Week 8 Thursday (3/3)

Week 8 Thursday (3/3) Courtney McManus

Today s Schedule Group Roll Call/Announcements Section 1 Presents Dr. Longuski shall impart wisdom upon us Group break-out/prepare for FDR C. McManus Project Manager

Final Design Review is next week! Thursday, March 10, 6-8 pm ARMS 1103 Format will be similar to CDR Each vehicle group presents Some technical groups present Everyone please try to make it Let me know if you absolutely cannot McManus, Courtney Project Manager

Schedule After Spring Break McManus, Courtney Project Manager

Time Presenter Group 8:40 Courtney McManus PM 1 8:45 Austin Hasse Aero 2 8:51 David Schafer Att/Con 3 8:57 Paul Frakes Att/Con 4 9:03 Sarah Jo De Fini Comm 5 9:09 Megan Sanders Mis Des ----------BREAK-------- 6 10:35 Trieste Signorino MisDes 7 10:41 Drew Crenwelge Power 8 10:47 Elle Stephan Power 9 10:53 Jared Dietrich Prop ----------BREAK-------- 10 11:10 David Wyant Prop 11 11:16 Michael Hill Prop 12 11:22 Zachary Richardson HF 13 11:28 Ben Stirgwolt HF ----------BREAK-------- 14 11:45 Andrew Curtiss StrcThrm 15 11:51 Kim Madden StrcThrm 16 11:57 Chris Luken 17 12:03 Alexander Roth

Austin Hasse : 4 th Presentation Job Description 3/ 3/ 2011 Aerodynamics Group Leader CTV Group Member Crew Capsule Group Member Tasks Parachute Sizing for Capsule Capsule Storage for Ballute, Tethers, Helium Tank, Parachute Preliminary CATIA Models for Ballute, Parachute Hasse, Austin Aerodynamics

Parachute Design Parachute Values Single Parachute Design by Austin Hasse Single Chute Radius = 22.32 m Packed Volume =.313 m^3 Mass = 359.8 kg (.36 T) Multi- Parachute Design by Austin Hasse Triple Shoot Radius = 15.78 m Pack Volume (3) =.47 m^3 Mass = 539.7kg (.54 T) Hasse, Austin Aerodynamics

Crew Capsule Storage Sizing Required Volume Total Height = 3.13 m Bottom radius = 1.99 m Ballute/Tethers Volume= 8.82 m^3 Height = 2.98 m Parachutes Volume = 0.47 m^3 Height =.04 m Helium Tank Volume = 1.13 m^3 Height =.11 m Section View of Ballute / Parachute Storage by Austin Hasse Hasse, Austin Aerodynamics

: Week 8 Presentations Vehicle Groups: - Communication Satellites - Rovers Schafer, David Tasks Completed: - Small Forces at Relay study - Rescue Rover ADCS study - CMG Sizing Code ADCS

Space Environmental Forces and Torques (Relay Satellite) (No Gravity) Environmental Forces (neglecting gravity) combine to 0.001433 N Maximum environmental torque (with current configuration) becomes 0.0430 Nm CMG set needed to counteract using 0.1 kw of energy has mass of just 1.2 kg and volume of 4.5x10-4 m 3 David Schafer Schafer, David ADCS

Rescue Rover Control 4 separate gimbaled thrusters (2 DOF) Requires around 135 kg of propellant for full roundtrip (attitude control only) Requires fairly powerful ADCS thrusters (about 2.5 kn) Working to reduce thruster force by increasing propellant mass and burn time ADCS thrusters Future Work: Add power variance to CMG code Finalize Rover thrusters Return to CTV and STV groups and pick up work Schafer, David ADCS

Paul Frakes : Week 8 Presentations Tasks Accomplished: STV Steering law: propellant mass requirement Comm. dish pointing Researched capsule docking problem Frakes, Paul Attitude Determination and Control Systems

STV Steering Law Assumptions: Time of flight = 2.77 yrs Thrust in the direction of velocity Model as shown right (use Parallel Axis Theorem to calculate I zz ) Thrust: 10 N I sp = 220 s No spin Propellant mass required: 484 kg Collaboration with Propulsion Group required to determine system mass Graphic courtesy Sonia Teran Frakes, Paul Attitude Determination and Control Systems

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 No mass/power/ volume specs found Frakes, Paul Attitude Determination and Control Systems

Sarah Jo DeFini : Week 8 Presentations Vehicle Groups: Supply Transfer Vehicle ISPP Stations This week s focus: Omni-directional link budget code DeFini, Sarah Jo Communication

ISPP Station Communication Telemetry and Low-Quality Visual Storage Tanks Harvester ISPP Station Harvester Station-Satellite RF dish Route through CTV when available Station-Tanks Data sent through cable Station-Harvester: Wireless Communication Coverage Area ~150 m DeFini, Sarah Jo Communication

Mass! Power! Volume! Wireless Antennas Mass: 0.034 kg each 1 ISPP + 3 harvesters = 0.14 kg Power: 0.1 W each 1 ISPP + 3 harvesters = 0.4 W Volume: 0.00004 m^3 each 1 ISPP + 3 harvesters = 0.0002 m^3 RF Dish Mass: 0.42 kg Power: 1.6 kw Volume: <0.05 m^3 (folded) DeFini, Sarah Jo Communication

Mission Design Supply Launch Vehicle (Group Lead) Rover Ascent/Descent Tasks Rescue Rover Trajectory Investigating Relay Satellite Possibilities Launch Vehicle Presentations Sanders, Megan Mission Design

km Rescue Rover Trajectory Rescue Rover 350 300 250 200 150 100 50 0 Ceres Surface Burn Coast Flat Ceres Assumption 45 angle during burn 689 km range 60 sec hover when landing -50-100 0 100 200 300 400 500 600 km Sanders, Megan Mission Design

Trajectory Results Outbound Trip Return Trip Round Trip Burn Propellant Mass (kg) Propellant Hover Propellant Mass (kg) Total Mass of Propellant (kg) Volume of Propellant (m 3 ) 734.7 30.9 765.6 3.19 673.5 28.1 701.6 2.93 1408.2 59 1467.2 6.12 Trajectory Characteristics Burn Time (min) Trip Time (s) Outbound Trip 1.2 2710 Return Trip 1.1 2737 Total 2.3 5447 Sanders, Megan Mission Design

Meet downstairs at 10:30.

: Week 8 Presentations Vehicle Groups: - CTV Launch Vehicles (Lead) - CTV Transfer Vehicle Signorino, Trieste Mission Design

CTV Return from Ceres Assumptions: Two Engines: Low Thrust and Kick Engine Isp = 5000s for Low Thrust and Isp = 458.3s for Kick Using Chemical Kick Engine finert kick = 0.1 0.05 Using MPD for Low thrust Engine finert lowthrust = 0.5 Phases of Return Trip: Starting in LCO (50km) Perform V at Ceres to begin trip home Low thrust spiral until CTV crosses Earth s orbit Obtain V for Hyperbolic trajectory goes to Aerodynamics Goal Return the CTV from Ceres without violating inert mass fraction set by the individual engine. Signorino, Trieste Mission Design

CTV Return Trajectory TOF (yrs) Vc (km/s) M prop_kick (T) finert kick Thrust (N) M prop_lt (T) finert lt V (km/s) 1.36 3.31 221.3 0.067 10 8.736 0.529 5.704 1.24 2.98 210.0 0.069 20 15.99 0.501 9.230 1.19 3.01 217.9 0.067 30 22.91 0.501 10.09 1.08 3.67 248.9 0.059 40 27.84 0.518 13.70 Future Work: Implement method on outbound trip for CTV Refine numbers as configuration is finalized Signorino, Trieste Mission Design

Drew Crenwelge 03 March 2011 Power Group: Nuclear Reactor Update - CTV Radiator Sizing CTV Ceres Surface Configuration - CTV Crenwelge, Drew Power Group

Nuclear Reactor Update Power (kwe) Total Mass (kg) PMAD Heat Reject Power Conv. HSHX Shield (LiH/W) Reactor Specific Power (kg/kwe) 2100 27006 4321 9251 4348 1350 3685 4051 12.86 Width (m) 1.8 Height (m) 1.55 Volume (m3) ~5.0 Radiator Area (m2) 3084 Crenwelge, Drew By Drew Crenwelge Power Group

CTV Crane/Arm Steps: Retract condo latch onto moveable brace. Begin rolling outward towards end of track. Rotate condo 180 deg. Lower condo to surface. Future Work: Determine dimensions of track (length, mass, etc). By Drew Crenwelge Crenwelge, Drew Power Group

Elle Stephan 3 March 2011 Communications Satellite Vehicle Lead ISPP Harvester Design Stephan, Elle Power

Ceres Orbiting Satellites Mass [kg] Power Generated [kw] Area [m²] Solar Array 151.2 11.45 180 * Per satellite Possible hinge to allow bending of arrays to ensure fitting inside Aries V Stephan, Elle Power

ISPP Harvesters Total Collection Time 1 Year 2 Years 3 Years 4 Years 5 Years Filled Mass [T] 32.3 16.5 11.5 8.76 7.3 Power [W] 527 516.2 512.8 511 510 Volume [m³] 21.23 15.25 7.5 5.62 4.63 *Based on 24hr day per harvester 2 trips per 24 hr day Li-ion rechargeable battery charged once a week **Will continue to research materials capable of fulfilling harvester requirements Stephan, Elle Power

Dietrich, Jared N Propulsion

Kick Motor goes Chemical Nuclear Thermal Issues: Assumption of an Impulsive burn is not valid Chemical Replacement: Constraints must provide a 10 km/s Delta V 1 Limited by Isp of ~450 sec for bipropellants 2 Mpay = 250.6 T (Vehicle mass before kick) f_inert = 0.04 (typical chemical value for bipropelllants) 3 Mprop 3,201.00 T Minert 129 T Mf 379 T Mo 3,476 T M (H2) 516 T Vol (H2) 6703 m^3 M (O2) 2580.9 T Vol (O2) 2263 m^3 Thrust 490 kn No. of Motors 4 4.15 m LO2 LH2 Ceres Kick 2.14 m Dietrich, Jared N Propulsion Image: Jared Dietrich

Kick Motor Jettison/CAD Choice of Motor to meet mission requirements: RL-10B-2 RL-10B-2 (Pratt & Whitney) The most reliable, safest, and highest-performing upper-stage engine in the world. Total Kick Motor Mass = 1.2 T Interstage Mass (Ares V) = 9.07 T 4 d Total Mass Reduction = 10.3 T (~1%) Ceres Motor Prop Mass = 20 T* Future Work: 1. Determine CG effects 2. Consider Same process for MPDT s 3. Size new Propellant tanks STV: Jared Dietrich Dietrich, Jared N Propulsion

Start at 11:10.

David Wyant March 3, 2011 Technical Group: Propulsion Vehicle Groups: Rovers Crew Ascent Vehicle Rover Engine and Drive Train Sizing Wyant, David Propulsion

Drive Train & Suspension Exploration Rover Mass (kg) Power (kw) Volume (m 3 ) Engine 135.02 36 0.3176 Transmissions 73.65 kg N/A 0.148 Suspension 200 kg N/A N/A Exploration Rover Stats Dry mass: 9093.4 kg Power: 21.98 kw Volume: 67.82 m 3 Exploration Rover Will utilize Zero-turning Radius Movement. Requires multiple, Continuously Variable Transmissions Wyant, David Propulsion

Rescue Rover Engine Sizing Engine Mass (kg) Power (kw) Volume (m 3 ) Main Thruster 112.2 N/A 2.141 ADCS Thrusters 69.4 N/A.024 Maneuvering Motors 28 4.66.0608 Main engine 40 kn Thrust 15:1 Throttling Ratio Propellant Mass: 1609.9 kg Maneuvering Motors Wheels to maneuver for airlock docking Will be identical to Exploration rover wheels Wyant, David Propulsion

Michael Hill : Presentation 4 Team Tasks: Propulsion Group Leader CTV Propulsion Ceres Regime Engine Kick Engine Hill, Michael Propulsion

Ceres Regime Engine Require 16.67 kn to 33.33 kn Isp = 468.76 sec @ 16.67 kn Isp = 469.08 sec @ 33.33 kn T/W = 61.49 System Combustion Chamber 9.67 Nozzle 2.50 Injector 7.57 Feed 12.28 Cooling 17.32 O 2 Turbomachinery 1.27 H 2 Turbomachinery 4.65 TOTAL: 55.25 Mass (kg) / Engine Hill, Michael Propulsion

Kick Engine Will use LH 2 /LOX Instead of NTR F = 1,500 kn @ Isp = 458.30 sec T/W = 57.57 System Mass (kg) / Engine Combustion Chamber 298.21 Nozzle 344.81 Injector 400.28 Feed 649.45 Cooling 915.49 O 2 Turbomachinery 42.45 H 2 Turbomachinery 5.19 TOTAL: 2655.88 Michael Hill Hill, Michael Propulsion

Zachary Richardson Week 8 Presentation: Group Lead: Human Factors & Science - ISPP Production and Sizing Updates - ISPP Timeline Trade Study Tasks Accomplished: Sizing of Electrolysis/Oven/Production rates for ISPP Updated ISPP schematic design with fellow ISPP group members Updated ISPP production values to fit mission timeline Richardson, Zachary Human Factors & Science

Total ISPP production, assumptions and origin of requirements Updated Total Production Values (for 1 ISPP station) *Water extracted (T) 38.7 **Hydrogen extracted (T) **Oxygen extracted (T) 105.1 400.5 *Stored at Ceres ambient temp (ice) **Stored in liquid form Note: Numbers are from various worst case scenarios so these values will most likely be reduced 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 for worst case where final V arriving at Earth = 13km/s Richardson, Zachary Human Factors & Science

ISPP Production Trade Study Production time (years) Regolith (T/day) Mass of Oven (kg) Volume of Oven (m^3) Power Oven Required (kw) Mass of Electrol izer (kg) Volume of Electroli zer (m^3) Power of Electr olizer (kw) Reactor mass (kg) Total ISPP mass (kg) 1 125 6435 78.9 744 12400 29.7 661 6394 25229 1.38 90 4962 59.4 536 9010 21.7 496 4735 18707 2* 62 3784 43.9 369 6260 15.3 341 3306 13350* 3 42 2942 32.7 250 4300 10.7 231 2288 9530 4 31 2480 26.6 185 3220 8.14 171 1733 7433 5 25 2228 23.3 149 2630 6.77 137 1066 5924 Upcoming Tasks Assist in thermal control calculations and final Harvester calculations Finalize entire ISPP facility masses for Design Freeze Determine final ISPP schematics including all components of the facility Richardson, Zachary Human Factors & Science

Ben Stirgwolt : Week 8 Presentations Human Factors & Science: Rover Docking with CTV CTV Air Circulation Stirgwolt, Ben Human Factors & Science

Rover Docking The Important Numbers o Max lifting height: 5.7 m o Mass: 41 kg o Power: 2.8 kw o Volume (retracted): 6.7 m 3 Stirgwolt, Ben Human Factors & Science

CTV Air Circulation Requirements [2]: o Airflow: 0.42 5.1 m 3 /min o Exhaust velocity: < 76 m/min o Ensure fresh air at crew member s head and keep acoustic exposure low Totals: (Including--Ducting, Common Cabin Air Assembly, Individual Bedroom Fans) o Mass: 405 kg o Power: 1.51. kw o Volume: 1.75 m 3 Stirgwolt, Ben Human Factors & Science

Start at 11:45.

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

Hydrogen Tankage Current LH2 Mass Requirement = 657770 kg Current LH2 Volume Requirement = 9264.4 m^3-8 Tanks with dimensions on right are required for STV -Tanks reused for ISPP Stations -Tanks are empty at Ceres Arrival -Fits inside slightly modified Ares V shroud -Mass of hydrogen is lower than Ares V capacity which means this payload can possibly be used on a small launch r vehicle Mass of Tank = 2.4295 t Volume of Tank = 1249.9 m^3 Payload Mass Per Tank = 84.651 t Payload Volume Per Tank = 1249.9 m^3 Total IMLEO = 677.210 t Total IVLEO = 9999.2 m^3 Picture by: A. Curtiss

Connection Arms Possible Configurations: 1. 4 L shaped arms, 2 detach for rotation Total Mass = 5063.7 kg Total Volume = 0.4521 m^3 2. 2 L shaped arms Total Mass = 4014.3 kg Total Volume = 0.7168 m^3 3. 2 A shaped truss structures Total Mass = 6302.9 kg Total Volume = 0.5628 m^3 Picture by: A. Curtiss

Kim Madden Week 8 Presentation, 3/3/11 - Structures & Thermal Control - Exploration and Rescue Rover - Group Lead This week: -Thermal Control for Rovers -Dividing Wall in Exploration Rover -Started Rover Catia Models

Thermal Control for Rovers MLI covers entire surface of rover to help prevent heat loss Al plates conduct rejected heat from electronics to heat pipes Plate is 0.5 m^2 distributed under all electronics, 5 mm thick Assume electronics are 65% efficient Heat pipe uses water to carry heat from plates to radiators under rover 8 (Exploration) or 4 (Rescue) sets of radiators to expel heat Multiple sets reduce size of each radiator Radiators fold up when desired temp is reached (293 K) to stop heat rejection Heat pipes have rubber connectors so they can bend, also stops water flow Exploration Rescue Mass (kg) Power (kw) Volume(m^3) Mass (kg) Power (kw) Volume(m^3) Heat Pipe (water + pipe) 21.82 0 0.16 17.79 0 0.11 Radiators 1763.13 0.25 0.63 956.96 0.25 0.34 MLI 12.73 0 0.045 10.97 0 0.039 Al Conducting Plates 7.025 0 0.0025 7.025 0 0.0025 Total 1804.71 0.25 0.837 992.752 0.25 0.491

Schematic of Thermal Control Heat out due to colder temps on Ceres Rover Heat in due to electronics in Rover Heat out via heat pumps and radiators Electronics Conducting Plate Radiators Heat Pump Picture by Kim Madden

Luken, Chris (Web Developer) Attitude Determination and Control Systems

Max Frontal Area 1520 m 2 Min Frontal Area 450 m 2 f o 1353 W/m 2 CTV Diagram Courtesy of Frank Fortunato Environmental Torque Solar Radiation Solar Wind Micro-meteorites Required m p 41.6 kg 0.0106 kg Negligible Luken, Chris (Web Developer) Attitude Determination and Control Systems

ΔH H ω = 2.275 rpm CTV Diagram Courtesy of Frank Fortunato Inertia 6x10 8 kg-m 2 Mass 230 T F att Isp 85 N delivered 328 (NTO, MMH) Attitude Thruster Pulse Arc ~ 16 deg Pulse Time ~ 0.6 s Illustration by Chris Luken Maneuver Propellant Mass Delivered ΔV Turning 3 Rev per Pulse 3.522 T 49.14 m/s Turning Fixed Efficiency 3.522 T 49.14 m/s Luken, Chris (Web Developer) Attitude Determination and Control Systems

Alexander Roth : Week 8 Presentations Technical Groups: Aerodynamics CAD Vehicle Groups: CTV Crew Capsule Crew Launch Vehicle Cargo Launch Vehicle Tasks Accomplished: Fitting CTV components into the Ares V payload shroud Modeled components for CTV and Crew Capsule Roth, Alexander Aerodynamics & CAD

Placement & Fitting into Ares V 4.4 m Items & Order of Removal in LEO: All CTV Compartments 2.1 MW Reactor Radiator Section Transmission Dish Receiving Dish UHF Dish 3 NTR Kick Motors MPD Slider Rail 4 MPDs Tether Spindle Tether Line Total Volume: 1155.97 m 3 of 1410m 3 Roth, Alexander 7.5 m 18.7 m 8.8 m Aerodynamics & CAD (1) Aerocapture Maneuver (at altitude h) CAD Model by Alexander Roth Inside Components by Trieste Signorino & Brendon White

Other CAD Models Made MPDs with Slider Rail Crew Capsule and Mounting Arms CAD Models by Alexander Roth Roth, Alexander Aerodynamics & CAD