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Space TransportationAtlas V / Auxiliary Payload Overview

Space TransportationAtlas V / Auxiliary Payload Overview

Lockheed Martin Space Systems Company

Lockheed Martin Space Systems Company

Jim England (303) 977-0861 Program Manager, Atlas Government Programs Business Development and Advanced Programs3 August 2006

Jim England (303) 977-0861 Program Manager, Atlas Government Programs Business Development and Advanced Programs3 August 2006

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Video – Take a Ride

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Reliable & Versatile Launch Vehicle FamilyReliable & Versatile Launch Vehicle Family

• Consecutive Successful Atlas Centaur Flights: 79 • First Flight Successes: 8 of 8 • Mission Success: 100% Atlas II, IIA, IIAS, IIIA, IIIB, and V Families • Retired Variants: A, B, C, D, E, F, G, H, I, II, IIA, IIAS, IIIA, IIIB

Mission Success: One Launch at a TimeMission Success: One Launch at a Time

Atlas IAC-69

Atlas IIAC-102

Atlas IIAAC-105

Atlas IIASAC-108

Atlas IIIAAC-201

Atlas IIIBAC-204

Atlas V-400AV-001

Atlas V-500AV-003

Jul 1990

8/118/11

Dec 1991

10/1010/10

Jun 1992

23/2323/23

Dec 1993

30/3030/30

May 2000

2/22/2

Feb 2002

4/44/4

Aug 2002

4/44/4

Jul 2003

3/33/3

First Flight X Successes / Y FlightsX/YX/Y

Retired

Retired

Retired

Retired

Retired

Retired

Retired

Retired

Retired

Retired

Retired

Retired

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Recent Atlas / Centaur EvolutionRecent Atlas / Centaur Evolution

Demonstrated LowDemonstrated Low--risk Continuous Improvementrisk Continuous Improvement

2012+

Atlas IIAS Atlas IIIA(SEC)

Atlas IAtlas II

Atlas IIA

7/90 12/93 5/00 2/02 8/02 7/03

2

6

10

14

18

22

26

30

Atlas V Family

SingleEngineCentaur

LO2TankStretch

RD-180Engine

CommonCentaur

5-m PLFGSO Kit

SRBs

LiquidStrap-ons

3.8-mCommonCoreBooster

SRBs

Atlas V(HLV)

Atlas V(500 Series)(0–5 SRBs)

Atlas IIIB(DEC)

Atlas V(400 Series)(0–3 SRBs)

AvionicsUpgrade

407

km (2

20 n

m) C

irc. C

apab

ility

(mT)

Atlas III FamilyAtlas I / II Family

Retired

Retired

Retired

Retired

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Atlas V Common Elements Atlas V Common Elements

RL10A-4-2Single or Dual

Engines

Atlas V 400(0-3 SRBs)

Atlas 500 (0-5 SRBs)

HLV

Common Centaur

RD-180 Engine

Common Propulsion

Common CoreBooster™

Solid Rocket Booster (SRB)

4.2-meterPLF

(LPF, EPF, XPF)

5.4-meterContraves PLF

(68, 77, 87)

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Atlas V Configuration SummaryAtlas V Configuration Summary

Vehicle Naming Convention: Atlas V xyz1st Digit = x = PLF Diameter (meters)2nd Digit = y = No. of SRBs (0 to 5)3rd Digit = z = No. of Centaur Engines (1 or 2)

VehicleSeries:

400 500 Heavy

PLFDiameter

No. ofStrap-Ons

No. CentaurEngines

The Atlas V Launch Vehicle Family Provides:• Modular, Common Element Design• 4 & 5 Meter Payload Fairings• Standard Payload Interfaces• Standard Kits for GSO

4.2 MeterLPFEPF

XEPF

0 thru 3 SRBs

1 or 2

5.4 MeterShort (68’)Med (77’)Long (87’)

0 thru 5SRBs

1 or 2

5.5 MeterLong (87’)

2 LRBs

1 or 2

500 HLV

Atlas V Launch Vehicle Family

400

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Atlas V ConfigurationsAtlas V Configurations

551551501501 HLVHLV411411 431431401401 521521421421 531531 541541511511

Flights: 401, 401, 521, 521, 431, 401, 551, 411Flights: 401, 401, 521, 521, 431, 401, 551, 411……..

--- --- --- --- ---

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Atlas V Launch HistoryAtlas V Launch History

Eight Missions: 100% Mission SuccessEight Missions: 100% Mission Success

AV-001Aug 21, 2002

AV-002May 13, 2003

AV-003Jul 17, 2003

AV-005Dec 17, 2004

AV-004Mar 11, 2005

AV-007Aug 12, 2005

AV-010Jan 19, 2006

AV-001AV-002AV-003AV-005AV-004AV-007AV-010

Perigee

Argument

of PerigeeInclination

Apogee/C3

Outer Circle Represents 3σ

Accuracy Requirement

1σ 2σ 3σ

AV-00820 Jan 2006

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AV-010 / Pluto New Horizons LaunchAV-010 / Pluto New Horizons Launch

• January 19, 2006• NASA Pluto New Horizons

Spacecraft• First 551 configuration• First Block 2 Avionics• First Block B SRB• Nuclear certification required• Nominal flight profile• Injection conditions well within 1

sigma– C3, RLA, DLA

Fastest Satellite Vehicle Fastest Satellite Vehicle Ever LaunchedEver Launched

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AV-010 Pluto: View from the flame bucketAV-010 Pluto: View from the flame bucket

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Video – Pluto NH

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Secondary Payload Carriers – 2006Secondary Payload Carriers – 2006

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Previous Atlas Secondary MissionsPrevious Atlas Secondary Missions

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Atlas V Secondary Payload CapabilitiesAtlas V Secondary Payload Capabilities• Internal Payload Carrier (IPC)

– Capability to Support Large Secondary Payloads

– Flight Scheduled on STP-1 (Dec 2006) – Flight Scheduled on LRO (Oct 2008) – All EELV and Commercial Mission As

Available (DMSP, NPOESS, GPS)

• eXternal Payload Carrier (XPC) – Supports Suborbital Flight Test

Requirements

• Others Carriers in Development – Type-C Carrier (TCC) – Aft bulkhead Carrier (ABC) – Upper Stage Payload Carrier (USPC) – Dual Payload Carrier (DPC)

Multiple Atlas Secondary Launch OptionsMultiple Atlas Secondary Launch Options

ESPA

IPC

XPC

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STP-1 with an IPC STP-1 with an IPC

• The November 2006 STP-1 Mission to demonstrate small satellite capability• The November 2006 STP-1 Mission to demonstrate small satellite capability

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Aux SC30” CubeUp to 6

C-29

ESPA

GPS II

53”

GPS IIF with an IPC GPS IIF with an IPC

• Performance Margin > 1500 lbs – IPC stack height shown is 53”– Max 106” IPC stack height possible

• Approx Weights of Bare Structure:– ESPA: 350 lbs– C-29: 100-175 lbs depending on wall thickness

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Atlas V IPC Stack OptionsAtlas V IPC Stack Options

Option 1: BaselineNo Separation SP54” Dia x 60” Ht

C-29

C-24

C-26

B1194 PSR

Option 2: w/ ESPANo Separation SP54” Dia x 60” Ht

C-29

ESPA

C-26

B1194 PSR

Option 3: Stack SeparationSeparation SP

48” Dia x 60” Ht

C-29

D1666 PSRD1666 PSR

C-24

B1194 PSR

Option 4: Stack Sep w/ ESPASeparation SP

48” Dia x 60” Ht

C-29

D1666 PSRD1666 PSR

ESPA

B1194 PSR

Option 5: Stack SeparationSeparation SP

48” Dia x 60” Ht

C-29

C-24

D1666 PSRD1666 PSR

B1194 PSR

Option 6: Stack Sep w/ ESPASeparation SP

48” Dia x 60” Ht

C-29

ESPA

D1666 PSRD1666 PSR

B1194 PSR

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Secondary Capability Addresses Technology MaturitySecondary Capability Addresses Technology Maturity

• Effective Space Acquisition requires continuous technology development and demonstration – which in turn requires routine, low cost access to space

• USG manifests 6-8 NSS payloads per year– Excess performance

available (GPS, DMSP, NPOESS, etc)

– Opportunity for 6 to 12 secondary payloads per year

Secondary Payloads Enable Block AcquisitionSecondary Payloads Enable Block Acquisition

System Production

System Development

Technology Development

Science &Technology

Block 1 Block 2 Block 3

Block 2 Block3 Block 4

Block 3 Block 4 Block 5

Block 4 Block 5 Block 6

SecondaryPayloads

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Atlas Secondary Manifest CapabilityAtlas Secondary Manifest CapabilityLE

GEN

D

Atlas V 500

Successfully LaunchedAtlas V

400

Launch Under ReviewLaunch Under Review**

Launch PadJ M M

1stJ S N

2ndJ M M

1stJ S N

2ndCY2007CY2006

J M M1st

J S N2nd

J M M1st

J S N2nd

CY2008

J M M1st

J S N2nd

J M M1st

J S N2nd

CY2009

LC-41

CCAFS

VAFB

SLC-3E

19 JanPluto

AV010/551

NROL-30AV009/401

WGS F1521

12 OctSTP-1

AV013/401

Reserved 1AV012/501

GPS IIF-2401

20 AprASTRA 1KRAV008/411

DMSP-18401

Reserved 2501

WGS F3521

NROL-24401

**

SDO401

15 Nov NROL-28AV006/411

CY2010 CY2011

AEHF-1531

GPS IIF-3401

GPS IIF-4401

SBIRS G-1401

NROL-41501

NROL-39501

NROL-45501

GPS IIF-6401

GPS IIF-7401

SBIRS G-2401

WGS F4521

GPS IIF-8401

STP-2401

AEHF-3531

MUOS-1541

NROL-38401

GPS IIF-12401

STTR-1401

MUOS-2541

NROL-33401

Secondary Opportunity

MSL541

Secondary Payload

LRO401

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Business Model for EELV Secondary PayloadsBusiness Model for EELV Secondary Payloads

• Identify specific missions to routinely fly secondary payloads (GPS-IIF, DMSP, etc.)

• Define standard interface (volume, weight, LV services, CG, etc.)– Mass simulators to maintain primary spacecraft schedule– Plug and play swap-ability– Technically and programmatically transparent to primary SV

• Business Model implementation – USG to direct their SV programs to include secondary payloads – USG to fund the non-recurring secondary mission capability –cost

based – Individual secondary payload flights for $1-2M per slot – cost based

Disruptive Capability for Spacecraft DemonstrationDisruptive Capability for Spacecraft Demonstration