Data relating to Flight 170 by H. Lantéri - Astrium - EADS
Data relating to Flight 170 by H. Lantéri - Astrium - EADS
Data relating to Flight 170 by H. Lantéri - Astrium - EADS
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Kourou<br />
February 200<br />
<strong>Data</strong> <strong>relating</strong> <strong>to</strong> <strong>Flight</strong> <strong>170</strong> <strong>by</strong> H. <strong>Lantéri</strong><br />
Spainsat<br />
Hot Bird 7A<br />
1
<strong>Flight</strong> <strong>170</strong><br />
Ariane 5 ECA – Satellites: Spainsat & Hot Bird 7A<br />
Contents<br />
1. Introduction.........................................3<br />
2. Launcher L527 .....................................4<br />
3. Payload .............................................. 13<br />
4. Launch campaign ............................... 17<br />
5. Launch window .................................. 20<br />
6. Final countdown................................. 21<br />
7. <strong>Flight</strong> sequence .................................. 25<br />
8. <strong>EADS</strong> SPACE Transportation<br />
and the Ariane programmes............... 27<br />
2
1. Introduction<br />
<strong>Flight</strong> <strong>170</strong> is the 26 th Ariane 5 launch and the first in 2006. An ARIANE 5<br />
ECA (Cryogenic Evolution type A), the most powerful version in the ARIANE 5<br />
range, will be used for this flight.<br />
This will be the 22 nd commercial mission for Ariane 5. Launcher 527, the 22 nd<br />
production phase Ariane 5, is the first of the 30 PA contract launchers, for<br />
which <strong>EADS</strong> SPACE Transportation is production prime contrac<strong>to</strong>r. 527 is<br />
consequently the first complete launcher <strong>to</strong> be delivered <strong>to</strong> Arianespace,<br />
integrated and checked out under <strong>EADS</strong> SPACE Transportation<br />
responsibility in the Launcher Integration Building (BIL).<br />
In a multi-payload configuration using the SYLDA 5 "A" (1,500 mm stretched)<br />
system, and a long pattern fairing, the launcher is carrying two<br />
telecommunications satellites: SPAINSAT in the upper position and HOT<br />
BIRD 7A in the lower position.<br />
Installed inside the long pattern fairing<br />
built <strong>by</strong>:<br />
CONTRAVES SPACE<br />
SPAINSAT built <strong>by</strong>:<br />
LORAL SPACE SYSTEM<br />
strapped <strong>to</strong> a type 1194 H adap<strong>to</strong>r built<br />
<strong>by</strong>:<br />
<strong>EADS</strong>-CASA<br />
mounted on two MFD-C additional ballast<br />
modules also built <strong>by</strong>:<br />
<strong>EADS</strong>-CASA<br />
HOT BIRD 7A built <strong>by</strong>:<br />
ALCATEL ALENIA SPACE<br />
strapped <strong>to</strong> a type 1195 H adap<strong>to</strong>r built<br />
<strong>by</strong>:<br />
<strong>EADS</strong>-CASA<br />
and placed inside the SYLDA 5 A built<br />
<strong>by</strong>:<br />
<strong>EADS</strong> ASTRIUM<br />
Operations in the Final Assembly Building (BAF) – where the satellites are<br />
integrated with the launcher – and actual launch operations on the Ariane 5 launch<br />
pad (ELA3) are coordinated <strong>by</strong> the Arianespace Operations Direc<strong>to</strong>rate (DO).<br />
3
2. Launcher L527<br />
Description<br />
The upper composite is mounted on the main<br />
cryogenic stage (EPC) and incorporates:<br />
ESC-A cryogenic upper stage,<br />
• Vehicle Equipment Bay,<br />
• 3936 cone,<br />
• SYLDA 5 payload carrier structure,<br />
• Fairing,<br />
The lower composite incorporates:<br />
• EPC (H175) main cryogenic stage with<br />
the new Vulcain 2 engine,<br />
• two identical EAP (P240) solid propellant<br />
strap-on boosters secured on either side of the<br />
EPC.<br />
Liquid helium sub-system tank<br />
Type C main cryogenic stage:<br />
The EPC is over 30 m high. It has a diameter of 5.4 m and an empty mass of only<br />
14.1 metric <strong>to</strong>ns. It essentially comprises:<br />
• large aluminum alloy tank,<br />
• thrust frame transmitting engine thrust <strong>to</strong> the stage,<br />
• forward skirt connecting the EPC <strong>to</strong> the upper composite, and transmitting<br />
the thrust generated <strong>by</strong> the two solid propellant boosters.<br />
4
2. Launcher L527 (continued)<br />
Compared with the Ariane 5 "generic" version of the main stage, the main changes<br />
are integration of the Vulcain 2 engine (generating 20% more thrust than the<br />
Vulcain 1), lowering of the tank common bulkhead, and strengthening of the<br />
forward skirt and thrust frame structures. As in the case of the previous A5 ECA<br />
launcher (L522) used for flight 167, the Vulcain 2 has undergone a number of<br />
changes, principally <strong>to</strong> the nozzle (shortened and strengthened) and the cooling<br />
system (dump-cooling).<br />
The tank is divided in<strong>to</strong> two compartments containing 175 <strong>to</strong>ns propellant<br />
(approximately 25 <strong>to</strong>ns liquid hydrogen and 149.5 <strong>to</strong>ns liquid oxygen). The Vulcain<br />
2 engine delivers of the order of 136 <strong>to</strong>ns thrust, and is swivel-mounted (two axes)<br />
for attitude control <strong>by</strong> the GAM engine actuation unit. The main stage is ignited on<br />
the ground, so that its correct operation can be checked before authorizing lift-off.<br />
The main stage burns continuously for about 530 s, and delivers the essential part<br />
of the kinetic energy required <strong>to</strong> place the payloads in<strong>to</strong> orbit.<br />
The main stage also provides a launcher roll control function during the powered<br />
flight phase <strong>by</strong> means of the SCR (roll control system).<br />
On burnout at an altitude of 156 km for this mission, the stage separates from the<br />
upper composite and falls back in<strong>to</strong> the Atlantic Ocean.<br />
Type B solid propellant strap-on boosters:<br />
Each booster is over 31 m high, and has a diameter of 3 m and an empty mass of<br />
40 <strong>to</strong>ns. Each booster contains 240 <strong>to</strong>ns solid propellant, and essentially comprises:<br />
• booster case assembled from seven cylindrical segments,<br />
• steerable nozzle (pressure ratio Σ = 11), operated <strong>by</strong> a nozzle actuation unit<br />
(GAT),<br />
• propellant in the form of three segments.<br />
The boosters (EAP) are ignited 6.05 s after the Vulcain engine. Booster thrust<br />
varies in time (approx. 600 <strong>to</strong>ns on lift-off or over 90% of <strong>to</strong>tal thrust, with a<br />
maximum of 650 <strong>to</strong>ns in flight. EAP burn time is about 140 s, after which the<br />
boosters are separated from the EPC <strong>by</strong> cutting the pyrotechnic anchor bolts, and<br />
fall back in<strong>to</strong> the ocean.<br />
Compared with the Ariane 5 "generic" version of the booster stage, the main<br />
changes include the elimination of one GAT cylinder, overloading of segment S1 <strong>to</strong><br />
increase thrust on lift-off, and the use of a reduced mass nozzle.<br />
5
2. Launcher L527 (continued)<br />
Type-A cryogenic upper stage:<br />
The ESC-A 3 rd stage has been developed for the Ariane 5 + ECA version, and is<br />
based on the HM7B engine previously used for the 3rd stage of the Ariane 4<br />
launcher.<br />
The ESC-A stage comprises:<br />
• two tanks containing 14.7 <strong>to</strong>ns propellant (LH2 and LOX),<br />
• HM7B engine delivering 6.5 <strong>to</strong>ns thrust in vacuum for a burn time of about<br />
940 s. The HM7B nozzle is swivel-mounted (two axes) for attitude control.<br />
As for flight 167, the ESC-A stage incorporates an additional helium sphere for<br />
pressurizing the upper stage tanks.<br />
The ESC-A delivers the additional energy required <strong>to</strong> place the payloads in<strong>to</strong> target<br />
orbit. This stage also provides a roll control function for the upper composite during<br />
the powered flight phase, and orients the payloads ready for separation during the<br />
ballistic phase using the SCAR (attitude and roll control system).<br />
6
2. Launcher L527 (continued)<br />
ESC-A thrust frame<br />
The first fully equipped ESC-A thrust frame was<br />
delivered <strong>to</strong> <strong>Astrium</strong> GmbH in Bremen on 13 February<br />
2002<br />
Copyright: <strong>EADS</strong>-ST<br />
Ariane 5 ECA launcher in transit <strong>to</strong> launch pad ZL3 for<br />
the launch sequence rehearsal (RSL).<br />
© Ds23230ESA/ARIANESPACE/Service optique CSG<br />
Type C vehicle equipment bay:<br />
The vehicle equipment bay (VEB) is a cylindrical carbon structure mounted on the<br />
ESC-A stage. The VEB contains part of the electrical equipment required for the<br />
mission (two OBCs, two new definition inertial guidance units, sequencing<br />
electronics, electrical power supplies, telemetry equipment with UCTM-D, etc.).<br />
Nose fairing:<br />
The ogival nose fairing protects the payloads during the atmospheric flight phase<br />
(acoustic protection on lift-off and during transsonic flight, and protection against<br />
aerothermodynamic flux).<br />
A long pattern fairing is used for this mission. It has a height of 17.0 m and a<br />
diameter of 5.4 m.<br />
The fairing structure includes two half-fairings comprising 10 panels. These<br />
sandwich panels have an expanded aluminum honeycomb core and two carbon<br />
fiber/resin skins.<br />
The fairing is separated from the launcher <strong>by</strong> two pyrotechnic devices, one<br />
horizontal (HSS) and the other vertical (VSS). The vertical device imparts the<br />
impulse required for lateral separation of the two half-fairings<br />
SYLDA 5 (Ariane 5 Dual Launch SYstem):<br />
This is one of the six versions of this 4.6-m internal diameter structure. SYLDA<br />
height varies from 4.9 m <strong>to</strong> 6.4 m (0.3-m increments) <strong>to</strong> cater for useful payload<br />
volumes from 50 m 3 <strong>to</strong> 65 m 3 . The SYLDA system makes it possible <strong>to</strong> carry a<br />
second main payload inside the fairing.<br />
A SYLDA "A" system with a height of 6.4 m will be used for this mission.<br />
7
2. Launcher L527 (continued)<br />
Payload mission<br />
The main mission of flight <strong>170</strong> is <strong>to</strong> place the SPAINSAT and HOT BIRD 7A<br />
payloads in<strong>to</strong> a specific geostationary transfer orbit (GTO):<br />
Apogee altitude 35,786 km<br />
Perigee altitude 250 km<br />
Inclination 5 °<br />
Perigee argument 178 °<br />
Ascending node longitude -120.2 ° (*)<br />
(*) in relation <strong>to</strong> a fixed axis, frozen at H 0 - 3s and passing through the ELA3<br />
launch complex in Kourou.<br />
SPAINSAT has a mass of 3,681 kg and HOT BIRD 7A 4,100 kg. Including the<br />
adap<strong>to</strong>rs, cylindrical sections and SYLDA dual launch system, the <strong>to</strong>tal launcher<br />
performance requirement for the orbit described above is 8946.1 kg.<br />
8
2. Launcher L527 (continued)<br />
<strong>Flight</strong> phases<br />
Taking H 0 as the basic time reference (1 s before the hydrogen valve of the EPC<br />
Vulcain engine combustion chamber opens), Vulcain ignition occurs at H 0 + 2.7 s.<br />
Confirmation of nominal Vulcain operation authorizes ignition of the two solid<br />
propellant boosters (EAP) at H 0 + 7.05 s, leading <strong>to</strong> launcher lift-off.<br />
Lift-off mass is about 777.5 <strong>to</strong>ns, and initial thrust 12,700 kN (of which 90% is<br />
delivered <strong>by</strong> the EAPs).<br />
After a vertical ascent lasting 5 s <strong>to</strong> enable the launcher <strong>to</strong> clear the ELA3 complex,<br />
including the lightning arres<strong>to</strong>r pylon in particular, the launcher executes a tilt<br />
operation in the trajec<strong>to</strong>ry plane, followed <strong>by</strong> a roll operation 5 seconds later <strong>to</strong><br />
position the plane of the EAPs perpendicularly <strong>to</strong> the trajec<strong>to</strong>ry plane.<br />
The EAP flight phase continues at zero angle of incidence throughout<br />
atmospheric flight, up <strong>to</strong> separation of the boosters.<br />
The purpose of these operations is <strong>to</strong>:<br />
• optimize trajec<strong>to</strong>ry and thus maximize performance;<br />
• obtain a satisfac<strong>to</strong>ry radio link budget with the ground stations;<br />
• meet in-flight structural loading and attitude control constraints.<br />
The EAP separation sequence is initiated when an acceleration threshold is<br />
detected, when the solid propellant thrust level drops. Actual separation occurs<br />
within one second.<br />
This is reference time H 1 , and occurs at about H 0 + 139.0 s at an altitude of<br />
64.7 km and a relative velocity of 1,983 m/s<br />
For the remainder of the flight (EPC flight phase), the launcher follows an attitude<br />
law controlled in real time <strong>by</strong> the on-board computer, based on information<br />
received from the navigation unit. This law optimizes the trajec<strong>to</strong>ry <strong>by</strong> minimizing<br />
burn time and consequently consumption of propellant.<br />
The fairing is jettisoned during the EPC flight phase as soon as aerothermodynamic<br />
flux levels are sufficiently low not <strong>to</strong> impact the upper (outer) payload<br />
9
2. Launcher L527 (continued)<br />
The EPC powered flight phase is aimed at a predetermined orbit established in<br />
relation <strong>to</strong> safety requirements.<br />
Shutdown of the Vulcain engine occurs when the following target orbit<br />
characteristics have been acquired:<br />
Apogee altitude 157.8 km<br />
Perigee altitude -1,141.1 km<br />
Inclination 6.765 °<br />
Perigee argument -41.311 °<br />
Ascending node longitude -119.577 °<br />
This is time reference H 2 .<br />
The subsequent ESC-A powered flight phase lasts a little over 15 minutes. This<br />
phase is terminated <strong>by</strong> a command signal from the OBC, when the computer<br />
estimates, from data calculated <strong>by</strong> the inertial guidance unit, that the target orbit<br />
has been acquired.<br />
This is time reference H 3 .<br />
The purpose of the following ballistic phase is <strong>to</strong> ensure:<br />
- pointing of the upper composite, firstly in the direction required <strong>by</strong> SPAINSAT,<br />
and then in that required <strong>by</strong> HOT BIRD 7A,<br />
- triple axis stabilization of the launcher before separation of SPAINSAT,<br />
- spin-up of the launcher at 1.5°/s for separation of HOT BIRD 7A,<br />
- separation of SPAINSAT (transverse spin-up at about 1.5°/s round Xs, using the<br />
dissymmetric spring system of the PAS 1194H payload adap<strong>to</strong>r), the SYLDA and<br />
HOT BIRD 7A,<br />
- final spin-up of the composite at 45°/s,<br />
- passivation of the ESC-A stage pressurized LOX tank and LH2 tank, preceded <strong>by</strong> a<br />
pre-passivation phase involving simultaneous opening of the eight SCAR nozzles.<br />
These operations contribute <strong>to</strong> short- and medium-term management of the mutual<br />
distancing of objects in orbit.<br />
10
2. Launcher L527 (continued)<br />
Phase 5: SPAINSAT separation<br />
Phase 12: HOT BIRD 7A separation<br />
11
2. Launcher L527 (end)<br />
The main cryogenic stage (EPC) falls back in<strong>to</strong> the Atlantic Ocean after separation<br />
(see below), breaking up at an altitude of between 80 and 60 km under the loads<br />
generated <strong>by</strong> atmospheric reentry.<br />
The stage must be depressurized (passivated) <strong>to</strong> avoid any risk of explosion of the<br />
stage due <strong>to</strong> overheating of residual hydrogen. A hydrogen tank lateral nozzle,<br />
actuated <strong>by</strong> a time delay relay initiated on EPC separation, is used for this purpose.<br />
This lateral thrust is also used <strong>to</strong> spin the EPC, and thus limit breakup-induced<br />
debris dispersion on reentry.<br />
The main cryogenic stage angle of reentry is -2.3°. Point of impact longitude is<br />
5.47°W.<br />
The Kourou, Galliot, Natal, Ascension Island, Libreville and Malindi ground stations,<br />
<strong>to</strong>gether with a shipboard station, provide radar visibility throughout the mission.<br />
12
3. Payload<br />
SPAINSAT<br />
Program and mission<br />
This satellite will be operated <strong>by</strong> HISDESAT. Built <strong>by</strong> SPACE SYSTEM / LORAL,<br />
SPAINSAT will provide secured telecommunications services in the X and Ka band.<br />
Mission<br />
SPAINSAT will deliver telecommunications services in the X (9 channels) and Ka (1<br />
channel) bands.<br />
SPAINSAT will take over from the SECOMSAT military payloads integrated in the<br />
HISPASAT 1A and 1B satellites, flown on Ariane in 1992 and 1993.<br />
SPAINSAT coverage from its 30° West orbit station circles the Atlantic (Spain,<br />
Europe, Africa and America).<br />
13
3. Payload (continued)<br />
The satellite<br />
SPAINSAT is based on the LORAL FS 1300 platform.<br />
* Dimensions<br />
* Mass<br />
* Power<br />
• 5.4 x 2.9 x 2.2 m<br />
• solar array deployed: 31.41 m<br />
• lift-off<br />
• dry<br />
• 4.5 kW BOL<br />
• 3.6 kW EOL<br />
• (batteries: 34 NiH2 cells)<br />
3,883 kg<br />
1,467 kg<br />
* Propulsion • in-orbit control and bi-liquid apogee engine<br />
* Stabilization<br />
* Transmission<br />
capacity<br />
* Orbital position • 30° West<br />
• X s axis spin at 1.5°/s on launcher/satellite separation and<br />
in GTO<br />
• Triple axis stabilization in orbit<br />
• 10 X-band and Ka-band transponders<br />
* Ground coverage • Spain, Europe, Africa, America<br />
Scheduled service life: 15 years<br />
Fit-Check<br />
14
3. Payload (continued)<br />
HOT BIRD 7A<br />
Program and mission<br />
With the commercial capacity of 23 satellites, providing coverage extending from<br />
continental Europe across the Atlantic <strong>to</strong> the Pacific zone, EUTELSAT SA is one of<br />
the world's leading satellite opera<strong>to</strong>rs.<br />
Based on a SPACEBUS 3000 B3 platform, HOT BIRD 7A is one of the sixteen<br />
telecommunications satellites built (or for which production is planned) for<br />
EUTELSAT <strong>by</strong> ALCATEL ALENIA SPACE.<br />
Mission<br />
The basic mission of HOT BIRD 7A will be <strong>to</strong> replace HOT BIRD 1. This will enable<br />
the new spacecraft, <strong>to</strong>gether with the other members of the HOTBIRD family in<br />
orbit and grouped at 13° East, <strong>to</strong> supply TV (676) and radio (565) programs <strong>to</strong> 100<br />
million households.<br />
Surplus HOT BIRD 7A capacity comprises transponders capable of replacing HOT<br />
BIRD 2, 3 or 4.<br />
15
3. Payload (end)<br />
The satellite<br />
* Dimensions<br />
* Mass<br />
* Power<br />
• 3.75 x 1.8 x 2.3 m (hxLxl)<br />
• 36.9 m with solar arrays deployed<br />
• lift-off<br />
• dry<br />
4,100 kg (forecast)<br />
1,740 kg<br />
• 9,800 W (en début de vie) - 2 solar arrays<br />
• NiH2 batteries (96 AH)<br />
* Propulsion • bi-liquid propellant with an apogee engine (400N).<br />
* Stabilization<br />
• Slow spin (1,5°/s) on separation<br />
• Triple axis stabilization in orbit<br />
* Transmission capability • Ku-band payload (38 transponders)<br />
* Orbital position • 13° E<br />
* Ground coverage • Europe<br />
Scheduled service life: 15 years<br />
Test in acoustic chamber<br />
Pho<strong>to</strong> Alcatel Alenia Space<br />
16
4. Launch campaign<br />
The Ariane 5 main cryogenic stage (EPC) in the<br />
integration dock at Les Mureaux, France, in<br />
course of preparation for containerization.<br />
Copyright: <strong>EADS</strong> ST pho<strong>to</strong>: Studio Bernot<br />
Ariane 5 ESC flight thrust frame at <strong>EADS</strong>-LV Les<br />
Mureaux, before departure for <strong>Astrium</strong> in<br />
Bremen.<br />
Copyright: <strong>EADS</strong> ST pho<strong>to</strong>: Studio Bernot<br />
The main cryogenic stage loading on board the<br />
"Toucan" in the port of Le Havre for shipment <strong>to</strong><br />
French Guiana.<br />
Copyright: <strong>EADS</strong> ST pho<strong>to</strong>: JL<br />
17
4. Launch campaign (continued)<br />
Principal phases of the flight <strong>170</strong> launch campaign:<br />
Depreservation and erection of the EPC stage in the<br />
January 3, 2006<br />
Launcher Integration Building (BIL)<br />
Transfer of solid booster stages (EAP) January 4<br />
Depreservation of the fairing January 4 and 5<br />
Depreservation and erection of the ESC-A stage January 13<br />
Depreservation and erection of the VEB January 13<br />
Arrival of HOT BIRD 7A in French Guiana January 19<br />
Arrival of SPAINSAT in French Guiana January 24<br />
SPAINSAT fit-check on its ACU adap<strong>to</strong>r January 24<br />
HOT BIRD 7A fit-check on its ACU adap<strong>to</strong>r January 25<br />
BIL BAF transfer February 4<br />
Commencement of combined operations plan<br />
February 8<br />
(launcher/satellites)<br />
SPAINSAT mated with and strapped <strong>to</strong> its adap<strong>to</strong>r<br />
Integration of composite (SPAINSAT + ACU) on SYLDA February 9<br />
HOT BIRD 7A mated with and strapped <strong>to</strong> its adap<strong>to</strong>r February 10<br />
Upper composite integrated with the launcher February 13<br />
Launch rehearsal February 15<br />
Launch readiness review February 19<br />
Launcher transferred from BAF <strong>to</strong> launch pad (ZL3) February 20<br />
Final countdown February 21<br />
18
4. Launch campaign (end)<br />
Kourou: transfer of the launcher (less fairing)<br />
from the Launcher Integration Building <strong>to</strong> the<br />
Final Assembly Building.<br />
Copyright: ESA/ARIANESPACE/Service optique CSG<br />
Kourou: erection of the ESC-A stage in the<br />
Launcher Integration Building (BIL).<br />
Copyright: ESA/ARIANESPACE/Service optique<br />
CSG<br />
Kourou: transfer of the launcher from the Final<br />
Assembly Building <strong>to</strong> the launch pad for the<br />
launch sequence rehearsal (RSL).<br />
Copyright: ESA/ARIANESPACE/Service optique CSG<br />
19
5. Launch window<br />
The window for a launch on February 21, 2006, with H 0 at 10.13 p.m. (TU)<br />
is 71 minutes:<br />
MADRID time<br />
February 21, 2006<br />
11.13 p.m. – 00.24 a.m.<br />
PARIS time<br />
February 21, 2006<br />
11.13 p.m. – 00.24 a.m.<br />
KOUROU time<br />
February 21, 2006<br />
07.13 p.m. – 08.24 p.m.<br />
UNIVERSAL TIME<br />
February 21, 2006<br />
10.13 p.m. – 11.24 p.m.<br />
The launch window will close at 11. 24 p.m. (T.U.).<br />
The launch window is based on a compromise between launcher and payload<br />
constraints.<br />
20
6. Final countdown<br />
The final countdown includes all operations for preparation of the launcher,<br />
satellites and launch base. Correct execution of these operations authorizes ignition<br />
of the Vulcain engine, followed <strong>by</strong> the solid propellant boosters at the selected<br />
launch time, as early as possible inside the launch window for the satellites. The<br />
countdown terminates with a synchronized sequence managed <strong>by</strong> the Ariane<br />
ground checkout computers, starting at H 0 - 7 min. In some cases, a presynchronized<br />
sequence may be necessary <strong>to</strong> optimize fuelling of the main cryogenic<br />
stage (H 0 - 16 min). If a countdown hold pushes time H 0 outside the launch window,<br />
the launch is postponed <strong>to</strong> D+1 or D+2, depending on the nature of the problem<br />
and the solution adopted.<br />
H 0 - 7 hours 30<br />
H 0 - 6 hours<br />
H 0 - 5 hours<br />
H 0 - 5 hours<br />
H 0 - 4 hours<br />
H 0 - 3 hours<br />
H 0 - 30 minutes<br />
H 0 - 7 minutes<br />
Checkout of electrical systems, red status indica<strong>to</strong>rs and<br />
countdown time.<br />
Flushing and configuration of the EPC and Vulcain<br />
engine for fuelling and chill-down<br />
Final preparation of the launch pad: closure of doors,<br />
removal of safety barriers, configuration of the fluid<br />
circuits for fuelling.<br />
Loading of the flight program<br />
Testing of radio links between the launcher and BLA<br />
Alignment of inertial guidance units<br />
Evacuation of personnel from the launch pad<br />
Fuelling of the EPC in four phases:<br />
pressurization of the ground tanks (30 minutes)<br />
chill-down of the ground lines (30 minutes)<br />
fuelling of the stage tanks (2 hours)<br />
<strong>to</strong>pping up (up <strong>to</strong> synchronized sequence)<br />
Pressurization of the attitude control and command<br />
systems:<br />
(GAT for the EAPs and GAM for the EPC)<br />
Fuelling of the ESC-A stage in four phases:<br />
pressurization of the ground tanks (30 minutes)<br />
chill-down of the ground lines (30 minutes)<br />
fuelling of the stage tanks (1 hour)<br />
<strong>to</strong>pping up (up <strong>to</strong> synchronized sequence)<br />
Chill-down of the Vulcain engine<br />
Preparation of the synchronized sequence<br />
Pre-synchronization status acquired<br />
21
6. Final countdown - Synchronized sequence<br />
The synchronized sequence starts at H 0 - 7 min and includes all final launcher<br />
operations before lift-off.<br />
These operations are controlled exclusively and au<strong>to</strong>matically <strong>by</strong> the ELA3<br />
operational checkout-command (CCO) computer. If the synchronized sequence is<br />
put on hold, this au<strong>to</strong>matically returns the launcher <strong>to</strong> its t H 0 - 7 min<br />
configuration.<br />
During the initial phase (up <strong>to</strong> H 0 - 6s), the launcher is gradually switched <strong>to</strong> its<br />
flight configuration <strong>by</strong> the CCO computer. If the synchronized sequence is placed<br />
on hold, the launcher is returned au<strong>to</strong>matically <strong>to</strong> its configuration at H0 - 7 min.<br />
In the second, irreversible phase of the sequence (H 0 - 6 s <strong>to</strong> H 0 - 3.2 s), the<br />
synchronized sequence is no longer dependent on CGS countdown time, and<br />
operates on an internal clock.<br />
The final phase is the launcher ignition phase. The ignition sequence is controlled<br />
directly <strong>by</strong> the on-board computer (OBC). The ground systems execute a number of<br />
actions in parallel with the OB ignition sequence.<br />
22
6. Final countdown - Synchronized sequence<br />
(continued)<br />
FLUID SYSTEMS<br />
H 0 - 6 min 30s<br />
Termination of <strong>to</strong>pping up (LOX and LH2)<br />
LOX and LH2 <strong>to</strong>pped up <strong>to</strong> flight value<br />
Launch pad safety flood valves opened<br />
ELECTRICAL SYSTEMS<br />
H 0 - 6 min 30s<br />
Arming of pyrotechnic line safety barriers<br />
H 0 - 6 min: Isolation of the ESC-A helium<br />
sphere<br />
H 0 - 4 min<br />
<strong>Flight</strong> pressurization of EPC tanks<br />
Isolation of tanks and start of EPC<br />
ground/OB interface umbilical circuit<br />
flushing<br />
Termination of ESC-A LOX <strong>to</strong>pping up<br />
ESC-A LOX transition <strong>to</strong> flight pressure<br />
H 0 - 3 min 40: termination of ESC-A LH2<br />
<strong>to</strong>pping up<br />
H 0 - 3 min10: ESC-A LH2 transition <strong>to</strong> flight<br />
pressure<br />
H 0 - 2 min: Vulcain bleeder valves opened<br />
Engine ground chill-down valve closed<br />
H 0 - 1min 5s<br />
Termination of ESC-A tank pressurization<br />
from the ground, and start of ESC-A valve<br />
plate seal-tightness checkout<br />
H 0 - 30s Verification of ground/OB<br />
umbilical circuit flushing<br />
EPC flue flood valves opened<br />
H 0 - 16.5 s Pressurization of POGO<br />
correc<strong>to</strong>r system<br />
Ventilation of fairing POP and VEB POE<br />
connec<strong>to</strong>rs and EPC shut down<br />
H 0 - 12 s Flood valves opening command<br />
H 0 - 3 min 30 : Calculation of ground H 0<br />
and verification that the second OBC has<br />
switched <strong>to</strong> the observer mode<br />
H 0 - 3 min<br />
H 0 loaded in the 2 OBCs<br />
H 0 loaded in OBCs checked against<br />
ground H 0<br />
H 0 - 2 min 30s: Electrical heating of EPC<br />
and VEB batteries, and electrical heating of<br />
the Vulcain 2 ignition system shut down<br />
H 0 - 1 min 50s:<br />
Pre-deflection of the HM7B nozzle<br />
H 0 - 1min 5s<br />
Launcher electrical power supply switched<br />
from ground <strong>to</strong> OB<br />
H 0 - 37s<br />
Startup of ignition sequence au<strong>to</strong>matic<br />
control system<br />
Startup of OB measurement recorders<br />
Arming of pyrotechnic line electric safety<br />
barriers<br />
H 0 - 22s<br />
Activation of launcher lower stage<br />
attitude control systems<br />
Authorization for switchover <strong>to</strong> OBC<br />
control<br />
23
6. Final countdown - Synchronized sequence (end)<br />
IRREVERSIBLE SEQUENCE<br />
H 0 - 6s<br />
Arming and ignition of AMEFs <strong>to</strong> burn hydrogen run-off during<br />
chill-down of the combustion chamber on Vulcain ignition<br />
Valve plate and cryogenic arm retraction commands<br />
H 0 -5.5s<br />
Ground information communication bus control switched <strong>to</strong><br />
OBC<br />
IGNITION SEQUENCE<br />
H 0 - 3s<br />
Checkout of computer status<br />
Switchover of inertial guidance systems <strong>to</strong> flight mode<br />
Helium pressurization activated<br />
LOX and LH2 pressures moni<strong>to</strong>red<br />
Navigation, guidance and attitude control functions activated<br />
H 0 – 2.5s<br />
Verification of HM7B nozzle deflection<br />
H 0 – 1.4s<br />
Engine flushing valve closed<br />
H 0 – 0.2s<br />
Verification of acquisition of the “cryogenic arms retracted” report<br />
<strong>by</strong> the OBC at the latest moment<br />
H 0 → H 0 + 6.65s<br />
Vulcain engine ignition and verification of its correct operation<br />
(H 0 +1s corresponds <strong>to</strong> opening of the hydrogen chamber valve)<br />
H 0 + 6.9s<br />
End of Vulcain engine checkout<br />
H 0 + 7,05s<br />
Ignition of the EAPs<br />
24
7. <strong>Flight</strong> sequence<br />
time /H 0<br />
(s)<br />
time/H 0<br />
(mn)<br />
event<br />
altitude<br />
(km)<br />
mass<br />
(kg)<br />
Vreal<br />
(m/s)<br />
- - - - EAP-EPC powered flight - - -<br />
7.31 0 ‘ 07 ‘’ Lift-off --- 776,659 0<br />
12.54 0 ‘ 12 ‘’ Start of tilt maneuver 0.09 749,749 37<br />
17.05 0 ‘ 17 ‘’ Start of roll maneuver 0.34 725,491 75<br />
32.05 0 ‘ 32 ‘’ End of tilt maneuver 2.46 647,828 211<br />
49.2 0 ‘ 49 ‘’<br />
Transsonic<br />
(Mach = 1)<br />
6.82 579,951 324<br />
66.4 1 ‘ 06 ‘’ Pdyn max. 12.7 510,971 494<br />
111.2 1 ‘ 51 ‘’<br />
138.5 2 ‘ 19 ‘’<br />
Transition <strong>to</strong> γ max<br />
(41.05 m/s 2 )<br />
Transition <strong>to</strong> γ = 6.11<br />
m/s²<br />
H 1<br />
39.3 311,896 1,540<br />
64.0 255,636 1,981<br />
139.3 2 ‘ 19 ‘’ EAP separation 64.7 176,737 1,982<br />
- - - - EPC powered flight - - - -<br />
194.0 3 ‘ 14 ‘’ Fairing jettisoned 105 156,540 2,223<br />
481 8 ‘ 01 ‘’<br />
Galliot-Natal<br />
intervisibility<br />
157 63,903 5,611<br />
533 8 ‘ 53 ‘’ EPC burnout (H 2 ) 156 47,077 6,869<br />
539 8 ‘ 59 ‘’ EPC separation 157 28,161 6,895<br />
- - - - ESC-A powered flight - - - -<br />
542 9 ‘ 02 ‘’ ESC-A ignition 157 28,161 6,897<br />
736 12 ‘ 16 ‘’ Lost Natal 156 25,373 7,356<br />
826 13 ‘ 46 ‘’ Acquisition Ascension 153 24,051 7,592<br />
1,051 17 ‘ 31 ‘’ Lost Ascension 172 20,739 8,211<br />
1,096 18 ‘ 16 ‘’ Acquisition Libreville 185 20,075 8,337<br />
1,246 20 ‘ 46 ‘’ 270 17,858 8,752<br />
1,396 23 ‘ 16 ‘’ Acquisition Malindi 443 15,630 9,158<br />
1484,9 24 ‘ 45 ‘’ ESCA burnout (H 3-1 ) 601 14,301 9399<br />
25
7. <strong>Flight</strong> sequence (continued)<br />
time /H 0<br />
(s)<br />
time/H 0<br />
(mn)<br />
event<br />
altitude<br />
(km)<br />
- - - - Ballistic phase - - -<br />
1,486.9 24 ‘ 47 ‘’<br />
Phases 1 and 2 - adjustment maneuvers at<br />
start of SCAR phase<br />
605<br />
1490.6 24 ‘ 51 ‘’ Phase 3 - start of SPAINSAT orientation 613<br />
1,623.7 27 ‘ 04 ‘’ SPAINSAT separation (H 4.1 ) 932<br />
1,633.5 27 ‘ 14 ‘’ Phase 6 – post-separation adjustment 958<br />
1,637.5 27 ‘ 18 ‘’ Phase 6 et 7 - SYLDA orientation maneuvers 970<br />
1,844 30 ‘ 44 ‘’ SYLDA separation (H 4.2 ) 1,615<br />
1,854 30 ‘ 54 ‘’ Phase 10 – start of HOTBIRD 7A orientation 1,649<br />
1,894 31 ‘ 34 ‘’ Phase 11 – spin-up at -1,5°/s 1,792<br />
1,925 32 ‘ 05 ‘’ HOT BIRD 7A separation (H 4.3 ) 1,904<br />
1,935 32 ‘ 15 ‘’ Phase 13 – start of composite despin 1,940<br />
1,939 32 ‘ 19 ‘’ Phase 14 – roll acquisition 1,955<br />
2,029 33 ‘ 49 ‘’<br />
Phase 15 – start of ESC-A orientation for<br />
avoidance phase<br />
2,296<br />
2,229 37 ‘ 09 ‘’ Phase 16 – start of spin-up at 45°/s 3,098<br />
2,318 38 ‘ 38 ‘’ Phase 17 – start of ESC-A pre-passivation 3,469<br />
2,319 38 ‘ 39 ‘’ Start of ESC-A passivation 3,470<br />
Note: This provisional flight sequence is coherent with the stage propulsion laws<br />
available at the time of drafting this document.<br />
26
8. <strong>EADS</strong> SPACE Transportation<br />
and the ARIANE programmes<br />
<strong>EADS</strong> SPACE Transportation is the European space transportation and orbital<br />
infrastructure specialist. The company designs, develops and builds Ariane family<br />
launchers, the Columbus labora<strong>to</strong>ry and the Au<strong>to</strong>mated Transfer Vehicle (ATV) for<br />
the International Space Station, atmospheric reentry vehicles, ballistic launchers for<br />
France's nuclear deterrent force and propulsion systems for space applications.<br />
<strong>EADS</strong> SPACE Transportation is a subsidiary of <strong>EADS</strong> SPACE. <strong>EADS</strong> SPACE, an<br />
<strong>EADS</strong> subsidiary, specializes in civil and military space systems. The company<br />
achieved 2004 sales worth € 2.6 billion, with a labor force of 11,000 in France,<br />
Germany, the United Kingdom and Spain.<br />
<strong>EADS</strong> SPACE Transportation has acquired extensive expertise, unrivaled in<br />
Europe, as industrial architect or prime contrac<strong>to</strong>r for large-scale strategic and<br />
space programs. This position is based on the company's ability <strong>to</strong> direct and<br />
coordinate the wealth of expertise required <strong>to</strong> design and develop complex projects.<br />
In line with the ESA resolution concerning restructuring of the Ariane launcher<br />
system, involving a redistribution of responsibilities between the various players<br />
involved in design, development and manufacture, Ariane program activities in the<br />
industrial domain are now structured round a single prime contrac<strong>to</strong>r (see European<br />
Space Agency Council Meeting at Ministerial level of May 27, 2003)<br />
As from the current Ariane 5 production batch (PA batch), <strong>EADS</strong> SPACE<br />
Transportation is consequently sole prime contrac<strong>to</strong>r for the Ariane 5<br />
system. In this context, the company is responsible for supplying Arianespace with<br />
complete, tested launchers, and for managing all contracts necessary for launcher<br />
production. <strong>EADS</strong> SPACE Transportation also supplies all component elements<br />
for Ariane 5, including the stages built in its Les Mureaux (France), Bremen<br />
(Germany) and Kourou (French Guiana) facilities, the Vehicle Equipment Bay, the<br />
flight program and numerous sub-assemblies.<br />
<strong>EADS</strong> SPACE Transportation is now the sole point of contact for the European<br />
Space Agency for future launcher development, acting as sole prime contrac<strong>to</strong>r in<br />
this domain also.<br />
<strong>EADS</strong> SPACE Transportation possesses the multidisciplinary expertise required <strong>to</strong><br />
control a program of this complexity:<br />
• program management: risk, configuration, dependability and documentation<br />
management<br />
• technical management: approval of the definition and qualification of launcher<br />
elements, overall coherence control and interface management<br />
• system engineering: integrated system (aerodynamic, acoustic, thermal,<br />
structural, flight mechanics, guidance and attitude control and POGO correction)<br />
studies, and testing (acoustic, thermal, dynamic and electrical models)<br />
• flight programs: design, qualification and development of flight programs, each<br />
specific <strong>to</strong> a particular mission<br />
• cus<strong>to</strong>mer assistance: the company plays a major role in Ariane launch<br />
campaigns, providing support for Arianespace throughout launch operations<br />
• mission analysis and flight data analysis after each launch<br />
27
8. <strong>EADS</strong> SPACE Transportation<br />
and the ARIANE programmes<br />
(continued)<br />
<strong>EADS</strong> SPACE Transportation is prime contrac<strong>to</strong>r for all Ariane 5 launcher stages -<br />
the main cryogenic stage (EPC), solid propellant boosters (EAP) and the various<br />
versions of the upper stage.<br />
The EPC is integrated in the company's vast Les Mureaux complex near Paris. This<br />
site is located close <strong>to</strong> Cryospace, an <strong>EADS</strong> SPACE Transportation/AIR LIQUIDE<br />
joint venture which manufactures the main stage propellant tanks. Also near<strong>by</strong> is<br />
the functional simulation facility where <strong>EADS</strong> SPACE Transportation developed<br />
the launcher's electrical system and software, as well as its guidance-attitude<br />
control and navigation system<br />
To ensure maximum safety, the solid propellant boosters are manufactured in<br />
French Guiana. <strong>EADS</strong> SPACE Transportation integrates the booster stages in<br />
dedicated buildings at the Guiana Space Center (CSG) with the MPS solid propellant<br />
mo<strong>to</strong>r supplied <strong>by</strong> Europropulsion, adding electrical, pyrotechnic, hydraulic,<br />
parachute recovery and other elements supplied from Europe. This is the first time<br />
that a major part of the launcher has been constructed in French Guiana. A<br />
complete Ariane 5 "assembly line" and launch system was built up in French Guiana<br />
between 1988 and 1996, including not only production facilities for the solid<br />
propellant boosters, but also assembly buildings for launcher elements shipped out<br />
from Europe and all payload preparation facilities.<br />
The different versions of the Ariane 5 upper stage are manufactured at the <strong>EADS</strong><br />
SPACE Transportation Bremen site in North Germany. Up <strong>to</strong> five upper stages<br />
can now be assembled simultaneously. The company's other German sites at<br />
Ot<strong>to</strong>brunn near Munich, and Lampoldshausen, supply the combustion chambers for<br />
the Ariane 5 Vulcain main engine, and the Aestus mo<strong>to</strong>r for the basic versions of<br />
the upper stage.<br />
<strong>EADS</strong> SPACE Transportation is also responsible for the Sylda5 (SYstème de<br />
Lancement Double Ariane5) built in its Les Mureaux (France).<br />
Ariane 5 Integration Site in<br />
Les Mureaux (France)<br />
Site internet <strong>EADS</strong> SPACE : www.space.eads.net<br />
Site internet ARIANESPACE : www.arianespace.com<br />
28