JuanCastillo29/space-mission-intelligence-data huggingface dataset:
The electronic version is the official approved document.

preclude ingestion of windborne contamination during transport to the launch vehicle, mate and post-mate operations. Potential for user access to the spacecraft/payload inside the encapsulated USA/PLF will be evaluated on a case-by-case basis. If available, this access can be used for subsequent incursions inside the USA/PLF through the access doors while the vehicle is within the VAB. Personnel garmenting, activities and work procedures are controlled to maintain the environment surrounding the encapsulated fairing to acceptable standards. Spacecraft/payload outgassing will be controlled within the SLS USA (which is a shared compartment with Orion and EUS) and PLF.
Cleanliness levels will be categorized as “generally” or “visibly” clean, to meet a wide range of cleanliness needs. A “generally” clean level ensures that parts are free of manufacturing residue, dirt, oil, grease, processing debris and any other extraneous contamination. This generally clean level should be assigned to hardware that is not sensitive to contamination and can be easily and quickly cleaned.
“Visibly” clean hardware will meet the requirements of the generally clean level and will be cleaned and qualitatively verified to be free of all particulate and non-particulate material visible to the normal eye. Hardware cleaned to this level will be continuously protected using heat-sealed double bagging until the hardware is integrated or assembled into the next level of assembly in a cleanroom environment. If the item is too large in size or weight, the visibly clean surfaces shall be prepackaged to cover all exposed critical surfaces.
There are four levels of visibly clean requirements. The first level is Standard, which will have an incident light level greater or equal to 500 lm/m2 with an inspection distance of 5 to 10 feet (1.5 to 3 m). The next level, Sensitive, will have the same incident light level as Standard, but with a closer inspection distance of 2 to 4 feet (0.6 to 1.2 m). A Highly Sensitive level will have an incident light level greater than or equal to 1000 lm/m2 with an inspection distance of 6 to 18 inches (0.15 to 0.45 m). Lastly a Custom requirement level may be set and is specified on a project-to-project basis. In addition, the visibly clean requirements may be subject to ultraviolet inspection. This inspection will utilize a wavelength of 3,200 to 3,800 angstroms.
OSA Mount

≤ 12U CubeSat type Secondary Payloads
PPL
CPL
Universal
Forward Ring
Stage Adapter (USA)
PLA PLA
Block 1 Upper Stage
Block 1B/2 Upper Stage Secondary Payload Brackets
Block 1B/2 Upper Stage
Upper Stage
6U CubeSat Dispenser (ref.) Aft Ring
(up to 16)
Block 1 shown for reference only Block 2 shown for reference only

[Figure: Figure 6-1. Range of SLS Spacecraft/Payload Accommodations]
 Orion spacecraft – crew capsule accommodated on an SLS Block 1 OSA or Block 1B/2
USA that determines initial mission trajectory via an upper stage injection burn
 PPL – uncrewed spacecraft/payload accommodated in an SLS Block 1/1B/2 PLA/PLF that
determines initial mission trajectory via an upper stage injection burn
o 5 m-class diameter payloads can be accommodated on Block 1 (reference only)
o 8.4 m-class diameter payloads can be accommodated on Block 1B
o 8.4 m-class and larger diameter payloads can be accommodated on Block 2
 CPL – uncrewed spacecraft/payload accommodated within an SLS Block 1B/2 PLA/USA;
compatible with an initial Orion-determined trajectory via an EUS injection burn
compatible with an initial Orion-determined trajectory via an EUS injection burn
o Orion docks to CPL and delivers CPL to its final destination (Orion CPL)
o Or, post-Orion separation, CPL delivers itself to final destination (independent CPL)
 SPL – accommodated within an SLS Block 1 OSA, Block 1B/2 PLA/USA, or Block 1B/2
PLA/PLF; compatible with an Orion or PPL initial trajectory via an EUS injection burn
to overall flight and ground systems architecture while not jeopardizing crew safety
or primary mission objectives
o Multiple locations available on the OSA for ≤12U-sized CubeSats
o Multiple locations available on the PLA for ≤27U-sized CubeSats
o Potential accommodation of larger than 27U SPL on or above the PLA

Figure 6-2 provides detail on a range of payload enclosure approaches potentially available to
spacecraft/payload depending on mission definition and timing.

90.0’ (27.4 m)
62.7’ (19.1 m) 47.0’ (14.4 m) 32.8’ (10.0 m)
4.85’ (1.48 m)

| Enclosure |  | 5.1m PLF | 5.1m PLF | OSA | 8.4m USA | 8.4m USA PLF | 8.4m PLF, Short | 10m PLF Short | 8.4m PLF, Long | 10m PLF Long |  |
| --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- | --- |
|  |  |  |  |  |  |  |  |  |  |  |  |
|  |  |  |  |  |  |  |  |  |  |  |  |
|  | Payload Type | 5m PPL | 5m PPL | 5m SPL | 8.4m CPL | 8.4m PPL | 8.4m PPL | 10m PPL | 8.4m PPL | 10m PPL |  |
|  | Length | 47.0 ft | 62.7 ft | 4.85 ft | 32.8 ft | 47.2 ft | 62.7 ft | 62.7 ft | 90 ft | 90 ft |  |
|  |  | 14.3 m | 19.1 m | 1.48 m | 10.0 m | 14.4 m | 19.1 m | 19.1 m | 27.4 m | 27.4 m |  |
|  | Diameter | 16.7 ft | 16.7 ft | 17.7 ft | 27.6 ft | 27.6 ft | 27.6 ft | 33.0 ft | 27.6 ft | 33.0 ft |  |
|  |  | 5.1 m | 5.1 m | 5.4 m | 8.4 m | 8.4 m | 8.4 m | 10.0 m | 8.4 m | 10.0 m |  |
| In | ternal Diameter | 15.1 ft | 15.1 ft | 16.7 ft | 24.6 ft | 24.6 ft | 24.6 ft | 29.9 ft | 24.6 ft | 29.9 ft |  |
|  |  | 4.6 m | 4.6 m | 5.1 m | 7.5 m | 7.5 m | 7.5 m | 9.1 m | 7.5 m | 9.1 m |  |
| Av | ailable Volume | 5,358 ft3 | 8,118 ft3 | 516 ft3 | 10,100 ft3 | 11,260 ft3 | 21,930 ft3 | 32,470 ft3 | 34,910 ft3 | 46,610 ft3 |  |
|  |  | 151.7 m3 | 229.9 m3 | 14.6 m3 | 286.0 m3 | 319 m3 | 621 m3 | 919 m3 | 988 m3 | 1,320 m3 |  |
| Pot (N | ential Availability o Earlier Than) | COTS | COTS | 2020 | 2024 | 2025 | 2025 | 2029 | 2029 | 2029 |  |
|  |  |  |  |  |  |  |  |  |  |  |  |

[Figure: Figure 6-2. Range of Potential SLS Payload Fairings and Stage Adapter Approaches]
PLF concept, if needed prior to the availability of a purpose-built 8.4 m PLF. The SLS 8.4m PLF,
Short concept is equivalent in height to today’s tallest ELV fairings and the 8.4m PLF, Long
concept is the tallest fairing length that can be accommodated within existing launch site
encapsulation facilities. These lengths are representative of the total range of 8.4m PLFs under
consideration, and not meant to imply a particular design implementation at this time. The SLS 10m
PLF concept is currently envisioned to support human lander missions, Mars exploration flights, as
well as large-volume payloads (e.g., nuclear thermal propulsion, large-aperture telescopes).

These fairings and adapters are used to encapsulate payload for SLS missions. Because this
“encapsulation” is both SLS Block-dependent (1, 1B or 2) and  configuration-dependent (crew or
cargo), the combination of fairing, adapters and payloads are referred to as the SLS ISPE. Figure
6-3 provides nominal ISPE details for SLS Block 1; the ISPE includes all equipment between the
SLS Core Stage and Orion for the crew configuration and all equipment above the SLS Core Stage
for the cargo configuration (shown for reference only). Figure 6-4 provides nominal ISPE details
for SLS Block 1B/2; the ISPE includes all equipment between the SLS EUS and Orion for the crew
configuration and all equipment above the SLS EUS for the cargo configuration.
Payload
Element
(ISPE)
ISPE

(PPL)
Payload Adapter (PLA)
Orion Stage Adapter (OSA) Interim Cryogenic Propulsion Stage (ICPS)
Booster
Booster
Booster
Booster
Launch Vehicle Stage Adapter (LVSA)
Stages
Stages
(Core)
(Core)

[Figure: Figure 6-3. SLS Block 1 Integrated Spacecraft/Payload Element (ISPE)]
initial crewed flights will deliver Orion on a trajectory around the Moon to test critical launch
vehicle and spacecraft systems. SLS will interface with Orion at its 18 ft (5.5 m) diameter
Spacecraft Adapter (SA) aft interface as shown in Figure 6-5. SLS Block 1 accommodates the SA
with a SLS provided OSA which provides a 16.7 ft (5.1 m) diameter interface to the ICPS. SLS
Block 1B/2 accommodates the SA with a SLS provided USA that provides a 27.6 ft (8.4 m)
diameter interface to the EUS.  Upon Orion separation from SLS, the Orion SA remains attached
to the SLS OSA (Block 1) or USA (Block 1B/2) during payload operations.
PPL launched on SLS are protected by a PLF that shields them from the external environment and contamination during ground operations, launch and ascent. PLFs incorporate hardware to control thermal, acoustic, electromagnetic and contamination environments for the payload. Ground services can provide the fairing with conditioned air, fueling/draining, power and command/telemetry relay, and standard access door locations. Ground services may also provide additional payload access to the encapsulated payload while in the VAB or nitrogen purge at the pad as optional services. During vehicle ascent, fairings protect the payload from aerodynamic, acoustic and thermal loads, and are jettisoned when an acceptable free molecular heating rate is reached.
SLS can accommodate a wide variety of fairings, ranging from existing ELV 5m-class diameter PLFs to SLS 8.4m or 10m-class diameter PLF concepts. The internal fairing envelopes shown in the following sections define the available payload dynamic envelope, relative to the payload separation plane. All SLS 8.4 m and 10 m PLFs envelopes presented here are still in the conceptual design stage. With the user community’s help, the SLS Program is in the process of identifying preferred fairing diameters and lengths to best accommodate potential exploration missions. Therefore, potential users should use the following information only for initial feasibility assessments. For the latest information on payload fairing accommodations, users should contact the SLS SPIE office directly at nasa-slspayloads@mail.nasa.gov.
5 m-class Diameter Payload Fairings (SLS Block 1 Reference Only)

For more information on using the composite 5.1 diameter PLFs (and their associated payload adapter interface to the ICPS) on SLS Block 1 shown in Figure 6.2, refer to the Delta IV User’s Guide. Other ELV provided 5m-class fairings may be compatible with Block 1, but would need to be assessed on a case-by-case basis.
8.4 m-class Diameter Payload Fairings (SLS Block 1B/2)

As shown in Figure 6-2, a number of representative SLS Block 1B/2 8.4m PLF concepts are under evaluation.
Adding a nose cone to the USA creates a composite 47 ft (14.4 m) long USA PLF that, while heavier than a custom-built 8.4m PLF, could be available earlier to support near term, non-Orion flights. The available USA PLF static envelope is shown in Figure 6-6. It is anticipated the USA PLF will offer installation of differently sized access doors, as needed, and an interior surface compatible with acoustic treatments, to meet environmental requirements.
The USA PLF concept of operations assumes that once in orbit, the upper portion of the USA PLF “canister” is jettisoned from the EUS (note: this is in contrast to a PLF, which is jettisoned in “sectors” during ascent and prior to orbit). The non-separable portion of the USA PLF remains with EUS during the injection burn; the height of this non-separable portion is less than the PLA interface.

[Figure: Figure 6-6. Composite 8.4 m USA PLF Concept]
The electronic version is the official approved document.

Figures 6-7 and 6-8 provide the available static envelope for the 8.4 m diameter short and long composite PLF concepts. These fairings jettison using traditional sectors versus the canister approach employed on USA PLF. Sectors are jettisoned during ascent (prior to LEO or direct insertion by the EUS).
The current length of 62.7 ft (19.1 m) for 8.4m PLF, Short concept represents the maximum length possible, based on ceiling hook height constraints of Kennedy Space Center’s (KSC) Payload Hazardous Servicing Facility. Potential exists for longer PLFs by lengthening the cylindrical section, as needed. The current maximum PLF length of 90 ft (27 m), as shown in the 8.4m PLF, Long, is constrained by the door and ceiling heights of Cape Canaveral Air Force Station’s (CCAFS’s) largest encapsulation facility.
As the Block 1B/2 design continues to mature, the structural limits of the SLS vehicle stack may preclude use of certain PLF diameter and length combinations. Therefore, potential users are encouraged to work with the SPIE office as soon as possible to define the feasibility of specific spacecraft/payload PLF diameter and length needs.
10 m-class Diameter Payload Fairings (SLS Block 2)

Once SLS transitions to the Block 2 configuration, using the enhanced performance of an 8.4 m diameter EUS and improved performance boosters, potential accommodation of larger diameter PLFs in the 10 m-class diameter is under analysis.
The current 10m PLF, Long concept represents the maximum 90 ft (27.4 m) length possible based on door width and door and ceiling hook height constraints of CCAFS’s largest encapsulation facility. Figure 6-9 provides the available static envelope for this 10 m diameter PLF. Potential exists for shorter 10m PLFs by shortening the cylindrical section as shown in Figure 6-10. A 62.7 ft (19.1 m) long 10m PLF can physically fit within KSC’s Payload Hazardous Servicing Facility for encapsulation, although additional study is required to determine the feasibility of simultaneous payload staging, handling and integration within the existing facility footprint.
As the Block 1B/2 design continues to mature, the structural limits of the SLS vehicle stack may preclude use of certain PLF diameter and length combinations. Therefore, potential users are encouraged to work with the SPIE office as soon as possible to define the feasibility of specific spacecraft/payload PLF diameter and length needs.
The Block 1B/2 configurations will use the enhanced performance of the EUS, which provides the potential of flying large or small CPLs (and potentially SPLs) within the USA during crewed Orion missions. Figure 6-11 provides the available static envelope for the 27.6 ft (8.4 m) diameter composite USA. This stage adapter offers installation of different-sized access doors, as needed, and an interior surface compatible with acoustic treatments, to meet environmental requirements.

[Figure: Figure 6-11. Composite Universal Stage Adapter (USA)]
The electronic version is the official approved document.

[Figure: Figure 6-12 depicts a USA concept of operations based on Orion docking/extraction of a large CPL (i.e., Orion CPL), as well as that for a self-propelled CPL (i.e., Independent CPL). It assumes that once on orbit and post Orion separation from the USA, the USA jettisons in a canister fashion (in contrast to typical jettison in sectors) to support CPL separation. Canister-style jettison results in the upper 85 percent of the USA structure, with the Orion SA still attached, being jettisoned as a single, circumferential ring. The non-separable 15 percent of the USA structure remains with the EUS; its height is at or less than the PLA separation plane to maximize CPL separation by Orion, or separation as an independent CPL.]
Payload mass accommodation can be increased or decreased depending on the number of composite
plies used and the amount of resource access (connector and bracket support interfaces) needed.
Depending on the spacecraft/payload interface diameter required, the composite PAF sectors can
also be lengthened or shortened as well. In general, PLAs that are shorter, and/or do not require a
PIA, will have a lower mass compared to those that do. It is anticipated that a variety of SLS PLA
[Figure: Figure 6-14. Representative PLA Configurations for CPL and PPL]

[Figure: Figure 6-15 provides the physical characteristics of three representative SLS Block 1B 8.4m PLAs. All current SLS PLA designs interface to the EUS at the bottom and utilize the same base cone angle (~45 degrees). As SLS is an 8.4 m-class diameter launch vehicle, in comparison to 5 m-class ELVs, it is generally more efficient to provide a spacecraft/payload-to-PLA interface diameter greater than 13.1 ft (4 m). Hence, the baseline PLA for initial SLS Block 1B flights will be the PLA4394. Other PLA concepts shown are provided for reference only to demonstrate accommodation commonality with current 5 m-class diameter ELV payload interfaces if needed.]
| PLA Concept | PLA Interface |  |  |  |  |
| --- | --- | --- | --- | --- | --- |
|  | Diameter To PIA in mm | Diameter To PSS in mm | Diameter To Payload in mm | Height to PSS (1) in mm | Payload Lift |
| PLA1575 | NA NA | 62.0 1,575 | 65.6 1,666 | 130.0 3,302 | (2) |
| PLA2624 | 173.0 4,394 | 103.3 2,624 | 103.3 2,624 | 115.8 2,940 | (2) |
| PLA4394 | NA NA | 173.0 4,394 | 173.0 4,394 | 82.3 2,089 | (2) |
configuration capable of supporting up to 19,842 lbm (9.0 t) of payload. A new PSS4394 currently
under development will accommodate a PPL/CPL interface of 173 in (4,394 mm) in diameter. This
configuration represents the shortest PLA and therefore maximizes available payload height within
the USA or PLF compared to other PLAs shown. PLA4394 provides an accommodation similar to
that shown in Figure 6-14 as “4.5m Module CPL.” Due to the proximity of the PLA to the upper
oxygen tank dome of the EUS, a “keep out zone” within the interior of the PLA must be maintained.
For the PLA4394, the CPL has the potential of “intruding” as much as 14.5 in (368 mm) in the
downward direction from the PAF/PSS interface plane: use of this PLA volume must be evaluated
on case-by-case basis. PLA4394 center of gravity (CG) offsets applicable to CPL mass ranging
from 9,546 lb (4.33 t) to 19,842 lb (9.00 t) include the following:
interface plane and a lateral CG offset (y-z) of 5 in (127 mm) from the nominal centerline
 SLS/Orion Rendezvous & Proximity Operations – no axial CG offset constraint from the
PAF/PSS interface plane and a lateral (y-z) CG offset of 10 in (254 mm) from the nominal
centerline
A “heavy” variant of the PLA4394 could support up to 89,580 lb (~40 t) Block 1B PPL
accommodation shown in Figure 6-14 as “7.5 Module PPL”.
COTS PSS) PLA concept using a PIA to decrease the Baseline PLA4394 spacecraft/payload
interface diameter without having to design and/or procure a unique PLA.  This configuration is
also represented in Figure 6-14 as “Science PPL”. PIAs might also be employed in a purely
cylindrical configuration to provide additional clearance above the PAF for CPL intrusion as needed
(e.g., payload docking/hatch or propulsion systems). If additional spacecraft/payload mass
accommodation is needed, a new, two-piece (PAF2624 + COTS PSS) PLA2624 would result in a
lower mass PLA, therefore providing additional spacecraft/payload performance.
- Co-manifested Payload
ECS
- Environmental Control System
EUS
- Exploration Upper Stage
ISPE
- Integrated Spacecraft/Payload Element
PLA
- Payload Adapter
PAF
- Payload Attach Fitting
PL
- Payload
PLF
- Payload Fairing
PPL
- Primary Payload
PSS
- Payload Separation System
USA
- Universal Stage Adapter

PL Command Channels
PL RS-422 Serial I/F
Verify this is the correct version before use.

option before then) until EUS separation from ML T-0 umbilicals at launch. Ground services provided through ML T-0 umbilicals include:
 Exploration Ground System’s (EGS) provided air and nitrogen bulk purges for compartment conditioning  Optional EGS-provided instrument purge (low volume for sensitive equipment)  68 twisted shielded pairs for sensors and sensor excitation (Note 1)  2 x RS-422 serial data cables (Note 1)  2 x Ethernet data cables (Note 1)  Up to 24 power cables (rated to 126 VDC, 14 A) (Note 1) Note 1: Available for use by spacecraft/payload provided electrical ground support equipment in the Mobile Launcher Payload User Room.
Flight Services. These data services are distributed from the EUS via the PLA to the spacecraft/payload. This interfaces/services are available to CPL or PPL starting with EUS separation from ML T-0 umbilicals at launch and end with separation from PAF umbilicals during payload jettison, post-EUS insertion burn. Flight services include:
 Separation or pyrotechnic signals for spacecraft use  Dual redundant RS-422 interfaces for interleaved health and status  downlinking and limited commanding to spacecraft  14 command channel interfaces that can provide discrete commanding Payload developers should note the EUS has no provision to provide electrical power to payloads post-liftoff. However, as an optional service, electrical power could be provided to payloads at the PAF interface using payload-provided batteries mounted by SLS on the PLA. This additional mass would be considered part of the total payload mass allocation.
SLS can accommodate SPLs, based on availability of excess capacity after accommodating: Orion (Block 1), or Orion and a CPL (Block 1B/2) for crewed missions, or PPL for cargo missions (Block 1B/2). In general, SPL accommodations range from 6U (unit) to 27U-class CubeSats, or the equivalent volume. Options for accommodating larger volumes are also being considered. For SPLs with mission requirements that include separation from SLS, deployment begins post-TLI after:
 Orion separation from ICPS (Block 1 crew missions) and ICPS disposal initiation  Orion/CPL separation from EUS (Block 1B/2 crew missions) and EUS disposal initiation  PLF/PPL separation from EUS (Block 1B/2 cargo missions) and EUS disposal initiation
Deployment System (SPDS). The SPDS provides a standard SPL interface via a COTS dispenser,
dispenser/SPL support structure, Avionics Unit and cable harnesses for deployment signal and
access to battery charging via the upper stage (provided by KSC ground services). Once Orion, or
Orion/CPL, or PLF/PPL has separated from the upper stage and the upper stage has completed its
disposal burn, SPLs can be deployed. To comply with SLS Program requirements for functional
failure tolerance, the SPDS design implements two identical independent discrete circuits to
preclude inadvertent dispenser activation. The SPDS includes:
to SLS Block 1B/2)
 Dispenser provided environmental interfaces for thermal, bonding/grounding,
electromagnetic compatibility, venting, shock, random vibration and load conditions
 Dispenser provided electrical power and data connectors (these connect to the SPDS
avionics unit via cables during ground and flight operations)
SLS Block 1 will accommodate the SPDS on the inner surface of the OSA as shown in Figure 6-
17. SLS Block 1B/2 will accommodate the SPDS on the outer surface of the PLA, as shown in
Figure 6-18.
SPL Mechanical Interfaces

The primary structural interface for an SPL is to an SLS-specified COTS dispenser. This dispenser provides the SPL a means for SLS integration, protection during launch and ascent, and deployment from the SLS. The SPDS can accommodate either a 6U, 12U or up to a 27U dispenser; the SPL must stay within allowed physical provisions for its associated dispenser. The SLS Block 1 OSA can physically accommodate up to 17 SPLs radially. The SLS Block 1B/2 can physically accommodate either one 27U SPL or a combination of 6U or 12U SPLs on each PLA sector. A maximum of 7 PLA sector locations could be made available on a flight by flight basis.
Physical provisions include the dimensional orientation of the payload inside the dispenser; maximum allowable dimensions, volume and mass; and the CG envelope. Figure 6-19 depicts the SPL dimensional orientation. Table 6-1 provides the dimensions, volume and mass numbers for both 6U and 12U dispensers (27U COTS dispensers are currently under development). Figure 6-20 provides the payload CG datum within the dispenser. Table 6-2 provides the CG envelope numbers for 6U and 12U dispensers. Based on the maximum allowable payload mass for a 6U dispenser (Table 6-1), an ejection rate of 3.9+/-0.2 feet/sec (1.2+/- 0.06 m/sec) is anticipated.