Project Future Moon PDR PDR PRESENTATIONS February 8th, 2019 1 Introduction Andrew Lang PM February 9th, 2019 2 Project Background ● Earth’s strong gravity well makes space exploration difficult ● Current exploration efforts discard most of what is launched from Earth’s surface ● More sustainable mission architecture is needed ● Experts advocate in situ resource utilization ● Paul Spudis proposed a lunar outpost near the poles and orbital propellant to fuel future missions to Mars 3 Project Solution Overview ● Conduct feasibility study of the systems proposed by Spudis that will fuel future missions to Mars ○ MINIMIZE MASS sent from EARTH ○ 100Mg of prop annually ● 14 Systems ● 3 Phases ○ Discovery ○ Development ○ Habitation 4 BACKUP: Storyboard (Discovery) *Cislunar vehicle and Major Launch Vehicle required for most/all stages Launch From Ensure/ Establish Earth into Lunar Connection Between Orbit Moon and Earth Communications Satellite Land on lunar Find/Confirm Use information surface (Landing sites of to select crater / Deployment water/light Scout Rover I Vehicle) Land in Demonstrate Move to crater regolith separation Development (L/DV) process Phase Scout Rover II 5 BACKUP: Storyboard (Development) Establish power Level Landing source, ground Area communications Landing Site Prep Land Assembly prefabricated (Possibly by materials Landing Site Prep) Resource Storage Land Ice Separate ice Store ice/water Harvester from the lunar in Resource Components & regolith Storage area Assemble Ice Harvester 6 BACKUP: Storyboard (Development) Begin transfer Store of ice into Propellant propellant Lunar Propellant Depot Land major sections of Assembly of Habitat structure components Habitat Infrastructure and life support 7 Insert Safe Habitation Haven into Phase Lunar Orbit Safe Haven BACKUP: Storyboard (Habitation) Note: At the current stage, the location to which propellant is being transported is being re-evaluated. Either a Orbiting Propellant Depot or the Mars Transport Vehicle will come after this Vehicle. A reusable lander is required for the Reusable Lunar crewed missions Launch Vehicle M1 Orbit Moon Crewed Mission 3 M3 Remote landing of landing vehicle Crewed Mission 2 8 BACKUP: Storyboard (Habitation) M3 Setup incomplete / One day stay on small scale aspects lunar surface of Habitat, small science aspect Crewed Mission 3 Repeat as necessary Land on Lunar Surface Lunar Surface Transport Insert into lunar orbit Remote missions for fuel storage using the Reusable Lunar Launch Orbiting Depot or Vehicle can begin Mars Transport 9 BACKUP M4 250 day stay on the Continue ice mining Moon missions and launches Crewed Mission 4 Humans arrive to or Fully fuelled Mars in the Mars Transport Vehicle Transport Vehicle. begins orbit to Mars Mars Transport Vehicle 10 SCOUT ROVER SPECIFICATIONS Group Lead: Myles Homan Rovers/Demonstration Systems February 9, 2019 11 Problem Requirements ● 12 rovers to search for water ice on the lunar poles and to demonstrate harvesting systems ● Need to minimize the mass and volume of this system Need to Determine ● What science/scouting equipment is necessary ● Mass and power requirements of science and demonstration equipment ● Power required to move the rovers and range Assumptions ● The mass of the motor, wheels, and chassis is 25 kg ● Aerodynamic resistance on the Moon is negligible ● The speed of the scout rover is constant Solution 1st wave- ● 4 scout rovers each to north and south pole ● Only scientific equipment necessary to detect water ice is carried 2nd wave- ● 4 scout rovers to best destinations chosen ● Both the scientific equipment to detect water-ice and the equipment to demonstrate the harvesting systems All rovers will have the same main design which includes ● Chassis ● Power system ● Main body 13 Detection/Demonstration Equip. Demonstration method: First 8 rovers: Detection Corer (planetary volatile extractor) Last 4 rovers: Demonstration ● double walled coring auger with inside heaters No science on scout rovers ● corer penetrates surface and captures regolith ● volatiles are sublimated, condensed, and stored Mass/Power/Volume of Detection and Demonstration Equipment: 14 Slide by: Pavi Ravi POWER SYSTEM Requirements ● Needs to provide 341 W peak power ● Needs to last until its mission is over After considering many power options, lithium-sulfur batteries were chosen due to its high power density 3 Specific energy W*hour/kg W*hour/m 500 350,000 Mass Mg Power W*hour Volume m3 0.02 10,000 0.0286 15 TOTAL M.P.V. and Performance Scout Rovers Demonstration Rovers Mass Mg Power kW Volume m3 Mass Mg Power kW Volume m3 0.0826 0.341 0.349 0.0957 0.319 0.4655 -Each set of 4 scout rovers will -Each set of 4 demonstration take up approximately 1.4 m3 and rovers will take up approximately has a mass of .357 kg 1.9 m3 and has a mass of .383 kg Range Time hours 29.32 Distance km 87 16 Backup: Detection/Demo Equip. Corer description: A Corer based volatiles extractor is essentially a dual wall coring auger. The outer wall is a traditional auger with shallow flutes, made of low conductivity composite material. The inner wall is perforated and also covered with heaters. The coring drill penetrates subsurface and captures a core. Heaters are turned on to sublime volatiles within the core. Volatiles then flow within the annual space between the inner conductive cylinder and the outer insulating cylinder (auger), and into a cold trap on the surface. Demonstration equipment references: ● http://rascal.nianet.org/wp-content/uploads/2016/08/PVEx-for-ISRU.pdf ● https://www.hou.usra.edu/meetings/V2050/pdf/8082.pdf ● https://www.hou.usra.edu/meetings/leag2016/presentations/Thursday/Indyk.pdf ● http://rascal.nianet.org/wp-content/uploads/2016/08/PVEx-for-ISRU.pdf 17 Slide by: Pavi Ravi BACKUP: Power 18 BACKUP: Power 19 BACKUP: Power 20 Major Launch Vehicle Overview Project Future Moon Preliminary Design Review February 9, 2019 21 Purpose REQUIREMENTS - Use a reusable rocket to minimize launch costs - Must launch at most a payload of 51.8 Mg and 2032 m3 (will change) - Four pressurized rovers, one empty MLDV and six astronauts - Must achieve a delta-V of 8.415 km/s from Cape Canaveral to LEO - The total initial mass launched from Earth's surface to Low Earth Orbit (LEO) should be minimized. THE MISSION - If MLDV design shrinks down and we can make launch payload in one launch - Launch to LEO and let the MLDV descent to the moon surface to bring rovers 22 Major Launch Vehicle SLS Block 2 Cargo - Provides us with more breathing room in terms of packing and allows for unexpected changes in payload masses and volumes. This was deemed the most logical choice for now given that not much is set in stone yet. QUANT. PARAMETERS - Mass: 980 Mg - Thrust: 52,000 kN - Payload to LEO: 130 Mg - Provides more freedom for - Payload volume: 905 m3 Possible Future Iterations depend on when final payload masses and volumes will be obtained. Major Launch Vehicle NEEDS FROM MLV TEAM - Finalize a MLDV design (PROP will get that done soon!) - Collaborate on payload packing with each team that will send payload *see Slack* MOVING FORWARD - I do not recommend working on this unless systems volumes are drastically changed and it is needed. Landing/Deployment Vehicle (LDV) Project Future Moon Preliminary Design Review February 10, 2019 Lunar Deployment Vehicle Background “This system delivers scout/demonstration rovers from lunar orbit to lunar surface” during the Discovery Phase Requirements HLR 1: “Land a dozen small rovers near the lunar poles…” HLR 3: “Prepare the lunar surface to avoid dust during landing” Solution 1) Major Launch Vehicle puts system in lunar orbit 2) Disposable vehicle takes 4 rovers near lunar surface 3) Sky crane maneuver to lower rovers to lunar surface Kyle Duckering Mission Design - LDV is an expendable system exclusively used during Discovery phase of mission - Must land 12 scout rovers on the north and south lunar poles - Descend from LLO (100 km altitude) -> Propulsive landing Step Description Avg. ΔV (km/s) 1 Enter descent arc 0.021 2 Propulsive landing 1.951 / TOTAL 1.922 Cody Hawkins Structures and CAD Structures Overview - Primary vehicle made out of aluminum - Structural mass will be <0.1 Mg - Moon crane must be able to lower ~0.2 Mg about 25m - Spectra fiber rope to be used to lower rovers - <1 kg in mass Tyler Stark - ~3,000 kg tensile strength Utilized Sky Crane maneuver for lunar lander in order to avoid dust and debris. Matthew Eustace Communications and Controls Communication Module Power: 25W ● 8X 71 kN, 300 isp thrusters. ○ offers redundant control on all axes Sense & Compute Module: Mass: 2 kg Power: 65 W Volume: 0.03 m^3 Kevin Sheridan Propulsion Parameters (All per thruster) Project Future Moon LDV Apollo Descent Propulsion System Thruster count 8 1 Thrust 71 kN 45 kN Inputs Isp 300 s 311 s Delta-v 1.9506 km/s 1.7 km/s* Dry Mass ? 2000 kg Propellant Mass (Aerozine 50) 11.36 mg 8.2 mg Calculated Pressurant Mass (He) 40 kg 22 kg LDV currently calls for 8 x 71 kN thrust, need to bring down required thrust (per thruster) to pass sanity check compared to Apollo Descent Stage or realize scale of lander Revisit required thrust or realize scale of payloads, implement LH2 architecture to increase Isp, avoid toxic hypergolics on landing site, and integrate with cislunar economy Sam Evani Power/Thermal Problem: Power components of the LDV Power Requirements: Power Sources: - Communications and Control - - Parallel battery Compute and Sensing Package - configuration requires 25 W (12-24V) Li-ion to provide