Launch Vehicles Technical Committee Report - 17th Annual Small Payload Rideshare Symposium Keith Karuntzos - United Launch Alliance Warren Frick - Orbital ATK June Rideshare Symposium 2015

Launch Vehicle Technical 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. June 20152Rideshare Symposium 2015

Launch Vehicle Committees Consolidation 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. June 20153Rideshare Symposium 2015

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 June 20154Rideshare Symposium 2015

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 June 20155Rideshare Symposium 2015

Small Launch Vehicles Currently Providing Rideshare Capabilities List TBD June 20156Rideshare Symposium 2015

Delta II P-POD DescriptionA set of three Cubesat P-POD dispensers attached to the Delta II second-stage mini- skirt. VehicleDelta II Capacity3 P-PODs (9 Cubesats) InterfaceP-POD Dispenser Mass1.33 kg (2.9 lb) per 1U Cubesat Volume10 cm 3 (4 in 3 ) per 1U Cubesat StatusOperational; first launch on NASA NPP Sheet Metal Adapter Plate P-POD Mini-skirt Delta II Second- Stage Guidance Section June 20157Rideshare Symposium 2015

C-Adapter Platform (CAP) Payload Volume C-Adapter Platform (CAP) C-Adapter Platform (CAP) DescriptionA 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. VehicleAtlas V, Delta IV Capacity4 CAPs per C-adapter Interface8-in Clampband Mass45 kg (100 lb) Volume23 cm x 31 cm x 33 cm (9 in x 12 in x 13 in) StatusQualified for GSO battery C-29 Adapter June 20158Rideshare Symposium 2015

Aft Bulkhead Carrier (ABC) ABC Payload Volume Aft Bulkhead Carrier (ABC) Atlas V Centaur Second Stage Aft Bulkhead Carrier (ABC) DescriptionAn 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. VehicleAtlas V Capacity1 ABC per Atlas V Interface15-in Bolted Interface Mass80 kg (176 lb) Volume51 cm x 51 cm x 86 cm (20 in x 20 in x 34 in) StatusOperational; first launch on NROL-36 (OUTSat - NPSCuL box with 8 P-PODs) Users Guide aunch_Vehicles/ABC_Users_Guide_2014. pdf June 20159Rideshare Symposium 2015

eXternal Payload Carrier (XPC) XPC Cover XPC Payload Atlas V Common Core Booster Solid Rocket Booster XPC DescriptionAn 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. VehicleAtlas V Capacity1 XPC per launch InterfaceVariable Mass1,810 kg (4,000 lb) Volume21.2 m 3 (750 ft 3 ) StatusConcept Development DeveloperSpecial Aerospace Services (SAS) (Tim Bulk, June Rideshare Symposium 2015

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 DescriptionA 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). VehicleAtlas V, Delta IV (4-m fairings) Capacity1 DSS-4 per launch, 2 payloads Interface62-in Bolted MassUpper Payload: 2,270 kg (5,000 lb) Lower Payload: 9,000 kg (19,800 lb) VolumeUpper 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) StatusCDR Aft Payload (Notional) Forward Payload (Notional) June Rideshare Symposium 2015

Dual Spacecraft System, 5-m (DSS-5) Payload Separation Ring (2 Places) DSS-5 Aft Payload (Notional) Forward Payload (Notional) DSS-5 DescriptionA 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. VehicleAtlas V, Delta IV (5-m fairings) Capacity1 DSS-5 per launch, 2 payloads Interface62-in Bolted MassForward Payload: 5,440 kg (12,000 lb) Aft Payload: 9,000 kg (19,800 lb) VolumeForward 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) StatusIn development; CDR June Rideshare Symposium 2015

EELV Secondary Payload Adapter (ESPA) 15-inch bolted interface (Six places) Payload envelope (x 6) ESPA Atlas V Centaur Second-Stage Forward Adapter EELV Secondary Payload Adapter (ESPA) DescriptionAn 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. VehicleAtlas V, Delta IV, Falcon 9 Capacity6 payloads per ESPA Interface15-in Bolted Interface Mass181 kg (400 lb) Volume61 cm x 71 cm x 96 cm (24 in x 28 in x 38 in) StatusOperational. First launch on STP-1 June Rideshare Symposium 2015

Separating ESPA DescriptionA 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. VehicleAtlas V, Delta IV, Falcon 9 CapacityVariable Interface62-in Bolted Interface Mass1,360 kg (3,000 lb) Volume350-cm dia. x 61 cm (138-in dia. x 24 in) StatusOperational. First launch on LRO/LCROSS LCROSS ESPA 62-in Separation Rings ESPA June Rideshare Symposium 2015

AQUILA DescriptionA 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). VehicleAtlas V, Delta IV CapacityMultiple payloads per AQUILA InterfaceMission-unique bolted Mass1,000 kg (2,200 lb) Volume142-cm dia. (56-in dia.) x 152 cm (60 in) StatusIn development. CDR , Qualification tests complete Images courtesy of ALS AQUILA (Tall configuration shown with ESPA) Atlas V 4-m Large Payload Fairing (LPF) Primary Payload Volume 8.1 m x 3.8-m dia. (320 in x 148-in dia.) A-Deck June Rideshare Symposium 2015

38” Dual Payload Attach Fitting (DPAF) Payload Separation Ring (2 Places) 38” DPAF Aft Payload (Notional) Forward Payload (Notional) 38-inch Dual Payload Attach Fitting (DPAF) DescriptionA 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. VehiclePegasus, Minotaur I (50" & 61" fairings) Capacity1 38-in DPAF per launch, 2 payloads Interface38-in Bolted MassForward Payload: Max performance of LV Aft Payload: Remaining performance VolumeForward 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) StatusOperational. First launch on SAC-B/HETE June Rideshare Symposium 2015

50” Dual Payload Attach Fitting (DPAF) 50-inch Dual Payload Attach Fitting (DPAF) DescriptionA 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. VehicleMinotaur-C (63" and 92" fairings), Minotaur 1 (61" fairing), Minotaur IV, VI Capacity1 50-in DPAF per launch, 2 payloads Interface38-in Bolted MassForward Payload: Max performance of LV Aft Payload/DPAF: Remaining performance VolumeForward 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) StatusOperational. First launch on KOMPSAT/ACRIMSat June Rideshare Symposium 2015 Payload Separation Ring (2 Places) D D 50” DPAF Aft Payload (Notional) Forward Payload (Notional) Payload Separation Ring (2 Places)

63” Dual Payload Attach Fitting (DPAF) Payload Separation Ring (2 Places) 63” DPAF Aft Payload (Notional) Forward Payload (Notional) 63-inch Dual Payload Attach Fitting (DPAF) DescriptionA 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. VehicleMinotaur-C with 92” fairing, Minotaur IV, VI, Antares Capacity1 63-in DPAF per launch, 2 payloads Interface38-in Bolted MassForward Payload: Max performance of LV Aft Payload/DPAF: Remaining performance VolumeForward 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) StatusOperational, first launch on GFO/ORBCOMM June Rideshare Symposium 2015

Multiple Payload Adapter Fitting (MPAF) Minotaur Fourth- Stage Multiple Payload Adapter Fitting (MPAP) DescriptionA 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. VehicleMinotaur-C with 92-in fairing, Minotaur IV, VI, Antares Capacity1 MPAF per launch, up to 8 payloads Interface38-in Bolted MassESPA Class: 181 kg (400 lb) Smaller Payloads: Up to 60 kg (130 lb) VolumeESPA 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) StatusOperational. First launch on STP- S27 Aft Payloads (2 to 4 Places) Forward Payload(s) Up to Four ESPA-Class June Rideshare Symposium 2015

Minotaur-C P-POD DescriptionA Cubesat P-POD dispenser attached to the Minotaur-C fourth Stage aft structure VehicleMinotaur-C Capacity1 P-PODs (3 Cubesats) InterfaceP-POD Dispenser Mass1.33 kg (2.9 lb) per 1U Cubesat Volume10 cm 3 (4 in 3 ) per 1U Cubesat StatusOperational. First launch on Glory Adapter Plate P-POD Minotaur-C Avionics Section June Rideshare Symposium 2015

Minotaur I Fourth Stage Motor Minotaur P-POD Minotaur-I P-POD DescriptionCubesat P-POD dispensers attached to the Minotaur I and IV fourth Stage motor VehicleMinotaur I with 61” Fairing, Minotaur IV Capacity 1 to 4 P-PODs (up to 12 Cubesats) InterfaceP-POD Dispenser Mass1.33 kg (2.9 lb) per 1U Cubesat Volume10 cm 3 (4 in 3 ) per 1U Cubesat StatusOperational; first launch on MightySat II.1 P-POD June Rideshare Symposium 2015

Pegasus P-POD Description2-U Cubesat P-POD dispenser attached to the Pegasus Avionics Section VehiclePegasus XL Capacity 2x2U CubeSat Dispensors(4 Cubesats) InterfaceP-POD Dispenser Mass1.33 kg (2.9 lb) per 1U Cubesat Volume10 cm 3 (4 in 3 ) per 1U Cubesat StatusIn Development. P-POD Pegasus Avionics Section June Rideshare Symposium 2015

Antares Ride Share June Rideshare Symposium 2015 Antares Ride Share DescriptionLarge toroidal volume VehicleAntares (all models) Capacity Variable InterfaceRail Mount MassUp to 500 kg (1,100 lb) VolumeLocation Dependent StatusIn Development Antares Second Stage

Ariane Structure for Auxiliary Payloads (ASAP 5) DescriptionThe 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. VehicleAriane 5 Capacity1 ASAP5 InterfaceMicro payload mm (11.7-in) Mini payload: 937-mm (37-in) clampband MassMicro payload kg (265 lb) Mini payload kg (660 lb) VolumeMicro payload m (23.6 in) cubed Mini payload m (59 in) cubed StatusOperational. First launch on SPOT 2 Separation System ASAP 5 Platform (8 Microsat Configuration) June Rideshare Symposium 2015 ASAP 5 Platform (2 Minisat/6 Microsat Configuration)

Athena IC, IIC, IIS Athena TBD DescriptionTBD VehicleAthena IC, IIC, IIS CapacityTBD InterfaceTBD MassTBD Volume10 cm 3 (4 in 3 ) per 1U Cubesat StatusIn Development P-PODs Up to 7 Sub-ESPA Class Payloads Orbit Adjust Module June Rideshare Symposium 2015

Athena IIC Athena TBD DescriptionTBD VehicleAthena IIC CapacityTBD InterfaceTBD Mass1.33 kg (2.9 lb) per 1U Cubesat Volume10 cm 3 (4 in 3 ) per 1U Cubesat StatusIn Development 3 ESPA-Class Payloads June Rideshare Symposium 2015 Orbit Adjust Module P-PODs

Falcon 9 TBD DescriptionTBD VehicleFalcon 9 CapacityTBD InterfaceTBD MassTBD VolumeTBD StatusTBD June Rideshare Symposium 2015

Launch Vehicle Points of Contact COMPANYVEHICLESNAME ArianespaceAriane, Soyuz, Vega Lockheed MartinAthenaGregory Orbital ATKAntares, Pegasus, MinotaurWarren SpaceXFalconCurt ULAAtlas, Delta, VulcanKeith Moog CSA Eng.ESPAJoe ALSAQUILAJack June Rideshare Symposium 2015

June 2015Rideshare Symposium