JuanCastillo29/space-mission-intelligence-data huggingface dataset:
& Gas
Sampling
Services

is available from four 0.375 in (9.525 mm) quick-disconnect couplings on the service bay west wall  Hypergol vents are located on service bay west wall  Propellant waste drain system is a non-storage system used in event of a spill.
The system consists of two trench drains in center of a sloped floor, 20 ft x 40 ft (6.1 m x 12.2 m) with a 2 in (51 mm) slope per 10 ft (0.3 m).
 There is an ammonia vapor vent pipe on west wall of the service bay.
Approximately 110 ft (33.5 m) of 4 in (102 mm) diameter high-density
Vehicle Assembly Building (VAB)

The VAB, shown in Figure 7-8, supports vertical integration and stacking of the encapsulated payload to the upper stage, and where applicable, the encapsulated payload to Orion. It consists of a main transfer aisle, low bay and four high bays that can support various customers and unique launch configurations. The VAB contains multiple cranes that can be used for lifting, stacking and mating various launch components. The SLS vehicles will be stacked in High Bay 3, which has the capability of accessing different locations around the launch vehicle using multiple fixed platforms. Similarly, receipt, inspection, checkout and final integration can be performed in the facility. The VAB contains weather/lightning protection and security.

[Figure: Figure 7-8. Vehicle Assembly Building (VAB)]

The low bay consists of eight checkout cells, low bay transfer aisle and four shop/processing areas, designated as areas K, L, M and N. The low bay transfer aisle is capable of receiving, staging, inspecting and transferring flight hardware components. The high bay area consists of six tower sections, noted as towers A, B, C, D, E and F, and four assembly areas, noted as HB1, HB2, HB3 and HB4. The high bays provide the capability for stacking, mating, integrating, servicing and final checkout of flight hardware components. HB1 and HB3 are located on the east side of the VAB and HB2 and HB4 are located on the west side. The east and west side high bays are separated by a transfer aisle, which is used for staging, lifting, stacking and integrating hardware prior to lifting into one of the high bays for final assembly. Figure 7-9 depicts the VAB floor plan; Table 7-7 details available resources.
HB3 has the capability to provide 360° access to the outer mold line of the encapsulated spacecraft/payload through the use of multiple fixed and moving platforms within the high bay.
The electronic version is the official approved document.

Access to the payload can be provided through doors within the base of the fairing. Specific access requirements will be developed during the planning stage of each mission.
The VAB provides interfaces to the ML and access to flight hardware. VAB systems that support the ML include ECS, pneumatics, handling and access, and the Ground Cooling Subsystem (GCS).

[Figure: Figure 7-9. Vehicle Assembly Building (VAB) Floor Plan]

[Table: Table 7-7. VAB Resource Overview]

|  | Resource |  |  | Description |  |
| --- | --- | --- | --- | --- | --- |
| Electrical/ Power |  |  |  Power enters at 13.8 kV, stepped down as needed to 480 VAC  Distributed throughout the facility and feeds end-user equipment at voltage levels of 480/277 or 208/120 with either single or three phase |  |  |
| Gases/ Liquids |  |  |  Provide compressed air at 125 psi  GN2 is supplied to high and low bays at pressure of 6,000 psi. Gas is distributed from High Pressure Gas Storage Building to Tower D, and then distributed to towers A, B, C, E, and F  GHe will be brought in on a tube bank when required  Conditioned air purge can be provided to the launch vehicle and payload on the ML in the VAB through umbilicals on the ML tower; temperature ranges |  |  |
The electronic version is the official approved document.

of this purge depend on the final ECS configuration but nominally range from 65-85° F
This facility has the capability to provide the following services: Spaceport Command and Control System (SCCS), Kennedy Integrated Test System (KITS), KSC Network (KNET), Operational Information System (OIS), Telephone, Paging and Area Warning System (PAWS), Operational Television (OTV) and Radio Frequency and Telemetry Station (RFTS).
The VAB high bays have a 250 and 325 ton (227 and 295 t) bridge cranes that operate on common support rails. The 250 ton crane is located on the east side while the 325 ton crane is on the west side of the VAB. Due to this configuration, the 325 ton crane does not have access to the extreme east side of HB1 or HB3, and the 250 ton crane does not have access to the extreme west side of HB2 or HB4. The maximum hook height (to the VAB floor) for all of these cranes is 462.5 ft (140.9 m).
The transfer aisle has a 175 ton (159 t) bridge crane that operates in the north and south directions only. The maximum hook height (to the VAB floor) for this crane is 160 ft 3 in (48.8 m).
Payload customer access will be provided within the VAB via EGS-supplied GSE and cleanrooms of ISO 8 classification. Cleanrooms ensure that planetary protection and contamination prevention will not be compromised. EGS can accommodate up to two access doors (each with a cleanroom entry way) for customers to access their payload. However, number and location will vary according to mission. The EGS Program has identified areas on the PLF and USA where doors may be located. This door map will serve as the customer’s template to use when designing and implementing door locations.
Mobile Launcher (ML)

The ML consists of the Mobile Launcher Base (MLB) and an integrated Mobile Launcher Tower (MLT), providing all of the service interfaces needed to physically integrate, test, service and launch the integrated SLS vehicle, including the encapsulated payload. While SLS and the ML are in the VAB, platforms provide access for mating all umbilicals on the MLT with the integrated vehicle; limited access is provided for last-minute payload closeout operations. Also, access will be provided to the Orion Crew Module (CM) via the Crew Access Arm (CAA) and to the base of the launch vehicle. The first ML will accommodate SLS Block 1 configurations while a second ML is being developed to support SLS Block 1B configurations. Figure 7-10 shows a ML configuration for SLS Block 1B.
The ML uses the Orion Service Module Umbilical (OSMU) and EUS Umbilical (EUSU), located on the MLT, to provide propellants, ground commodities, electrical, purges and access to Orion and the EUS. Provisions for PPL, CPL and SPL ground services will be routed through the SLS EUS Forward Adapter via the EUSU.
The ML is allocated to support SLS and Orion operations. It will support multiple Orion configurations and SLS blocks with scarring for extensibility. The ML consists of equipment and
The electronic version is the official approved document.

[Table: Table 7-8. ML Resource Overview]

|  | Resource |  |  | Description |  |
| --- | --- | --- | --- | --- | --- |
| Electrical/ Power |  |  |  Power provided through VAB, CT and pad  MLB provides voltage levels of 480/288 or 208/120 with either single or three phase  MLT provides the same voltage levels as MLB in addition to being capable of providing 120 V single phase  Both MLB and MLT provide grounding/lightning protection and are Class 1, Division 2-compliant, with the exception of pressurized spaces  Two 275 kW UPS units are available in static auto tie, providing AC voltage levels of 480 or 208/120 in either single or three phase |  |  |
| Gases/ Liquids |  |  |  Compressed air can be provided at 125 psi with a flow of 88 CFM  Conditioned air purge can be provided to launch vehicle and payload on MLB in VAB high bay, during rollout on CT, and at the pad through umbilicals on MLT. Flow rates depend on facility capabilities |  |  |

The Payload User Room is designed for payload ML operations that require close proximity to the payload. The room will serve as umbilical interface room for payload connections to EGS. EGS will provide transportation of payload customer GSE to the Payload User Room and will set up the room. The User Room will include space for all racks, cabling and other GSE as well as space for GN2 purge carts. The Payload User Room can accommodate up to three customers and one table per customer, and additional furniture and office supplies. Space to allow for troubleshooting will also be provided. At all times, the room will retain a positive pressure to ensure that the room is Class I Division II-compliant so customers will not have to make all of their GSE explosion-proof. The room will be staffed during electrical ground support equipment (EGSE) installation, connection, configuration and checkout. Additionally, the support room will be staffed during initial umbilical connection and EGS circuit connection and verification. Payload Test Operations will be accommodated as required. Additionally, after launch the room will be de-configured, and EGSE and purge carts will be removed.
Crawler-Transporter (CT)

The Crawler-Transporter (CT), shown in Figure 7-11, is diesel-powered and capable of transporting the ML with a vehicle stack along the crawlerway between the VAB and the launch pad. The CT lifts its load by lowering via the jacking, equalization and leveling (JEL) system, allowing it to drive under the ML. In addition to raising or lowering the height of the CT, the JEL system also keeps the ML level while transporting the enormous SLS stack on the ML. This system is critical for keeping the integrated vehicle nearly level to avoid any unnecessary loads on the vehicle structure.

[Figure: Figure 7-11. Crawler-Transporter]

The Shuttle era CT system was modified to carry the heavier SLS rocket, ML, and allow for an extended operation period. The CT comprises a variety of systems, which include JEL lifting cylinders, propulsion, braking, steering, generators, computers and controls. The CT interfaces with the ML at four structural pickup points that raise, lower and level the element. The CT will provide electrical power to the MPPUs during rollout for in-transit ECS purging. Additional power is available for ML electrical loads during rollout. Table 7-9 details CT resources available.

[Table: Table 7-9. CT Resource Overview]

|  | Resource |  |  | Description |  |
| --- | --- | --- | --- | --- | --- |
| Electrical/ Power |  |  |  Provide voltage levels of 480/277, three-phase power at 60 Hz to ML and vehicle while they are being transported |  |  |
| Gases/ Liquids |  |  |  ISO Class 8 conditioned air purge of 65-85° F (18 to 29° C) can be provided to the launch vehicle and payload on ML while in transit through umbilicals on MLT |  |  |
Pad B

Launch Complex 39B (LC-39B), or pad B, shown in Figure 7-12, is a human-rated space launch complex encompassing 57,289 ft2 (5,322.3 m2) that provides the services required for each launch.
The launch pad facilities at LC-39B work in conjunction with the ML and the Launch Control Center (LCC) to provide the necessary support to conduct launch operations. All pad B services are provided to the vehicle through the ML, except lightning protection. The facilities at LC-39B include cryogenic propellant storage and servicing equipment, electrical systems, a flame trench and flame diverters, HVAC, weather data instrumentation and lightning protection. Table 7-10 details available resources.

[Figure: Figure 7-12. Launch Complex 39B (LC-39B)]
The electronic version is the official approved document.

[Table: Table 7-10. Pad B Resource Overview]

|  | Resource |  |  | Description |  |
| --- | --- | --- | --- | --- | --- |
| Electrical/ Power |  |  |  Electrical distribution system supplied by three 13.8 kV feeders, two of which are backed up by generators at an emergency power plant  Distributed voltage levels of 480/277 or 208/120 with either single or three- phase as required  Two 275 kVA UPS units are available in static auto-tie configuration, capable of providing AC voltage levels at 480 or 208/120 in single or three-phase configuration |  |  |
| Gases/ Liquids |  |  |  Compressed air can be provided at 125 psi  ISO 8 conditioned air purge of 65-85° F (18 to 29° C) with humidity ratio of 37 grains per pound) can be provided to launch vehicle and payload on the ML at the pad through umbilicals on MLT  GHe and GN2 are supplied at nominal pressure of 6,000 psi and if needed 10,000 psi can be provided via mobile compressed gas trailer  GO2 can be provided at pressure of 6,000 psi through mobile compressed gas trailer  Breathing air can be supplied at 6,000 psi via fixed storage vessels |  |  |

The ML systems utilized at LC-39B include ECS, Kennedy Ground Control System, Ignition Overpressure/Sound Suppression (IOP/SS), GCS, Hazardous Gas Leak Detection (HGLD), pneumatics, weather (Wx), Sensor Data Acquisition Subsystem (SDAS), cryogenics and Ground Special Power (GSP). This facility has the capability to provide the following services: SCCS, KITS, OIS, PAWS, T&CD, OTV, Broadband Cable Distribution System (BCDS) and Photo Optical Control System II (POCS II).
Launch Control Center

The Launch Control Center shown in Figure 7-13, is a four-story building attached to the southeast corner of the VAB. The Launch Control Center is used to control operations interfaces with the launch vehicle and spacecraft/payload. Available communication and network capabilities include the checkout system in the firing rooms (FRs), RF antennas used to collect telemetry, weather radar and radar antennas used to skin-track launch vehicles. The U.S. Air Force provides vehicle tracking and telemetry resources, weather forecasting, control of nearby air- and sea-space, and flight-termination capabilities. Incoming and outgoing communications feeds through the Launch Control Center and various areas within KSC are provided via the Communications Distribution and Switching Center (CD&SC).

[Figure: Figure 7-13. Launch Control Center]

Firing Room (FR) 1, also known as the Young-Crippen Firing Room, will control all SLS launch operations. FR 4 provides the capability for spacecraft control rooms prior to and during launch. There are four smaller control rooms that can be expanded to accommodate teams of differing sizes. Rooms can be configured to support specific needs, allowing teams to bring in their own equipment. Secure access will be provided to each of the rooms, along with access to NASA communications infrastructure and electrical services, including UPS.
The EGS Program provides complete vehicle integration and launch services for the SLS launch vehicle and spacecraft/payload. A system of facilities, equipment and personnel trained in launch vehicle and integration and launch operations is in place.
Payloads are manufactured/assembled at the payload provider’s manufacturing facility and arrive at KSC in customer-provided shipping containers or by aircraft. Any support required for offloading at KSC can be negotiated during development of the LSSRD. Upon arrival at KSC, the spacecraft and associated GSE will be delivered to an assigned PPF or HPF for standalone processing. EGS provides transportation, handling and security for the spacecraft and customer-
The electronic version is the official approved document.

For all of the various payload elements, the same basic processing phases will be followed for payload encapsulation at the PPF. Figure 7-17 shows this process for a CPL encapsulated by a canister USA in an offline processing facility, but the process would be similar for PPL encapsulated by a sectored fairing. Prior to payload arrival, the USA Canister or PLF sectors are delivered to the PPF where they are inspected and prepared for payload encapsulation. The USA or PLF is debagged, cleaned and inspected, then placed on GSE for assembly and rotation operations. Encapsulation operations begin with the placement of the transportation pallet assembly in the encapsulation area and the installation of the PLA. The payload is then configured for encapsulation and mated to the PLA. Payload-specific integrated checkouts may be performed upon the completion of this procedure per the manufacturer’s requirements. The USA or PLF sectors are positioned and configured for encapsulation in the PPF HB. The USA or PLF is then mated to the PLA and the encapsulated payload is prepared for transportation from the PPF to the VAB. The payload transporter is equipped with an ECS capable of providing a conditioned air purge to the payload in transit. This allows for positive pressure, humidity and temperature control for encapsulated payloads up to 65,000 lbm (29,483 kg). Once in the VAB, the temporary ECS is disconnected and an integrated lift is used to move the encapsulated payload from the transportation pallet to the top of the integrated vehicle stack, where it is mated with the EUS.

[Figure: Figure 7-17. Payload Encapsulation Operational Flow (USA Example)]
Listed below is a synopsis of services that EGS provides to customers during the integration and processing operations. Standard services are not limited to this list:  Provide personnel, services, hardware, equipment, documentations, analyses and facilities to support mission planning, launch vehicle production, payload integration and launch  Provide all range and safety documents for payload customer to complete  Facilitate the range and safety integration process  Provide an adapter and technical support for a mechanical interface compatibility verification test at assigned processing facility  Provide transportation for the customer’s spacecraft container and all GSE  Provide ISO 8 cleanroom integration space for the payload and GSE prior to launch  Support customer’s hazardous operations  Provide GSE to support physical mating of payload to PLA, perform encapsulation and integration of encapsulated system to the launch vehicle  Process the launch vehicle and test electrical interfaces  Provide conditioned air into fairing during ground processing  Provide two access doors in the PLF/USA at pre-designed locations  Supply internet drops in customer processing facility  Supply electrical outlets in customer processing facility  Provide generators to customer processing facility  Provide security to customer processing facility  Provide all administrative items (chairs, desks, copiers, phones, filing cabinets, tables, etc.)  Ensure processing facility maintains humidity, temperature and particulate described in designated facility section  Supply cranes in processing facility  Supply contamination prevention garments  Provide propellant loading gases, hypergols  Provide transportation equipment  Provide facility equipment  Provide processing services such as battery disposal, calibration, decontamination, sample analysis, thermal analysis, etc.

Additional services that are not considered typical, but are still feasible are described as Non-Standard Services (NSS). These are services that are out-of-scope of current architecture capability and/or budget baseline. Below is a list of example NSS, but they are not limited to this list:  Extra cleanliness requirements otherwise specified by facility description (i.e. ISO 7)  Special facility environment requirements otherwise specified by facility description  Special purge requirements otherwise specified by facility description  Transportation requirements such as oversized loads or high-vibration sensitivity  Handling guidelines not mentioned in facility description (RF restrictions, height restrictions)  Training services
The electronic version is the official approved document.

 Facility reconfiguration to meet requirements  Direct payload interaction with LCS for pre-integration testing and launch support  Gases or commodities not mentioned in facility breakdown  Utilizing KSC personnel for pre-integration processing (alignments, machine, non-destructive evaluations)  Work time policy conflicting with KSC guidelines  Tool control plan that conflicts with KSC guidelines  Safety restrictions  RF attenuation/exposure monitoring  Alternative personnel protection requirements  Access door location on the conical section of the PLF or USA  Power provided to the payload during rollout
Exploration Systems Development (ESD), a division within NASA’s Human Exploration and Operations Mission Directorate (HEOMD), is responsible for management and integration of the Orion, SLS and EGS Programs. ESD is responsible for manifesting all spacecraft/payloads to be launched on SLS. The SLS Program is responsible for launch vehicle integration for all SLS missions. As part of the SLS Program, the SPIE office has the responsibility for spacecraft/payload integration into SLS throughout the lifecycle of a mission. EGS supports the SLS Program by performing launch site processing of the payload and mission-dependent equipment, including assessment and allocation of ground-related analytical requirements, as well as actual physical hardware processing. The Flight Operations Directorate (FOD) supports the SLS Program by managing integrated flight operations and flight rules including those for the payload.
Clear communication between the SLS, EGS and spacecraft/payload is essential to flight success. SLS and EGS have established procedures and interfaces to delineate areas of responsibility and authority between SLS, ground systems and spacecraft/payloads. Based on lessons learned from other programs, such as EELVs, ISS, and the Space Shuttle Program, the SLS - spacecraft/payload integration process is planned to be compatible with spacecraft/payload developer-defined milestones whenever possible. Therefore, this process could formally start with the spacecraft/payload’s Systems Requirements Review (SRR), or equivalent, and end with spacecraft/payload encapsulation, launch and deployment. The actual integration process and schedule can be tailored to meet SLS, EGS and spacecraft/payload requirements for each flight. Spacecraft/payload developers are encouraged to interact with SPIE and EGS as early as possible during the concept development phase. Early interaction facilitates mission and vehicle feasibility/compatibility analysis as well as schedule milestone discussion that will identify preferred flight and accommodation approaches.
SLS Program Responsibilities

The SLS Program is responsible for design, manufacture and integration of the launch vehicle. As part of the SLS Program, SPIE manages not only the development of spacecraft/payload accommodation hardware, but also manages the integration of the spacecraft/payload into SLS including: flight, ground and range safety; and electrical, mechanical, environmental and electromagnetic compatibilities. Other responsibilities of the SPIE office include guidance system integration, mission analysis, software design and ground and flight operations support.
SPIE will assign a Payload Integration Manager (PIM) to serve as the single spacecraft/payload point of contact for all integration activities for each spacecraft/payload on a specific mission. The PIM, representing the spacecraft/payload to the vehicle, will ensure the spacecraft/payload receives needed analytical, physical, and operations resources during all phases of integration and implementation. The SLS Program coordinates with the EGS Program to support payload ground activities and EGS Program integration activities including SLS Program representation to ensure cross-program integration.