Appendix R_Attach D.pdf

ID GRAC Text Rationale

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.

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.

BAA.LA 2 Ground Rule Crew portable carriers will withstand maximum pressure differential of 14.7 psi. Pressurized carriers will be packed at a launch site at atmospheric pressure and exposed to vacuum after launch.

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

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.

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.

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

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.

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.

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.

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

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.

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

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.

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

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).

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

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.

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.

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.

BAA.LA.12 Ground Rule Mobility elements perform traversal operations with supervised autonomy without continuous direct to Earth communications. Mobility solutions will not have continuous direct to Earth communications.

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

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.

BAA.LA.14 Assumption Waste to be collected inside will be removed from habitable elements and moved to disposal location. Per NASA's planetary protection policy.

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.

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.

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

BAA.LA.17 Assumption The acceptable temperature range of food items and medicine are 5-21 degrees C. Per acceptable food temperature range on the International Space Station.

BAA.LA.18 Assumption The acceptable temperature range of water is 10-30 degrees C. Per acceptable water temperature range on the International Space Station.

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

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.

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

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

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

Independent Review ID Ground Rule/AssumptioText Rationale Comments Column1 Column2 Suggested Text Rational Column3 Column4 Column5 Column6 BAA.LA.105 Ground Rule Mobility capable of up to 5 kilometers w ll be required to move cargo from point of landing to point of use.

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.

(BAA.LA.105)

Mobility capable of up to 5 kilometers will be required to move cargo from point of landing to point of use.

(BAA.LA.105)

Cargo will land in areas seperated from its point of use likely down-slope

Victor -Is this GRAC intended to cover power or range?

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

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 rea ly 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.

(BAA.LA.52)

Logistics will be de ivered in carriers ranging in size from crew portable to unsuited crew-ingressable

(BAA.LA.52)

A large portion of the logistics requires conditioned de ivery maintaining atmosphere and temperature. Therefore multiple pressurized logistics carriers will be required to deliver and move cargo on the surface. Some carriers w ll contain mission or crew specific items and will be carried by the crew on EVA other logistics will have long shelf lives and will be aggreggated into large

Victor - Make this an assumption rather than ground rule?

This goes back to how are we communicating GR vs A vs Contraints...are GRs and C unchangable but Assumptions capture reference approach that can be changed or is there some other interpretation?

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

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?

(BAA.LA.87)

Pressurized logistics should be kept at 14.7 PSI (1 atm).

Carriers should be able to endure more than a single pressure cycle.

(BAA.LA.87)

Carriers may be used as pressurized storage containers after logistics delivery

Victor - Carriers will withstand pressure deltas from launch through lunar environment

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

Monitor cargo status. <ZH> no update

(BAA.LA.92)

Carriers should have a communication interface and be able to minitor internal environments

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

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 (BAA.LA.75)

(BAA.LA.75)

Crew Portable Carrires must sUrvive an entire EVA without power while maintaining internal temperatures and pressures as dictated in BAA.LA.87 and

BAA.LA.90

Victor - Make this an assumption rather than ground rule?

BAA.LA.29 Ground Rule Elements will not remain docked wh le mob le While in the future it may be possible to traverse while docked this w ll 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 wh le mob le" or similar.

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.

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)

(BAA.LA.1)

external power wi l not be available at cargo landing locations but may be available at de ivery (point of use) locations

(BAA.LA.1)

Cargo landers wi l be specifically landed in areas away from other surface assets and thus external power will not be available at the point of cargo delivery

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

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 i hi h i di i H l D li L d If BAA.LA.119 Ground Rule Cargo wi l be transported in loads in the mass range of 1.5mt to 8mt.

Cargo may be modular and not necessarily a single element

<ZH> updated <Bhakta> Add a qua ifier - 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 Mobi ity platform with integrated MC <Goodliff> need to add rationale; agree with Reeve that we might want to put mass range

(BAA.LA.119)

Cargo Mobility should be capable of carrying at least 1500 kg.

(BAA.LA.119)

Minimum viable traverse numbers require at least 1500kg of cargo per traverse however heavier traverses add effeciency for carrying 8000kg of logistics on fewer traverses

BAA.LA.120 Ground Rule Mobility assets w ll be required to retain full performance capab ities after periods of extended darkness greater than 150 hrs.

During winter solstice most areas of the South Pole Region wi l 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).

(BAA.LA.120)

Mobility assets wi l need to be able to survive the South Pole Lunar Winter.

(BAA.LA.120)

The Lunar Winter invovles extended periods of darkness of up to 150 hours with comulative periods of 700 hours. limited energy availab lity and temperatures that can reach as low as 50 K. Data can be provided for specific areas on the lunar surface as deemed applicable

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

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

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

Based on terrain data gathered from LRV and Apollo 6 data; akin to some areas of the South Pole Region. LRV requirement was for 30cm diameter rocks.

<ZH> update to correct ID

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

Mobility solutions will not have continuous direct to Earth communications.

<ZH> updated <Goodliff> Need to add rationale; capitalize Earth (BAA.LA.124)

Must be able to continue to operate in severe communication latency and extended periods of Loss of Single (potentially many hours)

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

Per NASA's planetary protection policy <ZH> Generalized to "waste" <Clawson>What is the spec fic 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 spec fic aspect is needed but would we want to say something ike - Waste to be collected inside wi l be removed from habitable elements and moved to disposal location?

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

Surface habitation w ll not have an initial capability to transfer water via umb lical therefore water that needs to be transferred w ll be transferred via a water carrier.

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

"…water will be de ivered initially in dedicated water carriers with future extensibi ity to umb lical 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

(BAA.LA.8)

Not all surface elements will have the same water storage system and interface

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

<ZH> removed ref to PR

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

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

Per acceptable food temperature range on the International Space Station

<ZH> New GRAC

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

Per acceptable water temperature range on the International Space Station

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

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

While elements are mated sett ing and shifting of the surface terrain is to be expected. Unl ke 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 sett ing 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 wi l provide compensation for terrain sett ing" or such. Also remove SDS in rationale. <Bhakta>

<Clawson>Do we want their concepts to include this capability? Left as-is the Offerors wi l assume the element that they are mating to wi l 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.

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

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"

B L G d R l H l D i L d i h i l l d l g 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 De ivery Lander

H Ri i ) I d f i g "l g g " ld hi b communicated as Human class Deli ery Lander capacity?

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

<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

/ ff l d i 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

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 capabi ity 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

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

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 sim lar <Bhakta> <Cayse> is the Rationale still applicable? or is the rationale its own

GRAC?

Update to Crew Portable Carrier 1 and 4 CLIN

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

Natural and human-induced shadows may affect the visibility of crew and automated devices preventing clear resolution of topographical deta ls 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??????

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

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>

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).

<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>

BAA.LA.16 Ground Rule l l i h i d d d ki g configuration has coarse a ignment capabilities.

At least one element is in the docking envelope.

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) w ll execute fine alignment.

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

<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

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

<Cayse> recommend red to avoid constricting Trash study

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)

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

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

Can be combined with #105

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

"The active-androgynous interface needs power for the latches and a fine a ignment 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>

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

"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>

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.

<C. Thompson > This is covered or redundant in

BAA.LA.1 8

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.

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

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

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

<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

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

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

<V. Alvarez> Updated SC was sma l carrier BAA.LA.11 Assumption Crew Portable Carrier will be robotically staged near crew sites (HLS PR or SH) rather than near the logistics lander.

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 wi l not need to traverse to the cargo 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 deta ls… •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 deta ls lay the groundwork for "used" MCs becoming habitable volume once attached to SH?

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 wi l land on the lunar surface prior to HLS arrival (must be verified prior to crew landing authorization)

<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>

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

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 wi l need to be planar unless the Element incorporates the interfacing structural elements for loads or mass efficiency into its primary structure.

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

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

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.

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).

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 wi l be no passive to passive interface mating.

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 se f-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 de ivers 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

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

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

Expect to expand by end of FE and into SLE.

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

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).

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

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.

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

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 ikely dominating based on current elements post-EI.

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

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

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

The Surface Docking System (SDS) w ll not have environmental perception capabilities to reduce mass and power demands. An Element w ll 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>

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

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 l i l hi i h d h b li i

<Clawson>What does this mean for the Offerors? Does the coarse alignment capab lity 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>

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

Generally accepted minimum nominal mission surface stay length.

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.

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 from innovation.</Clawson>

BAA.LA.31 Assumption The SDI EVA Base ine 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.

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 from innovation.</Clawson>

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

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

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

BAA.LA.34 Ground Rule LTV wi l be fully contro lable by any on-board suited crewmember.

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

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

H bernation 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.

BAA.LA.37 Ground Rule LTV wi l be able to operate for 1300 km annually. "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."

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

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.

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

Travelling 20 km without needing to stop for charging is the minimum required range to enable a concept of operations that meets HEOMD utilization and science objectives.

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

Initial FE will require one docking port.

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

Appropriate distance and time to notification can be determined by task analysis. Hazard identification provides additional situation awareness for manual and remote operators to safely operate vehicle. Hazard notification assists the operator with preventing damage to Vehicle.

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

Lunar surface communications architecture requires the use of Wi-Fi and Ultra-High Frequency (UHF). Future updates to the surface communications architecture may include 3GPP as an addition or in lieu of other capabilities

BAA.LA.42 Ground Rule During crewed operations LTV wi l 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.

Note that this assumption does not obviate the need to design for loss of comm scenarios.

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

Continuous comm is scheduled in order to support uncrewed surface operations. LTV could act as surface comm relay for other nearby surface assets.

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

Strategy and programmatic risk mitigation. Manifests and element delivery schedules are subject to change. Power comm/nav grids may not be immediately available or accessible at remote locations. Later infrastructure upgrades may enable greater performance (for example mobile or remote charging stations).

BAA.LA.46 Assumption All habitable surface elements wi l provide commanding to other surface elements capable of being contro led remotely.

TBD

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

Mateable carriers accommodate the bulk of pressurized cargo as they maximize the efficiency of logistics transfer activity. Late stow items and personal crew items may be unable to be loaded into a Mated Carrier prior to its launch. Crew Portable Carrier may be used for these items.

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

Habitation systems need to have common interfaces to move resources between assets such as air fluids and power.

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 <Clawson>Should this say 'prior to Crew' instead lf 'prior to HLS'? Is there a timeframe? It could be important in order to determine how quickly the Offeror's concept needs to offload transport and position logistics prior to crew arrival.</Clawson>

BAA.LA.56 Power systems will need to be offloaded and transported around the surface Heavy duty mob lity capab lities are required to transport external power systems one time or continuously (ref.

LA.Pwr.160 LA.Pwr. 61)

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

It is expected that initial lunar surface system spares w ll be de ivered with the system subsequent required system spares will be delivered with logistics resupply

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.

These shorter slower traverses wh le fully loaded will help to maximize the performance capab lity for LTV while carrying heavy cargo loads.

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

These numbers are pulled from field test and Simulator data for average speeds without stops. LTV will have a top speed of 15 kph.

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

LTV can store power and recharge its internal power source without crew intervention.

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

Items that are l fe limited wi l need to be evaluated to ensure that they are delivered and used within the l fe-limit. Certain items that have longer life-limits could be planned to be delivered in previous year landers

<Clawson>What are these imits?</Clawson>

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.

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

<Clawson>Redundant to BAA.LA. 0</Clawson>

BAA.LA.71 Assumption The SDI EVA Base ine 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.

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>Redundant to BAA.LA.31</Clawson>

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

Current hatch size of JAXA EVA hatch (D Perr ) There is a lot of agency action around this hatch size dimension going on right now. We might not want to specify dimensions this specifically in a GRAC? This dimension also doesn't

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

PR would get as close to cargo lander as possible to fac litate transfer operations. Concerns about hitting lander or placing PR in shadow might limit the minimimum distance between lander and PR

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

<Clawson>Is this defining what the Offerors do NOT need to provide?</Clawson>

<V. Alvarez> Not sure we need this Ground Rule delete?

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

Minimum distance is required to prevent cargo lander from being damaged during HLS descent from plume impingement

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

Crew interaction with or near Crew Portable Carrier might introduce dust to the small carriers but otherwise its expected that sma l carriers will have minimal dust on them prior to EVA

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.

The PR and SH will have gas connections (O2 and N2) on the exterior of the elements for attaching swappable tanks that will be transferred via EVA/EVR

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

Tags with descriptions or color-coded features are needed to quickly identify contents inside carrier

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

Sma l pressurized carrier provides all the same functionality as a cargo transfer bags provide the same functionality (organization support during hand ing and loading and hazard control for fire)

<Clawson>Are Standard Cargo Transfer Bags defined elsewhere?</Clawson>

<V. Alvarez> maybe just reword "Cargo that does not need vacuum or thermal protection does not need to be delivered in pressurized carriers"?

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 spec fic do not have short she f- ife 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

Provide references to mated carriers

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 w ll be required for a l cases.

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

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

After lowered to the surface MC wi l rely on TBD independent or mobi ity element-provided power PR will not provide power for MC during uncrewed lunar night; crewed power needs are case-specific (cf. pp. 16 18 19)

MC wi l be lowered to the surface and ready for hand ing by mobility asset

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

Lo…