Rideshare Symposium 2015 1
Launch Vehicles Technical Committee Report -17th Annual Small Payload Rideshare Symposium
Keith Karuntzos - United Launch Alliance
Warren Frick - Orbital ATK
June 2015
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Launch VehicleTechnical Committee Descriptions
• Large Launch Vehicles Technical Committee– This committee will review the status of the current and pending large launch vehicles within the
United States. The focus should include both the supply side issues as well as the demand side issues. The compatibility with secondary adapters should be evaluated and the potential availability of secondary opportunities should be discussed; issues of access to secondary capability, scheduling, and manifesting should be identified. Issues, concerns, suggestions, and options should be noted, discussed, and summarized based on the collective views of the committee membership.
• Foreign Launch Vehicles Technical Committee– This committee will review the status of the current and pending launch vehicles available outside
the United States. The focus should include both the advantages and disadvantages of using foreign launchers. The types of secondary adapters or payload interfaces should be evaluated and the potential availability of secondary opportunities should be discussed; issues of access to secondary capability, scheduling, and manifesting should be identified as well as U.S. policies, restrictions, and processes required to take advantage of foreign launch opportunities. Issues, concerns, suggestions, and options should be noted, discussed, and summarized based on the collective views of the committee membership.
• Small Launch Vehicles Technical Committee– This committee will review the status of the current and pending small launch vehicles within the
United States. The focus should include both the supply side issues as well as the demand side issues. Performance, capability, strengths, limitations, availability, affordability should be reviewed. Shortfalls in projected capability and possible increases in demand should be documented; suggestions, concerns, options, and issues should be noted, discussed, and summarized based on the collective views of the committee membership.
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Launch Vehicle CommitteesConsolidation Recommendation
• Recommend that the three launch vehicle committees be combined into one committee to support all launch vehicles that provide rideshare offerings
• Suggested "Launch Vehicle Technical Committee" description– This committee will review the status of the current and pending launch
vehicles across the world. The focus should include both the supply side issues as well as the demand side issues. The types of and compatibility with secondary adapters or payload interfaces should be evaluated; the potential availability of secondary opportunities should be discussed; and the issues of access to secondary capability, scheduling, and manifesting should be identified. Issues, concerns, suggestions, and options should be noted, discussed, and summarized based on the collective views of the committee membership.
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Launch Vehicle Rideshare Capability Survey Report
• The following pages document the rideshare capabilities currently available or in development to support the launch of small payloads
• This Launch Vehicle Rideshare Capability Report will be an on-going work, to be updated on an annual basis by the launch service providers
• The report will be available for download from either the SPRSA website or other TBD location later this summer
• The initial release focuses on larger launch vehicles; we need the community's help in documenting capabilities for all other launch service providers– Please contact Keith Karuntzos at ULA to provide new/updated
information• [email protected]• 303-269-5499
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Large Launch Vehicles Currently Providing Rideshare Capabilities
• Arianespace– Ariane V, Ariane VI, Soyuz, Vega
• Lockheed Martin– Athena
• Orbital ATK– Antares; Minotaur I, IV, V, VI; Minotaur-C, Pegasus XL
• SpaceX– Falcon 9
• United Launch Alliance– Atlas V, Delta II, Delta IV, Vulcan
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Small Launch Vehicles Currently Providing Rideshare Capabilities
• List TBD
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Delta II P-POD
Delta II P-POD
Description A set of three Cubesat P-POD dispensers attached to the Delta II second-stage mini-skirt.
Vehicle Delta II
Capacity 3 P-PODs (9 Cubesats)
Interface P-POD Dispenser
Mass 1.33 kg (2.9 lb) per 1U Cubesat
Volume 10 cm3 (4 in3) per 1U Cubesat
Status Operational; first launch 10-2011 on NASA NPP
Sheet MetalAdapter Plate
P-POD
Mini-skirt
Delta II Second-Stage Guidance
Section
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C-Adapter Platform (CAP)
PayloadVolume
C-AdapterPlatform (CAP)
C-Adapter Platform (CAP)
Description A cantilevered platform attached to the side of a C-adapter to accommodate secondary payloads. The CAP was originally designed to accommodate batteries that are part of the Atlas V GSO extended-mission kit hardware.
Vehicle Atlas V, Delta IV
Capacity 4 CAPs per C-adapter
Interface 8-in Clampband
Mass 45 kg (100 lb)
Volume 23 cm x 31 cm x 33 cm(9 in x 12 in x 13 in)
Status Qualified for GSO battery
C-29Adapter
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Aft Bulkhead Carrier (ABC)
ABC Payload Volume
Aft Bulkhead Carrier (ABC)
Atlas V Centaur Second Stage
Aft Bulkhead Carrier (ABC)
Description An interface located at the aft-end of the Atlas V Centaur second-stage. A second ABC mission, GEMSat, launched in Dec 2013, and two additional missions are currently on contract for launch by ULA.
Vehicle Atlas V
Capacity 1 ABC per Atlas V
Interface 15-in Bolted Interface
Mass 80 kg (176 lb)
Volume 51 cm x 51 cm x 86 cm(20 in x 20 in x 34 in)
Status Operational; first launch 09-2012 on NROL-36 (OUTSat - NPSCuL box with 8 P-PODs)
Users Guide
http://www.ulalaunch.com/uploads/docs/Launch_Vehicles/ABC_Users_Guide_2014.pdf
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eXternal Payload Carrier (XPC)
XPC Cover
XPC
Payload
Atlas V Common Core Booster
Solid Rocket Booster
XPC
Description An inert solid rocket booster to hold small payloads for injection into a hypersonic suborbital trajectory. The XPC can accommodate one large payload, or a number of smaller payloads, and all are jettisonable during the sub-orbital trajectory of the first-stage.
Vehicle Atlas V
Capacity 1 XPC per launch
Interface Variable
Mass 1,810 kg (4,000 lb)
Volume 21.2 m3 (750 ft3)
Status Concept Development
Developer Special Aerospace Services (SAS)(Tim Bulk, [email protected])
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Dual Spacecraft System, 4-m (DSS-4)
Centaur Forward Adapter (CFA)
DSS canister with 3 plugs shown
Atlas V 4-m
Extra Extended Payload Fairing (XEPF)
DSS-4
Description A modular dual-manifest launch capability for 4-m fairings, using Centaur Forward Assembly hardware. The DSS-4 will have the same on-orbit concept of operations as the Delta II DPAF, delivering the two payloads to the same or similar orbits (Performance-limited).
Vehicle Atlas V, Delta IV (4-m fairings)
Capacity 1 DSS-4 per launch, 2 payloads
Interface 62-in Bolted
Mass Upper Payload: 2,270 kg (5,000 lb)Lower Payload: 9,000 kg (19,800 lb)
Volume Upper Payload: 365-cm-dia. x 658 cm (144-in-dia. x 259 in)Lower Payload: 254-cm-dia. x 445 cm (100-in-dia. x 175 in) (3-plug)
Status CDR 12-2009
AftPayload
(Notional)
ForwardPayload
(Notional)
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Dual Spacecraft System, 5-m (DSS-5)
Payload Separation
Ring(2 Places)
DSS-5
AftPayload
(Notional)
ForwardPayload
(Notional)DSS-5
Description A dual-manifest launch capability for 5-m fairings, using newly designed composite structure. The DSS-5 is expected to be first used in support of the GPS III program, with a first-flight of a GPS III dual manifest mission in 2017/2018.
Vehicle Atlas V, Delta IV (5-m fairings)
Capacity 1 DSS-5 per launch, 2 payloads
Interface 62-in Bolted
Mass Forward Payload: 5,440 kg (12,000 lb)Aft Payload: 9,000 kg (19,800 lb)
Volume Forward Payload: 457-cm-dia. x 762 cm (180-in-dia. x 300 in)Aft Payload: 375-cm-dia. x 487 cm (148-in-dia. x 192 in) (Standard DSS-5)
Status In development; CDR 12-2014
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EELV Secondary Payload Adapter (ESPA)
15-inch bolted interface (Six
places)
Payloadenvelope
(x 6)
ESPA
Atlas V Centaur Second-Stage
Forward Adapter
EELV Secondary Payload Adapter (ESPA)
Description An adapter located between the second-stage and the primary payload, which can accommodate up to six secondary payloads. ESPA hardware will be used to launch ANGELS on AFSPC-4 in 2014, and additional missions are being evaluated.
Vehicle Atlas V, Delta IV, Falcon 9
Capacity 6 payloads per ESPA
Interface 15-in Bolted Interface
Mass 181 kg (400 lb)
Volume 61 cm x 71 cm x 96 cm(24 in x 28 in x 38 in)
Status Operational. First launch 03-2007 on STP-1
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Separating ESPA
Separating ESPA
Description A separating rideshare payload that uses the ESPA ring as the structural bus of the satellite. A separating ESPA can use various separation ring hardware solutions from a number of vendors to separate from the ULA launch vehicle.
Vehicle Atlas V, Delta IV, Falcon 9
Capacity Variable
Interface 62-in Bolted Interface
Mass 1,360 kg (3,000 lb)
Volume 350-cm dia. x 61 cm(138-in dia. x 24 in)
Status Operational. First launch 06-2009 on LRO/LCROSS
LCROSS
ESPA
62-inSeparation Rings
ESPA
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AQUILA
AQUILA
Description A flat deck and cylindrical spacers, located between the forward-end of the second stage and the primary payload, providing volume for rideshare payloads inside the AQUILA system. AQUILA modular adapters are rated to support a primary payload mass up to 6,350 kg (14,000 lb).
Vehicle Atlas V, Delta IV
Capacity Multiple payloads per AQUILA
Interface Mission-unique bolted
Mass 1,000 kg (2,200 lb)
Volume 142-cm dia. (56-in dia.) x 152 cm (60 in)
Status In development. CDR 04-2012, Qualification tests complete
Images courtesy of ALS
AQUILA(Tall configurationshown with ESPA)
Atlas V 4-m
Large Payload Fairing (LPF)
Primary PayloadVolume
8.1 m x 3.8-m dia.(320 in x 148-in dia.)
A-Deck
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38” Dual Payload Attach Fitting (DPAF)
Payload Separation
Ring(2 Places)
38” DPAF
AftPayload
(Notional)
ForwardPayload
(Notional)38-inch Dual Payload Attach Fitting (DPAF)
Description A dual-manifest launch capability for 50 inch or larger fairings. The 38-inch DPAF is meant to fly a small-class satellite with an ESPA class satellite.
Vehicle Pegasus, Minotaur I (50" & 61" fairings)
Capacity 1 38-in DPAF per launch, 2 payloads
Interface 38-in Bolted
Mass Forward Payload: Max performance of LVAft Payload: Remaining performance
Volume Forward Payload: TBD-cm-dia. x TBD cm (TBD-in-dia. x TBD in)Aft Payload: TBD-cm-dia. x TBD cm (TBD-in-dia. x TBD in)
Status Operational. First launch 11-1996 on SAC-B/HETE
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50” Dual Payload Attach Fitting (DPAF)
50-inch Dual Payload Attach Fitting (DPAF)
Description A dual-manifest launch capability for 61 inch or larger fairings. The 50-inch DPAF is meant to fly a Pegasus-class payload with a sub-Minotaur-C class payload.
Vehicle Minotaur-C (63" and 92" fairings), Minotaur 1 (61" fairing), Minotaur IV, VI
Capacity 1 50-in DPAF per launch, 2 payloads
Interface 38-in Bolted
Mass Forward Payload: Max performance of LVAft Payload/DPAF: Remaining performance
Volume Forward Payload: TBD-cm-dia. x TBD cm (TBD-in-dia. x TBD in)Aft Payload: TBD-cm-dia. x TBD cm (TBD-in-dia. x TBD in)
Status Operational. First launch 12-1999 on KOMPSAT/ACRIMSat
June 2015
Payload Separation
Ring(2 Places)
D
D
50” DPAF
AftPayload
(Notional)
ForwardPayload
(Notional)
Payload Separation
Ring(2 Places)
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63” Dual Payload Attach Fitting (DPAF)
Payload Separation
Ring(2 Places)
63” DPAF
AftPayload
(Notional)
ForwardPayload
(Notional)63-inch Dual Payload Attach Fitting (DPAF)
Description A dual-manifest launch capability for 92-in or larger fairings. The 63-in DPAF is meant to fly a Minotaur-1 Class Payload with a sub Minotaur-C/IV Class Payload.
Vehicle Minotaur-C with 92” fairing, Minotaur IV, VI, Antares
Capacity 1 63-in DPAF per launch, 2 payloads
Interface 38-in Bolted
Mass Forward Payload: Max performance of LVAft Payload/DPAF: Remaining performance
Volume Forward Payload: TBD-cm-dia. x TBD cm (TBD-in-dia. x TBD in)Aft Payload: TBD-cm-dia. x TBD cm (TBD-in-dia. x TBD in)
Status Operational, first launch 10-1998 on GFO/ORBCOMM
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Multiple Payload Adapter Fitting (MPAF)
Minotaur Fourth-Stage
Multiple Payload Adapter Fitting (MPAP)
Description A multiple-manifest launch capability for 92-in or larger fairing vehicles. Eight payload capacity – including 4 ESPA-class payloads. The MPAF hardware can support four ESPA-sized payloads and up to four smaller payloads.
Vehicle Minotaur-C with 92-in fairing, Minotaur IV, VI, Antares
Capacity 1 MPAF per launch, up to 8 payloads
Interface 38-in Bolted
Mass ESPA Class: 181 kg (400 lb)Smaller Payloads: Up to 60 kg (130 lb)
Volume ESPA Class: 61 cm x 71 cm x 96 cm (24 in x 28 in x 38 in)Smaller Payloads: TBD-cm-dia. x TBD cm (TBD-in-dia. x TBD in)
Status Operational. First launch 11-2010 on STP-S27
Aft Payloads(2 to 4 Places)
ForwardPayload(s)
Up to Four ESPA-Class
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Minotaur-C P-POD
Minotaur-C P-POD
Description A Cubesat P-POD dispenser attached to the Minotaur-C fourth Stage aft structure
Vehicle Minotaur-C
Capacity 1 P-PODs (3 Cubesats)
Interface P-POD Dispenser
Mass 1.33 kg (2.9 lb) per 1U Cubesat
Volume 10 cm3 (4 in3) per 1U Cubesat
Status Operational. First launch 3-2011 on Glory
Adapter Plate
P-POD
Minotaur-C Avionics Section
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Minotaur I Fourth Stage Motor
Minotaur P-POD
Minotaur-I P-POD
Description Cubesat P-POD dispensers attached to the Minotaur I and IV fourth Stage motor
Vehicle Minotaur I with 61” Fairing, Minotaur IV
Capacity 1 to 4 P-PODs (up to 12 Cubesats)
Interface P-POD Dispenser
Mass 1.33 kg (2.9 lb) per 1U Cubesat
Volume 10 cm3 (4 in3) per 1U Cubesat
Status Operational; first launch 7-2000 on MightySat II.1
P-POD
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Pegasus P-POD
Pegasus P-POD
Description 2-U Cubesat P-POD dispenser attached to the Pegasus Avionics Section
Vehicle Pegasus XL
Capacity 2x2U CubeSat Dispensors(4 Cubesats)
Interface P-POD Dispenser
Mass 1.33 kg (2.9 lb) per 1U Cubesat
Volume 10 cm3 (4 in3) per 1U Cubesat
Status In Development.
P-POD
Pegasus Avionics Section
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Antares Ride Share
June 2015
Antares Ride Share
Description Large toroidal volume
Vehicle Antares (all models)
Capacity Variable
Interface Rail Mount
Mass Up to 500 kg (1,100 lb)
Volume Location Dependent
Status In Development Antares SecondStage
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Ariane Structure for Auxiliary Payloads (ASAP 5)
Ariane Structure for Auxiliary Payloads (ASAP5)
Description The ASAP 5 is a circular platform externally mounted to the forward end of the Ariane 5 upper stage. It can accommodate anywhere from 4 micro payloads to 8 mini payloads, depending on the configuration used.
Vehicle Ariane 5
Capacity 1 ASAP5
Interface Micro payload - 298-mm (11.7-in) Mini payload: 937-mm (37-in) clampband
Mass Micro payload - 120 kg (265 lb)Mini payload - 300 kg (660 lb)
Volume Micro payload - 0.6 m (23.6 in) cubed Mini payload - 1.5 m (59 in) cubed
Status Operational. First launch 01-1990 on SPOT 2
SeparationSystem
ASAP 5 Platform(8 Microsat Configuration)
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ASAP 5 Platform(2 Minisat/6 Microsat
Configuration)
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Athena IC, IIC, IIS
Athena TBD
Description TBD
Vehicle Athena IC, IIC, IIS
Capacity TBD
Interface TBD
Mass TBD
Volume 10 cm3 (4 in3) per 1U Cubesat
Status In Development
P-PODs
Up to 7 Sub-ESPAClass Payloads
Orbit Adjust Module
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Athena IIC
Athena TBD
Description TBD
Vehicle Athena IIC
Capacity TBD
Interface TBD
Mass 1.33 kg (2.9 lb) per 1U Cubesat
Volume 10 cm3 (4 in3) per 1U Cubesat
Status In Development
3 ESPA-ClassPayloads
June 2015
Orbit Adjust ModuleP-PODs
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Falcon 9
TBD
Description TBD
Vehicle Falcon 9
Capacity TBD
Interface TBD
Mass TBD
Volume TBD
Status TBD
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Launch Vehicle Points of Contact
COMPANY VEHICLES NAME EMAIL
Arianespace Ariane, Soyuz, Vega
Lockheed Martin Athena Gregory Kehrl [email protected]
Orbital ATK Antares, Pegasus, Minotaur Warren Frick [email protected]
SpaceX Falcon Curt Blake [email protected]
ULA Atlas, Delta, Vulcan Keith Karuntzos [email protected]
Moog CSA Eng. ESPA Joe Maly [email protected]
ALS AQUILA Jack Rubidoux [email protected]
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