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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
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