Week 11 Thursday (3/24)

Transcription

1 Week 11 Thursday (3/24) Courtney McManus

2 Schedule for the day Project Vision ideas! Presentations! Lecture!

3 Project Vision Emblem T-shirt, vest, etc ideas Would anyone like to be point person for this? McManus, Courtney Project Manager

4 Section 1 Presentation Schedule Time Presenter Group 8:40 Courtney McManus PM 1 8:45 Alexander Roth Aero 2 8:51 Austin Hasse Aero 3 8:57 David Schafer Att/Con 4 9:03 Paul Frakes Att/Con 5 9:09 Sarah Jo De Fini Comm BREAK for 1 hour (change rooms) 6 10:35 Trieste Signorino MisDes 7 10:41 Megan Sanders Mis Des 8 10:47 Drew Crenwelge Power 9 10:53 Elle Stephan Power BREAK 10 11:10 Jared Dietrich Prop 11 11:16 David Wyantt Prop 12 11:22 Michael Hill Prop 13 11:28 Zachary Richardson HF BREAK 14 11:45 Ben Stirgwolt HF 15 11:51 Andrew Curtiss StrcThrm 16 11:57 Kim Madden StrcThrm

5 Alexander Roth : Week 10 Presentations Technical Groups: Aerodynamics CAD Tasks Accomplished: Roth, Alexander Vehicle Groups: CTV Crew Capsule Crew Launch Vehicle Cargo Launch Vehicle Fitting all the CTV s components into Ares V payload shrouds Pictorial overview of the CTV s configuration throughout the mission DISCLAIMER FOR ALL SLIDES: CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders. Aerodynamics & CAD

6 Step 1: Launching CTV Total Launches for CTV = 7 1 for Chassis and Crew Cabin 3 for Secondary Tanks 3 for Primary Tanks Roth, Alexander Aerodynamics & CAD

7 Step 1: Launching CTV Chassis & Crew Cabin (1x) Primary Tanks [Dark Grey Frame] (3x) Roth, Alexander Secondary Tanks (for Earth Departure) [Tan Frame] (3x) Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

8 Step 2: CTV Built in LEO (aka: Geocentric Apogee Raise) Final configuration with Primary and Secondary tanks attached every-other S P P S P S S P P S Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

9 Step 3: Crew Arrival Crew Cabin lowers slightly so Capsule can dock unrestricted Capsule Docks to side of Crew Cabin (only temporarily) to transfer astronauts Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

10 Step 3: Crew Arrival Capsule then moves autonomously to top of CTV for parking Capsule remains there until earth aerocapture and reentry Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

11 Step 4: Earth Departure All propellant in Secondary tanks is used on a burn Empty Secondary tanks are then detached and discarded Roth, Alexander Aerodynamics & CAD

12 Step 5: Artificial Gravity to Ceres Tether fully extended to 84.98m (1 kwan) Crew Cabin rotates about the tanks (which act as a center counter weight) Radiator panels opened to cool reactor Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

13 Step 6: Ceres Orbit Insertion Tether retracted back for engine burns (crew cabin hooks back into rails for stability) Radiator panels closed and folded for engine burns Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

14 Step 7: Ceres Descent & Hover Hovering on Ceres requires only the small pink Ceres Regime motors Size difference compared to Kick motors shown below Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

15 Step 8: Artificial Gravity from Ceres Same configuration as in Step 5, except the CTV is traveling back to Earth Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

16 Step 9: Earth Aerocapture CTV configuration as it approaches Earth Capsule releases (shown next slide) CTV deploys ballute for aerocapture at Earth (but stays in LEO) Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

17 Step 10: End of Life (Capsule) Capsule reenters atmosphere and splashes down back on Earth Crew returns back home after long Ceres mission Roth, Alexander Aerodynamics & CAD CAD Models Combined Together by Alexander Roth Individual CAD Models Created by: Trieste Signorino, Brendon White, Drew Crenwelge, Austin Hasse, Michael Hill, Jared Dietrich, & Megan Sanders.

18 Step 10: End of Life (CTV) CTV stays in LEO Maintains ability to be reused Roth, Alexander Aerodynamics & CAD

19 Close-ups of Smaller Items Attached to the CTV MPD s attached to tethers, and can move freely along them Capsule docking port for parking Tether spindle for Crew Cabin Reactor mounting bracket near the Capsule parking area Roth, Alexander Aerodynamics & CAD

20 Close-ups of Smaller Items Attached to the CTV Large Telescope (for receiving) mounted on top of the Attic Small Telescope (for transmitting) mounted on top of the Attic Phased Array mounted on the top mount near the Capsule parking spot Roth, Alexander Aerodynamics & CAD

21 Austin Hasse : Final Presentation Job Description 3/ 24 / 2011 Aerodynamics Group Leader CTV Group Member Crew Capsule Group Member Tasks Final Designs of Damocles Ballute, ARC Ballute, and ARC Re-entry Parachute CATIA Models for Damocles Ballute, ARC Ballute, and ARC Re-entry Parachute Hasse, Austin Aerodynamics

22 Damocles Aerocapture Ballute Damocles Ballute CATIA model by Austin Hasse Damocles Vehicle Courtesy of Alex Roth Hasse, Austin Aerodynamics

23 Damocles Ballute Specifications Ballute Mass Ballute Spec. Ballute Packed Volume Ballute Tank Mass Ballute Tank Volume Tether Mass Tether Volume T 1.97 m^ T 1.05 m^ T 0.25 m^3 Value Total Damocles Ballute System Mass Volume T 3.27 m^3 Value Hasse, Austin Aerodynamics

24 ARC Aerocapture Ballute ARC Ballute CATIA model by Austin Hasse ARC Vehicle Courtesy of Alex Roth Hasse, Austin Aerodynamics

25 ARC Ballute Specifications Ballute Spec. Ballute Mass Ballute Volume Ballute Tank Mass Ballute Tank Volume Tether Mass Tether Volume kg m^ kg m^ kg m^3 Value Total ARC Ballute System Value Mass Volume m^3 Hasse, Austin Aerodynamics

26 Parachute Design Parachute Spec. Parachute Radius Packed Volume (3) Mass (3) Value m 0.47 m ^ T ARC Parachute CATIA model by Austin Hasse ARC Vehicle Courtesy of Alex Roth Hasse, Austin Aerodynamics

27 : Week 11 Presentations Vehicle Groups: - Communication Satellites - Rovers Schafer, David Tasks Completed: - STV inertia coding - Relay satellite saturation avoidance ADCS

28 Halo Satellites Ecco 1 and 2 Environmental forces Environmental Torques Positioning system Force [N] Torque [Nm] Mass [kg] Power [kw] Volume [m 3 ] CMG system Propulsion system NA Propellant Schafer, David ADCS

29 Ecco 1 and 2 Saturation Satellite passes out of phase every 4.5 hours Takes under 2.7 hours to bring CMG s back to 0% saturation Done while satellite is out of phase with mission crew Controlled by computer logic Perturbs a single gyro to force others to counteract torque Would cause loss in communications if done while in phase with mission crew Schafer, David ADCS

30 Relay Satellite Ecco Base Environmental forces Environmental Torques Positioning system Force [N] Torque [Nm] Mass [kg] Power [kw] Volume [m 3 ] CMG system Reaction Wheel system Propulsion system NA Propellant Schafer, David ADCS

31 Ecco Base Saturation Dual attitude control system CMG s operate alone until near saturation Computer logic perturbs a gyro as the rest of the gyros torque through their saturation point Perturbed gyro forces gyros to torque against each other and pull CMG system out of saturation Reaction wheels pick up control of full system Correct for satellite perturbations from outside and inside (CMG) torques Reaction wheels shut down after saturation avoided Schafer, David ADCS

32 Rescue Rover Control Position/attitude found using Motion Reference Units Inertial measurements catalogued with dual computer system 4 separate gimbaled 2.5 kn thrusters (2 DOF) Requires around 100 kg of propellant for full roundtrip (attitude control only) ADCS thrusters Schafer, David ADCS

33 Paul Frakes : Week 10 Presentations ADCS for STVs (Cassiopeia and Cepheus) and crew capsule (ARC) Environmental space forces and torques on STVs and ARC Solar radiation, solar wind, Van Allen belt particle collision, gravity gradient, atmospheric drag Steering law for STVs Comm. dish pointing on STVs ARC docking and additional maneuvers Frakes, Paul Attitude Control (ADCS)

34 STV Attitude Determination and Control Determination: Motion Reference Unit (inertial) and computer system Control: 6 motors per vehicle, gimbaled on Canfield joints Correct for: Misalignment/offset during Earth kick Environmental forces and torques: Van Allen belt particle collisions, atmospheric drag, solar radiation, solar wind, gravity gradient Steering law Frakes, Paul Attitude Determination and Control Systems

35 STV Attitude Control Notes: Thrust in the direction of velocity Each STV represented by model as shown right (with 6 strap-on shrouds, not 4) ACS thrusters coupled on 3 shrouds No spin (3-axis stabilization) ADCS mass required: STV1: 2342 kg STV2: 2573 kg Graphic courtesy Jared Dietrich Frakes, Paul Attitude Determination and Control Systems

36 STV Comm. Dish Pointing / Crew Capsule RCS Propose using Canfield joint for both vehicles 3 DoF system enabling full hemispherical pointing TRL ~4 Proposed by NASA for Reaction Control System on Orion Crew Capsule Reduces number of required RCS thrusters on capsule Using one type of gimbal reduces overall system complexity, development cost Frakes, Paul Attitude Determination and Control Systems

37 Crew Capsule Maneuvers Initial docking Drop into slightly lower LEO orbit to chase CTV, raise orbit to dock Four (4) near-ctv maneuvers Before Earth departure to make CTV nearly axisymmetric Upon Ceres arrival for rock storage access Before Ceres departure (again for symmetry) Upon Earth arrival to pick up crew Separation from CTV for Earth entry Frakes, Paul Attitude Determination and Control Systems

38 Crew Capsule Maneuvers Near-CTV 1, 3 2, 4 1. Before Earth departure to make CTV nearly axisymmetric 2. Upon Ceres arrival for rock storage access 3. Before Ceres departure (again for symmetry) 4. Upon Earth arrival to pick up crew CAD model courtesy Alex Roth Frakes, Paul Attitude Determination and Control Systems

39 Sarah Jo DeFini : Week 11 Presentations Vehicle Groups: Supply Transfer Vehicle ISPP Stations This week s focus: Final Design Presentation Summaries DeFini, Sarah Jo Communication

40 STV Communications Cassiopeia and Cepheus Tracking, Telemetry, and Command Ceres Monitors, records, and sends up to 24 health and status signals Transmits to TDRSS (15 m dish) once a month Maximum transmitting distance: 563,300,000 km Earth Drawing not to scale (Sarah Jo DeFini) Pointing requirement: within 2 degrees of target Operating Frequency: 26.5 GHz (S-band) Data Collection Rate: 368 bps Antenna efficiency: 0.7 DeFini, Sarah Jo Communications

41 STV Comm Mass, Power, Volume Telemetry Dish Mass = 1.7 kg Energy = 8.5 kw for 1 hour once a month for 17 months = 145 kwh 18 months = 153 kwh Volume = m^3 General Processing Computer Mass = 29 kg Power = 0.55 kw Volume = m^3 DeFini, Sarah Jo Communications

42 ISPP Station Communications APES 1&2 Telemetry and Low-Quality Visual o Station-Satellite Storage Tanks RF dish (1 m diameter) Route through CTV when available ISPP Station o Station-Tanks RF Dish (10 cm diameter) Harvester Harvester o Station-Harvester: Wireless Communication Coverage Area ~150 m Drawing not to scale (Sarah Jo DeFini) DeFini, Sarah Jo Communication

43 ISPP Comm Mass, Power, Volume RF Dish Tanks Mass: 0.18 kg Power: 5 W Volume: 0.05 m^3 (folded) RF Dish Station Mass: 0.42 kg Power: 1.6 kw Volume: <0.05 m^3 (folded) Wireless Antennas Mass: kg each 1 ISPP + 3 harvesters = 0.14 kg Power: 0.1 W each 1 ISPP + 3 harvesters = 0.4 W Volume: m^3 each 1 ISPP + 3 harvesters = m^3 DeFini, Sarah Jo Communication

44 See you downstairs at 10:30!!

45 : Week 10 Presentations Vehicle Groups: - CTV Launch Vehicles (Lead) - CTV Transfer Vehicle Signorino, Trieste Mission Design

46 CTV Launch Vehicles Launch 1: CTV Payload Ares V (1) Mass = 131,033 kg Volume = 412 m 3 Launch 2-4: Primary Tanks Ares V (3) Mass = 144, kg Volume = m 3 Launch 5-7: Secondary Tanks Ares V (3) Mass = 187,250 kg Volume = 688 m 3 Launch 8 : Crew Ares I (1) Mass = kg Volume = m 3 * Using extended shroud for Ares V CTV Launch Vehicles

47 CTV Outbound Trajectory Perform V from LEO V = 4.76 km/s m prop = 728,716 kg Turn on MPD Thrusters Thrust in direction of velocity vector with T = 33N TOF is 1.4 years m prop = 29,842 kg Perform V at Ceres to enter LCO V = 2.18 km/s m prop = 134,432.5 kg Signorino, Trieste Mission Design

48 CTV Return Trajectory Perform V for Ceres Departure V = 2.91 km/s m prop = 203,000 kg Turn on MPD Thrusters Thrust with 20N in direction of velocity TOF = 1.25 years m prop = 17,000 kg V = 7.89 km/s Signorino, Trieste Mission Design

49 Food Ops Since we got so far ahead this morning.we ll start presentations at 10:40 Get food! Thanks, Mission Design Group!

50 Tasks Accomplished: Earth Trailing Relay Satellite Supply Launch Vehicle Responsibilities: Mission Design - Member Supply Launch Vehicle Group Group Lead Rover Group Member Ascent/Re-entry Group Member Sanders, Megan Mission Design

51 Relay Satellite Transfer Orbit Picture by Megan Sanders Sanders, Megan Mission Design

52 Results Delta V (km/s) Escaping Earth Entering Transfer Trajectory Leaving Transfer Trajectory Total transfer angle Will end up 90 behind earth Will take half a year to get in place Sanders, Megan Mission Design

53 Drew Crenwelge 24 March 2011 Power Group: Power Budget CTV Radiation Shielding CTV Radiator Sizing -- CTV Nuclear Reactor -- CTV Crenwelge, Drew Power Group

54 CTV Power Budget Area Component Power Requirement (kw) Crew Cabin Food system 17 Recreation 2 House Cleaning 1 Maintenance System 2 Health Care system 2 Personal Comm. Devices 1 Air Filtration/Recycling System 16 Air Circulation & Ducting 2 Communication Dish/System 11 Freezer(s) 2 Hydroponics 2 Water Regeneration System 0.23 Center Low Thrust Motors 1960 Counter Weight Alternate Control Devices (CMG's) 0.6 Crenwelge, Drew Power Group

55 Radiation Shielding W Core LiH By Drew Crenwelge Radiation Shielding Specifications Thickness 1 st Layer of LiH m Tungsten Layer m 2 nd Layer of LiH m Mass Lithium Hydride 1055 kg Tungsten 2629 kg Total 3685 kg Lithium Hydride Tungsten Neutron Shielding Gamma Shielding Crenwelge, Drew Power Group

56 Heat Rejection - Radiators Carbon-Carbon Radiator Panels Coolant = Liquid Sodium Potassium Parameters Value Thermal Output 8.4 MW Solar Flux ~1400 W Carbon-Carbon Emissivity.85 Stefan-Boltzmann Constant e-8 W m^-2 K^-4 Coolant Temperature 890 K Environmental Temperature 167 K Radiator Area 278 m^2 Crenwelge, Drew Power Group

57 Nuclear Reactor Power Source Power (kwe) Total Mass (kg) PMAD Heat Reject Power Conv. HSHX Shield (LiH/W) Reactor Specific Power (kg/kwe) Width (m) 1.8 Height (m) 1.55 Volume (m3) ~5.0 Crenwelge, Drew By Drew Crenwelge Power Group

58 Elle Stephan 24 March 2011 Communications Satellite Vehicle Lead ISPP Harvester Design Stephan, Elle Power

59 Ceres Orbiting Satellites Mass [kg] Power Generated [kw] Area [m²] Solar Array * Per satellite Use of coil-able beam to allow for compact storage during transfer Stephan, Elle Power

60 ISPP Harvesters Mass [kg] Power [W] Volume [m^3] *Based on 24hr day per harvester (4 trips per day) Dimensions Length [m] 2.75 Height [m] 1.5 Depth [m] 1.75 *Excluding rocker-bogie drive system (6 total wheels) Stephan, Elle Power

61 Reconvene at 10:55

62 Dietrich, Jared N Propulsion 62

63 Supply Transfer Vehicle LH2 KICK MOTOR LO2 Quantity Mass 6 (3 per STV) 7,967 kg Power 0 Ceres Volume Thrust m^3 1,500 kn Isp sec Kick Kick Kick 4.15 m 2.14 m Dietrich, Jared N Propulsion 63

64 Supply Transfer Vehicle LH2 LO2 Ceres 2.2 m Ceres Regime Motor Quantity 2 (1 per STV) Mass kg Power 0 Volume m^3 Thrust 100 kn Isp 452 sec 1.55 m Dietrich, Jared N Propulsion 64

65 Supply Transfer Vehicle Power required determined by Thrust and Isp. Total Power = 2.45 MW Total Mass = 3,984 kg Quantity Mass Power Volume Thrust Isp MPD THRUSTERS 6 (3 per STV) 1,992 kg MW m^3 25 N 5000 sec Dietrich, Jared N Propulsion 65

66 Supply Transfer Vehicle Configuration of each STV: 3 MPDTs 1 Ceres Regime Motor 3 Kick Motors 1 Skirt Mass savings after Kick Motor jettison: 10,991 kg STV Configuration, Kick Motor Jettison Jared Dietrich Dietrich, Jared N Propulsion 66

67 Supply Launch Vehicle Ares V: Payload Mass = 188 T Usable Volume = 1,410 m^3 Cost = $1,826/kg Total Cost for STV $1.94 Billion Wet Mass = MT Dietrich, Jared N Supply Launch Vehicle Jared Dietrich Propulsion 67

68 David Wyant March 24, 2011 Technical Group: Propulsion Vehicle Groups: Exploration Rovers Rescue Rover Crew Capsule Rover Propulsion Overview Wyant, David Propulsion

69 Drive Train & Suspension Exploration Rover Mass (kg) Power (kw) Volume (m 3 ) Engine Transmissions N/A Chassis N/A Suspension N/A N/A Wheels N/A Exploration Rover Stats Dry mass: 11,502.6 kg Power: kw Volume: m 3 Nominal Operating Speed of 14.4 kmh (4 m/s) Wyant, David Propulsion

70 Rescue Rover Engine Sizing Engine Mass (kg) Power (kw) Volume (m 3 ) Main Thruster N/A ADCS Thrusters 28.0 N/A Maneuvering Motors Main engine 6 kn Thrust 10:1 Throttling Ratio Propellant Mass: kg Maneuvering Motors Wheels to maneuver for airlock docking Nominal Speed of 7.2 kmh (2 m/s) Wyant, David Propulsion

71 Michael Hill : Final Presentation Team Tasks: Propulsion Group Leader CTV Propulsion Hill, Michael Propulsion

72 Kick Engine LH 2 /LOX F = 1,500 Isp = sec T/W = System Mass (kg) / Engine Combustion Chamber Nozzle Injector Feed Cooling O 2 Turbomachinery H 2 Turbomachinery 5.19 TOTAL: Michael Hill Hill, Michael Propulsion

73 Spin-up/Attitude Engines Will use MMH/N2O4 engines (carry whole trip). 30 Isp = 328 sec Spin-up Propellant mass 1024 kg Attitude Control propellant mass [2] 392 kg - MMH mass 422 kg - MMH Tank Volume [3] m 3 - N2O4 mass 994 kg - N2O4 Tank Volume [3] m 3 Thrusters mass [4] 558 kg Hill, Michael Propulsion

74 Low Thrust Engine Magnetoplasma Dynamics (MPD) Thruster (4x) Isp = N Power Required = 490 kw/engine (Total = 1.96MW) System Engine 51.5 Power Processing Unit Mass (kg) / Engine TOTAL: 664 Michael Hill Hill, Michael Propulsion

75 Ceres Regime Engine (and FORCE) Require kn to kn Isp = sec sec T/W = System Mass (kg) / Engine Combustion Chamber 9.67 Nozzle 2.50 Injector 7.57 Feed Cooling O 2 Turbomachinery 1.27 H 2 Turbomachinery 4.65 TOTAL: Hill, Michael Propulsion Michael Hill

76 Zachary Richardson Week 11 Presentation: 3/23/2011 Group Lead: Human Factors & Science - Finalized ISPP Production - ISPP Facility Layout Tasks Accomplished: Finalized Electrolysis/Oven/Production rates for ISPP Finalized ISPP schematic design and components with the fellow ISPP group members Updated ISPP production values to fit mission timeline Helped ISPP group members with final tasks Richardson, Zachary Human Factors & Science

77 Total ISPP production, assumptions and origin of requirements Updated Total Production Values (for 1 ISPP station) Production Time (yrs) Production Time (days) 824 *Water extracted (T) **Hydrogen extracted (T) **Oxygen extracted (T) Note: Numbers are from various worst case *Stored scenarios at Ceres so these ambient values temp will (ice) most **Stored likely be in liquid reduced form Production values from the following sources: Rescue/Exp. Rovers Return and Transfer engines Life Support Assumptions: Rescue: 1 trip per week Rovers expend 100% of water and oxygen /trip Low Thrust and Ceres Kick are case where final V arriving at Earth = 7.89 km/s Production values include 20% fudge factor for extra supply Richardson, Zachary Human Factors & Science

78 ISPP Facility (Mass/Power/Volume) Specifications of Single ISPP Facility Component Mass (T) Power (kw) Nuclear Power Plant (w/radiators) Volume (m^3) 12.5 N/A 23.9 Oven 3.82 N/A* 43.9 Collection Bin & Conveyor Belt System Assumptions: *Oven heated by Reactor thermal energy. ** Hydrogen and Oxygen Tanks are being reused from STV Electrolysis Pipes/Condensers/Pumps Computer and Communications Storage Tanks ** Harvesters TOTALS: Richardson, Zachary Human Factors & Science

79 ISPP Layout Nuclear Power Plant, Oven, and Electrolizer are placed inside core STV unit (Ares-V cargo bay) STV Hydrogen and Oxygen tanks are reused for ISPP storage Collection Bin and Input/Output Conveyor Belts are deployed upon arrival Harvesters are placed in exterior STV cargo shrouds and begin regolith collection upon arrival Richardson, Zachary Human Factors & Science

80 Reconvene at 11:20

81 Ben Stirgwolt : Final Presentation Human Factors & Science: Artificial Gravity Radiation Sources & Limitations Hydroponics Experiments & Science Equipment Rovers Stirgwolt, Ben Human Factors & Science

82 Rotational Radius, R (m) Artificial Gravity 1000 Human Comfort Zone From a Human Factors perspective: 100 Comfortable, 5 of 5 researchers Comfortable, 4 of 5 researchers Comfortable, 3 of 5 researchers Angular Velocity, Ω (rpm) Optimal Ω = 2.0 rpm R = m Possible Ω = 3.0 rpm R = m Probably Not Ω = 4.0 rpm R = m Figure based on Hall, Ref. 1 Stirgwolt, Ben Human Factors & Science

83 Radiation Sources Radiation Source Galactic Cosmic Radiation (GCR) Solar Particle Event (SPE) Trapped Radiation Manmade Sources (i.e. radioisotropic power generators) Amount (Sieverts SV) 0.60 Sv/year 4.50 Sv/day 5.00E-4 Sv/day 0.05 Sv/year Annual Exposure Limit (Sv) Blood forming organs Eyes Skin Values based on Spaceflight Radiation Health Program at JSC, Ref. 2 Stirgwolt, Ben Human Factors & Science

84 Hydroponics Photo by: Ben Stirgwolt Produces 5% of daily required food Utilizes LEDs to keep temperature low & low power required Plant transpiration dehumidified and then recycled System serves as redundancy for environmental control system Crop selection based on nutritional content and variety: Strawberry Chard Tomato Green onion Radish Sweet potato Stirgwolt, Ben Human Factors & Science

85 Science & Experimental Rover Equipment & Experiments o Heat flow probe o Electromagnetic sounder o Thermal emission spectrometer o Alpha particle X-ray spectrometer o Microscope o Magnetic array o Rock abrasion tool o Panoramic cameras o Surface Electrical properties experiment o Seismic experiment o Meteorite experiment o Transverse gravimeter o Small research telescope o UV Astronomical telescope Ceres Surface Properties Physics & Astronomy Stirgwolt, Ben Human Factors & Science

86 Rovers Exploration Rover Sufficient room for crew of 2 for 7 days o Separate areas for navigation, sleep, experimentation 2 docking ports one on either side of rover 2 robotic arms fore & aft o Move regolith into storage containers o Rocks of interest examined on-site in glove-box Rescue Rover Capable of rescuing 4 astronauts o 2 medical beds & stocked with medical supplies o Capable of mission length of 1 day 2 docking ports one on either side of rover Cockpit of Exploration Rover Sketch by Ben Stirgwolt Stirgwolt, Ben Human Factors & Science

87 Color Schemes Selection of colors for common area of CTV Astronauts select their individual bedroom colors Summer Day Bunglehouse Blue Torchlight Loch Blue Social Butterfly Georgian Bay Bee Midday Denim Blue Sky Mass: 1.42 kg Volume: 1.18E-3 m 3 Power: 0.0 kw Stirgwolt, Ben Human Factors & Science

88 Andrew Curtiss Groups - Structures & Thermal - Crew Capsule - Supply Transfer Vehicle - Supply Launch Vehicle Accomplishments - STV Design/Configuration - Launch Vehicle Estimations - Crew Capsule Swivel Arm Design - STV module connector, manifest, hydrogen tankage, radiation shielding, thermal control system, landing gear design - Payload storage container/stv vessel design - Crew Capsule Capsule structural mass estimation, heat shield backing structure estimation

89 STV Landing Legs Design and Assumptions - Upper part contains spring mechanism to absorb landing impact up to 10 m/s - Lower part compresses into upper part - Landing dish allows stable landing on rough terrain - Leg pieces made from carbon fiber - Spring made from strengthened steel - Four legs on STV lander as seen in diagram Shock absorbing Lander legs Picture by: Andrew Curtiss

90 Landing Legs Mass Summary Component Material Mass (kg) Volume (m 3 ) Upper Leg Carbon Fiber Lower Leg Carbon Fiber Footpad Carbon Fiber Spring Strengthened Steel The combined mass of the 4 legs is: Mass = kg Volume =.1388 m 3 Power = 0 kw!!

91 STV Configuration Picture by: Andrew Curtiss

92 Kim Madden Week 11 Presentation, 3/24/11 - Structures & Thermal Control - Exploration and Rescue Rover - Group Lead

93 Thermal Control System Heat out due to colder temps on Ceres, space Heat in from heater, when needed Vehicle Heat in due to electronics, humans in vehicle Heat out via heat pumps and radiators Electronics Conducting Plate Radiators Heat Pump Picture by Kim Madden

94 Heater for Exploration Rover, CTV Heat pipe carries heat from power supply to rover Internal Combustion Engine for Rover Reactor for CTV Leads to small radiators inside vehicle 1 for Rover 10 for CTV, near air ducts Radiators can be opened or closed to let heat into vehicle at the crew members discretion Power Source Vehicle Radiator Picture by Kim Madden

95 Circular Cross Section of Exploration Rover 2.8 m Outside: Al, 1.5 cm thick -Doubles as radiation shielding, pressure vessel, and resists buckling 4.0 m Polyethylene,4cm Radiation shielding Floor: Al, 2 cm thick -Can hold 2/3 of HFS mass during launch 1.5 m Assumptions: -Accel at launch ~6g s 4.3 m

96 Circular Cross Section of Rescue Rover Outside: Al, 1.5 cm thick -Doubles as radiation shielding, pressure vessel, and resists buckling 2.4 m Polyethylene,4cm Radiation shielding Floor: Al, 2 cm thick -Can hold 2/3 of HFS mass during launch 3.0 m Assumptions: -Accel at launch ~6g s -Internal pressure = 1 atm 1 m 3.4 m

97 Windshields for Rovers For 2 Windshields Exploration Rescue Mass kg kg Structural Volume 0.58 m^ m^3 Internal Volume m^ m^3 Assumptions: -Made of Polycarbonate -1.5 cm thick -Weld Efficiency = 70% ½a a