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