MISSION OVERVIEW SLC-41CCAFS, FL

Mission OverviewU.S. Airforce

The ULA team is proud to be the launch provider for the Tracking Data and Relay Satellite-K (TDRS-K) mission. The TDRS system is the third generation space-based communication system used to provide tracking, telemetry, com-mand and high-bandwidth data-return services for the National Aeronautics and Space Administration’s (NASA) Space Network.

The TDRS project offi ce at NASA’s Goddard Space Flight Center manages the TDRS-K development effort and our direct customer for this launch is the NASA Launch Services Program (LSP).

The ULA team is focused on attaining Perfect Product Delivery for the TDRS-Kmission, which includes a relentless focus on mission success (the perfectproduct) and also excellence and continuous improvement in meeting all of theneeds of our customers (the perfect delivery).

Launched together with our NASA partners, the TDRS-K mission marks the fi rst 2013 Evolved Expendable Launch Vehicle (EELV) launch. My thanks to the entire team for their dedication in bringing TDRS-K to launch and also to NASA for entrusting ULA to deliver this critical capability to orbit.

Go Atlas, Go Centaur, Go TDRS-K!

Jim Sponnick

Vice President, Mission Operations

1

Atlas V TDRS-K

Atlas V TDRS-K32

TDRS-K SATELLITE | Overview

The Tracking and Data Relay Satellite System (TDRSS) is a space-based communication system used to provide tracking, telemetry, command, and high-bandwidth data return services. The TDRSS, also referred to as the NASA Space Network, consists of satellites in geosynchronous stationary orbits and the associated TDRS ground stations located at White Sands, NM and Guam. Aboard each satellite are multiple antennae that send and receive signals to and from the ground to multiple satellites simultaneously. As a result, the TDRSS provides a wide variety of services to meet customers’ needs and demands.

Microwave communications equipment and gimbaled antennae are the primary payload of each TDRS. The TDRSS is capable of providing near continuous high bandwidth (S, Ku, and Ka band) telecommunications services for Low Earth orbiting spacecraft and expendable launch vehicles, including the Hubble Space Telescope and the International Space Station. The TDRS System is a basic agency capability and a critical national resource.

Image Courtesy NASA/Goddard Space Flight Center

54

4-m

Payload

Fairing

LaunchVehicleAdapter

Atlas V Booster

RD-180

Engine

TDRS-K

Satellite

Centaur

4-m

Payload

Fairing

LaunchVehicleAdapter

Atlas V Booster

RD 1

TDRS-K

Satellite

Centaur

Aft Stub Adapter

InterstageAdapter

RL10A Centaur

Engine

ATLAS V 401 LAUNCH VEHICLE | Expanded ViewATLAS V 401 LAUNCH VEHICLE | Overview

The Atlas V 401 consists of a single Atlas V booster stage, the Centaur upper stage, and a 4-m

diameter payload fairing (PLF).

The Atlas V booster is 12.5 ft in diameter and 106.5 ft in length. The booster’s tanks are

structurally rigid and constructed of isogrid aluminum barrels, spun-formed aluminum domes,

and intertank skirts. Atlas booster propulsion is provided by the RD-180 engine system (a single

engine with two thrust chambers). The RD-180 burns RP-1 (Rocket Propellant-1 or highly

purifi ed kerosene) and liquid oxygen, and delivers 860,200 lb of thrust at sea level. The

Atlas V booster is controlled by the Centaur avionics system, which provides guidance, fl ight

control, and vehicle sequencing functions during the booster and Centaur phases of fl ight.

The Centaur upper stage is 10 ft in diameter and 41.5 ft in length. Its propellant tanks are

constructed of pressure-stabilized, corrosion resistant stainless steel. Centaur is a liquid hydro-

gen/liquid oxygen- (cryogenic-) fueled vehicle. It uses a single RL10A-4-2 engine producing

22,300 lb of thrust. The cryogenic tanks are insulated with a combination of helium-purged

insulation blankets, radiation shields, and spray-on foam insulation (SOFI). The Centaur forward

adapter (CFA) provides the structural mountings for the fault-tolerant avionics system and the

structural and electrical interfaces with the spacecraft.

The TDRS-K mission is encapsulated in the 4-m (14-ft) diameter extended payload fairing (EPF).

The EPF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction

with vertical split-line longerons. The vehicle’s height with the EPF is approximately 192 ft.

Atlas V TDRS-K

66666666666666666666666666666666666666666666666666666666666666666666666666666666666666666666666666666666666666

VIF

3

1

6

7

8 9

10

11

4 5

32

SPACE LAUNCH COMPLEX 41 (SLC-41) | Overview

1 Vertical Integration Facility (VIF) (See inset)

2 Bridge Crane Hammerhead3 Bridge Crane4 Launch Vehicle5 Mobile Launch Platform (MLP)

6 Launch Vehicle7 Centaur LO2 Storage8 High Pressure Gas Storage9 Booster LO2 Storage10 Pad Equipment Building (PEB)

11 Pad ECS Shelter

6

ATLAS V TDRS-K | Mission Overview

The TDRS-K mission will be fl own on an easterly trajectory from Space Launch Complex 41 at

Cape Canaveral Air Force Station (CCAFS), FL. The TDRS-K satellite will be released into a highly

elliptical geosynchronous transfer orbit (GTO).

The mission begins with ignition of the RD-180 engine approximately 2.7 seconds prior to liftoff.

Liftoff occurs at T+1.1 seconds. Shortly after the vehicle clears the pad, it performs its pitch/yaw/

roll maneuvers.

Following maximum dynamic pressure, the RD-180 is throttled down to 95%. Guidance steering

is enabled approximately 140 seconds into fl ight. At 212 seconds, the vehicle throttles up to a

constant 5.0 G-level. Approximately 10 seconds prior to booster engine cutoff (BECO), the

Atlas V throttles down to a constant 4.6 G’s. BECO occurs 242 seconds into fl ight followed by

Centaur separation approximately 6 seconds later.

Approximately 4 minutes into fl ight, the Centaur stage ignites its main engine (MES-1) which

begins a 14-minute burn to place the vehicle into a parking orbit. Eight seconds into the fi rst

Centaur burn, the payload fairing is jettisoned.

Following an 82-minute coast, the Centaur main engine is ignited for a second burn (MES-2),

nearly 59 seconds in length. Two seconds after main engine cutoff (MECO-2), the Centaur

begins a spacecraft separation attitude alignment and spins up to 5 RPM. TDRS-K is released

approximately 106 minutes after liftoff.

7

Atlas V TDRS-K

1

2

5 6 7 8

Approximate Values

Launch:Flight Azimuth: 101.4°

Orbit at Separation:

Perigee: 4,312.7 km (2,328.7 nmi)

Apogee: 35,788.9 km (19,324.5 nmi)

Eccentricity: 0.6°

Inclination: 25.9°

Argument of Perigee: 180.0°

98

SEQUENCE OF EVENTS | Liftoff to SeparationFLIGHT PROFILE | Liftoff to Separation

Atlas V TDRS-K

Time(seconds)Event

Time(hr:min:sec)

RD-180 Engine Ignition

T=0 (Engine Ready)

Liftoff (Thrust to Weight >1)

Begin Pitch/Yaw/Roll Maneuver

Maximum Dynamic Pressure

Atlas Booster Engine Cutoff (BECO)

Atlas Booster/Centaur Separation

Centaur First Main Engine Start (MES-1)

Payload Fairing Jettison

Centaur First Main Engine Cutoff (MECO-1)

Centaur Second Main Engine Start (MES-2)

Centaur Second Main Engine Cutoff (MECO-2)

TDRS-K Separation

-00:00:02.7

00:00:00.0

00:00:01.1

00:00:17.6

00:01:31.4

00:04:02.0

00:04:08.0

00:04:18.0

00:04:26.0

00:18:13.9

01:40:17.0

01:41:15.7

01:46:01.7

-2.7

0.0

1.1

17.6

91.4

242.0

248.0

258.0

266.0

1,093.9

6,017.0

6,075.7

6,361.7

1

2

34

67

5

8

ATLAS V PROCESSING | Cape Canaveral

1110

ATLAS V PRODUCTION & LAUNCH | Overview

Centaur

Booster

InterstageAdapter

4-m Payload Fairing Halves

Spacecraft

SLC-41Testing &Launch

MobileLaunchPlatform

SpacecraftProcessing

FacilitySpacecraft Processing,Testing & Encapsulation

PayloadTransporter

Antonov

Container Ship

Vertical Integration Facility

Launch Vehicle Integration & Testing, Spacecraft Mate,

Integrated Operations

Mariner

Atlas Spaceflight Operations Center (ASOC)Receiving & Inspection Launch Control CenterCommunication Center Mission Director’s CenterSpacecraft Control Room ITAR Facility

Denver, CO• ULA Headquarters &

Design Center Engineering

San Diego, CA• Centaur Tank Fabrication

Harlingen, TX• Payload Fairing/Adapter Fabrication

• Booster Adapter Fabrication

• Centaur Adapter Fabrication

ation

Khimki, Russia• RD-180 Engine Fabrication

at NPO Energomash

catioon

Decatur, AL• Booster Fabrication & Final Assembly

• Centaur Final Assembly

Cape Canaveral Air Force Station, FL• Payload Processing & Encapsulation

• Launch Vehicle Processing

• Encapsulated Payload Mating

• Launch

,

West Palm Beach, FL• RL10 Engine Fabrication at

Pratt & Whitney Rocketdyne

11

Atlas V TDRS-K

1312

GROUND TRACE | Liftoff to Separation

Longitude (deg)

Geod

etic

Lat

itude

(de

g)

80

60

40

20

0

-20

-80

-60

-40

-135 -90 -45 0 1359045

Telemetry Ground Station

Launch Vehicle /Spacecraft Groundtrack

TDRS Asset Geostationary Orbital Position

1 = MECO-1 (0:18:13.9) | 2 = MES-2 (1:40:17.0) | 3 = MECO-2 (1:41:15.7) | 4 = TDRS-K Separation (1:46:01.7)

TDRS 49

TEL-4

Antigua

TDRS 275Guam1

2

Diego GarciaTDRS 174

3 4

Atlas V TDRS-K

COUNTDOWN TIMELINE | Launch-1 Day

1514

Atlas V TDRS-K

Launch-1 Day MLP TRANSPORT TO PAD

Flight Control Preps

T-11:30 T-11:00 T-10:00 T-9:00 T-8:00 T-7:00 T-4:00T-6:00 T-5:00

Transport Preps Pad Connections

T-3:00

RP-1 Tanking

Transport Preps Pneumatic System Preps

MLP Transport Preps MLP Roll MLP Connect

MLP Hard Down

WeatherBrief

StatusCheck

WeatherBrief

StatusCheck

Ground CommandControl Comm.,

Radio Frequency/Flight Termination

System

Atlas/CentaurPneumatics &

Propulsion

EnvironmentalControl System,

Flight Control

COUNTDOWN TIMELINE | Launch Day

1716

Atlas V TDRS-K

Launch Day

WeatherBrief

T-2:00

Open Loop Test & Monitor Preps

Power Application, System Preps,

Flight Control/Guidance Tests & Countdown Preps

Centaur LH2/LO2 Preps Atlas

Propulsion/Hydraulic Preps Storage Area Chilldown

T-1:00 T-:45 T-:30 T-:15 T-:04H

Flight Control

Final Preps

PressurizeChilldown &

Tanking

T-0

:04

(T-4

) &

Hold

ing

StatusCheck

T-3:00T-4:00T-5:00T-6:00T-6:20

StartCount

ECS GN2 Preps

Open/Closed Loop Tests

All Systems on GN2

StatusCheck

WeatherBrief

LAUNCH

Flight Control

Ground CommandControl Comm.,

Radio Frequency/Flight Termination

System

Atlas/CentaurPneumatics &

Propulsion

EnvironmentalControl System

United Launch Alliance | P.O. Box 3788 Centennial, CO 80155 | www.ulalaunch.com

Copyright © 2009 United Launch Alliance, LLC. All Rights Reserved.

Copyright © 2013 United Launch Alliance, LLC. All Rights Reserved. Atlas is a Registered Trademark of Lockheed Martin Corporation. Used with Permission.