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

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

June 2015

2Rideshare Symposium 2015

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.

June 2015


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.

June 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• [email protected]• 303-269-5499

June 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 2015


Small Launch Vehicles Currently Providing Rideshare Capabilities

• List TBD

June 2015


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

June 2015


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

June 2015


Aft Bulkhead Carrier (ABC)

ABC Payload Volume


Atlas V Centaur Second Stage


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)


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

June 2015





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])

June 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

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)

June 2015


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


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

June 2015


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


Mass 181 kg (400 lb)


Status Operational. First launch 03-2007 on STP-1

June 2015


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


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

June 2015


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

June 2015


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


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

June 2015



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



Mass Forward Payload: Max performance of LVAft Payload/DPAF: Remaining performance


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)



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



Mass Forward Payload: Max performance of LVAft Payload/DPAF: Remaining performance


Status Operational, first launch 10-1998 on GFO/ORBCOMM

June 2015


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


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

June 2015


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)




Status Operational. First launch 3-2011 on Glory

Adapter Plate

P-POD

Minotaur-C Avionics Section

June 2015


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)




Status Operational; first launch 7-2000 on MightySat II.1

P-POD

June 2015


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)




Status In Development.

P-POD

Pegasus Avionics Section

June 2015


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

24

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)

June 2015 Rideshare Symposium 2015

ASAP 5 Platform(2 Minisat/6 Microsat

Configuration)


Athena IC, IIC, IIS

Athena TBD

Description TBD

Vehicle Athena IC, IIC, IIS

Capacity TBD

Interface TBD

Mass TBD


Status In Development

P-PODs

Up to 7 Sub-ESPAClass Payloads

Orbit Adjust Module

June 2015


Athena IIC

Athena TBD

Description TBD

Vehicle Athena IIC

Capacity TBD

Interface TBD



Status In Development

3 ESPA-ClassPayloads

June 2015

Orbit Adjust ModuleP-PODs


Falcon 9

TBD

Description TBD

Vehicle Falcon 9

Capacity TBD

Interface TBD

Mass TBD

Volume TBD

Status TBD

June 2015

Rideshare Symposium 2015 28

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]

June 2015

Rideshare Symposium 2015 29June 2015

Documents

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