Heavy Launchers by Alain Souchier president Association Planète Mars France EMC11 Neuchâtel, 1...
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Transcript of Heavy Launchers by Alain Souchier president Association Planète Mars France EMC11 Neuchâtel, 1...
Heavy Launchersby Alain Souchier
president Association Planète Mars FranceEMC11 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 51967 – 1973
13 flights130+15 t
Energya1987 – 1988
2 flights88 t +
Shuttle1981 – 2011135 flights
35 +70+20 t
N11969 – 1972
4 flights95 t
World heavy and semi heavy launchers
LEO payload comparisons
SLS 100-150t
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
GSLVMk2 Mk35t 10t
A6
13t
Atlas 5
18t
Angara
4-35tLiberty 21t
3 5
12t 25-50t
Long March
Chinese HLLV
100-150t
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 launcherThe selected configuration remains close to the old Ares 5
RS25 = SSME shuttle engine in an expandable versionPoussée 225 t vacuum thrustSpecific 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 Xproposals
Space X proposals
Beginning of 2011, Space X has proposed to fly the Falcon 9 Heavy as soon as 2013.
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] 1,700 292Isp (vac) [sec] 322 448T/W [lbf/lbm] 150 55
Merlin 2
LOX/RPGG cycle
Raptor
LOX/LH2SC cycle
Angara family
2014 ?
RD 190 LOX/kéro staged combustion 196-212 t thrust engine
Angara familycryo 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 m1 YF 100 (120t) LOX/kero
Diameter 3,35 m2 YF 100 (120t) LOX/kero
Diameter5 m2 YF 77 (50t) LOX/LH2
Diametrer 5 m2 YF 75D LOX/LH2
Diameter 3,35 m1 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-100 120 thrust engines
5 m diameter LOX/LH2 central core with 4 YF-77 50 thrust engines
50 t LEO payload
China
Two different versions of the heavy launcherTo 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 impulseVacuum specific impulseChamber pressure
Mixture ratioOxydiser flowratePropellant flowrateArea ratio
LOX/Kero 700 t engine: staged combustion cycle
LOX/LH 200 t engine: gaz generator cycle
Heavy chinese launcher engines
ChineChinese Moon programme: heavy launcher use
A5 ECAVULCAIN 2
A5 ECBVULCAIN 2(+rallumage)
A5 ECBVULCAIN 2MPS2
A5 ECBVEDAMPS2
A5H620 Ø 8m5 VULCAIN 24 MPS
A5 ECBVULCAIN 23EPC4 MPS1
A5 H620 Ø 8m5 VULCAIN 22 MPS4 SRB (US)
A5 H9205 VULCAIN 22 MPS4 SRB(US)
No launch pad modifications Launch pad modifs
Production facilities modifs
International cooperation
120
100
60
40
80
20
140
LEO payload in tonnes
Increasing modifications
Ariane 5 growth potential for space exploration
European capabilities (1)
A5 ECBVULCAIN 24 MPS1
A5H Ø 9,8m5 VULCAIN 26 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
A5L4pH6204 EAP80t
A5L6PpH 6202 EAP 4SRB110t
A5L4PpH6202 EAP 2SRB100t
A5L+6PpH7452EAP 4SRB130t
DésignationCentral CoreBoostersLEO payload
A5L++6PpH9202EAP 4SRB140t
Lift off with 4SRB + 5 VulcainEAP ignition at SRB shut off
European capabilities (4)
Example of US Europe cooperation
SRB US
European capabilities (5)Budgetary capabilities
Russie
1 75
2 00
0
• 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 171 481 773 1133
• Payload mass (kg)• Parking orbit • ( H circ = 200 km, i = 63 ° ) 3.8 14.6 24.5 35.0• Geotransfer ( i = 25 ° , • H p = 5500 km), • Breeze M/KVSK (com. SC) - 3.6 (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) - 2.0 (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 launchersAngara family
Long March 5 - Engines
Version CZ-5-200 CZ-5-320 CZ-5-504 CZ-5-522 CZ-5-540
Boosters -- 2xCZ-5-200, YF-120t
4xCZ-5-300, YF-120t
2xCZ-5-200 2xCZ-5-300, YF-120t
4xCZ-5-200, YF-120t
First stage CZ-5-200, YF-120t CZ-5-300, YF-120t CZ-5-500, 2xYF-50t
CZ-5-500, 2xYF-50t
CZ-5-500, 2xYF-50t
Second stage CZ-YF-73, YF-73 CZ-5-KO, CZ-5-HO, 2xYF-75 CZ-5-HO, 2xYF-75 CZ-5-HO, 2xYF-75
Third stage (not used for LEO) -- CZ-5-HO, YF-75 -- -- --
Thrust (at ground) 134 Mgf (1.34 MN) 720 Mgf (7.2 MN) 1064 Mgf (10.64
MN)824 Mgf (8.24
MN)584 Mgf (5.84
MN)
Launch weight 82 t 420 t 800 t 630 t 470 t
Height (maximal) 33 m 55 m 62 m 58 m 53 m
Payload (LEO 200 km) 1.5 t 10 t 25 t 20 t 10 t
Payload (GTO) -- 6 t 14 t 11 t 6 t
CZ-5-540 :10 engines in the lower stack