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The 198th Ariane mission will place two communications satellite into geostationary transfer orbit: INTELSAT 17 for the international satellite operator Intelsat, and HYLAS 1 for the European operator Avanti Communications.
This will be the 54th Ariane 5 launch. The launcher will be carrying a total payload of 8,867 kg, including 8,069 kg for the INTELSAT 17 and HYLAS 1 satellites, which will be released into their targeted orbits.
The launch will be from Ariane Launch Complex No. 3 (ELA 3) in Kourou, French Guiana.
Launch opportunity:
{colsp=6}#1:
Window |
{colsp=6}
There is O-F's calendar event created for this launch, for which you can request a reminder, that will be sent via e-mail on set time before the launch.
Payload:
Launch Vehicle:
{colsp=2}Characteristics
|
{colsp=2}
Height| up to 52 m
Diameter| up to 5.4 m
Liftoff mass| 780 tonnes
Payload mass| 9.6 tonnes
{colsp=2} Type-C main cryogenic stage:
Live Coverage Of The Launch::
Launch Preparations:
Links:
Countdown & Launch Sequence:
-11:30:00|{colsp=4}
-07:30:00|{colsp=4}
-06:00:00|{colsp=4}
-05:00:00|{colsp=4}
–04:50:00|{colsp=4}
-04:00:00|{colsp=4}
–03:20:00|{colsp=4}
–01:10:00|{colsp=4}
-00:30:00|{colsp=4}
-00:07:00|{colsp=4}
-00:06:30|{colsp=4}
-00:06:00|{colsp=4}
-00:04:00|{colsp=4}
-00:03:40|{colsp=4}
-00:03:30|{colsp=4}
-00:03:10|{colsp=4}
-00:03:00|{colsp=4}
-00:02:30|{colsp=4}
-00:02:00|{colsp=4}
-00:01:50|{colsp=4}
-00:01:05|{colsp=4}
-00:00:37|{colsp=4}
-00:00:30|{colsp=4}
-00:00:22|{colsp=4}
-00:00:16.5|{colsp=4}
-00:00:12|{colsp=4}
{colsp=5}
-00:00:06|{colsp=4}
-00:00:05.5|{colsp=4}
{colsp=5}
-00:00:03|{colsp=4}
-00:00:02.5|{colsp=4}
-00:00:01.4|{colsp=4}
-00:00:00.2|{colsp=4}
+00:00:00|{colsp=4}
+00:00:01|{colsp=4}
+00:00:06.65|{colsp=4}
+00:00:06.9|{colsp=4}
+00:00:07.05|{colsp=4}
{colsp=2}
+00:00:07.31|
+00:00:12.54|
+00:00:17.05|
+00:00:32.05|
+00:00:50.1|
+00:01:08.4|
+00:01:53.6|
+00:02:22.0|
+00:02:22.8|
{colsp=5}
+00:03:10.9|
+00:05:05.0|
+00:07:47.2|
+00:08:54.5|
+00:09:00.5|
{colsp=5}
+00:09:01.4|
+00:09:04.6|
+00:12:27.4|
+00:13:26.4|
+00:14:00.4|
+00:18:06.6|
+00:18:18.2|
+00:20:05|
+00:23:05.7|
+00:24:46.5|
{colsp=5}
+00:24:59|{colsp=3}
+00:27:25|{colsp=2}
+00:27:35|{colsp=3}
+00:29:41|{colsp=2}
+00:29:51|{colsp=3}
+00:34:47|{colsp=2}
+00:34:57|{colsp=3}
+00:42:36|{colsp=3}
+00:44:06|{colsp=3}
+00:45:02|{colsp=3}
+00:45:47|{colsp=3}
+00:49:36|{colsp=3}
+00:49:40|{colsp=2}
Injection Orbit:
(*) in relation to a fixed axis, frozen at H0 - 3s and passing through the ELA3 launch complex in Kourou.
This will be the 54th Ariane 5 launch. The launcher will be carrying a total payload of 8,867 kg, including 8,069 kg for the INTELSAT 17 and HYLAS 1 satellites, which will be released into their targeted orbits.
The launch will be from Ariane Launch Complex No. 3 (ELA 3) in Kourou, French Guiana.
Launch opportunity:
Window |
Universal / UTC
|
Paris / CEST
|
Kourou / GFT
|
Washington / EDT
|
Tokyo / JST
start:
|
18:39
|
19:39
|
15:39
|
1:39 p.m.
|
03:39
end:
|
21:54
|
22:54
|
18:54
|
4:54 p.m.
|
06:54
on:
|
Nov. 26, 2010
|
Nov. 26, 2010
|
Nov. 26, 2010
|
Nov. 26, 2010
|
Nov. 27, 2010
{colsp=6}
[highlight]L[eventtimer]2010-11-26 18:39;%c%%ddd%/%hh%:%mm%:%ss%[/eventtimer][/highlight]
There is O-F's calendar event created for this launch, for which you can request a reminder, that will be sent via e-mail on set time before the launch.
Payload:
INTELSAT 17:
HYLAS 1:
|
INTELSAT 17 is a telecommunication satellite built by SPACE SYSTEMS / LORAL in Palo Alto (California) for the operator INTELSAT. It is LORAL's 45th satellite delivery to INTELSAT.
INTELSAT 17 is a powerful satellite designed to provide a wide range of telecommunication services in Europe, the Middle East, Russia and Asia. With a mass of 5.5 tons, INTELSAT 17 will occupy an orbital position of 66 degrees East and will enable INTELSAT to extend its C-band coverage while providing video services for the Indian Ocean region. INTELSAT 17 will replace the INTELSAT 702 satellite.
INTELSAT 17 is the 49th satellite entrusted to the Ariane range by INTELSAT (INTELSAT, GALAXY, PAS, PANAMSAT and TELSTAR families) since INTELSAT F7 (Flight 7, Ariane 1, on 19th October 1983).
INTELSAT 17 is a powerful satellite designed to provide a wide range of telecommunication services in Europe, the Middle East, Russia and Asia. With a mass of 5.5 tons, INTELSAT 17 will occupy an orbital position of 66 degrees East and will enable INTELSAT to extend its C-band coverage while providing video services for the Indian Ocean region. INTELSAT 17 will replace the INTELSAT 702 satellite.
INTELSAT 17 is the 49th satellite entrusted to the Ariane range by INTELSAT (INTELSAT, GALAXY, PAS, PANAMSAT and TELSTAR families) since INTELSAT F7 (Flight 7, Ariane 1, on 19th October 1983).
HYLAS 1:
HYLAS 1 is a 2.5 ton satellite, built by an industrial consortium comprising Astrium and the Indian Space Research Organisation (ISRO), on behalf of the new British operator Avanti. It was built around ISRO's I-2K platform, already used for the Indian INSAT satellites. The payload was designed and built by Astrium and then delivered to Bangalore in India, where satellite integration and testing took place before shipment to French Guiana.
HYLAS 1 is an innovative telecommunication satellite equipped with Ka and Ku band repeaters, designed to offer broadband services across Europe, and more particularly to remote rural areas, from its orbital position of 33.5 degrees West.
HYLAS 1 is an innovative telecommunication satellite equipped with Ka and Ku band repeaters, designed to offer broadband services across Europe, and more particularly to remote rural areas, from its orbital position of 33.5 degrees West.
Characteristics
|
INTELSAT 17
|
HYLAS 1
Customer:
|
- INTELSAT
- AVANTI Communications
Prime contractor:
|
- SPACE SYSTEMS LORAL
- ASTRIUM and ISRO
Mission:
|
- Telecommunications satellite
- Broadband services
Mass:
|
- Total mass at lift-off: 5 540 kg
- Dry mass: 2 393 kg
- Total mass at lift-off: 2 570 kg
- Dry mass: 1 125 kg
Stabilization:
|
- 3 axis stabilized
- Slow transverse spin on launcher/satellite separation
- 3 axis stabilized
Dimensions:
|
- 7.7 x 2.7 x 3.4 m
- Span in orbit: 36.1 m
- 2.5 x 1.6 x 1.5 m
- Span in orbit: 36 m
Platform:
|
- LS 1300 OMEGA BUS
- I-2 K Bus
Payload:
|
- 46 Ku-band transponders
- 28 C-band transponders
- 8 Ka-band transponders
- 2 Ku-band transponders
On-board power:
|
- 12.4 kW (end of life)
- Lithium Ion cell batteries
- 3200 W (end of life)
Propulsion:
|
- R-4D-11
- 440 Newton thrust biliquid apogee motor
Life time:
|
- 15 years
- 15 years
Orbital position:
|
- 66° East
- 33.5° West
Coverage area:
|
- Europe, Middle East, Russia, Africa, Central Asia
- Europe
Images (clickable)
|
Launch Vehicle:
Ariane 5 ECA
Height| up to 52 m
Diameter| up to 5.4 m
Liftoff mass| 780 tonnes
Payload mass| 9.6 tonnes
The latest version of the Ariane 5 launcher, Ariane 5 ECA, is designed to place payloads weighing up to 9.6 tonnes into GTO. With its increased capacity, Ariane 5 ECA can handle dual launches of very large satellites.
Launcher L556
The upper composite is mounted on the main cryogenic stage (EPC) and incorporates:
- Fairing
- SYLDA 5 payload carrier structure,
- The Upper Composite, which comprises:
- ESC-A cryogenic upper stage
- Vehicle Equipment Bay
- 3936 cone
The lower composite incorporates:
- EPC (H175) main cryogenic stage with the new Vulcain 2 engine
- two EAP (P240) solid propellant strap-on boosters secured on either side of the EPC
{colsp=2} Type-C main cryogenic stage:
The EPC is over 30 m high. It has a diameter of 5.4 m and an empty mass of only 14.1 metric tons. It essentially comprises:
- large aluminium alloy tank;
- thrust frame transmitting engine thrust to the stage;
- forward skirt connecting the EPC to the upper composite, and transmitting the thrust generated by the two solid propellant strap-on boosters.
The tank is divided into two compartments containing 175 tons propellant (approximately 25 tons liquid hydrogen and 149.5 tons liquid oxygen). The Vulcain 2 engine delivers of the order of 136 tons thrust, and is swivel-mounted (two axes) for attitude control by the GAM engine actuation unit. The main stage is ignited on the ground, so that its correct operation can be checked before authorizing lift-off.
The main stage burns continuously for about 535 s, and delivers the essential part of the kinetic energy required to place the payloads into orbit.
The main stage also provides a launcher roll control function during the powered flight phase by means of the SCR (roll control system).
On burnout at an altitude of 178 km for this mission, the stage separates from the upper composite and falls back into the Atlantic Ocean.
Type-C solid propellant strap-on boosters:
Each booster is over 31 m high, and has a diameter of 3 m and an empty mass of 38 tons. Each booster contains 240 tons solid propellant, and essentially comprises:
- booster case assembled from seven steel rings,
- steerable nozzle (pressure ratio Σ = 11), operated by a nozzle actuation unit (GAT),
- propellant in the form of three segments.
Compared with the ARIANE 5 “generic” version of the booster stage, the main changes include the elimination of one GAT cylinder, overloading of segment S1 to increase thrust on lift-off, and the use of a reduced mass nozzle (this reduces the mass of the structure by about 1.8 tonnes).
Type-A cryogenic upper stage:
The ESC-A 3rd stage has been developed for the ARIANE 5 ECA version of the ARIANE 5 Plus launcher, and is based on the HM7B engine previously used for the 3rd stage of the Ariane 4 launcher.
The ESC-A stage comprises:
- two tanks containing 14.7 tons propellant (LH2 and LOX),
- HM7B engine delivering 6.5 tons thrust in vacuum for a burn time of about 936 s. The HM7B nozzle is swivel-mounted (two axes) for attitude control.
The ESC-A delivers the additional energy required to place the payloads into target orbit. This stage also provides a roll control function for the upper composite during the powered flight phase, and orients the payloads ready for separation during the ballistic phase using the SCAR (attitude and roll control system).
The C-Fibre Placement type Equipment Bay:
The vehicle equipment bay (VEB) is a cylindrical carbon structure mounted on the ESC-A stage. The VEB contains part of the electrical equipment required for the mission (two OBCs, two inertial guidance units, sequencing electronics, electrical power supplies, telemetry equipment, etc.). For the third time, the VEB cylinder and cone have been produced using a new process involving depositing carbon fibres on a mould before baking of the structure.
The upper composite (ESC-A stage + VEB + 3936 cone) for launcher L556 was assembled for the seventeenth time at the Astrium ST site in Bremen, in order to meet needs resulting from the increase in production rates for the coming years.
Nose fairing:
The ogival nose fairing protects the payloads during the atmospheric flight phase (acoustic protection on lift-off and during transonic flight, aerothermodynamic flux).
A long pattern fairing is used for this mission. It has a height of 17 m and a diameter of 5.4 m.
The fairing structure includes two half-fairings comprising 10 panels. These sandwich panels have an expanded aluminium honeycomb core and two carbon fibre/resin skins.
The fairing is separated from the launcher by two pyrotechnic devices, one horizontal (HSS) and the other vertical (VSS). The vertical device imparts the impulse required for lateral separation of the two half-fairings.
The fairing has been coated with a new FAP (Fairing Acoustic Protection) product since flight 175-L534.
SYLDA 5 (ARIANE 5 dual-launch system):
This system provides for a second main payload inside one of the three fairing models. There are six different versions of this internal structure which has a diameter of 4.6 m. SYLDA height varies between 4.9 and 6.4 m (0.3 m increments) for useful payload volumes between 50 and 65 m3.
For this mission, a SYLDA 5 ‘A’ with a height of 6.4 m will be used. It enables the carriage of a payload in the lower position, HYLAS.
Live Coverage Of The Launch::
You can watch the broadcast of the launch live on Arianespace's Videocorner.
The live coverage for the first launch attempt on Videocorner will start 20 minutes before the window opening time, at about 18:20 UTC / 1:20 p.m. EDT - i.e.[eventtimer]2010-11-26 18:20? in| ;%c% %h%:%mm%[/eventtimer] hours[eventtimer]2010-11-26 18:20?.| ago.;%c%[/eventtimer]
You can also watch the launch on TV via satellite (where available), from: HOT BIRD™ (Transponder 155), 13° East, Frequency: 11604 MHz, Horizontal Polarisation, Symbol rate: 27.500 Msps, FEC 5/6, DVB-S, QPSK, MPEG-2, No encryption / Free to air.
The live coverage for the first launch attempt on Videocorner will start 20 minutes before the window opening time, at about 18:20 UTC / 1:20 p.m. EDT - i.e.[eventtimer]2010-11-26 18:20? in| ;%c% %h%:%mm%[/eventtimer] hours[eventtimer]2010-11-26 18:20?.| ago.;%c%[/eventtimer]
You can also watch the launch on TV via satellite (where available), from: HOT BIRD™ (Transponder 155), 13° East, Frequency: 11604 MHz, Horizontal Polarisation, Symbol rate: 27.500 Msps, FEC 5/6, DVB-S, QPSK, MPEG-2, No encryption / Free to air.
Launch Preparations:
Timeline:
Arianespace mission updates:
Date
|
Event
Sep. 17, 2010
|
- Campaign start review
- EPC depreservation and erection in the launcher integration building (BIL)
Sep. 18, 2010
|
- Transfer of Solid Booster Stages (EAP)
Sep. 20, 2010
|
- Mating of the EAPs with the EPC
Sep. 22, 2010
|
- Depreservation and erection of the Upper Composite
Oct. 07, 2010
|
- Launcher Synthesis Control
Oct. 12, 2010
|
- Arrival in Kourou of HYLAS 1 and beginning of preparation campaign in building S1 B
Oct. 25, 2010
|
- Arrival in Kourou of INTELSAT 17 and beginning of preparation campaign in building S1 B
Nov. 02, 2010
|
- Launcher acceptance by Arianespace
Nov. 5, 2010
|
- Transfer from BIL to BAF
Nov. 8-10, 2010
|
- HYLAS 1 filling operations
Nov. 11-13, 2010
|
- INTELSAT 17 filling operations
Nov. 14, 2010
|
- INTELSAT 17 integration on adaptor (ACU)
Nov. 15, 2010
|
- INTELSAT 17 transfer to Final Assembly Building (BAF)
- HYLAS 1 integration on adaptor
Nov. 16, 2010
|
- INTELSAT 17 integration on Sylda
Nov. 17, 2010
|
- Fairing integration on Sylda
- HYLAS 1 transfer to Final Assembly Building (BAF)
Nov. 18, 2010
|
- HYLAS 1 integration on launcher
Nov. 19, 2010
|
- Upper composite integration with INTELSAT 17 on launcher
Nov. 20, 2010
|
- ESC-A final preparations and payloads control
Nov. 22, 2010
|
- Launch rehearsal
Nov. 23, 2010
|
- Arming of launch vehicle
Nov. 24, 2010
|
- Arming of launch vehicle
- Launch readiness review (RAL) and final preparation of launcher
Nov. 25, 2010
|
- Roll-out from BAF to Launch Area (ZL), launch vehicle connections and filling of the EPC liquid Helium sphere
Nov. 26, 2010
|
- Launch countdown including EPC and ESC-A filling with liquid oxygen and liquid hydrogen
Arianespace mission updates:
- 2010-10-29: Payload preparations are underway for Arianespace's fifth Ariane 5 mission of 2010
- 2010-11-08: Arianespace’s fifth Ariane 5 is ready to receive its Intelsat 17 and HYLAS 1 satellite payloads
- 2010-11-24: Arianespace’s Ariane 5 mission is a “go” with Intelsat 17 and HYLAS 1
- 2010-11-25: Ariane 5 is ready for Arianespace’s fifth launch of 2010
Links:
- Arianespace:
- Arianespace to launch HYLAS
- Ariane 5 launcher
- Launch Kit:
- ESA:
- Hylas home page
- Hylas-1 video
- ESA Telecom: Hylas-1 project overview
- News:
- 2006-05-15: Contract for the innovative flexible broadband satellite HYLAS
- 2006-11-10: Bringing satellite broadband to Britain
- 2009-11-06: Hylas-1 payload shipped to India
- 2010-06-04: Hylas-1 on schedule for launch
- 2010-09-29: Hylas-1 gets green light for spaceport trip
- 2010-10-20: Hylas-1 satellite readied for launch from Europe’s Spaceport
- 2010-11-19: Hylas-1 mated with its launcher
- 2010-11-23: Hylas-1 advances European telecom technology
- 2010-11-25: “After launch, our real mission begins”: Andrea Cotellessa, Hylas-1 Project Manager interview
- 2010-11-26: Hylas-1 in place for launch
- 2010-11-26: Hylas-1 launch
- Intelsat:
- EADS Astrium:
- UK Space Agency:
- Broadband TV News:
- Aviation Week: Arianespace To Launch Intelsat 17
- Avanti communications: Launch date set for HYLAS 1
- Spaceflight Now: Ariane 5 launcher ready for another dual-payload flight
EnglishCountdown & Launch Sequence:
H0-[HH:MM:SS]
|{colsp=4}
Event
-11:30:00|{colsp=4}
- Start of final countdown
-07:30:00|{colsp=4}
- Checkout of electrical systems.
- Flushing and configuration of the EPC and Vulcain engine for fuelling and chilldown
-06:00:00|{colsp=4}
- Final preparation of the launch pad: closure of doors, removal of safety barriers, configuration of the fluid circuits for fuelling.
- Loading of the flight program
- Testing of radio links between the launcher and BLA
- Alignment of inertial guidance units
-05:00:00|{colsp=4}
- Evacuation of personnel from the launch pad
- Pressurization of the attitude control and command systems: (GAT for the EAPs and GAM for the EPC)
–04:50:00|{colsp=4}
- Fuelling of the EPC in four phases:
- pressurization of the ground tanks (30 minutes)
- chilldown of the ground lines (30 minutes)
- fuelling of the stage tanks (2 hours)
- topping up (up to synchronized sequence)
-04:00:00|{colsp=4}
- Fuelling of the ESC-A stage in four phases:
- pressurization of the ground tanks (30 minutes)
- chilldown of the ground lines (30 minutes)
- fuelling of the stage tanks (1 hour)
- topping up (up to synchronized sequence)
–03:20:00|{colsp=4}
- Chilldown of Vulcain main stage engine
–01:10:00|{colsp=4}
- Check of connections between launcher and telemetry, tracking and command systems
-00:30:00|{colsp=4}
- Preparation of the synchronized sequence
-00:07:00|{colsp=4}
- Beginning of the synchronized sequence
-00:06:30|{colsp=4}
- Termination of topping up (LOX and LH2)
- LOX and LH2 topped up to flight value
- Launch pad safety flood valves opened
- Arming of pyrotechnic line safety barriers
-00:06:00|{colsp=4}
- Isolation of the ESC-A helium sphere
-00:04:00|{colsp=4}
- Flight pressurization of EPC tanks
- Isolation of tanks and start of EPC ground/OB interface umbilical circuit flushing
- Termination of ESC-A LOX topping up
- ESC-A LOX transition to flight pressure
-00:03:40|{colsp=4}
- Termination of ESC-A LH2 topping up
-00:03:30|{colsp=4}
- Calculation of ground H0 and verification that the second OBC has switched to the observer mode
-00:03:10|{colsp=4}
- ESC-A LH2 transition to flight pressure
-00:03:00|{colsp=4}
- H0 loaded in the 2 OBCs
- H0 loaded in OBCs checked against ground H0
-00:02:30|{colsp=4}
- Electrical heating of EPC and VEB batteries, and electrical heating of the Vulcain 2 ignition system shut down
-00:02:00|{colsp=4}
- Vulcain bleeder valves opened
- Engine ground chilldown valve closed
-00:01:50|{colsp=4}
- Pre-deflection of the HM7B nozzle
-00:01:05|{colsp=4}
- Termination of ESC-A tank pressurization from the ground, and start of ESC-A valve plate seal-tightness checkout
- Launcher electrical power supply switched from ground to OB
-00:00:37|{colsp=4}
- Start-up of ignition sequence automatic control system
- Start-up of OB measurement recorders
- Arming of pyrotechnic line electric safety barriers
-00:00:30|{colsp=4}
- Verification of ground/OB umbilical circuit flushing
- EPC fuel flood valves opened
-00:00:22|{colsp=4}
- Activation of launcher lower stage attitude control systems
- Authorization for switchover to OBC control
-00:00:16.5|{colsp=4}
- Pressurization of POGO corrector system
- Ventilation of fairing POP and VEB POE connectors and EPC shut down
-00:00:12|{colsp=4}
- Flood valves opening command
{colsp=5}
IRREVERSIBLE SEQUENCE
-00:00:06|{colsp=4}
- Arming and ignition of AMEFs to burn hydrogen run-off during chill-down of the combustion chamber on Vulcain ignition
- Valve plate and cryogenic arm retraction commands
-00:00:05.5|{colsp=4}
- Ground information communication bus control switched to OBC
{colsp=5}
IGNITION SEQUENCE
-00:00:03|{colsp=4}
- Checkout of computer status
- Switchover of inertial guidance systems to flight mode
- Helium pressurization activated
- LOX and LH2 pressures monitored
- Navigation, guidance and attitude control functions activated
-00:00:02.5|{colsp=4}
- Verification of HM7B nozzle deflection
-00:00:01.4|{colsp=4}
- Engine flushing valve closed
-00:00:00.2|{colsp=4}
- Verification of acquisition of the “cryogenic arms retracted” report by the OBC at the latest moment
+00:00:00|{colsp=4}
- Vulcain engine ignition
+00:00:01|{colsp=4}
- Opening of the hydrogen chamber valve
+00:00:06.65|{colsp=4}
- Vulcain engine verification of its correct operation
+00:00:06.9|{colsp=4}
- End of Vulcain engine checkout
+00:00:07.05|{colsp=4}
- Ignition of the EAPs
{colsp=2}
EAP-EPC powered flight
|
mass (Mg)
|
Vrel (m/s)
|
altitude (km)
+00:00:07.31|
- Lift-off
773.8
|
0
|
0
+00:00:12.54|
- Start of tilt manoeuvre
747.2
|
35.9
|
0.090
+00:00:17.05|
- Start of roll manoeuvre
723.2
|
73.6
|
0.347
+00:00:32.05|
- End of roll manoeuvre
645.8
|
210.1
|
2.440
+00:00:50.1|
- Transsonic (Mach = 1)
575.8
|
324.1
|
7.020
+00:01:08.4|
- Speed at Pdyn max
503.2
|
506.0
|
13.4
+00:01:53.6|
- Transition to γmax (41.2 m/s2)
305.6
|
1564.7
|
41.1
+00:02:22.0|
- Transition to γ = 6.15 m/s2 H1
251.2
|
1992.1
|
67.9
+00:02:22.8|
- EAP separation
176.1
|
1993.5
|
68.6
{colsp=5}
EPC powered flight
+00:03:10.9|
- Fairing jettisoned
158.2
|
2195
|
106.8
+00:05:05.0|
- Intermediate point
121.3
|
3043
|
163.3
+00:07:47.2|
- Acquisition Natal
68.6
|
5311
|
179.9
+00:08:54.5|
- EPC burnout (H2)
46.9
|
6897
|
177.8
+00:09:00.5|
- EPC separation
28.0
|
6924
|
177.9
{colsp=5}
ESC-A powered flight
+00:09:01.4|
- Lost Galliot
28.0
|
6925
|
177.9
+00:09:04.6|
- ESC-A ignition
28.0
|
6926
|
177.9
+00:12:27.4|
- Lost Natal
25.1
|
7415
|
169.8
+00:13:26.4|
- Acquisition Ascension
24.2
|
7566
|
167.7
+00:14:00.4|
- Minimum altitude
23.7
|
7655
|
167.3
+00:18:06.6|
- Lost Ascension
20.1
|
8304
|
203.3
+00:18:18.2|
- Acquisition Libreville
19.9
|
8336
|
207.7
+00:20:05|
- Intermediate point
18.3
|
8615
|
263.4
+00:23:05.7|
- Acquisition Malindi
15.6
|
9096
|
456.5
+00:24:46.5|
- ESC-A burnout (H3-1)
14.1
|
9365
|
638.4
{colsp=5}
“Ballistic” phase
+00:24:59|{colsp=3}
- Phase 3 - Start of INTELSAT 17 orientation
666
+00:27:25|{colsp=2}
- INTELSAT 17 separation (H4.1)
9030
|
1036
+00:27:35|{colsp=3}
- Phase 5 - Start of SYLDA orientation
1064
+00:29:41|{colsp=2}
- SYLDA separation (H4.2)
8706
|
1456
+00:29:51|{colsp=3}
- Phases 7 & 8 - Start of HYLAS orientation
1490
+00:34:47|{colsp=2}
- HYLAS separation (H4.3)
7945
|
2585
+00:34:57|{colsp=3}
- Phases 10 to 13 - ESC-A breakaway
2624
+00:42:36|{colsp=3}
- Phase 14 - ESC-A orientation for the final spin-up
4543
+00:44:06|{colsp=3}
- Phase 15 - Start of spin-up at 45°/s
4931
+00:45:02|{colsp=3}
- Oxygen tank passivation (breakdown S34)
5173
+00:45:47|{colsp=3}
- Phase 16 - Start of ESC-A pre-passivation
5366
+00:49:36|{colsp=3}
- ESC-A passivation (breakdown S37)
6342
+00:49:40|{colsp=2}
- End of Arianespace Flight mission
6105
|
6354.2
Injection Orbit:
Perigee altitude:
| 250 kmApogee altitude:
| 35 786 kmInclination:
| 2.0°Perigee argument:
| 178°Ascending node longitude:
| -121.87°(
*
)(*) in relation to a fixed axis, frozen at H0 - 3s and passing through the ELA3 launch complex in Kourou.
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