines propulsion bay

Russian heavy and semi heavy launchers Angara family

Angara Family Performance Data Descriptions Angara 1.2 (Small-lift) Angara 3 (Medium-lift) Angara А5 (Heavy-lift)Angara А7 (Heavy-lift) Lift-off mass,t Payload mass (kg) Parking orbit ( H circ = 200 km, i = 63 ° ) Geotransfer ( i = 25 °, H p = 5500 km), Breeze M/KVSK (com. SC) (w/KVSK) 7.5 (w/KVTK ) 12.5 (w/KVTK-A7) 2.4 (w/Breeze M) 5.4 (w/Breeze M) GSO ( H circ = 35,786 km, i = 0°), Breeze M/KVTK (federal SC) (w/KVSK) 4.6 (w/KVTK) 7.6 (w/KVTK-A7) 1.0 (w/Breeze M) 3.0 (w/Breeze M) Russian heavy and semi heavy launchers Angara family

Long March 5 - Engines VersionCZ-5-200CZ-5-320CZ-5-504CZ-5-522CZ Boosters-- 2xCZ-5-200, YF- 120t 4xCZ-5-300, YF- 120t 2xCZ xCZ , YF-120t 4xCZ-5-200, YF- 120t First stageCZ-5-200, YF-120tCZ-5-300, YF-120t CZ-5-500, 2xYF- 50t Second stageCZ-YF-73, YF-73CZ-5-KO,CZ-5-HO, 2xYF-75 Third stage (not used for LEO)LEO --CZ-5-HO, YF-75-- Thrust (at ground) 134 Mgf (1.34 MN)Mgf MN 720 Mgf (7.2 MN) 1064 Mgf (10.64 MN) 824 Mgf (8.24 MN) 584 Mgf (5.84 MN) Launch weight82 t420 t800 t630 t470 t Height (maximal)33 m55 m62 m58 m53 m Payload (LEO 200 km)LEO 1.5 t10 t25 t20 t10 t Payload (GTO)GTO--6 t14 t11 t6 t CZ :10 engines in the lower stack