LAUNCH VEHICLE DOWNSELECT

•A Wide Variety of Launch Systems Are Available Today

•Initial Downselect Constraint Based Upon UMRM Requirements• Primary Payload Size• TOF Concerns

• Initial Downselect Constraint• Launch Vehicle Should Be Capable of Lifting At Least 10,000 kg into LEO

LAUNCH VEHICLE DOWNSELECT

Ariane 5 Atlas V Delta IV

Proton Titan IV Zenit

Six Expendable Vehicles

LAUNCH VEHICLE DOWNSELECT

EVALUATION CRITERIA

1) Reliability• Vehicle Success Rate• Family Success Rate

2) Launch Inclination Availability

3) Usable Volume of Largest Fairing

4) Cost

5) Payload Capability To LEO

LAUNCH VEHICLE DOWNSELECT

Ariane 5 Atlas V - 500Delta IV Heavy

Proton M Titan IVB Zenit 3SL

Family Success Rate (success percentage)

92% 87% 95% 88% 91% 83%

Vehicle Success Rate (successes/attempts)

11/13 1/1 * 2/2 ** 1/1 *** 5/6 7/8

Launch Inclination Availability (degrees)

5 - 10028.5 - 55, 63 - 120

28.5 - 51, 63 - 120

51.6, 63.4, 72.7

28.5 - 55, 63 - 120

all

Approximate Volume of Largest Available Fairing

(m3)160 205 255 235 240 140

Cost ($M)

150 - 180 85 - 110 140 - 170 100 - 112 350 - 450 75 - 95

Payload To LEO (kg)

16,000 20,050 23,040 21,000 21,680Non-Standard

Mission

* Atlas V - 400 Series** Delta IV-M*** thru 1999

LAUNCH VEHICLE DOWNSELECT

Ariane 5 Atlas V - 500Delta IV Heavy

Proton M Titan IVB Zenit 3SL

Family Success Rate (success percentage)

92% 87% 95% 88% 91% 83%

Vehicle Success Rate (successes/attempts)

11/13 1/1 * 2/2 ** 1/1 *** 5/6 7/8

Launch Inclination Availability (degrees)

5 - 10028.5 - 55, 63 - 120

28.5 - 51, 63 - 120

51.6, 63.4, 72.7

28.5 - 55, 63 - 120

all

Approximate Volume of Largest Available Fairing

(m3)160 205 255 235 240 140

Cost ($M)

150 - 180 85 - 110 140 - 170 100 - 112 350 - 450 75 - 95

Payload To LEO (kg)

16,000 20,050 23,040 21,000 21,680Non-Standard

Mission

* Atlas V - 400 Series** Delta IV-M*** thru 1999

LAUNCH VEHICLE DOWNSELECT

Ariane 5 Atlas V - 500Delta IV Heavy

Proton M Titan IVB Zenit 3SL

Family Success Rate (success percentage)

92% 87% 95% 88% 91% 83%

Vehicle Success Rate (successes/attempts)

11/13 1/1 * 2/2 ** 1/1 *** 5/6 7/8

Launch Inclination Availability (degrees)

5 - 10028.5 - 55, 63 - 120

28.5 - 51, 63 - 120

51.6, 63.4, 72.7

28.5 - 55, 63 - 120

all

Approximate Volume of Largest Available Fairing

(m3)160 205 255 235 240 140

Cost ($M)

150 - 180 85 - 110 140 - 170 100 - 112 350 - 450 75 - 95

Payload To LEO (kg)

16,000 20,050 23,040 21,000 21,680Non-Standard

Mission

* Atlas V - 400 Series** Delta IV-M*** thru 1999

LAUNCH VEHICLE DOWNSELECT

Ariane 5 Atlas V - 500Delta IV Heavy

Proton M Titan IVB Zenit 3SL

Family Success Rate (success percentage)

92% 87% 95% 88% 91% 83%

Vehicle Success Rate (successes/attempts)

11/13 1/1 * 2/2 ** 1/1 *** 5/6 7/8

Launch Inclination Availability (degrees)

5 - 10028.5 - 55, 63 - 120

28.5 - 51, 63 - 120

51.6, 63.4, 72.7

28.5 - 55, 63 - 120

all

Approximate Volume of Largest Available Fairing

(m3)160 205 255 235 240 140

Cost ($M)

150 - 180 85 - 110 140 - 170 100 - 112 350 - 450 75 - 95

Payload To LEO (kg)

16,000 20,050 23,040 21,000 21,680Non-Standard

Mission

* Atlas V - 400 Series** Delta IV-M*** thru 1999

LAUNCH VEHICLE DOWNSELECT

Ariane 5 Atlas V - 500Delta IV Heavy

Proton M Titan IVB Zenit 3SL

Family Success Rate (success percentage)

92% 87% 95% 88% 91% 83%

Vehicle Success Rate (successes/attempts)

11/13 1/1 * 2/2 ** 1/1 *** 5/6 7/8

Launch Inclination Availability (degrees)

5 - 10028.5 - 55, 63 - 120

28.5 - 51, 63 - 120

51.6, 63.4, 72.7

28.5 - 55, 63 - 120

all

Approximate Volume of Largest Available Fairing

(m3)160 205 255 235 240 140

Cost ($M)

150 - 180 85 - 110 140 - 170 100 - 112 350 - 450 75 - 95

Payload To LEO (kg)

16,000 20,050 23,040 21,000 21,680Non-Standard

Mission

* Atlas V - 400 Series** Delta IV-M*** thru 1999

LAUNCH VEHICLE DOWNSELECT

Ariane 5 Atlas V - 500Delta IV Heavy

Proton M Titan IVB Zenit 3SL

Family Success Rate (success percentage)

92% 87% 95% 88% 91% 83%

Vehicle Success Rate (successes/attempts)

11/13 1/1 * 2/2 ** 1/1 *** 5/6 7/8

Launch Inclination Availability (degrees)

5 - 10028.5 - 55, 63 - 120

28.5 - 51, 63 - 120

51.6, 63.4, 72.7

28.5 - 55, 63 - 120

all

Approximate Volume of Largest Available Fairing

(m3)160 205 255 235 240 140

Cost ($M)

150 - 180 85 - 110 140 - 170 100 - 112 350 - 450 75 - 95

Payload To LEO (kg)

16,000 20,050 23,040 21,000 21,680Non-Standard

Mission

* Atlas V - 400 Series** Delta IV-M*** thru 1999

LAUNCH VEHICLE DOWNSELECT

Atlas V-552 Delta IV-Heavy

PRIMARY LAUNCH SYSTEMS

LAUNCH VEHICLE CONFIGURATION

ATLAS V-552

Single Common Core Booster (CCB)Powered By A Single NPO Energomash/Pratt & Whitney RD-180 LOX/RP-1 Engine

Solid Rocket Boosters (SRB’s)5 Aerojet SRB’s For Added Performance

Fairing5-m Diameter Composite Fairing

Centaur Upper Stage and AdapterDual Engine Centaur (DEC) Consisting of Two Pratt & Whitney RL10A-4-2 LOX/LH2 Engines

LAUNCH VEHICLE CONFIGURATION

ATLAS V-552

LONG COMPOSITE FAIRING

• 5 m diameter by 23.4 m

• bisector fairing

• graphite epoxy face sheets

• aluminum honeycomb core

LAUNCH VEHICLE CONFIGURATION

ATLAS V-552

TYPE D PAYLOAD ADAPTER

• Marmon-type clampband separation system

• Requires special payload interface adapter to be manufactured

• Hardware adapter will attach to the main tank aft structure, surrounding the 7 MITEE engines

• Must jettison adapter prior to spacecraft’s initial burn

LAUNCH VEHICLE CONFIGURATION

DELTA IV-HEAVY 70-m

60-m

50-m

3 Common Booster Cores (CBC’s)Each Powered By A Single Rocketdyne RS-68 LOX/LH2 Engine

Interstage AdapterHousing A Single Pratt & Whitney LOX/LH2 RL10-B2 Engine

Fairing5-m Diameter Composite Fairing Encapsulating Payload and Attach Fittings

LAUNCH VEHICLE CONFIGURATIONDELTA IV-HEAVY

COMPOSITE FAIRING• 5 m diameter by 19.1m• bisector fairing• graphite epoxy foam core• composite sandwich structure

LAUNCH VEHICLE CONFIGURATION

DELTA IV-HEAVY

Delta IV 1666-5 PAF

• Marmon-type clampband separation system

• Aft structure of each add-on tank will be designed to accommodate this connection interface