MISSION OVERVIEW GE-1A Launch on the Proton Launch Vehicle
October 2000
MISSION OVERVIEW GE-1A Launch on the Proton Launch Vehicle
October 2000
Typical Launch Countdown and Flight Events Summary EVENT
HR:MIN:SEC
Stage one ignition, 40% thrust
-00:00:01
Begin stage one thrust to 100%
00:00:00
Liftoff
00:00:00.57
Stage one thrust to 100%
00:00:01
Maximum dynamic pressure
00:00:70
Stage two ignition
00:02:00
Stage one/two separation
00:02:06.7
Stage three vernier engine ignition
00:05:30.0
Stage two engine shut down
00:05:32.0
Stage two/three separation
00:05:35.0
Stage three main engine ignition
00:05:37.0
Payload fairing jettison
00:05:44.2
Stage three main engine shutdown
00:09:30
Stage three vernier engine shutdown
00:09:48.3
Stage three upper stage separation (Block DM)
00:09:48.7
Block DM upper adapter jettison
00:10:43.7
SOZ unit first settling burn (SOZ 1)
01:08:50
Block DM first burn
01:13:49
SOZ unit second settling burn (SOZ 2)
06:15.05
Block DM second burn
06:20.04
Block DM payload separation
06:41:54 GE-1A Mission Overview ii
Table of Contents Sections Section 1 - GE-1A Program Overview . . . . . . . . . . . . . . . . . . . . . . . . 1-1 Section 2 - Proton ascent profile. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 Section 3 - Proton Overview. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1 Section 4 - Launch Campaign Processing . . . . . . . . . . . . . . . . . . . . . . . . . 4-1 Section 5 - Launch Management. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
5-1
Section 6 - History. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .
6-1
List of Figures Figure 1-1 GE-1A shown deployed on orbit . . . . . . . . . . . . . . . . . . . . 1-2 Figure 2-1 Proton ascent profile . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1 Figure 2-2 Proton ascent ground track and vacuum impact points. . . . . . . 2-3 Figure 2-3 Insertion into GTO . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-3 Figure 3-1 Proton family of vehicles . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-2 Figure 3-2 Major components of the Proton D-1-e launch vehicle . . . . . . . . 3-4 Figure 3-3 Standard Proton payload fairings . . . . . . . . . . . . . . . . . . . . . . . .
3-5
Figure 4-1 Overview of Baikonur Cosmodrome . . . . . . . . . . . . . . . . . . . . . . 4-1 Figure 4-2 Detailed view of the Baikonur Cosmodrome . . . . . . . . . . . . . . . . 4-2 Figure 4-3 Transportation of the GE-1A satellite to Baikonur . . . . . . . . 4-3 Figure 5-1 ILS management structure . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5-1 Figure 6-1 Organization of International Launch Services . . . . . . . . . . . . . 6-1 Figure 6-2 ILS strategic advantages. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-2 GE-1A Mission Overview iii
Section 1
GE-1A Program Overview Mission Objective
improvements and a 15-year design life.
Americom Asia-Pacific, LLC is a joint venture
The payload configuration provides 28 high
formed by GE American Communications, Inc.
powered Ku-Band transponders. The spacecraft
and Lockheed Martin Global Telecommunications
has dual surface, shaped, 96-inch, 85-inch and 44-
to provide satellite telecommunications services in
inch reflectors and is a three-axis stabilized plat-
Asia.
form with single-axis oriented multi-panel solar
Combining unmatched expertise in satellite
arrays. The dry mass of the spacecraft is approx-
communications, customer knowledge, world
imately 1,601 kg and the liftoff mass is approxi-
renowned state-of-the-art technology and global
mately 3,593 kg after the spacecraft is loaded with
name recognition, Americom Asia-Pacific, LLC
propellants. The physical dimensions (L x W x H)
will offer the highest-level of customer service.
of the spacecraft are approximately 3.1 m x 2.5 m
Initially, Americom Asia-Pacific is planning to
x 6.1 m. Fully deployed, it will measure approxi-
provide broadcasting and telecommunications in
mately 27 meters across the solar wing span and
India, China, and SE Asia. The company plans to
approximately 9 meters across the antennas. The Proton/GE-1A mission is to inject the
provide a full range of services on a global scale. The GE-1A spacecraft was built by Lockheed
spacecraft into an optimized Geosynchronous
Martin Space Systems Company in Sunnyvale,
Transfer Orbit (GTO). Following separation from
California for Americom Asia-Pacific, LLC.. The
the Block DM upper stage, the spacecraft onboard
A2100AX represents the newest generation of
liquid apogee engine will be fired in a series of
satellites, designed specifically for geostationary
burns to raise perigee, lower inclination and to cir-
communications missions, which takes advantage
cularize the orbit. The satellite will be eventually
of benefits derived from the latest technology
located in geostationary orbit at 108 degrees E.L.
GE-1A Mission Overview 1-1
Figure 1-1 GE-1A shown deployed on-orbit
GE-1A Mission Overview 1-2
Section 2
Proton Ascent Profile Proton Ascent Profile
Once GE-1A is in the parking orbit, it will be propelled to its transfer orbit by the Block DM.
The first three stages of the Proton will use a standard ascent trajectory to place the fourth
The six, stage one RD-253 engines are ignited
stage, or Block DM, and GE-1A satellite into a
at approximately T-1.8 seconds and are com-
200 km (108 nautical miles) circular parking orbit
manded to 40% of nominal thrust.
inclined at 51.6 degrees as shown in Figure 2-1.
increased to 100% at T-0 seconds. Liftoff confir-
Thrust is
Figure 2-1 Proton ascent profile
GE-1A Mission Overview 2-1
mation is signaled at T+0.57 seconds. The staged
onds after third stage separation, the Block DM
ignition sequence allows verification that all
releases its shrouds and executes a series of pro-
engines are functioning nominally before being
grammed turns, culminating in a maneuver to
committed to launch. The Proton executes a roll
properly align its longitudinal axis for the first
maneuver beginning at T+10 seconds to align the
burn. After the alignment maneuver, the Block
flight azimuth to the desired direction. The vehi-
DM enters into a stabilized flight mode. Twenty
cle incurs its maximum dynamic pressure of 800
five minutes after the longitudinal alignment
pounds per square foot at approximately 70 sec-
maneuver, the Block DM executes a 180-degree
onds into the flight. After the flight of the first
turn about the roll axis to compensate for possible
stage, stage two’s four RD-0210 engines begin
gyroscopic drift.
their ignition sequence and are commanded to full
maneuver, the Block DM reaches the first ascend-
thrust when stage one is jettisoned at 126.7 sec-
ing node, and the two SOZ unit’s axial loading
onds. Stage three’s vernier engines are ignited at
engines begin a 300.0 second burn to settle the
330.0 seconds followed by stage two shutdown at
propellants. After the settling burn, the main
332.0 seconds. Stage two separation occurs after
engine ignites, raising the transfer orbit apogee to
six small, solid retro-fire motors are ignited at
slightly above geosynchronous altitude. See
335.1 seconds into flight. Stage three’s single RD-
Figures 2-2, 2-3. The first main engine burn lasts
0210 engine is ignited at 337.0 seconds and burns
approximately 402.0 seconds. The Block DM then
until shut down at 570.0 seconds. The four vernier
enters stabilized flight for approximately five
engines burn for an additional 10 seconds and are
hours required in order to reach transfer orbit
shutdown at 588.3 seconds. After a five second
apogee. During this time, the Block DM executes
coast, the stage three retro-fire motors are ignited
maneuvers to meet GE-1A sun angle and thermal
and stage three is separated from the upper stage.
constraints.
Payload fairing jettison occurs during stage three
apogee, the Block DM initiates another 300.0 sec-
flight at 344.2 seconds.
ond propellant settling burn followed by a main
Forty minutes after the roll
After reaching the transfer orbit
The Block DM and GE-1A are delivered to the
engine burn to raise perigee and reduce inclina-
215 km (116 nautical miles) near-circular parking
tion. The Block DM then maneuvers to prepare
orbit with a 51.6 degree inclination. Fifty five sec-
for spacecraft separation.
Separation occurs
GE-1A Mission Overview 2-2
approximately six hours and 41 minutes after lift-
lower its inclination in order to arrive in geosta-
off. After separation, GE-1A will perform a series
tionary orbit.
of apogee burns that will raise its perigee and
Figure 2-2 Proton ascent ground track and vacuum impact points
Figure 2-3 Insertion into orbit
GE-1A Mission Overview 2-3
Section 3
Proton Overview Proton Overview
Background and History
Proton is the most capable, commercial,
Development of the Proton launch vehicle was
expendable launch vehicle presently in opera-
undertaken in the early 1960s, under the direction
tional service.
It offers larger beginning-of-life
of the Soviet academician, V. N. Chelomey. The
(BOL) masses in geostationary orbit (GSO) than
first launch took place in July 1965. The two-
any other commercial launch system, as well as
stage D version, last flown in 1966, was used to
larger delivered payload masses into most low-,
launch four flights of the Proton satellite series,
intermediate-, and high-energy orbits. Proton’s
from which the launch vehicle takes its name.
three-stage configuration is used primarily to
The two-stage D version has been superseded by
launch large payloads into low earth orbit, while
the three-stage D-1 (SL-13) model and the four-
the four-stage configuration is used to launch
stage D-1-e (SL-12) model, both of which are cur-
spacecraft
high-energy trajectories (geo-
rently in use. An improved version of the Proton
transfer, geosynchronous, geostationary, and
(Proton M) is now in development. Figure 3-1
interplanetary).
shows the Proton launch vehicle family.
into
Proton’s fourth stage possesses a multiple restart
The Block DM fourth stage of the Proton was
capability that allows it to perform all orbit change
developed independently during the 1960s as the
maneuvers necessary to place a spacecraft into its
fifth stage of the Russian manned lunar launch
final orbit, without requiring use of the spacecraft’s
vehicle, the N1-L3. It was originally known in
on-board propellant supply. Proton can deliver
Russia as the Block D (“block” is the common
payloads of up to 22 metric tons to low-earth orbit,
translation of the Russian word denoting a rocket
or up to 2.1 metric tons to geosynchronous orbit.
“stage”, while “D” is the fifth letter in the Russian
GE-1A Mission Overview 3-1
Figure 3-1 Proton family of vehicles
GE-1A Mission Overview 3-2
cess rate over its last 50 launches.
alphabet). The vehicle was upgraded during the 1970s to the current Block DM (modernized) version. The Proton model numbers D, D-1, D-1-e,
General Description of the Proton Family
SL-13, and SL-12 are the designations currently
The Proton is currently available as a three-
in common use in the United States, with the D
stage D-1 (SL-13) model and as a four-stage D-1-e
numbers having been applied by the Library of
(SL-12) model which will be used for commercial
Congress and the SL numbers originating with
launches. See Figure 3-2. A variety of supple-
the U.S. Department of Defense.
mental orbital propulsion units, in a range of
Proton has flown more than 200 missions and
capabilities, can be used with either the three- or
has orbited the Salyut series space stations and
the four-stage Proton. In addition, there are mul-
the Mir Space station modules. It has launched
tiple fairing designs presently qualified for flight.
the Ekran, Raduga, and Gorizont series of geosta-
A “Standard Commercial Payload Fairing” has
tionary communications satellites (which provided
been developed specifically to meet the needs of
telephone, telegraph, and television service within
western customers.
Russia and between member states of the
The lower three stages of the Proton are pro-
Intersputnik Organization), as well as the Zond,
duced by the Khrunichev State Research and
Luna, Venera, Mars, Vega, and Phobos inter-plan-
Production Space Center (KhSC) plant in Moscow.
etary exploration spacecraft. The Proton has also
Production of the Block DM fourth stage is carried
launched the entire constellation of Glonass posi-
out by Russian Space Complex (RSC) Energia,
tion location satellites. All Russian geostationary
also in Moscow. Production capacity for the com-
and interplanetary missions are launched on
mercial Proton is approximately five to six vehi-
Proton. Approximately 90% of all Proton launch-
cles per year.
es have been the four-stage version.
Overall height of the vehicle in either configu-
The Proton launch vehicle has a long history of
ration is approximately 61 m (200 ft), while the
outstanding reliability. From its first operational
diameter of the second and third stages, and of the
launch in 1970 to the present day, Proton has
first stage core tank, is 4.1 m (13.5 ft). Maximum
averaged a 92.5% success rate. Today, the Proton
diameter of the first stage, including the outboard
launch vehicle has a 96% (moving average) suc-
fuel tanks, is 7.4 m (24.3 ft). The Block DM fourth
GE-1A Mission Overview 3-3
stage, when present, has an external diameter of
(20.6 ft) in length, with an inert mass at separa-
3.7 m (12.1 ft). Total weight of the Proton at launch
tion of 2,440 kg (5,378 lbm) and a total propellant
is approximately 691,500 kg (1,524,000 lbm).
mass of 15,050 kg (33,180 lbm). It is three-axis stabilized in unpowered flight by a storable bipro-
D-1-e (Four-Stage) Variant
pellant (N2O4/UDMH) attitude control system, comprised of two “SOZ” (or “micro”) thruster units
The Proton D-1-e (which will launch GE-1A) is a series-staged vehicle consisting
Payload
of four stages. The lower three
Fourth Stage Equipped with one liquid propellant rocket engine developing 86kN thrust, and two “micro” engine clusters for attitude control and ullage maneuvers.
stages are identical to those of the three-stage Proton D-1, and use
Fairing
nitrogen tetroxide (N2O4) and unsymmetrical
dimethylhy-
Forward shroud
drazine (UDMH) as propellants.
Third Stage Equipped with one fixed singlechamber liquid propellant rocket engine developing 0.6 MN thrust and one liquid propellant control rocket engine, with four gimbaled nozzles, developing 30 kN thrust.
The fourth stage, known as the Block DM, uses liquid oxygen and synthetic kerosene, or synthin. See Figure 3-2.
Second Stage
The Block DM (fourth stage) is
Equipped with four gimbaled single-chamber liquid propellant rocket engines developing a total thrust of 2.3 MN.
optimized for multi-burn space transfer operations.
Its main
engine (model number 11D58M) delivers a vacuum thrust of 83.5n
First Stage
(1.88 x 104 lbf), is gimbaled to pro-
Equipped with six gimbaled single-chamber liquid propellant rocket engines developing a total thrust of 9 MN.
vide three-axis control during Strap-on fuel tanks
powered flight operations, and can be restarted as many as seven times during flight. The stage is
3.7 m (12.1 ft) in diameter, 6.28 m Figure 3-2 Major components of the Proton D-1-e launch vehicle
GE-1A Mission Overview 3-4
located at the base of the Block DM. The fourth
Proton.
The Standard Commercial Payload
stage can impart a rate of rotation up to 1.5 rpm
Fairing is shown in Figure 3-3. It is a two-piece,
for spacecraft separation. Guidance, navigation,
hinged, clamshell structure of monocouqe compos-
and control of the fourth stage are provided by a
ite sandwich construction. It does not incorporate
triple redundant digital avionics package, which
separation rocket motors, and no pyro gases are
can be ground commanded in flight, if necessary.
released during operation.
Multiple payload fairings are available for the
Figure 3-3 Standard Proton payload fairings (Shown here with the GE-1A
payload adapter system)
GE-1A Mission Overview 3-5
Section 4
Launch Campaign Processing Proton Operations Overview
build-up takes place in an integration and test facility capable of supporting four simultaneous
The Proton is launched from the Baikonur
Proton assembly and checkout operations.
Cosmodrome, located just east of the Aral Sea in the Republic of Kazakhstan. See Figures 4-1, and
GE-1A, which has been flown to the Baikonur
4-2. After transportation of the Proton’s stages by
Cosmodrome from LMSS facilities in Sunnyvale
rail from the factories in Moscow, launch vehicle
California, is processed in a separate satellite
Figure 4-1 Overview of Baikonur Cosmodrome
GE-1A Mission Overview 4-1
preparation building. GE-1A will be fueled in a
bly. The flight-ready Proton launch vehicle and
nearby facility. The spacecraft is then integrated
spacecraft assembly is then transported to the
with the Proton’s fourth stage, encapsulated with-
commercial Proton launch pad, where vehicle
in the payload fairing, and transported as a com-
erection and launch vehicle propellant loading
pleted unit to the Proton integration and test
takes place. Launch occurs nominally six days
facility.
after transportation to the pad. An overview of the transportation flow for GE-1A is shown in Figure
At the Proton integration and test facility the
4-3.
orbital unit is mated to the Proton’s first three stages and an end-to-end systems check performed on the completed vehicle/spacecraft assem-
Figure 4-2 Detailed view of the Baikonur Cosmodrome
GE-1A Mission Overview 4-2
Moscow Customs Procedures
Figure 4-3 Transportation of the GE-1A satellite to Baikonur
GE-1A Mission Overview 4-3
Section 5
Launch Management Launch Management
necessary for efficient program completion. The scheme for the partitioning of the work
International Launch Services functions as the prime contractor to manage all tasks associated
among
ILS
partners,
Lockheed
Martin,
with the provision of the launch vehicle and related
Khrunichev State Research and Production
integration and launch services in the United States
Center (KhSC), and Russian Space Complex
and Commonwealth of Independent States includ-
(RSC) Energia has been devised to use the
ing all required liaison with government organiza-
strengths of each company in the most efficient
tions and agencies. ILS and its constituent compa-
manner. See Figure 5-1.
nies provide for cost-effective delivery of resources
Figure 5-1 ILS management structure
GE-1A Mission Overview 5-1
Section 6
History tomers worldwide. See Figure 6-1.
In January of 1993, a joint venture was entered into by Lockheed Corporation of the United States
In 1995, Lockheed Corporation merged with
and Khrunichev State Research and Production
Martin Marietta of the United States to form
Space Center and Russian Space Complex (RSC)
Lockheed Martin. Within the newly formed com-
Energia of the Russian Federation. The joint ven-
pany there existed two commercial launch service
ture, Lockheed Khrunichev Energia International
companies;
(LKEI), was created for the purpose of offering
Commercial Launch Services (CLS) which offers
Russian-built Proton rockets to commercial cus-
the Atlas family of launch vehicles to commercial
LKEI and Martin Marietta’s
Figure 6-1 Organization of International Launch Services
GE-1A Mission Overview 6-1
result is a launch service provider that offers two of
customers worldwide. Soon after the Lockheed Martin merger was
the world’s most reliable and affordable launch
complete, International Launch Services was cre-
vehicles with launch schedule flexibility that
ated to offer both the Proton and Atlas launch vehi-
exceeds that of all other launch providers in busi-
cles to commercial customers worldwide.
ness today. See Figure 6-2 below.
The
Figure 6-2 International Launch Services strategic advantages
GE-1A Mission Overview 6-2