Appendix R_Attachment D_Ground Rules Assumptions Constraints.pdf

ID GRAC Text

BAA.LA.1 Ground Rule Mobility capable of on the order of 5 kilometers will be required to move cargo from point of landing to point of use.

BAA.LA.2 Ground Rule Crew portable carriers will withstand maximum pressure differential of 14.7 psi.

BAA.LA.3 Ground Rule Carrier(s) should be able to log/transmit internal environmental data, such as pressure and temperature.

BAA.LA.4 Ground Rule The internal temperature of the crew portable carrier will not exceed temperature ranges of cargo for up to 8 hours of unpowered EVA transfer.

BAA.LA.5 Ground Rule Elements and/or carriers will not remain docked while mobile.

BAA.LA.6 Ground Rule All surface elements will be capable of receiving and transferring power (bi-directional) from sources external to and separate from the element power systems.

BAA.LA.7 Ground Rule Cargo may be offloaded from heights between 2m to 7m.

BAA.LA.8 Ground Rule Cargo may be transported in loads in the mass range of 1.5mt to 8mt.

BAA.LA.9 Ground Rule Mobility elements will be required to retain full performance capablities after periods of extended darkness greater than 150 hrs.

BAA.LA.10 Ground Rule Mobility elements must be able to traverse on slopes +/- 20 degrees while unloaded.

BAA.LA.11 Ground Rule Mobility elements must be able to navigate through or around extreme terrain reliefs beyond macro topography as described in BAA.LA.10.

BAA.LA.12 Ground Rule Mobility elements perform traversal operations with supervised autonomy without continuous direct to Earth communications.

BAA.LA.13 Assumption Pressurized logistics will be delivered in a combination of mateable and crew portable carriers.

BAA.LA.14 Assumption Waste to be collected inside will be removed from habitable elements and moved to disposal location.

BAA.LA.15 Assumption For the habitable surface elements, water will be delivered initially in dedicated water carriers, with future extensibility to umbilical transfer considered.

BAA.LA.16 Assumption Habitable surface elements will have an interface for berthing/docking of a mateable carrier.

BAA.LA.17 Assumption The acceptable temperature range of food items and medicine are 5-21 degrees C.

BAA.LA.18 Assumption The acceptable temperature range of water is 10-30 degrees C.

BAA.LA.19 Assumption Mating elements will provide compensation for terrain settling.

BAA.LA.20 Assumption Surface docking/mating concepts provide their own pressurization and environmental control capability.

The following definitions from ESDMD-001 Rev A, 2023 Moon to Mars Architecture Definition Document apply throughout these GRACs:

Asset: All items that are in place and being used as part of the exploration architecture.

Cargo: Items less than 6t that are transported from one location to another Carrier: A transport structure or container used to secure and protect logistics items that require transport to the point of use.

Element: Any exploration system that enables a high-level functional allocation (e.g., crew transport, habitation, logistics delivery) that are primarily selfsufficient

Rationale

This distance could be as little as tens of meters to separate from lander shadowing, around 1 km to reduce blast ejecta constraints, or as great as 5 km to support separation between landing zones and habitation zones.

Pressurized carriers will be packed at a launch site at atmospheric pressure and exposed to vacuum after launch.

Monitor cargo status.

8 hrs in maximum nominal EVA time. Assumed that crew remove thermal blanket and disconnect any power interfaces for crew portable carrier, or that this is done autonomously at the beginning of the EVA.

While in the future it may be possible to traverse while docked, this will not be considered. Furthermore unintentional movement from settling, or tunnel pressurization may occur. Element is any exploration system that enables a high-level functional allocation that are primarily self-sufficient.

Given mass constraints on landers and environmental considerations of the South Pole region, providing excess power and/or receiving excess power from other surface assets likely will be needed. Logistics carriers are not considered elements, and may need to receive power from a surface element but are not required to transfer power to elements.

This height range envelopes the deck height of current lander concepts. Whether offloading functionality is provided by the lander or mobility element is subject to trade.

Cargo may be configured in modular/palletized configurations and not limited to individual items/carriers. An entire load may not need to be moved at once.

During winter solstice, most areas of the South Pole Region will experience darkness greater than 700 hours; with very few experiencing darkness less than 350 hours. The duration of darkness/shadow is closely related to height above surface and surrounding terrain, which calls for the >150 hrs of darkness protection (energy storage).

Lunar terrain reconaissance has identified slopes greater than 20 degrees. Represenative Lunar Surface traverses between points of interest have been identified that may be completed within 20 degree limits. Proposals must perform analysis to determine what slopes are able to be traversed/negotiated while loaded.

Based on terrain data gathered from LRV and Apollo 16 data; akin to some areas of the South Pole Region. LRV requirement was for 30cm diameter rocks.

Mobility solutions will not have continuous direct to Earth communications.

A large portion of the logistics requires conditioned delivery, maintaining atmosphere and temperature. In certain scenarios, large carriers will need to mate with surface habitation. In other scenarios, carriers will be used by crew during EVA. Therefore different sized pressurized logistics carriers will be required to deliver and move cargo on the surface.

Per NASA's planetary protection policy.

Surface habitation will not have an initial capability to transfer water via umbilical, therefore water that needs to be transferred will be transferred via a water carrier.

In order to support the architecture and enable IVA transfer of logistics from mateable carrier to pressurized surface element, each surface habitation element needs to have a berthing/docking interface.

Per acceptable food temperature range on the International Space Station.

Per acceptable water temperature range on the International Space Station.

While elements are mated, settling and shifting of the surface terrain is to be expected. Unlike microgravity docking, it should not be assumed that the relative position of elements remains fixed. Elements mated on the surface may move relative to each other due to terrain settling and shifting. To compensate for settling, six degrees of motion may be needed to keep the forces and torques in the allowable loads for both the Elements and the docking concept.

These capabilities would significantly increase mass and complexity to include this subsystem. The subsystem would likely include any sensors for measuring, monitoring, and feedback. Source of gases and ECLSS-specific equipment undefined at this stage. Solutions that depend on pressurization should quantify their needs and assumptions t

Independent Review ID Ground Rule/AssumptioText BAA.LA.105 Ground Rule Mobility capable of up to 5 kilometers will be required to move cargo from point of landing to point of use.

BAA.LA.52 Assumption Pressurized logistics will be delivered in a combination of mateable and crew portable carriers.

BAA.LA.87 Ground Rule Crew portable carriers will withstand maximum pressure differential of 14.7 psi

BAA.LA.92 Ground Rule Carrier(s) should be able to log/transmit internal environmental data, such as pressure and temperature.

BAA.LA.75 Ground Rule The internal temperature of the crew portable carrier will not exceed temperature ranges of cargo for up to 8 hours of unpowered EVA transfer

BAA.LA.29 Ground Rule Elements will not remain docked while mobile

BAA.LA.1 Ground Rule All surface elements will be capable of receiving and transferring power (bi-directional) from sources external to and separate from the element power systems.

BAA.LA.118 Ground Rule Cargo must be offloaded from heights between 2m to 7m

BAA.LA.119 Ground Rule Cargo will be transported in loads in the mass range of 1.5mt to 8mt.

BAA.LA.120 Ground Rule Mobility assets will be required to retain full performance capablities after periods of extended darkness greater than 150 hrs.

BAA.LA.121 Ground Rule Mobility assets must be able to traverse on slopes +/- 20 degrees.

BAA.LA.123 Ground Rule Mobility assets must be able to navigate through or around extreme terrain reliefs beyond macro topography as described in BAA.LA.121

BAA.LA.124 Ground Rule Mobility assets perform traversal operations with supervised autonomy without continuous direct to Earth communications

BAA.LA.50 Assumption Waste to be collected inside will be removed from habitable elements and moved to disposal location

BAA.LA.8 Assumption For the habitable surface elements, water will be delivered initially in dedicated water carriers, with future extensibility to umbilical transfer considered

BAA.LA.47 Assumption Habitable surface elements will have an interface for berthing/docking of a mateable carrier.

Assumption The acceptable temperature range of food items and medicine are 5-21 degrees C

BAA.LA.90 Assumption The acceptable temperature range of water is 10- 30 degrees C

BAA.LA.21 Assumption Mating elements will provide compensation for terrain settling

BAA.LA.26 Assumption Surface docking/mating concepts provide their own pressurization and environmental control capability

BAA.LA.103 Ground Rule Human class Delivery Lander is the will land large cargo and is designed to meet basic human rating which supports crew in the vicinity of HLS and/or crew access to an Surface Habitation/SH atop the Human class Delivery Lander

BAA.LA.122 Ground Rule Mobility assets must be capable of holding position on an inclined surface of +/ 20 degrees during offload operations.

BAA.LA.74 Assumption Crew portable carriers are positioned within Extravehicular activity (EVA) suit reach envelope when EVA crew begin EVA crew portable carrier transfer operations

BAA.LA.79 Assumption crew portable carriers provide a stable internal environment when exposed to vacuum and lunar surface conditions

BAA.LA.51 Assumption Surface elements will be arranged to minimize the impact of shadows on co-located surface elements.

BAA.LA.84 Ground Rule 1 Cargo Transfer Bag Equivalent (CTBe) is .0537m3

BAA.LA.91 Ground Rule Carrier(s) handles should maintain a minimum clearance distance between the lower surface of the handle and the mounting surface of 2.25 in (5.7cm).

BAA.LA.16 Ground Rule At least one element in the intended docking configuration has coarse alignment capabilities.

At least one element is in the docking envelope.

BAA.LA.100 Ground Rule PR will not be used to transport pressurized logistics items to other surface assets

BAA.LA.101 Ground Rule Mated Carrier and Crew Portable Carrier will provide cargo and trash disposal for Artemis surface mission(s)

BAA.LA.102 Ground Rule While attached to crew surface asset Mated Carrier will not be used as crew safe haven or extra crew volume (e.g., sleeping quarters)

BAA.LA.117 Ground Rule Mobility must be able to transport cargo in distances of at least 5km.

BAA.LA.18 Assumption The fine alignment capability is collocated with the active-androgynous interface.

BAA.LA.19 Assumption Mating active-androgynous and passive interfaces creates a contained space (distance and volume) between the two hatches of the Elements.

BAA.LA.57 Mobility systems used for offloading cargo will need to be able to reach the deck height of a Mid-sized class Lander.

BAA.LA.107 Ground Rule HLS lands 4 crew on the surface and depart the HLS for separate destinations/vehicles

BAA.LA.108 Ground Rule The interface between PR/SH and LC provides the crew capability to separate from Mated Carrier in the event of an emergency

BAA.LA.109 Ground Rule Crew-specific or short shelf-life items (e.g. food) will be delivered in Crew Portable Carriers on Human Landing System (HLS)

BAA.LA.11 Assumption Crew Portable Carrier will be robotically staged near crew sites (HLS, PR or SH) rather than near the logistics lander.

BAA.LA.110 Assumption For this assessment, Mated Carrier is positioned by TBD means as needed to support docking to PR/SH/Human-class Delivery Lander

BAA.LA.111 Assumption PR may provide more than one hatch for operational flexibility

BAA.LA.112 Assumption SH assumed to have dual hatches (one at airlock, one from pressurized section)

BAA.LA.113 Assumption Docking interface is interoperable across elements (standard interface enables PR, SH, HLS, and MC to all be attached to support various ConOps)

BAA.LA.114 Assumption MC details…

BAA.LA.116 Assumption MC can be used for trash disposal and provide planetary protection

BAA.LA.12 Assumption Crew logistics that do not arrive with HLS will land on the lunar surface prior to HLS arrival (must be verified prior to crew landing authorization)

BAA.LA.13 Assumption Logistics usage rates used for studies are based on SA-TM20230615-1A, Exploration Planning Guide

BAA.LA.14 Ground Rule The SDI mating surfaces (active-androgynous and passive) will be planar. Additionally, where the SDI is mounted to an element (i.e. bolt pattern or weld interface), the SDI mounting interface will need to be planar unless the Element incorporates the interfacing structural elements for loads or mass efficiency into its primary structure.

BAA.LA.15 Ground Rule At least one element in the intended docking configuration is transported (itself or by another element) to the docking location.

BAA.LA.17 Ground Rule The Surface Docking System (SDS) is comprised of two interfaces (active-androgynous, passive), and fine alignment capability. The Element-to- Element mating using the SDI may consist of a docking configuration of an active-androgynous to passive interface or an active-androgynous to active-androgynous interface. There will be no passive to passive interface mating.

BAA.LA.2 Ground Rule Surface habitation concepts will support a minimum of two crew for nominal operations.

BAA.LA.20 Assumption Elements can accommodate reasonable axial and transverse loads imparted by the Surface Docking System (SDS) during docking and pressurization.

BAA.LA.23 Ground Rule Open hatch position does not interfere with logistics transfer.

BAA.LA.24 Ground Rule A Surface Docking Interface (SDI), when mounted on an element, will be done such that it is parallel to the gravity vector (within the vertical plane)

BAA.LA.25 Ground Rule Surface Docking Interface (SDI) volume is sufficient for logistics transfer.

BAA.LA.27 Assumption Surface Docking System (SDS) has adequate ground clearance and no interference from terrain obstacles.

BAA.LA.28 Assumption The elements that are intending to dock are positioned at terrain elevations within the capabilities of the coarse alignment system(s).

BAA.LA.3 Ground Rule Surface habitation concepts will support missions lengths of 7 days without resupply for the initial mission.

BAA.LA.30 Ground Rule The element containing the active side of the interface will be able to supply actuation power to the SDS to enable fine alignment, latching, and pressurization.

BAA.LA.31 Assumption The SDI EVA Baseline is sized for suited crew transfer (1m x 1.5m). Mass breakdown of the Baseline SDI does not include the mass of the hatch door, or resulting pressure vessel support structure.

BAA.LA.32 Ground Rule LTV will be operable for no less than eight continuous hours out of any 24-hour period when operating outside of a Permanently Shadowed Region (PSR).

BAA.LA.33 Ground Rule LTV can be fully operated by remote operators on Earth.

BAA.LA.34 Ground Rule LTV will be fully controllable by any on-board suited crewmember.

BAA.LA.36 Ground Rule LTV will be capable of traversing 50 km when uncrewed.

BAA.LA.37 Ground Rule LTV will be able to operate for 1300 km annually.

BAA.LA.38 Ground Rule LTV can traverse slopes of at least 20 degrees at all directions of approach.

BAA.LA.39 Ground Rule LTV can traverse 20 km on full charge without recharge while at full performance.

BAA.LA.4 Assumption Habitable surface elements will have an interface for berthing/docking of a mateable carrier.

BAA.LA.40 Ground Rule LTV will have autonomous hazard identification for unsafe operational conditions.

BAA.LA.41 Assumption LTV will use the lunar surface comm architecture for communication with other surface elements.

BAA.LA.42 Ground Rule During crewed operations LTV will have continuous comm (two-way voice at minimum;

telemetry, video, and other higher-rate data are also desired) with ground and crew in other surface assets, unless all comm paths briefly blocked.

BAA.LA.43 Ground Rule During uncrewed operations, while LTV is being remotely operated, LTV will have scheduled continuous comm.

BAA.LA.45 Assumption Independent Ops: Early, Mobile & Independently operating elements will be internally self-sufficient and “stand-alone” for core capabilities and performance.

BAA.LA.46 Assumption All habitable surface elements will provide commanding to other surface elements capable of being controlled remotely.

BAA.LA.48 Assumption Logistics will be delivered in a mix of mateable carriers and crew portable carriers.

BAA.LA.5 Assumption Surface habitation concepts will be capable of exchanging consumables with other habitable surface assets.

BAA.LA.54 Ground Rule Crew Portable Carrier will be robotically staged near crew sites (rather than lander sites).

BAA.LA.55 Ground Rule Crew logistics arrive prior to HLS

BAA.LA.56 Power systems will need to be offloaded and transported around the surface

BAA.LA.6 Assumption Logistics resupply will include sub-sequent system spares.

BAA.LA.60 Assumption When transporting large logistics, LTV is expected to travel shorter distances and lower speeds, over known terrain, around the local Artemis Base Camp area and between logistical landers and other lunar surface assets.

BAA.LA.61 Assumption LTV will have an expected nominal average speed of 5 kph or less when crewed (and less than 2 kph average when uncrewed).

BAA.LA.66 Ground Rule LTV is capable of fully recharging within 16 hours using onboard capabilities, without crew assistance.

BAA.LA.7 Ground Rule Perishable logistics items within their shelf-life time limits will be provided for the entire mission.

BAA.LA.70 Ground Rule The element containing the active side of the interface will be able to supply actuation power to the SDS to enable fine alignment, latching, and pressurization.

BAA.LA.71 Assumption The SDI EVA Baseline is sized for suited crew transfer (1m x 1.5m). Mass breakdown of the Baseline SDI does not include the mass of the hatch door, or resulting pressure vessel support structure.

BAA.LA.72 Ground Rule EVA hatch size is 1.5m (59in) tall by 1m (39.3in) wide

BAA.LA.73 Ground Rule At the beginning of EVA transfer operations, PR will be within 8m of the lander

BAA.LA.80 Ground Rule At a minimum, for each misson Human Landing System (HLS) will provide the crew and their personal items along with their personal med kit, xEVA suits and other xEVA equipment worn during an EVA

BAA.LA.81 Ground Rule The minimum distance between the HLS and cargo lander is 2km

BAA.LA.82 Ground Rule The maximum distance between the HLS and cargo lander is 10km

BAA.LA.83 Ground Rule Crew Portable Carrier will be maintained dust free prior to EVA transfer to the Pressurized rover

BAA.LA.85 Ground Rule Carriers are not returned to Earth for reuse, and waste can be stored inside them on the lunar surface once the logistics contents have been depleted.

BAA.LA.9 Assumption For the PR and SH, gas will be delivered in gas tanks and be transferred via EVA/EVR.

BAA.LA.93 Ground Rule Crew Portable Carrier allows for external physical identification of contents within Crew Portable Carrier

BAA.LA.95 Ground Rule Cargo that does not need vacuum or thermal protection can be delivered in standard cargo transfer bags.

BAA.LA.99 Ground Rule Mated Carrier cargo is limited to pressurized logistics items (e.g. crew supplies, consumables, spares, utilization) that are not crew specific, do not have short shelf-life, or are not externally stowed

BAA.LA.97 Ground Rule Mated carrier (MC) size is TBD and varies depending on the case being assessed; see cases on pp. 14 ff. for assumptions specific to each case

BAA.LA.98 Ground Rule Small cargo carrier (SC) is a 2 CTBE size pressurized carrier with empty mass of 48kg / avg loaded mass of 64-102kg (TBR). Some use of SC will be required for all cases.

BAA.LA.88 Ground Rule External surface of small carrier will not exceed touch temperature limits of EVA glove and hand

BAA.LA.104 Ground Rule MC will be lowered to the surface and ready prior to crew arrival (see comment for proposed change)

BAA.LA.22 Ground Rule Surface Docking System (SDS) does not articulate while pressurized.

BAA.LA.106 Ground Rule LTV and PR are pre-positioned in proximity, but outside hazardous zone, for HLS and Human-class Delivery Lander landing

BAA.LA.35 Ground Rule LTV can survive no less than 150 hours of continuous darkness without recharge.

BAA.LA.44 Ground Rule "LTV will provide the following allocations of power across all active payload interface ports for powering active payloads:

- 400 W while stationary

- 200 W while traversing

- 50 W during periods of shadow or darkness"

BAA.LA.58 Ground Rule LTV will support 800 kg at full performance.

BAA.LA.59 Ground Rule LTV will support 1600 kg at a reduced performance.

BAA.LA.62 Ground Rule LTV will provide robotic manipulation capabilities.

BAA.LA.63 Ground Rule LTV is not responsible for providing a capability to load/unload cargo, logistics, or payloads from the

LTV.

BAA.LA.64 Ground Rule LTV will have lighting to support vehicle operations, utilization of storage areas and payloads, manipulation, science, and public engagement under all ambient lighting conditions, including regions of shadow and PSRs.

BAA.LA.49 Assumption Legacy systems will be used for packaging of logistics inside the MC.

BAA.LA.86 Assumption Internal volume of Small carriers will experience a delta pressure of less than 5psi

BAA.LA.94 Assumption Items delivered in a small pressurized carrier do not need to be in a cargo transfer bag (CTB)

BAA.LA.96 Assumption Small carrier Internal volume will be .5 - 2 CTBe

BAA.LA.76 Assumption Maximum two handed lifting from the ground is 67.5kg for suited crew member in 1/6g

BAA.LA.77 Assumption [removed tables]

BAA.LA.78 Assumption [removed tables]

BAA.LA.10 Assumption Material handling systems will be available for IVA

BAA.LA.69 Assumption The SH will have at least one berthing/docking interface and a separate EVA ingress/egress capability

BAA.LA.53 Mobility Systems: Cargo offloaded from (landers) needs a mobility asset to transport to use location(s).

Ground Rule Foundational exploration core habitation will support 4 crew for up to the mission duration in a continguous volume by the end of Foundational Exploration.

Ground Rule Surface habitation concepts, when aggregated with other habitable elements, will provide capability for 4 crew simultaneous don/doff.

Ground Rule Surface habitation concepts will be relocatable.

Ground Rule Berthing operations are out of scope for the Ground Rule Lunar Terrain Vehicle (LTV) will be designed to carry two suited crewmembers.

Ground Rule LTV's primary role is crew transport; exploration and science are performed on an opportunistic basis.

Ground Rule LTV will be deployable from lander to lunar surface without assistance from crewmembers.

Ground Rule LTVS will provide operational support for 10 years starting from initial checkout.

Ground Rule LTV will accommodate a single crewmember loading, unloading, safely restraining, and transporting a single incapacitated crewmember.

Ground Rule LTV will support Artemis 5 and subsequent missions.

Ground Rule Nominal EVAs with LTV will be conducted by two crewmembers.

Ground Rule The LTV will communicate with Earth using Relay to Earth paths via Lunar Communication Relays (i.e. HLS, Gateway, Lunar Communication Relay and Navigation Satellite (LCRNS)) or communicate with Earth using Direct-to-Earth (DTE) paths.

Ground Rule The LTV will be used as a relay for EVA communications to Earth.

Ground Rule LTV can determine its location with an accuracy of 10 m radially within 600 seconds for all operating modes.

Ground Rule LTV will provide sufficient status (e.g., power state, position, vehicle health, etc.) for awareness and control of vehicle.

Ground Rule LTV will have a clock synchronized with the NASA-

Ground Rule Berthing operations are out of scope for the trade space.

Ground Rule For Configuration A, a single MC may provide cargo to one or more habitable surface assets during an Artemis mission. For Configuration B, a single MC will provide cargo only for PR and another single MC will provide cargo only for SH.

Constraint Surface habitation concepts will hold to current Human class Delivery Lander mass

Constraint The xEVA will not receive recharge power from the LTV.

Assumption Crew will not be present during periods of continuous lunar night.

Assumption Foundational exploration core habitation will provide a minimum of 2 open docking ports, available for pressurized element mating, in its fully assembled/deployed configuration, mounted to a vertical plane, accessible from the lunar surface.

Assumption Habitation concepts will utilize augmented power to enable crewed presence during lunar night.

Assumption Foundational exploration core habitation will accommodate radiation protection measures to reduce exposure for longer duration missions in Foundational Exploration.

Assumption Foundational exploration core habitation will reduce ECLSS logistical dependence on Earth per crew member by including capability to evolve through the end of Foundational Exploration.

Assumption Surface habitation should be scalable to crew sizes within a contiguous volume to support Mars forward capability.

Assumption Crew will not close the hatch and repressurize a habitable surface element unless critical EVA suit spares are inside

Assumption The SH will have at least one berthing/docking interface and a separate EVA ingress/egress capability

Assumption Mass savings estimations for IVA-only sized SDIs will be dissimilar dependent on the number of hatches scarred on the impacted element.

Assumption LTV will not traverse past 10 km (odometer distance) from a habitable volume during crewed missions with a singular mobility asset.

Assumption LTV will not traverse past 20 km (odometer distance) from a habitable volume (not including PR) during crewed cooperative missions with the

PR.

Assumption During uncrewed operations, while LTV is in hibernation mode, low rate comm (telemetry) will be available but is not required for survival.

Assumption LTV will have low bandwidth communications

DTE.

Assumption Surface habitation elements supply the xEVA system with oxygen, water, and power for suit recharge and umbilical operations with addition of CO2 removal.

Assumption Pressurized Rover cabin nominally operates at exploration atmospheres (8.2psi/34% O2).

Assumption Power Cables that are >100 m are assumed to be not relocatable.

Assumption Power cable lengths are assumed to have a 30% added length to account for deployment routing issues.

Assumption Crew will not close the hatch and repressurize a habitable surface element unless critical EVA suit spares are inside

Assumption Mass savings estimations for IVA-only sized SDIs will be dissimilar dependent on the number of hatches scarred on the impacted element.

Assumption Solar declination for hot cases is -1.539 deg Assumption Solar declination for cold cases is -1.554 deg Assumption Surface-based MC has similar system capabilities as single-segment Cygnus. Trade space for capabilities (e.g. comm, avionics, power generation/storage, heat rejection, etc.) is being scoped in SAC24.12 task.

LTV is capable of exploration from a habitable surface asset within operational constraints with the following distance capabilities:

Mobility Systems: Provide power energy transfer to… classes of mobility to classes of power...

Mobility Systems: sizing of the wheels, height off surface (for pressurized tunneling, actuators, etc.)

Heavy duty mobility… for Power Generation Stations relocation

Heavy duty robotic assets… availability to assist in deployment of Power Generation Stations relocation bi-directional power transfer capability Mobility as a service to all related subarchitectures…

Rationale Comments Column1 This distance could be as little as tens of meters to separate from lander shadowing, around 1km to reduce blast ejecta constraints, or as great as 5 km to support separation between landing zones and habitation zones.

<ZH> updated text and rationale <Bhakta> Put this as an approximate value instead of a not to exceed? Also, what does this mean when we are calling the PR and MPH further down as the habitable elements - this could get confusing so maybe this is : "Elements should land ~5km from surface assets already emplaced".

<ZH> updated text. Need to update rationale <Clawson>Should we forgoe the Human-class Delivery Lander/MC nomenclature in favor of logistics delivery lander?</Clawson> <Johnson> Suggest generically referring to "habitation or habitable elements" That would encompass Surface Habitation, PR, SH, etc.

<Goodliff> Can we add a pointer to the mobility needs white paper in the rationale or pull some of the rationale from the white paper and have the white paper as reference? Suggested text: This distance could be as little as tens of meters to separate from lander shadowing, around 1km to reduce blast ejecta constraints, or as great as 5 km to suppport separation between landing zones and habitation zones.

A large portion of the logistics requires conditioned delivery, maintaining atmosphere and temperature. In certain scenarios, large carriers will need to mate with surface habitation. In other scenarios, carriers will be used by crew during EVA. Therefore different sized pressurized logistics carriers will be required to deliver and move cargo on the surface.

<ZH> Define in BAA Intro? Need to update rationale <Clawson>Is a mateable carrier really envisioned to be manipulated by two crew on EVA? Current matable carrier concepts are large enough for crew entry. Is this leftover from SPLC concept?</Clawson>

<R. Lambert> We need to define what constitutes a mateable carrier

<Goodliff> would be good to have definitions of mateable and crew portable carriers. Rationale needs to be cleaned up to delineate expectations between the two types.

Pressurized carriers will be packed at a launch site at atmospheric pressure and exposed to vacuum after launch

<ZH> only for CPC, confirmed with Victor <Goodliff> should this just be CPCs? Or is it both carriers? Also isn't there some factor of safety so is it 14.7 max or something slightly higher?

Monitor cargo status. <ZH> no update

8 hrs in maximum nominal EVA time. Assumed that crew remove thermal blanket and disconnect any power interfaces for crew portable carrier, or that this is done autonomously at the beginning of the EVA

<Bhakta> Change Crew Portable Carrier to lower case across the board. <Bhakta>

<ZH> Updated to JC suggestion <Clawson>Suggest: The internal temperature of the Crew Portable Carrier will not exceed temperature ranges of cargo for up to 8 hours of unpowered EVA transer.</Clawson>

<R. lambert> Reword or split into multiple lines…. Pair this with

BAA.LA.90

While in the future it may be possible to traverse while docked, this will not be considered. Furthermore unintentional movement from settling, or tunnel

<ZH> Updated to JJ suggestion <Johnson> Could be phrased more simply, "Elements will not remain docked while mobile" or similar.

Given mass constraints on landers and environmental considerations of the South Pole region,providing excess power and/or receiving excess power from other surface assets likely will be needed.

<ZH> Will discuss with TC <Goodliff> If this one is to stay, this isn't a good rationale for the public. Suggest - Given mass constraints on landers and environmental considerations of the South Pole region,providing excess power and/or receiving excess power from other surface assets likely will be needed. (sorry Zaida, didn't finish my thought yesterday)

Given current lander concepts. <ZH> Updated to include min range <Bhakta> Agree with the previous comment - 7m seems high and HDL specific can we put in a range that maybe more aligned to CLPS, Argonaut, and maybe Gov Ref Mission for HDL? <Bhakta>

<ZH> Updated to generic language <Clawson>Is this always the case. Human-class Delivery Landers are offloading larger payloads like PR and Surface Habitation. 7m seems quite high indicating an Human class Delivery Lander If we are

Cargo may be modular and not necessarily a single element

<ZH> updated <Bhakta> Add a qualifier - that the cargo may be modular and not necessarily a single element <Bhakta>

<ZH> addresses lower limit and updated text. Need to add GRAC for HR comment <Clawson>Suggest: 'Transported cargo will be in the mass range of 3.5mt to 8mt.</Clawson>

(H. Riccio) This mass range is predominantly derived from transporting MCs. The distance can be significant in this category (10s kms). Suggestion to add additional GR where cargo in the >12mt range can be "relocated." (10s m)

<R. Lambert> - 1.5 mt should be lower limit, opens trade space and is larger than what LUV can do.... Proposers can prose a Mobility platform with integrated MC <Goodliff> need to add rationale; agree with Reeve that we might want to put mass + range

During winter solstice, most areas of the South Pole Region will experience darkness greater than 700 hours;

with very few experiencing darkness less than 350 hours.

The duration of darkness/shadow is closely related to height above surface and surrounding terrain, which calls for the >150 hrs of darkness protection (energy storage)

<ZH> Added JJ rationale <Johnson> May want to add to the rationale that the duration of darkness/shadow is closely related to height above surface and surrounding terrain, which calls for the >150 hrs of darkness protection (energy storage).

Lunar terrain reconaissance has identified slopes greater than 20 degrees. Represenative Lunar Surface traverses between points of interest have been identified that may be completed within 20 degree limits.

<ZH> no update

Based on terrain data gathered from LRV and Apollo 16 data; akin to some areas of the South Pole Region. LRV requirement was for 30cm diameter rocks.

<ZH> update to correct ID

Mobility solutions will not have continuous direct to Earth communications.

<ZH> updated <Goodliff> Need to add rationale; capitalize Earth

Per NASA's planetary protection policy <ZH> Generalized to "waste" <Clawson>What is the specific impact to the Offeror's? Is this part of the trash that needs to be disposed of? How much is there?</Clawson>

<V. Alvarez> This is part of the trash that needs to be disposed of, not sure if we are allowed to point to any white papers not on the SAO website that would identify rates of generation <Goodliff> Is there a broader "waste" assumption that should be included? I don't know why this specific aspect is needed but would we want to say something like - Waste to be collected inside will be removed from habitable elements and moved to disposal location?

Surface habitation will not have an initial capability to transfer water via umbilical, therefore water that needs to be transferred will be transferred via a water carrier.

<ZH> reworded <Johnson> Do we want to restrict this? That naturally calls for more crew interaction than robotic umbilical solutions that may be desired in the long term. Consider re-phrasing to something like:

"…water will be delivered initially in dedicated water carriers, with future extensibility to umbilical transfer considered"

<V. Alvarez> +1 on Jim's comment for reword

<Goodliff> Assumption is reworded but I think the rationale needs to also be reworded to reflect the updated assumption

In order to support the architecture and enable IVA transfer of logistics from mateable carrier to pressurized surface element, each surface habitation element needs to have a berthing/docking interface.

<ZH> removed ref to PR

<Goodliff> Is PR having a interface going to be ok to say in public?

Per acceptable food temperature range on the International Space Station

<ZH> New GRAC

Per acceptable water temperature range on the International Space Station

<ZH> Added GRAC <Bhakta> Split into 2 - one for food and one for water.

While elements are mated, settling and shifting of the surface terrain is to be expected. Unlike microgravity docking, it should not be assumed that the relative position of elements remains fixed. Elements mated on the surface may move relative to each other due to terrain settling and shifting. To compensate for settling, six degrees of motion may be needed to keep the forces and torques in the allowable loads for both the Elements and the docking concept.

<ZH> Updated <Bhakta> Agree with Jim - if we want this capability lets make it more explicit - "mating elements will provide compensation for terrain settling" or such. Also, remove SDS in rationale. <Bhakta>

<Clawson>Do we want their concepts to include this capability?

Left as-is, the Offerors will assume the element that they are mating to will perform this.</Clawson>

<Johnson> Along these lines, lunar seismic loads? Need to check the timing of the RFP with the updated DSNE which will touch on seismic I believe.

These capabilities would significantly increase mass and complexity to include this subsystem. The subsystem would likely include any sensors for measuring, monitoring, and feedback. Source of gases and ECLSS-specific equipment undefined at this stage. Solutions that depend on pressurization should quantify their needs and assumptions

<ZH> Updated <Cayse> Wording of rationale seems to conflict with the Assumption

<Bhakta> Recommend that we make this a positive assumption:

"Surface docking/mating concepts provide their own pressurization and environmental control capability." Since PR and MPH currently are not accounting for this gas and if they did it would need replenishing anyway. <Bhakta>

<Johnson> Need to add to the rational that any solutions that depend on pressurization should quantify their needs and assumptions?

<Victor> Change SDS to "docking/mating concepts"

(H.Riccio) Instead of saying "large cargo" could this be communicated as Human class Delivery Lander capacity?

<Johnson> We need to be consistent here…landers/habs are looking at initial emplacement at <10 deg if I recall, so this hints at a difference between the ability to handle higher slopes for traverse

vs. on/off load operations.

Cargo lander designs are unknown. Assumption that cargo landers can place crew portable carrier on the lunar surface simplify conops and allow for assessment without knowing details of landers

<Bhakta> Is this more mission planning/operations and not needed for this BAA? Recommend delete or reword? <Bhakta> <Goodliff> Agree with Bhakta, something more generic about not exceeding capability of suits might be better/more clear?

<Cayse> what if cargo landers provide a ladder up to the CPCs?

does that count as within EVA suit reach?

<ZH> no update

The use of conditioned stowage for vacuum protection is only needed for items that need vacuum protection

<ZH> Updated <Bhakta> Crew portable carriers provide a stable internal environment when exposed to vacuum and lunar surface conditions - or similar <Bhakta> <Cayse> is the Rationale still applicable? or is the rationale its own

GRAC?

Update to Crew Portable Carrier, 1 and 4 CLIN

Natural and human-induced shadows may affect the visibility of crew and automated devices, preventing clear resolution of topographical details, surface detection, or distinction between surface characteristics. It can also affect the thermal management of surface elements.

<ZH> marked red <Bhakta> Recommend deleting this one. This is more on how we place and use any items on the surface <Bhakta>

<Clawson>This may prodice concepts that are required to operate in a specific orientation, reducing flexibility.</Clawson>

<r.Lambert> what are we trying to tell a vendor or responder????

That we will tell them where to go? That they should expect to be shadowed by other elements, or that they should try to not shadow other elements??????

Based on 50.2cm x 42.5cm x 24.8cm. Known 27.2kg maximum mass for cargo in a 1 CTBe may not be relevant for items stowed within crew portable carrier

<Clawson>Should the dimensions be in the actual GR? Are they free to design carriers of different dimensions based on the GR volume?</Clawson>

<Clawson>This appears to assume a particular concept for where handles are mounted and where mounting surfaces are. Should we genericize this to be in terms of clearance?</Clawson>

Either one or both of the elements in the docking configuration will need to maneuver to the docking capture envelope (similar to HLS-S-R-0071 Surface Operations Vertical Orientation). After this coarse alignment, Surface Docking System (SDS) will execute fine alignment.

<Cayse> if keeping this one, maybe make this a broader statement that both PR and LTV are primarily crew/science transport with minimal logistics capability <Cayse> recommend red to avoid constricting Trash study

<Cayse> recommend red unless we think industry will unnecessarily self impose safe haven requirements on their solutions

Can be combined with #105

"The active-androgynous interface needs power for the latches and a fine alignment system would need power for actuation and sensing. Collocating the active-androgynous and fine alignment system provides mass savings."

<Bhakta> Recommend delete <Bhakta>

<Clawson>This is specific to the government concept. It may constrain the Offeror from innovation.</Clawson>

"The design and performance of a fine alignment system impacts the size of the contained space. Prior docking testing with fine alignment capabilities resulted in a tunnel length of 3' to 4'."

<Bhakta> Recommend delete <Bhakta>

<Clawson>This is specific to the government concept. It may constrain the Offeror from innovation.</Clawson>

<C. Thompson > This is covered or redundant in

BAA.LA.118

This GRAC or one with height (118) (H. Riccio) I suggest adding in height figures because 'Mid-Size Lander' (MSL) is a NASA-internal term that may not be useful to an external audience.

Two crew ingress the LTV and traverse to the Surface Habitation/SH. Two crew ingress the SH.

Two crew ingress the PR and drive to the LC rendezvous location

<Cayse> I think the Ground Rule text is missing some words. Does not make sense as-is

<Clawson>Does this imply, for example, that the crew must be able to separate the Mated Carrier by themselves without power or mobility system operation, etc.?</Clawson>

<Cayse> Do we need a GRAC that spells out that MC hatches should be able to be opened from the inside? Think crew member trapped inside an MC

<Clawson>What is SC? All acronyms should be spelled out</Clawson>

<V. Alvarez> Updated, SC was small carrier Logistics will be delivered in a mix of Mated Carrier, Crew Portable Carrier, unpressurized items, and gas tanks. The Mated Carrier will be mobile or be able to be moved and Crew Portable Carrier, gas tanks, and unpressurized items can be moved via lunar utility vehicle meaning the crew will not need to traverse to the cargo lander

•MC is launched pressurized. Details of pressure control are TBD.

•MC provides some ECLSS functions (e.g. fire detection/suppression) but does not enable MC as an independently-habitable volume (cf. LC-A-05) •MC does not provide Trace Contaminant Control System (TCCS) or its own O2/N2 supply for atmospheric regulation •When docked, host vehicle provides remaining necessary ECLSS functions in order to allow the crew to enter the MC •MC provides active TCS to control temperature above dew point but does not provide active humidity removal.

•If impacts to PR/SH are significant, future trades will be necessary to reassess functions provided by MC

<Cayse> do these details lay the groundwork for "used" MCs becoming habitable volume once attached to SH?

<Clawson>What needs to be verified? That they landed or that they have been transported, or that a MC has been mated or that it can be pressurized, etc.?</Clawson> reference document

For Modular bolt-on SDI, the mounting interface will need to be planar, either through an adapter or by features designed integral the Elements structural design.

<Clawson>Why is this needed?</Clawson>

The two elements in the docking configuration may not be deployed to the surface close enough to each other for docking operations to occur. Docking operations start with coarse alignment and conclude with separation and stowage of Surface Docking System (SDS).

Docking consists of coarse alignment and fine alignment functions. The fine alignment capability is assumed to be provided by the Surface Docking System, whereas the Element provides coarse alignment.

At a minimum, Element-to-Element mating needs at least one active-androgynous interface because it contains the latching mechanism.

Due to negligible mass differences it is assumed that any active interface will also be androgynous. An active interface would have a latching mechanism but no catches, whereas an active-androgynous has both and can self-mate."

<Clawson>Do we want to specify an active and passive or leave it to the Offeror to define? This is specific to the current government concept for a Surface Docking System. The Offeror concept may only have an androgynous system, for example.</Clawson> (H.Riccio) Suggested Text: "Element-to-Element mating using a surface docking method will employ at minimum one active or active-androgynous docking interface. There will be no passive-to-passive interface mating in Surface docking."

(Crew) Two Assumptions:

1) MC delivers logistics to desired location (< 5km) and within a docking envelope (e.g. terrain slope, access by another element).

2) MC provides a mechanism interface to dock an MC and another pressurized element

Initial FE crew size is two crew in one habitable element.

Expect to expand by end of FE and into SLE.

Elements should be aware of imparted forces that occur from docking and pressurization. For example, pressurization forces scale with the size of the Surface Docking System (SDS).

There are various possible hatch designs such as hatches that swing, on rails, or removeable (a few examples). This Ground Rule allows analysis focused on hatch opening dimensions and not on the potential hatch opening interference.

Surface Docking Interface (SDI) will not be located on angled or horizontal planes.

<Clawson>The text is ambiguous.</Clawson> <Johnson> Just verifying…we don't want to entertain any vertical docking solutions, correct (i.e., a port on the zenith/nadir of a future hab)? Agree horizontal is likely dominating based on current elements post-EI.

There are various possible configurations of mass and volume combinations that will be evaluated relative to logistics transfer efficiency.

The Surface Docking System (SDS) will not have environmental perception capabilities to reduce mass and power demands. An Element will need to verify that there are no obstacles within the workspace of the SDS.

For example, avoiding rocks at a height that could cause a puncture when the SDI inflates during pressurization.

<Clawson>Is there a reference for expected obstacles?</Clawson>

For successful docking to occur, the elements jointly need to be able to achieve a position within the coarse alignment envelope. This means that elements should not be positioned at significantly different terrain elevations or slopes as this might exceed the capabilities

<Clawson>What does this mean for the Offerors? Does the coarse alignment capability now dictate the difference in terrain elevations or should we specify a difference in terrain elevations that their coarse alignment needs to deal with?</Clawson>

Generally accepted minimum nominal mission surface stay length.

The SDS is not a stand alone element and will have no way to generate or store energy for fine alignment actuation.

<Clawson>This is specific to the government concept. It may constrain the Offeror fro

The EVA Baseline SDI is based off of Phase 03 SAS (Surface Attachment System) design metrics and mass breakdown. The SAS sizing and performance reflects the most known data on docking transfer in a surface gravity environment.

<Clawson>This is specific to the government concept. It may constrain the Offeror fro

The system must have a minimum availability for operations of eight (8) hours per day when not in a survival condition or operating in a PSR in the wide range of Lunar South Pole lighting conditions

LTV can be operated by a single crewmember without assistance from another crewmember. LTV will need to be operable and reconfigurable by one crewmember, in order to transport an incapacitated crew member.

Hibernation locations that meet minimum survival durations have been identified and are at least 50 km apart (odometer). Greater distances can be reached as long as design driven operational constraints are maintained.

"Total annual travel distance compiled from the following:

• 500 km during crewed periods (including use by crew on Vehicle and remote operators while crew not onboard)

Reference ACD-50044 and ESDMD-410 for examples of types of traverses included in annual travel."

The LTV will nominally be traversing slopes less than 20 degrees for both crewed and uncrewed periods and traversing 20-degree slopes for limited activities such as travel into a PSR. Histograms of the Connecting Ridge region show that the ability to handle a 20° slope provides access to most of the region.

Travelling 20 km without needing to stop for charging is the minimum required range to enable a concept of operations that meets HEOMD…