Presentation Contents

Transcription

1 OTOS

2 Presentation Contents Mission Requirements Mission Operations Architecture Design Reference Missions Habitat Configuration CONOPS Life Support Contingency Accommodations Plans for Experimental Testing Mass Estimates Propellant Mass Estimates Cost Estimates Baseball Card References

3 Fast Facts Crew Capacity: 6 Duration: 15 years Pressurized Modules: 8 (Counting Airlock + Lander) Mass (Total) 600 Metric Tons Pressurized Volume (Total) 2600 m3 Standard Module Size Length - 13 m Diameter - 7 m Rotating Ring Diameter: 60 m Total Length: 44.1 m Docking: 2 available NASA Docking Adapters Power: 150 KW supplied by Solar Arrays Propulsion: X3 Hall Effect Thruster and High Thrust Chemical Propellant Launch Vehicles: SLS and Falcon 9, In Space Assembly Description: This habitat has a 3D Cross structure and is capable of providing 1g of Earth s gravity. Weighing in at approximately 400 Metric Tons this space transit vehicle brings a crew of six to multiple journeys to Mars and journeys to the Moon, Phobos, or Deimos prior to major resupply. It also has the capability to visit the surface of these bodies with a surface habitat that can safely land and ascend.

4 Mission Requirements Delivery to Low Earth Orbit Launch Vehicles: SLS and Falcon 9 Must launch in sections, assembly required Arrive at 6778 km LEO Delta V required: 10 km/s Assemble habitat and propulsion systems Leave LEO for:» GTO» Earth Surface *NOTE* Future resupply missions occur at LEO

5 Mission Requirements Assembly of Craft Astronauts required to assemble habitat Will need robotic arm Habitat will be launched in pieces Start with center Module (SLS 1B, 8.4M Long Fairing) Multiple SLS or Falcon 9 launches to send separate truss/module/solar array structures Last, connect modules and solar array system Note: Solar Arrays, transfer tubes, radiators will be in stowed form during launch

6 Mission Requirements Assembly of Craft Launch Vehicle #Launches Central Module SLS 1B 8.4M PFL Long 1 Artificial Gravity Modules SLS 1B 8.4M PFL Long 4 Artificial Gravity Structural Members SLS 1B 8.4M PFL Long 1 EVA Airlock, Folded Solar Arrays, Transfer Tubes SLS 1B 8.4M PFL Long 1 Lander/Habitat, Folded Radiators, Comms Arrays SLS 1B 8.4M PFL Long 1 Propulsion Module SLS 1B 8.4M PFL Long 1 Supply (Food, Materials, Propellant, Etc) Falcon 9 3 Crew Launch Falcon 9 1 Part(s)

7 Mass Estimates Solar Panels: 73 MT Structure: 300 MT Food (6 people,15 yr): 28 MT Water (6 people, 15 yr): 94 MT Surface Habitat: 40 MT Batteries: 7 MT HIAD: 10 MT Life Support Systems: 10 MT Air Supplies: 30 MT

8 Launch Cost Estimates Falcon 9: $62-92 million LEO: 22,800-63,800 kg GTO: 8,300-26,700 kg PL to Mars: 4,020-16,800 kg SLS: $ million LEO: 70, ,000 kg GTO: ~40,000 kg Need 9 SLS Launches, 4 Falcon 9 Total Launch Costs: $ million *$ per launch

9 Mission Requirements Delivery to Earth Transfer Orbit Leave: 6788 km LEO Arrive: km GTO Delta V required: 3.85 km/s Low Thrust X3 Hall Thruster Trajectory Leave GTO for:» Low Mars Orbit (LMO)» Low Lunar Orbit (LLO)» LEO resupply mission

10 Design Reference Missions Locations: orbits & surfaces of Moon, Mars, Phobos, Deimos, and Earth Crew Size: 6 Duration: 15 years Crew Rotation Interval: 5 years Resupply Interval: 5 years

11 Mission Operations Architecture Mars/Lunar Landing

12 Mission Requirements Delivery to Low Lunar Orbit Leave: km Earth GTO Arrive: km LLO Low thrust electric propulsion used Delta V: 3.92 km/s Time of flight: days Leave LLO for:» Lunar Surface» Earth GTO

13 Mission Requirements Lunar Surface Emplacement no atmosphere requires only thrusters for landing

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15 Mission Requirements Delivery to Low Mars Orbit Leave: km Earth GTO Arrive: km LMO Low thrust electric propulsion used Delta V required: km/s Time of flight: 733 days Leave LMO for:» Mars Surface» Low Phobos Orbit (LPO)» Low Deimos Orbit (LDO)» Earth GTO

16 Mission Requirements Mars Surface Emplacement Delta V: 5.21 km/s Aerocapture to 500 km circular orbit via 13 m HIAD Hypersonic deceleration via 11 m HIAD Subsonic powered descent Powered ascent stage in ascent spacecraft

17 Mission Requirements Arrival at Mars

18 Mission Requirements Trade Study Precision Complexity Surface Contamination Mass Weighted Totals HIAD Rigid Aeroshell Supersonic Retro-Propulsion Weighting

19 Mission Requirements Approaches to Landing on Mars Rigid Aeroshell: A rigid heat shield used for aerocapture and hypersonic entry deceleration. Hypersonic Inflatable Aerodynamic Decelerators (HIAD): A deployable aeroshell that consists of an inflatable structure that maintains its shape. Allows a larger aeroshell to be stowed inside launch shroud. Supersonic Retro-Propulsion: Propulsion system used to decelerate a supersonic spacecraft.

20 Mission Requirements Difficulties for Landing on Mars Martian atmosphere Dense enough to create significant heating Not dense enough to decelerate the habitat sufficiently Lack of a complete knowledge of the atmosphere Density variations, aerodynamics, and winds Past successful landings on Mars have relied on Viking EDL technologies that are capable of delivering payloads of 0.9 t. Need new technologies to land habitat with mass ranging of 30 t to as much as 80 t

21 Mission Operations Architecture Phobos/Deimos Landing

22 Mission Requirements Delivery to Low Phobos Orbit Leave: km LMO Arrive: 40 km LPO Delta V required: km/s Time of flight: 3.8 hours Leave LPO for:» Phobos Surface» LMO

23 Mission Requirements Delivery to Low Deimos Orbit Leave: km LMO Arrive: 20 km LDO Delta V required: 1.03 km/s Time of flight: 15.1 hours Leave LDO for:» Deimos Surface» LMO

24 Mission Requirements Phobos and Deimos Surface Emplacement no atmosphere Requires only thrusters for landing

25 Mission Operations Architecture Refuel/Rotation Rendezvous

26 Mission Requirements Two Resupply Missions Year 5 & 10 Food/water/ toiletries Propellent Life support consumables Materials for repairs Replacements New Crew *Year 10 include extra propellant to safely return to Earth surface dv 10 km/s*

27 Mission Requirements Crew Rotation The Crew will be rotated every 5 years Occurs the same time as resupply mission After 1 trip to Mars» TOF to Mars 2 yrs» Max surface mission 1 yr» TOF to Earth 2 years» Mars trip can be shortened by adding thrusters or assisting with high thrust bursts

28 Habitat Configuration Approach to Artificial Gravity Up to 1g 30 m. radius of rotation 5.48 rpm rotation Will need extensive astronaut vetting to best ensure tolerance to this rotation rate as 3 rpm ~95% population and 7 rpm ~Max adaptable Rotation torques reacted out by CMG The 1g requirement makes the entire architecture obscenely large & massive Real mission may be better suited for partial (Mars level) gravity.

29 Habitat Configuration Approach to Artificial Gravity Circled Modules See up to 1g Telescoping transfer tubes to get from main Spine to each module.

30 Habitat Configuration Docking Interfaces NASA Docking Adapter Based on International Docking Standard 4 on Craft (2 used to link Spine Modules), 2 Usable (1 nominally for Lander Habitat, 1 for Crew craft)

31 Habitat Configuration Photovoltaic Arrays ISS system: 100 KW/2000 sq meter at LEO OTOS Habitat: 100 KW OTOS Propulsion: 50 KW Total OTOS Power: 150 KW Area: 6000 sq meters using ISS panels» 150 KW at Mars» 300 KW at Earth Mars Solar Strength is 50% of Earth

32 Habitat Configuration Photovoltaic Arrays

33 Power Required Based on ISS Panels

34 Habitat Configuration Batteries Lithium Ion Batteries for non sunlit periods» Total of 36 needed Compared to Nickel Hydrogen battery: It has shorter design life» No Issue b/c resupply missions Has higher power output Smaller (195 kg each) More power efficient Cheaper Li-Batteries have overcharging problems Charged by Solar Panels

35 Habitat Configuration Electrical System

36 Propulsion System X3 Xenon Gas Hall Thruster 2 10 m x 1 m radiators for Propulsion & ECLSS Black Box Chemical Propulsion System

37 Propellent Mass Estimates Earth to Mars (RT): 166 kg Xenon Earth to Moon (RT): 62.8 kg Xenon Mars to Phobos (RT): 7.24 kg Xenon Mars to Deimos (RT): kg Xenon Moon Landing/Ascent: 223 kg Mars Landing/Ascent: kg Phobos Landing/Ascent: 20 kg Deimos Landing/Ascent: 74 kg M0,space transit 400 MT M0,surface 40 MT *RT=round trip

38 CONOPS Crew Necessities Toiletries: toothpaste (potentially powdered or tabs to minimize mass), shaving cream, etc. Food for 15 years Workout equipment: Bicycle Treadmill Advanced Resistive Exercise Device Windows

39 CONOPS Typical Day for the Crew 06:00 Alarm wakes up the crew. Get dressed, shave, brush teeth, eat breakfast, and read messages or the news. 07:30 Crew meets to discuss what needs to be done that day. 08:00 Crew prepares for work and by reviewing procedures and gathering materials. 08:30 Crew performs science experiments, maintenance, mission preparations, environmental sampling, etc. 13:00 Crew eats lunch. 14:00 Crew continues working and, in intervals, completes mandatory 2 hours of daily exercise. 19:00 Crew meets to discuss what has been completed and what needs to be continued tomorrow. 19:30 Crew eats dinner, cleans, and has personal time. 21:30 Crew s bedtime to complete 8+ hours of sleep.

40 Module Definitions Standard modules measure 7 m diameter 13 m length Each standard module has 4x 1.5 m diameter windows EVA Airlock 7 m diameter 4 m lenght

41 Module 1 Floor Plan Hot Water Heater Food Heater Food Prep Area Cold Storage Ambient Storage Sink Ladder Dining/Meeting Table Greenhouse Lounge

42 Module 2 Floor Plan Bed 2 Bed 3 Bed 4 Bed 5 Storage Storage Ladder Sink 1 Shower 1 Bed 6 Sink 2 Storage Toilet 1 Toilet 1 Shower 2 Bed 1

43 Module 3 Floor Plan Exercise Equipment and Storage Resistive Exercise Device Treadmills Bicycle Ladder Biology Laboratory Medical Bay

44 Module 4 Floor Plan COM Station Avionics ECLSS Geology Laboratory Ladder Main Workstation Educational Activities Station

45 Module 5 and 6 Module 5 Central Module Connects modules 1, 2, 3, 4, and 6 2 Docking ports, 1 nominally connected to 6 and 1 free Used for storage Module 6 Connects to Module 5, Lander/Habitat, EVA airlock module Zero g experiments Sensors and avionics banks More Storage

46 Habitat Configuration Surface Habitat Internal Layout

47 Habitat Configuration Communication Use DSN to Communicate X-Band 8GHz Ka-Band 32 GHz 2 UHF 2m Dish High Gain Antennas (MRO Style) 2 Low Gain S-Band Antennas (Voyager Style)

48 Life Support CO2 Scrubbing Use a combination of Russian Vozdukh & US Carbon Dioxide Removal Assembly Both use a combination of desiccant beds and absorption beds The desiccant beds before and after the absorption to dehydrate and rehydrate the air. The absorption beds take the CO2 from the air and when the reach full capacity it is replaced with the other while it is heated and allowed to vacuum desorbed into space. Lithium hydroxide canister will also be kept in reserve in order to supplement the scrubbers during maintenance.

49 Life Support Water Recycling The water processing system using a rotating distiller to compensate for times when there is a lack of gravity. Urine is processed and sent to the water processor along with other wastewater and excess water from the air. The processor then removes free gases and solid materials, and other impurities using multi-filtration beds and a catalytic reactor. The output is then checked for electrical conductivity to determine purity.

50 Life Support O2 Regeneration Will use the Oxygen Generation System from the ISS. Electrolysis of water from the water processing system produces oxygen Excess hydrogen vented into space. It can produce between 2.3 to 9 kg of oxygen per day. Oxygen canisters will be held in reserve for use during repairs.

51 Life Support O2 and N2 Supplies Would use liquid storage for O2 and N2 contingency supplies. This would mean.3-.7kg tank per kg O2. It would also require about 210 kj/kg to vaporize. 30 MT required for tanks and gases.

52 Life Support Thermal Control The Active Thermal Control System from the ISS will be used to maintain the temperature for the crew and equipment. Heating is not needed due to the excess heat generated from the equipment. Excess heat is collected by ammonia and then transferred to heat exchangers which output the heat to space. There will be two separate loops such that one can continue to transport the heat if the other is damaged and needs repairs.

53 Habitat Configuration Thermal Radiators The thermal radiators will have tubes of ammonia that transfer the heat to radiator panels. These panels will then radiate the heat into space. Up to 70 kw can be rejected at max capacity.

54 Life Support Air Circulation There will be a ventilation system that connects the various modules to the thermal controls system, the carbon dioxide and oxygen systems. This system will ensure an even distribution temperature and composition. Personal fans will be available if the crew spends extended time immobile.

55 Life Support Atmosphere Design The atmosphere will be 21% O2 and 79% N2. Temperature will be kept between 72 and 78 degrees Fahrenheit. Humidity will be between 40 and 70 percent.

56 Life Support Diagram

57 Contingency Accommodations Fire Survival Design High temperature insulation on chemical canisters Testing objects for flammability in a special test chamber before putting on-board the habitat Smoke detectors in the ventilation systems Train crew to act accordingly in the event of a fire (procedure similar to that of the ISS): First, turn off ventilation system to slow the spread of the fire Next, shut off power to the affected unit Last, use on-board fire extinguishers to put out the flames

58 Contingency Accommodations Depressurization Survival Design Built-in software will detect the rapid depressurization of the habitat Also detects the location of the leak Crew will be trained to isolate the leak in a timely fashion by shutting the appropriate airlocks

59 Plans for Experimental Testing Solar arrays redesign to reduce mass/area Design/Experiment on thrusters to create more thrust/ lower time of flight Ground tests and flight tests of HIAD Establish structural performance limits Material testing of high-strength, lightweight, inflatable materials capable of withstanding high temperatures Life-size habitat mock up Test maneuverability of design Conduct Human Factors Testing

60 Glamour Shots

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64 Glamour Shots

65 References Solar Radiation Earth/Mars Power of ISS Price Per kg refuel ISS mission Robotic refueling mission: Estimate of cost of falcon 9 launch capabilities: Explanations of space flights: Falcon 9 overview Wikipedia: Propulsion Textbook: Rocket Propulsion Elements 9th Edition by George Sutton & Oscar Biblarz MMOD Layer Design

66 References Lithium Ion and Nickel Hydrogen Batteries Carbon Dioxide Scrubbing Oxygen Generation Thermal Control Mars EDL EDL Technologies HIAD Technology