GRA_for_Gateway.xlsx
XLSX spreadsheet 45 KB Posted
- Attached to
- Human Space Flight Technical Integration Contract (HSFTIC) Federal contract opportunity
- Solicitation number
- 80JSC019R0023
About this file
This document provides details of a forthcoming solicitation for the Human Space Flight Technical Integration Contract (HSFTIC). Key information includes that NASA/JSC plans to issue a Request for Proposal (RFP) on or about November 1, 2019, with a response due date of on or about December 11, 2019. The anticipated period of performance is a one year base period with four one-year options. The NAICS code is 541715 with a size standard of 1,250 employees. The procurement is a total small business set-aside. The solicitation and any amendments will be available at the listed websites. Prospective offerors shall notify the agency of their intent to submit an offer and are responsible for downloading solicitation documents. All contractual technical questions must be submitted in writing. The Center Ombudsman information is provided.
GRA for Gateway
View the file
Other files for this federal contract opportunity
Show all 50
Human Space Flight Technical Integration Contract (HSFTIC) has more files on GovTribe.
On GovTribe
Work with this file on GovTribe
- Download the original file
- Contacts named in this file
- Similar government files
- Ask GovTribe AI about this file
Text version
owssvr
| ID Number | Ground Rule and Assumption | Ground Rule and Assumption Rationale | GRA Type | GR or A | Allocation | Primary Discipline | Owner/OPR | Stakeholders | Status | Approval Date | Approval Level | Transition Target | Transition Date | Analysis Cycle | Analysis Action # | Analysis Package # | Table/Configuration | Active/Retired | Pictures | Item Type | Path |
| DSG-M-G-01 | The Lunar Orbital Platform-Gateway (Gateway) shall comply with HEOMD-004, Human Exploration Requirements, Section 3.2. | HEOMD-004, Section 3.2, contains the Gateway Level 1 requirements. Including it in the Gateway GRAs eliminates the need to include GRAs that duplicate the requirements. | Mission | Ground Rule | 1;#Gateway | 3;#Requirements | 4;#Adamek | 5;#RD | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 6;#N/A | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-G-02 | Gateway elements and logistics shall be capable of being launched on a commercial launch vehicle (TBR) or as a co-manifested payload on the Space Launch System (SLS). | The nominal plan is to launch Gateway elements as a co-manifested payload on SLS and the capability to do so is covered by Level 1 requirement: DSG-R-11. Having a backup keeps trade space open for a robust assembly sequence, and protects for development issues with co-manifesting, extended flight suspension of SLS or Orion, etc. TBR pending discussion at Level 2 and assessment of the impacts and risks. | Mission | Ground Rule | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 9;#Elements, Loads ＆ Dynamics | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-G-03 | The Gateway shall maintain one accessible docking port for contingencies (TBR). | Ensures access for Orion and other visiting vehicles in the event of a docking port failure. A prior assessment determined Orion cannot be docked to the Gateway in the same plane as the PPE solar arrays (+/- Z for the Gateway reference architecture) because the Orion tail to Sun requirement and Gateway solar array pointing cannot both be met. This GR applies after EM4 (TBR). | Mission | Ground Rule | 1;#Gateway | 12;#RPOD | 8;#Hill | 13;#Elements, Loads ＆ Dynamics, GN＆C | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | 85 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-G-04 | Gateway elements delivered as a CPL on SLS shall achieve space-to-ground communications through the delivery vehicles (EUS through TLI, Orion during transit) communication system. | The ground will need insight into the Gateway systems for health and status monitoring. In addition, the ground will need to be able send commands to the Gateway elements to re-configure and initialize systems. Gateway elements will have a hardline interface with the EUS/Orion. Gateway elements will exchange data using this hardline data interface which will be relayed to/from ground using the EUS's communication system while attached and then the Orion's C&DH system when attached for CPL that are delivered by Orion. | Mission | Ground Rule | 1;#Gateway | 14;#Comm | 15;#Vitalpur | 16;#SLS, Orion, Comm | Approved | 3/6/18 | DSCB | 17;#SLS Gateway IRD | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-G-05 | The Gateway shall comply with the HEOMD-003 Deep Space Exploration Systems Certification Requirements and Standards. | Compliance protects crew safety, ensures hazard controls, and interoperability requirements. Gateway elements will comply with an HEOMD-003 applicability matrix. | Mission | Ground Rule | 1;#Gateway | 21;#Safety | 22;#Kampe | 23;#FCS, ECLSS, Operations | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 130 | DP-28 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-G-06 | The Gateway shall accommodate crew exercise. | Exercise is required for Gateway missions longer than 14 days. Maintains crew health during stays in microgravity environment longer than 14 days at the Gateway. | Mission | Ground Rule | 18;#Utilization Module, Habitat, Airlock | 19;#FCS | 20;#Flint | 23;#FCS, ECLSS, Operations | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 22, 39, 68, 158 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-G-07 | The Gateway shall allow for safe disposal of the on-orbit Gateway at the end of its useful life. | Consideration of the method of disposal during design will ensure required resources and functions are available. Safe disposal is important to protect future exploration environments and destinations. | Mission | Ground Rule | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 26;#GN＆C | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 87, 94 | DP-37 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EN-G-01 | The Gateway shall nominally operate in a near-rectilinear halo orbit (NRHO). | Orbit trade studies identified a near-rectilinear halo orbit as optimal for minimal energy orbit maintenance, and accessibility to multiple deep space destinations. Specifically, an orbit with apolune over the south pole was selected for extended Lunar communications with surface assets. | Environment | Ground Rule | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 27;#thermalpowercommutilization | Approved | 3/23/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 212 | DP-61 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EN-G-02 | Gateway elements shall be capable of operating at a maximum solar distance of 1.03 Astronomical Units (AU) (TBR). | Maximum solar distance for NRHO. This solar distance does not include Low Lunar Orbit (LLO). Assumes operation between translunar injection and cislunar orbits. Transfer orbits are below this maximum solar distance. | Environment | Ground Rule | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 27;#thermalpowercommutilization | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EN-G-03 | Gateway elements Shall be capable of operating at a minimum solar distance of 0.97 AU (TBR). | Minimum solar distance for NRHO. This solar distance does not include LLO. Assumes operation between translunar injection and cislunar orbits. Transfer orbits are above this minimum solar distance. | Environment | Ground Rule | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 27;#thermalpowercommutilization | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EN-G-04 | The nominal flight attitude for uncrewed flight, shall be the Solar Pressure Equilibrium Attitude (SPEA) with the PPE Solar Arrays positioned towards the Sun. | The SPEA is defined to balance the solar pressure torque and is assumed to require a minimal amount of energy to maintain the attitude, and therefore minimize the propellant and power requirements for orbit maintenance. Additional work will be performed in subsequent Analysis Cycles to include consideration of gravity gradients during the portions of the NRHO closest to the moon and to define attitude deviations from SPEA for other operational modes such as orbit maintenance, orbit transfers, visiting vehicle docking/separation, science pointing requirements, and any other excursions identified. Approved DSCB 6 Dec 2017. DSG&T-DP-17. | Environment | Ground Rule | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 28;#GN＆C, Power, Thermal, Comm | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 126 | DP-17 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EN-G-05 | The nominal flight attitude for crewed flight shall be the SPEA with the Orion solar arrays (tail) positioned towards the Sun. | The SPEA is defined to balance the solar pressure torque and is assumed to require minimal amount of energy to maintain the orbit, and therefore minimize the propellant and power requirements for orbit maintenance. Orion requires the tail-to-sun attitude to satisfy thermal constraints. Approved DSCB 6 Dec 2017. DSG&T-DP-17. | Environment | Ground Rule | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 28;#GN＆C, Power, Thermal, Comm | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 126 | DP-17 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EN-G-06 | The Gateway shall maintain a minimum distance above the Lunar surface of 1500 km (TBR) at perilune of the NRHO. | Minimum Lunar distance is required to ensure orbit maintenance capability and needed to define natural environments for thermal and power systems, and Lunar observation opportunities for utilization. NRHO is an elliptical orbit with a perilune of approximately 2,000 km and an apolune of approximately 75,000 km. Low Lunar Orbits (LLO) are not planned because Orion cannot reach LLO and Gateway costs and technical challenges are significantly higher for orbit maintenance, power, communications, and thermal constraints. More detailed information on NRHO and candidate orbits for mission excursions are documented in IECST-05 Mission Cislunar Missions Mission Design Document (MDD). DSG&T-DP-61. | Environment | Ground Rule | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 29;#GN＆C, Power, Thermal, Comm, Utilization | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-61 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-01 | Gateway elements shall comply with the DSG&T Margin Management Plan for mass, power, and performance margins. | Fidelity/Maturity of assessments should drive margins. | Element | Ground Rule | 1;#Gateway | 30;#RM | 31;#Moore | 32;#GN＆C, Power, Thermal, Comm, FCS | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 108 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-02 | Gateway elements and visiting vehicles shall be initially docked to the Gateway, with the exception of the Robotic Lunar Ascent Element (RLAE). | The Gateway Phase 1 elements including the Hab, Airlock, and Logistics Modules will be initially docked. Modules may later be rotated by the robotic arm for final location/attachment to the Gateway. The RLAE will be robotically grappled and, if required, berthed to a robotic attachment mechanism on the Gateway. Orion will be docked each time it visits the Gateway. | Element | Ground Rule | 33;#HabAirlockLM | 12;#RPOD | 34;#Cryan | 35;#Elements | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | 23, 132 | DP-46, DP-23 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-03 | Gateway Elements shall have a 800mm diameter transfer passageway between Elements mated with IDSS-Compliant interfaces. | IDSS compliant mechanisms only provide an 800mm diameter passageway for a distance of 3-4 ft when mated. Items to be transferred between pressurized Gateway Elements need to be sized appropriately. | Element | Ground Rule | 33;#HabAirlockLM | 36;#Struc Mech | 37;#Nagy | 35;#Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 23 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-04 | The Gateway shall be the passive vehicle for docking events. | Visiting vehicles will be the active vehicle for docking events including Logistics Modules, Gateway element delivery, and DST docking. The Gateway does not have the capability to be the chase vehicle. The Gateway will be commanded to free drift as the visiting vehicle performs the docking maneuver. | Element | Ground Rule | 1;#Gateway | 12;#RPOD | 34;#Cryan | 38;#FSW, GN＆C | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-05 | The Gateway shall have the capability to conduct remote inspection. | Inspection of external surfaces is required to track material degradation, support anomaly investigations, and perform nominal pre-operation checkouts, e.g., pre-docking. Analysis indicates the Robotic Arm is capable of inspection of all Gateway phase 1 hardware except the solar arrays. Approved DSCB 6 Dec 17. DSG&T-DP-34. | Element | Ground Rule | 1;#Gateway | 39;#Robotics | 40;#Callen | 35;#Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-34 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-06 | Gateway elements shall support the Robotic Arm translation to adjacent Gateway element(s). | Robotic Arm must be able to relocate from element to element to cover anticipated on-orbit operations. Approved DSCB 6 Dec 17. DSG&T-DP-34. | Element | Ground Rule | 1;#Gateway | 39;#Robotics | 40;#Callen | 35;#Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-34 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-07 | Gateway Robotic Arm translation paths shall be single fault tolerant to a mechanical failure. | A sufficient number of grapple fixtures must be provided so that the robotic arm can translate around a failed grapple fixture. Approved DSCB 6 Dec 17. DSG&T-DP-34. | Element | Ground Rule | 1;#Gateway | 39;#Robotics | 40;#Callen | 35;#Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-34 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-08 | The Gateway PPE shall generate power, perform attitude control, orbit changes, and provide space to ground communication for the Gateway stack. | Since the PPE is the first element of the Gateway, it must include the specified functionality to operate autonomously. Other Gateway functions such as habitable volume, Lunar communications, etc. can be deferred to other elements. This ground rule applies to the Phase 1 Gateway stack. | Element | Ground Rule | 41;#PPE | 7;#Inter Perf | 42;#Hack | 43;#FSW, GN＆C, Mission Design, Power, C＆DH, Comm | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 4 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-09 | Each Gateway element shall be capable of storing and distributing power, controlling temperature, and providing command and data handling independent of other elements. | The specified functions are the responsibility of each element. Since the Gateway is delivered in elements at approximately 1-year intervals, the design of each element should be as self-contained as practical. Power storage applies to the PPE, Utilization Element, Habitat, and Airlock. | Element | Ground Rule | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 44;#Power, C＆DH, Thermal | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 4, 41, 63, 77, 141 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-10 | The Gateway shall have a system architecture that allows sharing of resources (to include power, thermal control, C&DH, and ECLSS for pressurized elements) across element interfaces. | The purpose is to have the capability to respond to real time on-orbit anomalies and failures. | Element | Ground Rule | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 45;#Power, Thermal, C＆DH, ECLSS | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 4, 41, 63, 77, 141 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-11 | The Gateway shall provide power, data, mechanical, and video interfaces to support external robotic operations. | Each Low Profile Grapple Fixture (LPGF) has four (4) power circuits, each rated at 20A. Gateway interfaces need to reflect the integrated interface requirements for robotic operations. | Element | Ground Rule | 1;#Gateway | 39;#Robotics | 40;#Callen | 46;#Power, C＆DH, Struc/Mech, Comm | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 4, 41, 63, 77, 141 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-12 | The Gateway shall provide mechanical, power, and data interfaces to support external equipment and payloads. | Gateway interfaces need to reflect the integrated interface requirements for attached equipment and payloads. Current plan is to place an optical communications DTO external on the PPE. | Element | Ground Rule | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 47;#Struc/Mech, Power, C＆DH, Robotics, Utilization | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 4, 41, 63, 80, 141 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-13 | Gateway elements shall provide bi-directional power feeds to each axial docking port interface for the pass-through of primary power. | The Gateway primary power transmission from the PPE to the Gateway elements utilize bi-directional axial port feeds. This bi-directional power transmission allows element launch order independence and integrates (if applicable) the Gateway distributed battery system to be able to power the Gateway during eclipses and allows the distributed batteries to recharge. The element-to-element primary power is redundant and protects from a docking connector failure. | Element | Ground Rule | 1;#Gateway | 48;#Power | 49;#Lawrence | 50;#Power | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 106 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-14 | The Gateway shall provide the capability to isolate volumes in the event of depressurization of one element. | Allows the crew to survive a rapid depressurization event by closing hatches to isolate the leak from the crew. Operational planning and training should ensure the crew doesn’t isolate the leak between themselves and the crew transportation vehicle. | Element | Ground Rule | 33;#HabAirlockLM | 51;#ECLSS | 52;#Sargusingh | 53;#Safety, FCS | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | Crew Survival Req 01/24/2018 to DIWG | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EL-G-15 | The Gateway integrated engineering coordinate system shall be in accordance with DSG&T-DP-40 as shown in Figure DSG-EL-G-15. | A common reference coordinate system is needed to exchange technical data and analysis results to ensure a consistent understanding of engineering data. The selected coordinate system is consistent with the PPE reference coordinate system to minimize rework. | Element | Ground Rule | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 54;#All Analysis Teams | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 202 | DP-40 | Active | Gateway Reference Coordinate System | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | |
| DSG-SY-G-01 | The Gateway shall provide a human shirt sleeve environment at a nominal operating pressure of 101 kPa (14.7 psia) at 21% O2. | The crew must be able to operate within the Gateway in a shirt sleeve human rated environment during IVA operations. The structure should be designed to a pressure range and the interoperability standard. | System | Ground Rule | 33;#HabAirlockLM | 51;#ECLSS | 52;#Sargusingh | 58;#FCS | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 32A | DP-64 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-02 | Gateway payloads shall provide computational resources required by the payload. | The Gateway design cannot anticipate and accommodate future payload computational needs. Approved at DSCB on 8 November 2017. DSG&T-DP-01. | System | Ground Rule | 55;#Payloads | 56;#Utilization | 57;#Goodliff | 59;#C＆DH | Approved | 3/6/18 | DSCB | 60;#Payload IRD | FSR | 11;#IAC1 | 118 | DP-01 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-03 | The Gateway Robotic Arm shall have the capability to berth elements up to TBD kg to the Gateway. | Berthing capability as backup for docking increases robustness and element reconfiguration capability allows for propellant free reconfiguration, e.g. airlock reorientation. The nominal plan is to berth the Robotic Lunar Ascent Element (RLAE) to the Gateway. There is also a potential need to reposition the A/L after initial docking. DSG&T-DP-34 presented by CSA. | System | Ground Rule | 61;#Robotic Arm | 39;#Robotics | 40;#Callen | 35;#Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A/217 | DP-34/TBD | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-04 | The PPE shall provide up to 32 kW (TBR) to the rest of the Gateway stack. | The Gateway Open Architecture study indicates a 32kW power allocation is required for non-PPE elements. Details are provided in DP-27. Discussed DSCB 6 Dec 17. DSG&T-DP-27. PPE CR in work to address TBR. | System | Ground Rule | 41;#PPE | 48;#Power | 49;#Lawrence | 62;#PPE | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 103 | DP-27 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-05 | The Gateway shall provide an energy storage system to provide power to the Gateway elements during non-insolation periods of at least 1.5 hours. | Once the element is attached to the Gateway, that element’s battery is part of the integrated Gateway primary power system and feeds all elements of the Gateway. Collectively, all the batteries have to supply power to the Gateway during non-insolation periods such as an eclipse. The overall battery energy is rated to maintain 1.5 hours. The 1.5 hours is based on a Lunar synodic resonance NRHO which will essentially eliminate the Earth shadow and keep the Lunar eclipses less than 1.5 hours. DSG&T-DP-61. | System | Ground Rule | 1;#Gateway | 48;#Power | 49;#Lawrence | 63;#Elements, Mission Design | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 212 | DP-61 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-06 | The Gateway elements shall provide an energy storage capability to provide power to the element from launch to Orion extraction. | Gateway elements such as the Hab and AL will need battery power to prevent low temperature violations (water freeze) during the time of launch until Orion can augment the element with power. These element batteries will be integrated into the overall Gateway power system once docked to the Gateway. | System | Ground Rule | 1;#Gateway | 48;#Power | 49;#Lawrence | 35;#Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 103 | DP-27 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-07 | The Docking DC-to-DC Converter Unit (DDCU) shall implement a dc-isolated output with a variable voltage and variable current limit. | Docking DDCU output set points are required for the voltage and current because visiting vehicles (Orion included) may have their own power sources that require specific protection for the vehicle grounding, wiring, and operational limits. Vehicles with direct battery coupling to the bus are especially sensitive. | System | Ground Rule | 1;#Gateway | 48;#Power | 49;#Lawrence | 35;#Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 106 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-08 | Gateway elements shall maintain subsystems and module thermal limits independent of flight attitudes. | Provides operational flexibility. The Hab Module will have to support human habitation between long periods of dormancy (uncrewed periods) which require it to have a range of thermal control to prevent condensation and be able to recover from uncrewed to a crewed configuration that supports a shirt sleeve environment for the crew. | System | Ground Rule | 1;#Gateway | 64;#Thermal | 65;#Ungar | 66;#Mission Design | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 150 | DP-47 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-09 | The Gateway shall be able to change the Gateway attitude to any orientation (as needed) to meet operational constraints for both crewed (with Orion) and uncrewed (without Orion) configurations. | The main drivers requiring attitude deviations from solar pressure equilibrium are for SEP performed orbit maintenance maneuvers, crewed operations with Orion such as docking events where the Gateway is the passive vehicle, and for the Orion tail-to-sun requirement. | System | Ground Rule | 1;#Gateway | 67;#GN＆C | 34;#Cryan | 68;#Power, Thermal, Comm, Orion | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 15 | DP-66 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-10 | The Gateway shall have a high rate communication system. | Deep space communication systems will be evolving to higher data rates by deployment of the Gateway systems. The system may accommodate four modes: high-rate (listed), low-rate (for S/C health and housekeeping), docking, and inter-vehicle. | System | Ground Rule | 1;#Gateway | 14;#Comm | 15;#Vitalpur | 69;#N/A | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 123 | DP-26 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-11 | The Gateway shall support simultaneous communications with at least 3 users. | The Gateway will need to communicate with multiple users at the same time to support Gateway to Earth communications, Gateway to Visiting vehicle communications, Gateway to EVA communications, Gateway to Lunar assets, etc. Each communication link is a full duplex link that supports transmit/receive at the same time. DSG&T-DP-25. | System | Ground Rule | 1;#Gateway | 14;#Comm | 15;#Vitalpur | 70;#Operations | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 122 | DP-25 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-12 | During nominal operations, the Gateway shall provide space-to-ground communications for itself and attached visiting vehicles. | The Gateway must provide space-to-ground communication for its own system. Providing this service for attached vehicles reduces power required by the attached vehicle and simplifies operations. | System | Ground Rule | 1;#Gateway | 14;#Comm | 15;#Vitalpur | 71;#Orion, Logistics Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 161 | DP-70 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-13 | The Gateway shall provide an S-Band communications link to communicate with visiting vehicles. | The S-band comm is used to generate the range and range-rate measurements that are required by the visiting vehicle GNC. Additionally, the International Rendezvous Standard specifies telemetry between the vehicles exchanging state and health data to be used by each vehicle’s GNC/FDIR. The data includes the absolute state data (position, velocity, attitude, attitude rate, time of validity) and status/health data (GNC mode(s)). The rationale for this is that the data exchange between the Gateway and Orion/VV over the S-band link would be 1) quicker than through the ground links, and 2) establishes the preferred method of communication for deep space missions. | System | Ground Rule | 1;#Gateway | 14;#Comm | 15;#Vitalpur | 71;#Orion, Logistics Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 162 | DP-71 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-14 | The Gateway shall be designed to be maintainable, except for the PPE. | The Gateway must survive for long periods without crew and should therefore, not be dependent on crew EVA. | System | Ground Rule | 1;#Gateway | 7;#Inter Perf | 72;#Jones | 73;#Logistics, all systems ＆ elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-15 | The Gateway shall provide EVA interfaces for contingency maintenance and repair. | HEO-004 specifies the Gateway shall provide the capability for EVA operations. EVA interfaces are designed to be compatible with EVA operations. This includes restraining the crewmember, safeguarding both the vehicle and crewmember while working, and accommodating EVA contingency operations using a standard EVA tool set. Interfaces must comply with EVA-EXP-035 (TBR). | System | Ground Rule | 1;#Gateway | 74;#EVA | 75;#Johnson | 47;#Struc/Mech, Power, C＆DH, Robotics, Utilization | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 44 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-16 | The Gateway Robotic Arm shall support EVA operations including an EVA crewmember based on the Robotic Arm. | The Robotic Arm will need to be able to reach EVA work sites and support crew members with positioning of tools and hardware. | System | Ground Rule | 61;#Robotic Arm | 74;#EVA | 75;#Johnson | 77;#Robotics | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 45 | DP-47 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-17 | The Gateway shall provide the capability for the crew to perform command and control and communication functions, excluding robotic arm operations, from within any habitable Gateway element. | Crew capability (data/command interfaces) provides monitoring of the caution & warning (C&W) as well as nominal and off-nominal control of life support, thermal control, communication, and other system functions necessary for safe operations from any habitable element. This ground rule does not apply to the Robotic Arm. | System | Ground Rule | 33;#HabAirlockLM | 78;#C＆DH | 79;#Higbee | 69;#N/A | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-18 | The Gateway shall be capable of remote transition from an uncrewed state to be compatible with crew ingress. | Need to be able to verify the Gateway is ready to receive the crew prior to launch. | System | Ground Rule | 1;#Gateway | 78;#C＆DH | 79;#Higbee | 80;#Operations, ECLSS | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-G-19 | Gateway external Orbital Replaceable Units (ORUs) shall be EVR compatible. | The Gateway must survive for long periods without crew and should therefore, not be dependent on crew EVA. | System | Ground Rule | 1;#Gateway | 7;#Inter Perf | 81;#Arnold | 82;#Mission Design, GN＆C | Approved | 3/6/18 | DSCB | 83;#ADD | FSR | 11;#IAC1 | 129 | DP-18 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-01 | Gateway stack configurations and mass properties assumptions are included below. | A reference configuration is needed to ensure consistency of analyses for requirement development and feasibility. IAC 2 update includes the PPE, ESPRIT Element, Utilization Element, Habitat, Robotic Arm, Airlock, and Robotic Lunar Ascent Element. | Mission | Assumption | 1;#Gateway | 7;#Inter Perf | 81;#Arnold | 54;#All Analysis Teams | Approved | 3/6/18 | DSCB | 83;#ADD | FSR | 11;#IAC1 | 129 | DP-18 | Gateway stack configurations - masses include 500 kd PMR | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | |
| DSG-M-A-02 | EVAs will not occur during visiting vehicle rendezvous, proximity operations, and docking activities. | Protects the crew during these events. Assumption is needed so we don't need a 4th simultaneous communication path and so we don't combine EVA loads with docking event loads. | Mission | Assumption | 1;#Gateway | 84;#Operations | 85;#Greene | 86;#Comm, EVA | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | 122 | DP-26 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-03 | The Gateway will accommodate crew exercise of 1.5 hours per day per crew member (TBR). | Exercise is required for missions longer than 14 days. Maintains crew health during stays in microgravity environment longer than 14 days. | Mission | Assumption | 1;#Gateway | 19;#FCS | 20;#Flint | 70;#Operations | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | 22, 39, 68, 158 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-04 | The Gateway will accommodate crew scheduled operations of 7.5 hours per on-duty day (TBR). | Scheduled operations time is based on Shuttle Crew Scheduling Constraints since Shuttle mission times are relevant to the planned 30-day mission for the Gateway. ISS GGR&C specifies 6.5 hours per day with 2.5 hours of exercise required due to the longer duration ISS missions. | Mission | Assumption | 1;#Gateway | 19;#FCS | 20;#Flint | 70;#Operations | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | 158 | TBD | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-05 | Logistic Element launched on a Commercial Support Flight (CSF) has an initial on-orbit mass of 6t (TBR). It leaves 2.5t (TBR) of logistics at the Gateway and removes 1.5t (TBR) of logistics when it departs. | On-orbit mass based on Commercial Support Flight (CSF) delivery capability of 6.5t and an assumed 500kg payload attach fitting. Assumption based on ISS experience for logistics consumed and disposed. | Mission | Assumption | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 87;#Logistics Elements | Approved | 3/6/18 | DSCB | 88;#IAD | FSR | 11;#IAC1 | 71, 73, 76, 77, 218 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-06 | A Logistics Element launched as a CPL has an initial on-orbit mass of 9t (TBR). It leaves 4.2t (TBR) of logistics at the Gateway and removes 1.1t (TBR) of logistics when it departs. | On-orbit mass based on SLS delivery capability of 10t and an assumed 1000kg payload attach fitting. Assumption based on ISS experience for logistics consumed and disposed. | Mission | Assumption | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 87;#Logistics Elements | Approved | 3/6/18 | DSCB | 88;#IAD | FSR | 11;#IAC1 | 71, 73, 76, 77, 218 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-08 | The logistics necessary to support a crewed mission at the Gateway will be at the Gateway at least 30 days prior to a crew arrival or arrive at the Gateway with the crew. | The Mission Management Team would want to know that all required logistics are available at the Gateway or planned for launch with the crew prior to a crewed Flight Readiness Review. | Mission | Assumption | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 90;#FCS, Operations, Logistics | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | 71, 73, 76, 77, 218 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-09 | The design reference Gateway NRHO, specified in Ground Rule DSG-EN-G-01, will be a 9:2 Lunar synodic resonance NRHO. | Synchronizing the period of the Gateway NRHO with the average synodic Lunar period (the time for one revolution of the Moon around Earth), will significantly reduce Earth and Lunar eclipses in the Gateway orbit. The 9:2 resonance effectively eliminates Earth eclipse and reduces Lunar eclipse to ~10.5 per year with durations less than 1.3 hours. This reduces battery requirements and thermal constraints. DSG&T-DP-61. | Mission | Assumption | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 91;#GN＆C, Comm | Approved | 3/6/18 | DSCB | 88;#IAD | FSR | 11;#IAC1 | 212 | DP-61 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-10 | The Logistics Module (LM) will be capable of autonomously executing separation and departure from the Gateway and disposal into a heliocentric orbit. | During the course of Gateway operations, the logistics module (LM) will dispose of waste objects from the gateway. The LM will perform a small maneuver to escape from the NRHO, subsequently moving away from the vicinity of the Earth and Moon into a heliocentric orbit. | Mission | Assumption | 1;#Gateway | 24;#Mission Design | 25;#Whitley | 87;#Logistics Elements | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 93 | TBD | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-M-A-11 | For disposal from the NRHO, the LM will execute a maneuver of 15 m/s (TBR) in the velocity direction at perilune to escape from the vicinity of the Moon. | To ensure heliocentric disposal and avoid Earth or Moon impact or an earthbound trajectory, the magnitude, direction, and timing of the disposal maneuver must be considered. If oriented correctly in the Sun-Earth rotating frame, solar gravity will pull the LM into heliocentric orbit. From the 9:2 lunar synodic resonant NRHO, a 15 m/s maneuver results in orbit escapes from the vicinity of the Moon in less than a full revolution. Further analysis will bound the problem and fully define limits for errors on the LM to assure heliocentric escape after disposal from the Gateway. | Mission | Assumption | 92;#LM | 24;#Mission Design | 25;#Whitley | 87;#Logistics Elements | Approved | 3/6/18 | DSCB | 88;#IAD | FSR | 11;#IAC1 | 93 | TBD | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-01 | Gateway elements will provide two 3kW (TBR) dc-isolated converter power feeds (power out from Gateway element only) to each radial docking port interface and two 3kW (TBR) dc-isolated converter bi-directional power feeds at the one axial port utilized by Orion during initial outbound delivery of the Gateway element. Orion input power to this axial port will be limited to Orion’s switch limit of 15A. | Radial docking ports require redundant Gateway provided power out to the visiting vehicle. The one axial port utilized for Orion initial outbound delivery to NRHO requires a redundant bi-directional power feed to allow power to be received by the Gateway element from Orion. DC-isolated power is required to protect and meet all EMI and power quality requirements of both the Gateway and the visiting vehicle. | System | Assumption | 1;#Gateway | 48;#Power | 49;#Lawrence | 93;#NDS | Approved | 3/6/18 | DSCB | 94;#L3 Specs and IRDs | FSR | 11;#IAC1 | 106 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-02 | The PPE, Utilization Element, Habitat, and Airlock will each provide at least 12kWh of batteries (60%DoD at 15-year life) with a minimum charge/discharge rate of 612kW. | Once the element is attached to the Gateway, that element’s battery is part of the integrated Gateway primary power system and feeds all elements of the Gateway. Collectively, all the batteries have to supply power to the Gateway during non-insolation periods such as an eclipse. The overall battery energy is sized to maintain 1.5 hours of nominal 32 kW operations. | System | Assumption | 1;#Gateway | 48;#Power | 49;#Lawrence | 95;#PPE, Utilization Element, Hab, A/L | Approved | 3/6/18 | DSCB | 99;#L3 Spec | FSR | 11;#IAC1 | 103 | DP-27 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-03 | The Gateway communication subsystem will support a 10 Mbps (TBR) uplink data rate. | A 10Mbps uplink data rate supports video conferencing when the Gateway is crewed, software uploads, etc. and margin to relay data to other elements. DSG&T-DP-26, December 6, 2017. | System | Assumption | 1;#Gateway | 14;#Comm | 15;#Vitalpur | 70;#Operations | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 123 | DP-26 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-04 | The Gateway communication subsystem will support a 100 Mbps (TBR) RF downlink data rate. | A 100Mbps RF downlink data rate supports video conferencing when the Gateway is crewed, motion imagery, engineering data, relay data to other elements and margin for growth until an optical communication system becomes part of the operational baseline. DSG&T-DP-26, December 6, 2017. | System | Assumption | 1;#Gateway | 14;#Comm | 15;#Vitalpur | 96;#Operations, Utilization | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 123 | DP-26 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-05 | The Gateway will transition from an uncrewed state to be compatible with crew ingress within two (2) weeks. | Two weeks is driven by wanting to make sure the Gateway is ready to receive the crew prior to launch. | System | Assumption | 1;#Gateway | 78;#C＆DH | 97;#Smith | 96;#Operations, Utilization | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-06 | The Gateway Robotic Arm reach is assumed to be 7m. | Current concept design assumption from CSA. Approved DSCB 6 Dec 17. DSG&T-DP-34 presented by CSA. | System | Assumption | 61;#Robotic Arm | 39;#Robotics | 40;#Callen | 98;#Int Perf, EVA | Approved | 3/6/18 | DSCB | 83;#ADD | FSR | 11;#IAC1 | N/A | DP-34 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-07 | The Gateway will provide a temporary stowage location for the Robotic Arm Tool & ORU Caddy. | A sufficient number of grapple fixtures must be provided and located to allow for unintrusive temporary stowage of the Tool & ORU Caddy on the Gateway. Note that the Caddy also supports Small Dexterous Arm (SDA) temporary stow. DSG&T-DP-34 presented by CSA. | System | Assumption | 1;#Gateway | 39;#Robotics | 40;#Callen | 76;#Struc/Mech | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-34 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-08 | The Gateway will accommodate deployment and operations of two or more LPGF based External Carriers. | A single LPGF base can be used to accommodate eight or more small payloads or ORUs and is thus an effective means to meet future science and logistics requirements. The interface footprint on elements is minimized while maximizing options for custom pointing/orientation of the small payloads or ORUs. DSG&T-DP-34 presented by CSA. | System | Assumption | 1;#Gateway | 39;#Robotics | 40;#Callen | 100;#Struc/Mech, Utilization | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 66, 144 | DP-34 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-10 | The Gateway will accommodate Robotic Arm self-maintenance using the science airlock when necessary. | The science airlock is required for Robotic Arm self-maintenance operations. Suitably located LPGFs required for SDA operations to support removal of Robotic Arm ORUs and passing into the science airlock. DSG&T-DP-34 presented by CSA. | System | Assumption | 1;#Gateway | 39;#Robotics | 40;#Callen | 101;#CSA | Deleted | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | N/A | DP-34 | Retired | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-11 | Gateway external maintenance and repair will be performed robotically. | The Gateway must survive for long periods without crew and should therefore, not be dependent on crew EVA. | System | Assumption | 1;#Gateway | 39;#Robotics | 40;#Callen | 102;#ESPRIT | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-34 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-12 | Gateway internal maintenance and repair will be performed robotically or by crew members. | The Gateway must survive for long periods without crew and should therefore, not be totally dependent on crew. | System | Assumption | 1;#Gateway | 39;#Robotics | 40;#Callen | 70;#Operations | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-13 | The Gateway will provide EVA compatible accommodations for redundant EVA translation paths. | Translation aids, such as EVA Handrails, and a path free of obstructions or hazards must be designed to support the movement of EVA crew members between the crew lock and EVA work sites. Redundant paths for crewmember to translate across and between elements to achieve single-fault tolerance requirement for returning crew safely back to the airlock and as a backup to robotics. EVA systems require each module of the stack to provide 1 translation path at each (axial circumference) end of the module as well as radial handrails as necessary. This path will allow for translating the circumference of the axial end of a module thereby enabling module to module translation. Note: PPE L5 requirements specify one translation path. | System | Assumption | 1;#Gateway | 103;#Robotics/FCS | 72;#Jones | 70;#Operations | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-14 | The Gateway will support EVA as a backup to EVR. | Certain scenarios will require EVA to support EVR operability, for example, Robotic Arm activation, Robotic Arm maintenance and repairs, and backup for robotic tasks. | System | Assumption | 1;#Gateway | 74;#EVA | 75;#Johnson | 76;#Struc/Mech | Approved | 3/6/18 | DSCB | 2;#L2 Spec | FSR | 11;#IAC1 | 45 | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-15 | The Gateway will support at least 2 EVAs per crewed mission after delivery of the Gateway Airlock. | EVAs will be needed to support EVA exploration objective (demonstration testing) as well as contingency repair. A reference number of EVAs per crewed mission is necessary for logistics planning, ECLSS design, and crew time planning. If additional EVAs are needed, consumables would be supplied through logistics. | System | Assumption | 1;#Gateway | 74;#EVA | 75;#Johnson | 104;#EVR, Operations | Approved | 3/6/18 | DSCB | 10;#ConOps | FSR | 11;#IAC1 | 44 | DP-47 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-16 | The Gateway science airlock will be used on average twice per week during crewed missions and once per month during uncrewed operations. | This is needed to reserve enough gas for depress/repress. Uncrewed operations use of the science airlock is based on initial feedback from the Science Workshop. | System | Assumption | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 105;#EVA | Approved | 3/6/18 | DSCB | 88;#IAD | FSR | 11;#IAC1 | 44 | DP-48 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-SY-A-17 | The Gateway shall use 1% for probability of critical habitat failure. | This assumption will be used for sparing and logistics planning. It is based on ISS experience. | System | Assumption | 1;#Gateway | 7;#Inter Perf | 57;#Goodliff | 106;#Utilization | Approved | 3/6/18 | DSCB | 88;#IAD | FSR | 11;#IAC1 | N/A | DP-46 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-EN-G-07 | The Gateway shall have the capability to maintain a near-circular orbit at a minimum distance above the Lunar surface of TBD km. | Minimum Lunar distance is required to ensure orbit maintenance capability and needed to define natural environments for thermal and power systems, and Lunar observation opportunities for utilization. The Gateway design reference mission is a NRHO with a perilune of approximately 2,000 km and an apolune of approximately 75,000 km. A minimum altitude circular orbit is defined to provide a capability reference for planning Lunar observation science. The TBD will be resolved as part of the Gateway IAC 2. | Environment | Ground Rule | 1;#Gateway | 7;#Inter Perf | 8;#Hill | 107;#Safety | Approved | 3/6/18 | DSCB | 88;#IAD | FSR | 11;#IAC1 | 77 | DP-36 | Active | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||
| DSG-U-A-01 | 1,000 kg per crewed mission will be provide for utilization. This mass will be shared as follows: 450 kg Technology/Capability development, 275 kg Science, and 275 kg International Partners/Commercialization. The split between internal and external mass is TBD. | The DSG upmass is driven by the desire to accommodate technology & capability demonstrations, science needs, and international partner/commercial requests. Initial estimates were determined by mass required to achieve candidate test objectives. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-02 | Power available for utilization is a minimum of 4 kW during crewed operations and a minimum of 4 kW (TBD) during uncrewed operations. | Payloads will require power to operate while attached to the gateway. 4 kW is derived from DSG-DP-27. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-03 | The Gateway will provide TBD Data Management storage/capabilities/rules/allocation for the management of utilization payload data. | Based on initial feedback from the Science Workshop, some payloads would benefit from Gateway data management resources. Data storage is a finite resource and needs to be allocated. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-04 | Payload(s) will be launched in place with the PPE (TBR). | Based on initial feedback from the Science Workshop, there is a desire to launch one or more payloads in place on PPE. It is understood that only minimal resources would be available and that launch loads could limit this opportunity. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-05 | Gateway provides TBD dedicated computational resources for utilization payloads. | Based on initial feedback from the Science Workshop, some payloads would benefit from computational resources. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-06 | Gateway provides command and control for utilization payloads, including centralized command loads (e.g. instrument timing, cubesat deployment, etc.). | Payloads will need to be commanded by the gateway. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-07 | TBD allocation is available for utilization downlink. | To be defined by utilization payload needs. Several utilization payloads could require real-time video capability (e.g. telerobotics). | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-08 | Gateway provides thermal control for internal payloads. | Limits payloads volume and mass. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-09 | An average of four (TBR) hours per crew per work day per week will be allocated for dedicated utilization crew time. | Given past history, it’s important to allocate dedicated time to utilization as utilization tends to fall to the bottom of the priority list. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-10 | Each element (excluding PPE) will have TBD WMIs and LPGFs to support payloads. | The number of external payload attach locations is needed for utilization planning. The interface plate should allow for additional capability of long duration stare/pointing. Multiple instruments may be hosted on a single WMI or LPGF, assuming the instruments stay within the resource, structural and volume envelopes. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-11 | Up to 2 kW (TBR) power is available to external payloads attached to a WMI or LGPF. | Common interfaces will guide the development of payloads for the gateway. WMIs and LPGFs will contain data, command, and power interfaces. Thermal management is the responsibility of the external payload. Another 2 kW is available through the LPGF for system power. If it is not needed by the robotic system, it can be available for payloads. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-12 | A minimum of 1 (TBR) docking port and 1 (TBR) berthing port will be available for utilization. | Visiting vehicles (non-Orion) will require a dedicated docking port. Lunar landers and/or ascent modules will require docking or berthing. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-13 | The Gateway will provide at least TBD m3 within the Utilization Element, for powered payloads. | Several of the utilization payloads will need internal volume. Payloads may need to be collocated within the volume to allow sharing of resources. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA | ||||||||||||||||
| DSG-U-A-14 | The Gateway will provide at least 1 (TBR) m3 within the Habitat Element , for powered payloads. | Several of the utilization payloads will need internal volume. Payloads may need to be collocated within the volume to allow sharing of resources. | Assumption | Item | sites/deepspace/dashboard/SEI/Req/Lists/GatewayGRA |
This is the start of the file's text. The full file is on GovTribe.
File details come from the government source that posted it. Updated .