Space Launchers - Ariane

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THE ARIANE FAMILY

Veronique: French Veronique sounding rocket launched from Columb Bechar to an altitude of 104

km.

Europa I: (1964) Europe's first space launcher. First stage British Blue Streak IRBM, second stage

French, third stage German. All orbital launch attempts failed due to unreliability of third stage.

Project cancelled after withdrawal of British support and replaced by Ariane.

Europa II: (1971) As Europa I but with solid propellant fourth stage.

Diamant A: (1965) First French indigenous satellite launch vehicle.

Diamant B: (1970) Upgraded Diamant with liquid stage; antecedent of Ariane.

Ariane 1: (1979) First successful European commercial launch vehicle, developed from L3S Europa

launch vehicle replacement design.

Ariane 2: (1983) As Ariane 1 but with stretched third stage.

Ariane 3: (1984) As Ariane 2 but with solid rocket motor strap-ons.

Ariane 4: As Ariane 2 with stretched first and third stages. See Ariane 40, 42L, 44L, 42P, 44P, 44LP

for figures on varous combinations of solid and liquid propellant strap-on motors.

Ariane 44LP: (1988) Ariane 4 with 2 liquid rocket + 2 solid rocket strap-ons.

Ariane 44L: (1989) Ariane 4 with 4 liquid rocket strap-ons.

Ariane 40: (1989) Ariane 4 with no strap-on motors. A fully fueled Ariane core cannot lift off the

ground without strap-on liquid or solid motors. When Ariane 4 is launched in this configuration, the

propellant tanks of the first and second stages are not completely filled.

Ariane 42P: (1990) Ariane 4 with 2 solid rocket strap-ons.

Ariane 44P: (1991) Ariane 4 with 4 solid rocket strap-ons.

Ariane 42L: (1993) Ariane 4 with 2 liquid rocket strap-ons.

Ariane 5: (1996) Completely new design.

ARIANE FAMILY RECORD

First launch: 24-Dec-1979

Number launched: 83 thru Feb-1996

Launch sites: Kourou, French Guiana; ELA-1 (Ariane 1-3; site closed Dec-1989), ELA-2 (Ariane 2-4),

and ELA-3 (completed 1995 for Ariane 5)

Vehicle success rate: 91.57% thru Feb-1996

Success rate, past 25 launches: 92.0% thru Feb-1996

ARIANE 4 SPECIFICATIONS

First launch: 15-Jun-1988

Number launched 55 thru Feb-1996

Launch sites: Kourou ELA-2

Principal uses: delivery of 1,900-4,800 kg payloads into GTO for apogee kick motor insertion into

GEO

Vehicle success rate: 94.55% thru Feb-1996

Performance:

Dedicated 7o GTO: 1,900 kg (A40; H10+ 2,020; H10-3 2,105), 2,600 kg (A42P; H10+ 2,740; H10-3

2,930), 3,000 kg (A44P; H10+ 3,290; H10-3 3,465), 3,200 kg (A42L; H10+ 3,350; H10-3 3,480),

3,700 kg (A44LP; H10+ 4,030; H10-3 4,220), 4,200 kg (A44L; H10+ 4,460; H10-3 4,820)

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Dual 7o GTO: 1,700 kg (A40), 2,400 kg (A42P), 2,600 kg (A44P), 2,800 kg (A42L), 3,300 kg (A44LP),

3,800 kg (A44L)

Sun-synchonous: 2,740 kg (A40), 3,400 kg (A42P), 4,100 kg (A44P), 4,500 kg (A42L), 5,000 kg

(A44LP), 6,000 kg (A44L)

LEO 7o: 4,600 kg (A40), 6,000 kg (A42P), 6,500 kg (A44P), 7,000 kg (A42L, 44LP, 44L - structurally

limited)

Escape: 2,600 kg for 5 km2/s2 missions

Availability: 12 launches per year

Cost: $40-50 million for 1,200-1,600 kg (A40), $55-65 million for 2,000-2,500 kg (A42P), $65-80

million for 2,500-3,000 kg (A44P), $90-110 million for &gt3,000 kg (A42L and above)

Number of stages: 3 + up to 4 strap-ons

Overall length: 56.35-60.13 m depending on fairing/payloads

Principal diameter: 3.80 m

Launch mass: 245,000 kg (A40), 324,000 kg (A42P), 356,000 kg (A44P), 363,000 kg (A42L),

421,000 kg (A44LP), 484,000 kg (A44L)

Launch thrust: 2,720 kN (A40), 3,944 kN (A42P), 4,060 kN (A42L), 5,140 kN (A44P), 5,270 kN

(A44LP), 5,400 kN (A44L)

Guidance: Matra Marconi Space inertial in stage 3 Vehicle Equipment Bay, with Sextant laser gyro

providing attitude data from stage 1 separation. Some 600 parameters are telemetered on 2.1 GHz.

Ariane follows pre-programmed attitude profile during first stage burn.

ARIANE 4 SOLID STRAP-ONS

Pairs of PAP strap-ons are carried by the 42P/44P/44LP variants (44P two pairs).

Length: 12.05 m

Diameter: 1.07 m

Mass at ignition: each 12,660 kg

Propellant: CTPB 1613

Propellant mass: each 9,500 kg

Thrust: each 650 kN SL average

Burn time: 33 s (igniting at launch, 4.2 s after the main engines)

Separation: two spring pairs (66 kN forward, 59 kN aft) ensure 6o/s rotation away from base at 5

m/s separation rate. Separation in pairs 89 s after launch (42P), 80 + 70.3 s (PAP 1/3 + 2/4, 44P)

and 67 s (44LP)

ARIANE 4 LIQUID STRAP-ONS

Pairs of PAL strap-ons are carried by the 42L/44L/44LP variants (44L two pairs).

Engine: single SEP Viking 6, canted at fixed 10o

Length: 18.60 m

Diameter 2.22 m

Dry mass: each 4,550 kg

Oxidiser: nitrogen tetroxide

Fuel: UH25 (UDMH + 25% hydrazine)

Propellant mass: each 39,000 kg (A44L/44LP), 37,000 kg (A42L)

Thrust: each 670 kN SL at launch, 753 kN vac average

Burn time: 142 s (igniting with main engines, 3.4 s before launch)

Separation: the PALs are pyrotechnically released at 149.1 s/37.5 km after burnout at 143.6 s and

separated by six solid BPD motors identical to the stage 1 retrorockets

ARIANE 4 STAGE 1

Designation: L220

Engine: four SEP Viking 5, canted at fixed 3.8o

Length: 28.39 m (including 3.31 m interstage 1/2)

Diameter: 3.80 m

Dry mass: 17,515 kg

Oxidizer: nitrogen tetroxide




Propellant mass: 167,500 kg (A40), 217,200 kg (A42P), 201,000 kg (A42L), 227,100 kg

(A44P/44LP/44L)

Thrust: 2,718 kN SL

Burn time: 150 s (A40), 196 s (A42P), 181 s (A42L), 205 s (A44P/44LP/44L)

Attitude control: engine gimballing

Separation: stage 1/2 separation is commanded by the VEB when stage 1 thrust decays to 50%.

The four stage 2 acceleration solids fire, followed 2 s later by the interstage explosive cord + stage

1's eight BPF solid retros. Stage 2's Viking 4 ignites after a further 1 s, its solids burn out 4 s later

and are jettisoned with a 4 s delay

ARIANE 4 STAGE 2

Designation: L33

Engine: single SEP Viking 4

Length: 11.61 m

Diameter: 2.60 m

Dry mass: 3,400 kg



Propellant mass: 34,600 kg

Thrust: 798 kN vac

Burn time: 125 s

Attitude control: pitch/yaw by engine gimballing; roll by two sets of 50 kN thrusters mounted on

rear skirt fed from Viking's gas generator. Guidance begins about 10 s after stage 1 separation (stage

1 executes pre-programmed profile)

Separation: at about 344 s, 147.4 km, 5,379 m/s, assisted by two solid deceleration rockets;

sequence begins when stage 2 has added required delta V

ARIANE 4 STAGE 3

Specifications are given in H10/H10+/H10-3 order.

Designation: H10/H10+/H10-3

Engine: single cryogenic open cycle SEP HM-7B

Length: 10.73 m/11.05 m/11.05 m

Diameter: 2.60 m

Dry mass: 1,200 kg/1,240 kg/1,240 kg, excluding interstage 2/3

Oxidizer: liquid oxygen

Fuel: liquid hydrogen

Propellant mass: 10,800 kg/11,140 kg/11,860 kg

Thrust: 63 kN vac/63.2 kN vac/64.8 kN vac

Burn time: 720 s/750 s/780 s, until desired GTO has been achieved in single direct ascent burn

beginning about 347 s after launch

Attitude control: the Roll & Attitude Control System (SCAR) maintains roll control during main engine

burn (engine gimballing provides pitch/yaw) and 3-axis following cut-off. SCAR consists of two sets

of diametrically opposed triple thrusters fed with gaseous hydrogen; total impulse >15 kNs. Two aft-

facing nozzles depressurize the LOX tank after cut-off and are sequenced as part of the attitude

control system and collision avoidance maneurver following payload separation. Spin stabilization of

about 10 rpm is provided for payload deployment

ARIANE 4 VEHICLE EQUIPMENT BAY

Matra Marconi Space's 520 kg 1.037 m high VEB performs guidance, data processing, sequencing,

telemetry, tracking and destruction function. A digital flight control system replaced Ariane 2/3's

analog equipment.

PAYLOAD FAIRING/CARRIER

Three basic lengths of Contraves' 25 mm-thick aluminum alloy honeycomb two-piece fairings are

available: 8.6 m (type 01, 740 kg, 60 m3), 9.6 m (type 02, 800 kg, 70 m3) and 11.1 m (type 03, 86

m3, available on special request). The fairing halves are separated by pyrotechnic cord and piston

when the heating flux has reduced to 1,135 W/m2, at about 285 s/115.3 km during stage 2's burn.



The base clampband is released first. Several standard payload adapters are available.

Acceleration load: 4.0 g at end stage 1 burn, 4.1 g at end stage 2, 1.6 g end stage 3 (for A40);

7.3 g rms max vibration

Acoustic load: 142 dB integration at launch + transonic

Thermal load: max 500 W/m2 radiated by fairing/Spelda

Ariane 3 used the Sylda for dual launches, encapsulating the lower satellite and mounting the forward

payload on its front face. Ariane 4 introduced the larger aluminum honeycomb Spelda as part of the

fairing assembly. The lower 3.97 m diameter, 2.78 m high cylinder (Short Spelda) is attached to the

VEB and topped by an interface for the upper payload. Short Spelda masses 408 kg, provides a 34 m3

payload envelope, and can carry a 2,800 kg forward load. Separation is achieved by pyrotechnic line

charge around the circumference and six springs. The 458 kg Long Spelda adds a further 1 m

cylindrical section, provides 42 m3 payload envelope, and can carry a 1,900 kg upper load. The 1.78

m-long Mini-Spelda can carry 24 m3 payloads of 400-1,000 kg. This 337 kg unit can handle a 3,200

kg forward load. The 350 kg Mini-Spelda+300 version stretches Mini-Spelda's cylinder by 300 mm for

26 m3 payloads.

ARIANE 5 SPECIFICATIONS

First launch: 4-Jun-1996

Number launched 2 thru end-1997

Launch sites: Kourou ELA-3

Vehicle success rate: 50% thru end-1997

Performance:

GTO (7o): 6,800 kg single or 5,970 kg double payload version

Sun-synchronous (800 km, 98.6o): 10,000 kg

Space Station transfer (70 x 300 km, 51.6o): 18,000 kg

Lunar transfer: 4,450 kg dedicated

Shared GTO mission: 400 kg lunar orbiter + 200 kg-payload lunar lander

Number of stages: 2 + 2 strap-ons

Overall length: 45.71-51.37 m

Principal diameter: 5.40 m

Launch mass: 746,000 kg

Launch thrust: 11.4 MN sea level

Guidance: provided by the Vehicle Equipment Bay encircling stage 2

ARIANE 5 BOOSTERS

Designation: P230

Length: 31.16 m

Diameter: 3.05 m

Empty mass: each 40,000 kg

Propellant: PCA + HTPB + aluminum solid

Propellant mass: each 237,700 kg

Thrust: each 5,250 kN SL at launch

Burn time: 132 s

Separation: at about 55 km

ARIANE 5 CORE STAGE 1

Designation: H155

Engine: single cryogenic gas generator cycle SEP Vulcain

Length: 30.7 m

Diameter: 5.40 m

Dry mass: 12,600 kg



Propellant mass: 156,200 kg max



Thrust: 900 kN SL at launch, 1,145 kN vac

Burn time: 580 s

Attitude control: engine gimbaled ±6o for pitch/yaw control

ARIANE 5 STAGE 2

Designation: L9-7

Engine: single DASA Aestus storable propellant, open cycle, pressure-fed, reignitable

Length: 3.3 m

Diameter: 3.94 m

Dry mass: 1,190 kg


Fuel: monomethyl hydrazine


Thrust: 27.5 kN vac

Burn time: 1,100 s

Attitude control: engine gimbaled ±6o for pitch/yaw control

ARIANE 5 VEHICLE EQUIPMENT BAY

Matra Marconi Space's VEB commands missions from its position encircling stage 2 and incorporates

an attitude control system, providing roll control during stage 1/2 burns and 3-axis control after

burnout. The 5.4 m diameter, 1.56 m high, 1,400 kg unit carries 70 kg of hydrazine.

PAYLOAD FAIRING/CARRIER

Contraves provides two standard 5.40 m diameter fairings to accommodate 4.57 m diameter

payloads: 12.70m/2.3 t short and 17 m long units. The fairing jettisons at about 191 s/106 km during

stage 1 burn when aerodynamic heating has reduced to 1,135 W/m2. The 880 kg Speltra, the

equivalent of Ariane 4's Spelda, increases the length of the upper composite by 5.66 m and permits

the launch of double payloads. Standard payload adapters are available.

Acceleration load: 4.2 g at end P230 burn, 3.4 g at end EPC burn, 0.4 g at end EPS burn; lateral

acceleration does not exceed 0.25 g

Acoustic load: 142 dB at launch/transonic

Thermal load: max 1,000 W/m2 radiated by fairing + VEB

EUROPROPULSION / P230 Application: Ariane 5 strap-on boosters

First flown: 4-Jun-1996

Length: 26.77 m (stage 31.16 m)

Diameter: 3.05 m

Mass at ignition: 268,700 kg

Propellant

type: HTPB 68% ammonium perchlorate, 18% aluminum, 14% PBHT liner

shape: main section cylindrical, forward segment 15 rectangular slots

mass fraction: 0.884 for 237.7 t loading


Burn time: 132 s

Thrust: 5,250 kN SL at launch; 4,931 kN vac average, 6,637 kN vac max

Specific impulse: 271 s vac

Total impulse: better than 630 MNs

Pressure: 59.9 atm max

SEP / VIKING 5C & 6 Application: Ariane 4 stage 1 (four Viking 5C), Ariane 4 PAL liquid strap-on (single Viking 6,

specifications as for Viking 5C but with different layout for PAL accommodation)


Number flown: 212 x Viking 5C, 106 x Viking 6 to end-1995



Number flown: 212 x Viking 5C, 106 x Viking 6 to end-1995

Dry mass: 826 kg

Length: 2.87 m

Maximum diameter: 0.99 m

Mounting: gimbaled for pitch/yaw/roll control

Engine cycle: open gas generator

Oxidizer: nitrogen tetroxide, delivered at 173.3 kg/s (Viking 6 173.7 kg/s)

Fuel: UH25, delivered at 101.9 kg/s (Viking 6 101.5 kg/s)

Mixture ratio: 1.70 (Viking 6 1.71)

Turbopump: 10,000 rpm, 2,500 kW power rating. Single-shaft turbopump driven by gas generator

consuming 1.2 kg/s propellants

Thrust: 752 kN vac, 678 kN SL

Specific impulse: 278.4 s vac

Expansion ratio: 10.5:1

Combustion chamber pressure: 58 atm

Combustion chamber temperature: about 3,000oC

Burn time: 209 s Viking 5C, 143 s Viking 6

SEP / VIKING 4B Application: Ariane 2-4 stage 2

First flown: 4-Aug-1984

Number flown: 75 to end-1995

Dry mass: 826 kg

Length: 3.51 m


Mounting: gimbaled for pitch/yaw control

Oxidizer: nitrogen tetroxide, delivered at 175.0 kg/s

Fuel: UH25, delivered at 103.0 kg/s

Mixture ratio: 1.70

Turbopump: as Viking 5C/6

Thrust: 805 kN vac



Combustion chamber pressure: 58.5 atm

Burn time: 125 s

SEP / HM-7B Application: Ariane stage 3

First flown: 4-Aug-1984

Number flown: 79 HM-7/7B to end-1995

Dry mass: 155 kg

Length: 2.01 m


Mounting: gimbaled for pitch/yaw control



Mixture ratio: 4.76 for H10 stage, 4.66 H10+, 5.04 H10-3

Turbopump: 60,500 rpm, 380 kW single turbine powered by gas generator requiring 0.25 kg/s

propellants

Thrust: 62.3 kN vac H10/H10+, 63.8 kN vac H10-3

Specific impulse: 446 s vac H10, 446.1 s vac H10+, 445 s vac H10-3



Burn time: 735 s H10, 760 s H10+, 790 s H10-3

SEP / VULCAIN

Application: Ariane 5 core stage




Number flown: 1 to end-1996

Dry mass: 1,475 kg

Length: 3.00 m


Mounting: gimbaled ±6o for pitch/yaw control

Engine cycle: open gas generator

Oxidizer: liquid oxygen, delivered at 225.6 kg/s

Fuel: liquid hydrogen, delivered at 36.4 kg/s (+9 kg/s LOX/LH2 for gas generator, attitude control

thrusters, nozzle dump cooling and pressurization)

Mixture ratio: 6.2 in chamber, 0.94 gas generator

Oxidizer turbopump: 130 kg mass, 13,700 rpm, 3.3 MW, 150 atm discharge pressure

Fuel turbopump: 240 kg mass, 34,500 rpm, 11.9 MW, 160 atm discharge pressure

Thrust: 1,145 kN vac, 900 kN SL


Expansion ratio: 45:1

Combustion chamber pressure: 110 atm

Burn time: 580 s (design life: 6,000 s + 20 starts)

DASA / AESTUS L9 Application: Ariane 5 stage 2


Number flown: 1 (launcher failed during stage 1 burn)

Dry mass: 111 kg

Length: 2.20 m


Mounting: gimbaled ±6o by electromechanical actuators

Engine cycle: pump-fed

Oxidizer: nitrogen tetroxide, delivered at 5.89 kg/s

Fuel: MMH, delivered at 2.87 kg/s

Mixture ratio: 2.05

Thrust: 27.5 kN vac

Specific impulse: 324 s vac



Burn time: 1,100 s

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Space Launchers - Ariane