Vehicle Configurations
| Configuration |
Stage 1 |
Stage 2 |
Fairing Diameter |
Payload Interface |
| Falcon 9 Full Thrust |
9 Merlin 1D Engines |
1 Merlin 1D Vacuum (MVacD) Engine |
5.2 m (17.1 ft) |
36.9 in (937 mm) or 47 in (1194 mm) |
- SpaceX has offered two performance levels for the Falcon 9 Full Thrust on NLS-II. The first level includes booster performance holdbacks to allow for a Return-to-Launch-Site (RTLS) first stage recovery. The second level provides higher performance by allowing the first stage to be recovered via the SpaceX Automated Spaceport Drone Ship (ASDS), positioned downrange from the launch site. Both performance levels are included on this site for planning purposes; however any questions regarding pricing and availability should be directed to the LSP Flight Projects Office personnel listed on the contacts page.
Optional (Non-Standard) Services
The following non-standard services are not intended as a comprehensive list of all those available; they are intended to highlight major configuration, interface or launch site changes that significantly affect cost and/or the mission design.
Configuration:
- There are currently no available configurations alternate to the standard service.
Interface:
- The provider does not currently offer an alternate adapter as a non-standard service.
Launch Site:
- There are currently no alternate sites to those in the standard service, which are determined based on mission orbit requirements.
Additional Vehicle Information
Click
here to visit the Launch Service Contractor's vehicle information website. Most providers offer an electronic payload planner's guide, which may be available for download on their site.
Note: The LSC websites are owned and operated by entities other than NASA; therefore the contents and access requirements for information on their sites may change at any time. The links have been provided as a source for additional information regarding the launch vehicles (configurations, operations, mechanical/electrical interfaces, etc) but should be used with caution. There may be differences between the information presented on the LSC website and what is available through the NLS II contract. In such instances, the NLS II data is what has been contractually obligated to NASA.
Vehicle Configurations
| Configuration |
Stage 1 |
Stage 2 |
Fairing Diameter |
Payload Interface |
| Falcon Heavy |
3 cores, each with 9 Merlin 1D Engines |
1 Merlin 1D Vacuum (MVacD) Engine |
5.2 m (17.1 ft) |
36.9 in (937 mm) or 47 in (1194 mm) |
- SpaceX has offered two performance levels for the Falcon Heavy on NLS-II. The first level includes booster performance holdbacks to allow for first stage recovery. The second level provides higher performance by utilizing the full vehicle capability, foregoing recovery of the first stage. Both performance levels are included on this site for planning purposes; however any questions regarding pricing and availability should be directed to the LSP Flight Projects Office personnel listed on the contacts page.
Optional (Non-Standard) Services
The following non-standard services are not intended as a comprehensive list of all those available; they are intended to highlight major configuration, interface or launch site changes that significantly affect cost and/or the mission design.
Configuration:
- There are currently no available configurations alternate to the standard service.
Interface:
- The provider does not currently offer an alternate adapter as a non-standard service.
Launch Site:
- There are currently no alternate sites to those in the standard service, which are determined based on mission orbit requirements.
Additional Vehicle Information
Click
here to visit the Launch Service Contractor's vehicle information website. Most providers offer an electronic payload planner's guide, which may be available for download on their site.
Note: The LSC websites are owned and operated by entities other than NASA; therefore the contents and access requirements for information on their sites may change at any time. The links have been provided as a source for additional information regarding the launch vehicles (configurations, operations, mechanical/electrical interfaces, etc) but should be used with caution. There may be differences between the information presented on the LSC website and what is available through the NLS II contract. In such instances, the NLS II data is what has been contractually obligated to NASA.
Vehicle Configurations
| Configuration |
Stage 1 |
Stage 2 |
Fairing Length |
Fairing Diameter |
Payload Interface |
| New Glenn |
GS1 (7 BE-4 Engines) |
GS2 (2 BE-3U Engines) |
21.9 m (72 ft) |
7 m (23 ft) |
Standard Capacity 1575 mm (62 in) payload adapter (PA), with various available COTS separation systems (937 mm, 1194 mm or 1666 mm) |
Optional (Non-Standard) Services
The following non-standard services are not intended as a comprehensive list of all those available; they are intended to highlight major configuration, interface or launch site changes that significantly affect cost and/or the mission design.
Configuration:
- There are currently no alternate New Glenn configurations available through this contract.
Interface:
- High Capacity 3169.9 mm (124.8 in) adapter. Separation system will be determined by mission-specific needs and is not accounted for in this configuration.
Launch Site:
- There are currently no alternate sites to those in the standard service, which are determined based on mission orbit requirements.
Additional Vehicle Information
Click
here to visit the Launch Service Contractor's vehicle information website. Most providers offer an electronic payload planner's guide, which may be available for download on their site.
Note: The LSC websites are owned and operated by entities other than NASA; therefore the contents and access requirements for information on their sites may change at any time. The links have been provided as a source for additional information regarding the launch vehicles (configurations, operations, mechanical/electrical interfaces, etc) but should be used with caution. There may be differences between the information presented on the LSC website and what is available through the NLS II contract. In such instances, the NLS II data is what has been contractually obligated to NASA.
Vehicle Configurations
| Configuration |
Stage 1 Motor |
Stage 2 Motor |
Stage 3 Motor |
Stage 4 |
Fairing Diameter |
Payload Interface |
| Pegasus XL |
Orion 50S XL |
Orion 50 XL |
Orion 38 |
- |
1.27 m (50 in) |
967 mm (38 in) |
Optional (Non-Standard) Services
The following non-standard services are not intended as a comprehensive list of all those available; they are intended to highlight major configuration, interface or launch site changes that significantly affect cost and/or the mission design.
Configuration:
- The Pegasus XL with HAPS (Hydrazine Auxiliary Propulsion System) configuration adds a liquid monopropellant 4th stage to the standard configuration. HAPS is intended to improve injection accuracy; however may also provide enhanced performance to some orbits.
Interface:
- 254 mm (10 in) adapter
- 432 mm (17 in) adapter
- 3-point payload adapter, providing 3 attach points on a 1 m (39.38 in) interface
Launch Site:
Depending on mission orbit requirements, 3 options are available as alternates to the standard service launch site, Vandenberg Space Force Base (VSFB)
- Reagan Test Site (RTS) at Kwajalein
- Cape Canaveral Space Force Station (CCSFS)
- Wallops Flight Facility (WFF)
Additional Vehicle Information
Click
here to visit the Launch Service Contractor's vehicle information website. Most providers offer an electronic payload planner's guide, which may be available for download on their site.
Note: The LSC websites are owned and operated by entities other than NASA; therefore the contents and access requirements for information on their sites may change at any time. The links have been provided as a source for additional information regarding the launch vehicles (configurations, operations, mechanical/electrical interfaces, etc) but should be used with caution. There may be differences between the information presented on the LSC website and what is available through the NLS II contract. In such instances, the NLS II data is what has been contractually obligated to NASA.
Vehicle Configurations
| Configuration |
Stage 1 |
Stage 2 |
Fairing Length |
Fairing Diameter |
Payload Interface |
| VC0 |
2 BE-4 Engines |
2 RL10C Engines (Dual Engine Centaur) |
Short: 15.5 m (51 ft) |
5.4 m (17.7 ft) |
1194 mm (47 in) PSR with lightweight C22 adapter |
Optional (Non-Standard) Services
The following non-standard services are not intended as a comprehensive list of all those available; they are intended to highlight major configuration, interface or launch site changes that significantly affect cost and/or the mission design.
Configuration:
Solid rocket boosters (SRBs) can be added to the VC0 configuration to increase the performance capability.
- VC2 adds 2 GEM 63XL motors to the VC0 configuration.
- VC4 adds 4 GEM 63XL motors to the VC0 configuration.
- VC6 adds 6 GEM 63XL motors to the VC0 configuration.
A longer fairing is available for spacecraft that require more volume
- Long: Includes a 5.8 m (19 ft) extension, to increase the fairing length to 21.3 m (70 ft)
Interface:
- 1666 mm (65.6 in) adapter
Launch Site:
- There are currently no alternate sites to those in the standard service, which are determined based on mission orbit requirements.
Additional Vehicle Information
Click
here to visit the Launch Service Contractor's vehicle information website. Most providers offer an electronic payload planner's guide, which may be available for download on their site.
Note: The LSC websites are owned and operated by entities other than NASA; therefore the contents and access requirements for information on their sites may change at any time. The links have been provided as a source for additional information regarding the launch vehicles (configurations, operations, mechanical/electrical interfaces, etc) but should be used with caution. There may be differences between the information presented on the LSC website and what is available through the NLS II contract. In such instances, the NLS II data is what has been contractually obligated to NASA.