PROJECT MANAGER TREVOR JAHN - engineering.purdue.edu · (2.16.2016) Three Copies of 1 Page Resume in lecture (2.16.2016) First Peer Evaluation (2.18.2016) Action items are assigned

PROJECT MANAGER TREVOR JAHN THURSDAY LAB 3/4/2016

Semester Schedule and Expectations

PDR SLIDES NEW PRESENTATION FORMAT

*Mike and I will be making a full edited draft by next week Introduction • Mars mission summary Organized by Mission Architecture (broad information) • Washington Series (2018-2020) • Adams Series (2021-2024) • Jefferson Series (2024-2028) • Madison Series (2028-2036) • Monroe Series (2036+) APENDIX (supporting information) • All specific information • A lot like your backup slides

DUE DATES THIS WEEKEND Saturday 3.5.2016 10 pages total (first 5 from before with an additional new 5 pages) for the final report 10:00 pm to PM • 12 point font • Times New Roman • Double Spaced • PUT YOUR NAME ON IT • 1 in margins • Code is acceptable but can not count for more than 3

pages Sunday 3.6.2016 Edits to PDR slides by 10:00 pm to PM • Notes on Share Drive • Slides with only broad relevant data • Appendix slides with specific information

SEMESTER TIMELINE Project Legacy – Semester Schedule Subject to Change

Week: 6 Feb 14 –

20

(2.16.2016) Three Copies of 1 Page Resume in lecture

(2.16.2016) First Peer Evaluation

(2.18.2016) Action items are assigned in lecture

(2.20.2016) 10:00 pm first five pages are due for the final report DRAFT

to PM via email

Week: 7 Feb 21 –

27

(2.23.2016) Three copies of 1 Page Resume in lecture

(2.25.2016) Action items from week 6 are resolved

(2.25.2016) After lecture Design Freeze is in effect

Week: 8 Feb 28 –

March 5

(2.29.2016) Preliminary Design Review (PDR)

(3.1.2016) Action items assigned as a result of PDR

(3.1.2016) Three copies of Long Resume due on Tuesday

(3.5.2016) 10:00 pm second five pages of the Final Report

DRAFT to PM via email (ten pages total) with the first five

pages and any revisions included

(3.6.2016) 10:00 pm updated PDR slides to PM via email Week: 9 March 6

– 12 (3.8.2016) 3 Copies of Long Resume due on Tuesday

(3.10.2016) Action items resolved and presented in lab

(3.10.2016) After lecture Design Freeze in effect

(3.11.2016) 10:00 pm third set of five pages of the Final Report

DRAFT to PM via email (fifteen pages total) with the first ten

pages and any revisions included

SEMESTER TIMELINE Week:

10

March 13

– 19 Spring Break

Week:

11

March 20

– 26 (3.22/24.2016) Report writing exercises in class

(3.22.2016) Second Peer Evaluation

(3.25.2016) Critical Design Review (CDR) Week:

12

March 27

– April 2 (3.31.2016) PM and APM present to AAE Industrial Advisory Council

(Tentatively 9:30 am)

(3.31.2016) Report groups are assigned to finish up report topics Week:

13

April 3 –

9 (4.4.2016) Final report due to PM via email for assembly into near final

draft

(4.5.2016) Go over near final draft of the final report for review

(4.7.2016) Final report due to Professor Longuski and Professor Minton

(4.7.2016) Mike Griffin visit (lunch and afternoon class visit) Week:

14

April 10 –

16 (4.14.2016) PM and APM give dry run of final presentation 8:30 am –

11:20 am Week:

15

April 17 –

23 (4.19.2016) Website and video are due

^more info on this in the coming weeks (as of 2.16.2016)

(4.21.2016) Final Formal Presentation is given by PM and APM –

Stewart Room 206 from 8:00 am – 12:30 pm

(4.21.2016) CLASS ENDS FOR THE SEMESTER

SCIENCE GROUP CALEB ENGLE

3 March 2016

Properties of Lunar Regolith for Digging, Power

Requirements of ISRU, Fuel Depot Location Map

REGOLITH PROPERTIES Objective: Describe properties of lunar regolith pertaining to digging

Reasoning: We have to dig up what we will use for ISRU

• Depth of regolith is estimated to be about 6 – 8 meters

• As previously mentioned, regolith sticks to almost everything

• Porosity ~50%, similar to sand with some larger pieces mixed in

• Dry regolith on surface fairly easy to scoop up and move around

• Regolith and ice mixture will be hard and need special equipment to break apart,

such as a conical rotating bit

Bart, G. D., et. Al. Icarus Gertsch, L., et Al. Scholar’s Mine

POSSIBLE SOLUTION

Mass: 0.0021Mg for one bit

Power:

Volume: .000261m3 for one bit

Recommendation: Put rotating conical bits on end of rover scoop attachment

10cm

5cm

POWER FOR ISRU For furnace pressure of 1atm and regolith starting temperature of

-243.15°C

Volume of furnace needed = 68m3

Volatile Amount Needed Per Day (Mg)

Amount Regolith Needed (Mg)

Power Required (kWh)

H2O 0.0071 0.250 0.012825

CO2 0.0087 14 0.485

CH4 0.02 102 2.4

Total = 3kWh

POWER CALCULATIONS

Heat energy = specific heat * mass * delta T

Specific Heat = 0.76 for lunar regolith

H2O: 3% of regolith

Need 0.0071Mg = 7.1kg

(250kg) * (0.03) = 7.5kg

delta T = 0 – (-243) = 243

() * (0.76) * (243) = 46.170 Joules = 12.825Wh

CH4: 0.65% relative to H2O

Need 0.02Mg = 20kg

(102,000kg) * (0.03) * (0.0065) = 20kg

delta T = -148 – (-243) = 95

(102,000) * (0.76) * (95) = 8,664,000 Joules = 2,406Wh

POWER CALCULATIONS

CO2: 2.17% relative to H2O

Need 0.0087 = 8.7kg

(14,000) * (.03) * (.0217) = 9kg

delta T = -79 - (-243) = 164

(14,000) * (0.76) * (164) = 1,746,000 Joules = 485Wh

FUEL DEPOT, ISRU, LAUNCH PAD, BASE

STRUCTURES AUSTIN BLACK

L-REx: Lunar Rover Excavator

L-REX ARCHITECTURE

Objective: Clear lose regolith from crater blasted holes to allow habs to be oriented.

Reasoning: Several tons of regolith need to be excavated after impact process, with shovel being remotely operated from XM.

Hydraulic power was determined not to be applicable in the harsh lunar temperature cycle.

Want to minimize storage space for when shovel is not in use.

Use “pallet” base designed by Amit Soni of structures group.

Shovel CAD by: Austin Black Rover CAD by: Ariel Dimston

Austin Black

SOLUTION: L-REX NEEDS TO BE ABLE TO EXCAVATE HEAVY LOADS, AND ACHIEVE SPECIFIC REACH

Mass: 1.987 Mg

Power: 1230.24 kWh (total)

Volume: 0.66 m3 (material)

Actuators allow hydraulic style of movement without hydraulic fluid.

Fully outstretched orientation achieves reach required for excavating hab hole.

Rover can excavate hole using loose regolith as ramp, and then clear ramp to complete rectangular hole.

Linear Actuators

Aluminum Supports

Pallet Base

Steel Shovel

CAD model from Austin Black

Austin Black

REFERENCE Part Material Mass (Mg) Volume (m3)

Actuator 2090 Al 0.013 0.0015

Motor Casing Sigmatex 0.0034 0.002

A-Frame 2090 Al 0.036 0.02

Middle U-Beam 2090 Al 0.016 0.01

End U-Beam 2090 Al 0.0095 0.0032

Bracket 2090 Al 0.00009 0.000032

Actuator Pin 2090 Al 0.00001 0.000009

U-Beam Rod 2090 Al 0.00041 0.00014

Scoop Steel 0.082 0.5 (interior)

Pallet 2090 Al 1.735 0.6

% Bolt or Pin In Double Shear Equation Calculator % Amit Soni % AAE 450 - Structures %% Defintion of Variables F = 680.547; % Applied Force [N] d = [1:.001:30]; % Bolt/Pin Diameter [mm] t1 = 20; % Large Plate Thickness [mm] t = 150; % Small Plate Thickness [mm] FS = 1.35 % Factor of Safety Sigma_Yield = 655.00194; % Yield Strength of A286 Steel [MPa] Sigma_Allow = Sigma_Yield/FS; %% Shear Stress - Single Shear Sigma_shear = (4*F)./(2.*pi.*d.^2); % Shear stress average [MPa] %% Bearing Stress

B_t = F./(2.*t.*d); % Bearing Area Stress for small plate [N/mm^2] B_t1 = F./(t1.*d); % Bearing Area Stress for large plate and Bolt/Pin figure(1) plot(d,Sigma_shear,[0,d(end)],[Sigma_Allow,Sigma_Allow]) title('Double Shear Calculation for Bolt') xlabel('Bolt Diameter [mm]') ylabel('Average Shear Stress [Mpa]') grid on %%% Maximum Load Before Shear F = [0:1:25000] dML = 10; Sigma_shearML = (4*F)./(2.*pi.*dML.^2); B_tML = F./(2.*t.*dML); B_t1ML = F./(t1.*dML);

Austin Black

REFERENCE

16°

24 m

3 m

10.46 m

1.2 m

4.5 m

Gap between shovel pallet and ground level

Fully extended configuration

3 m

Side view of habitat rectangular “hole”

Austin Black

REFERENCE

Linear Actuator Cutaway sketch by Austin Black

Scoop actuator load: 416.25 kg (full regolith load) A-frame actuator load: 944.53 kg (full regolith load)

U-beams modeled as simple beams with overhang, and max overhang at end of beam determined.

Max overhang for center U-beam, subject to greatest bending moments in structure. Lower U-Beam

and Actuator Coupled Force

P

Actuator A-frame

Austin Black

REFERENCE

Austin Black

STRUCTURES AMIT SONI

JVA-01: Rover Attachment/Detachment Vehicle

JVA-01 DESIGN Objective: Design mechanism to attach and remove rover attachments

Reasoning: Shirt-sleeve pressurized environment and radiation exposure prevents astronauts from attaching and detaching the rover attachments

• Miniaturization and redesign of

ATHLETE (1/4th scale)

• Universal pallet design for ease of

addition and removal

• Pallet will attach to rover

• Slides on rail

• Universal pallet design for ease of

addition and removal

Detailed design for JVA bed:

* CAD design and concept art by Amit Soni

Amit Soni 2

Universal Pallets

Part Material Mass (Mg) Volume (m3)

Slide Bar (x2) Al 2090 0.1023 3.542*10-2

Slant Torsion Bar (x2)

Al 2090 0.01872 3.542*10-2

Torsion Bar Al 2090 0.008320 2.879*10-3

Pallet Al 2090 0.4483 0.1551

Total ---- 0.5776 0.2289

JVA Bed

FEA ANALYSIS ON JVA BED

Overall Vehicle:

Mass: 1.2 Mg (with legs)

Power: 390 W per use

Volume: 14 m3

• FEA of Bed and Pallet

• Load applied on Pallet: 8,500N

• (2Mg load +30% uncertainty)*FS=2.00

•Fixture locations for legs (6x)

•Max Stress: 18.05 MPa

•Yield Stress: 50.5 MPa

•Bed and Pallet can withstand load of attachments

•To CAD and analyze loads on legs next.

*SolidWorks FEA model by Amit Soni

Amit Soni 3

JVA BED DIMENSIONS *All dimensions in meters

Amit Soni 4

*Concept art and dimension drawing by Amit Soni

FEA BACKUP

Static Strain Deformation Scale:1 Max Strain: 1.218e-4

Static Deformation Deformation Scale:1 Max Deformation: 8.1mm

*SolidWorks FEA models by Amit Soni Amit Soni 5

SAMPLE ATTACHMENT

Benjamin Mishler 6

1

2

3

REFERENCES

1 Wilcox, B., Litwin, T., Biesiadecki, J., Matthews, J., Heverly, M., Morrison, J., Townsend,

J., Ahmad, N., Sirota, A., and Cooper, B., "Athlete: A cargo handling and manipulation

robot for the moon", Journal of Field Robotics, vol. 24, 2007, pp. 421-434.

Amit Soni 7

POWER AND THERMAL TYLER MURRAY

Base Construction Reasoning

Base Construction Timeline

BASE CONSTRUCTION REASONING Objective: Determine how to dig out lunar base

Reasoning: Effectively bury habs

• Looked at case involving 6 impactors

• After impactors: 1480 m3, 2219 Mg excavated

• To create base layout below, additional

1326.08 m3, 1989.12 Mg need to be excavated

• 16 degree ramp necessary to allow easy access for construction rover

16°

24 m

3 m

10.46 m

Model created by Jake Elliott

Tyler Murray

BASE CONSTRUCTION TIMELINE

Mass (excavated): 1989.12 Mg

Power: 1230.24 kWh (over 271 days)

Volume (excavated): 1326.08 m3

Recommendation: Dig

• Scoop capable of extracting 0.5 m3 (0.75 Mg) of regolith at a time

• Knowing electromotive characteristics (voltage & amps) of actuator, able to determine

power to operate

• Each scoop requires 480 W, total of 2653 scoops yields a total of 1230.24 kWh

• By moving 15 Mg of regolith a day, base digging would be completed in 271 days,

completion soon after Jefferson series begins (1 year prior to 1st astronauts arrive)

• The construction rover would require 10 kW a day and need 28.8 hours to fully re-charge

Tyler Murray

BACK UP SLIDES

Updated Power distribution prior to 3/3/2016 Lab Max power = 185.825 kW

Tyler Murray

BACK UP SLIDES %Tyler Murray

%Volume and mass needed to dig base

Th = 253.15; % Temperature of habitat [K]

Tm_d = 220; % Temperature outside day [K]

Tm_n = 170; % Temperature outside night [K]

Tm = linspace(Tm_n,Tm_d,12);

day1_m = (1:12); %hours

day1_n = (12:23); %hours

day2_m = (23:34); %hours

day2_n = (34:45); %hours

T_diff = zeros(1,12);

T_diff(1) = Th - Tm(1);

for i = 2:12

T_diff(i) = Tm(i) - Tm(i-1);

end

T_des = Th - Tm(1); % Temperature

difference

v_hab = 330; % volume of habitat [m^3]

d_air = 1.3; % density of air [kg/m^3]

m_air = d_air * v_hab; % mass of air in hab

[kg]

cp_air = 1.005; % specific heat of air

[kJ/(kg.K)]

Tyler Murray

h = 9.45; % [m]

r = 3.334; % [m]

A_surf = (2 * pi * r * h) + (2 * pi * r^2); %

Surface Area [m^2]

Th = 253.15; % Temperature of habitat [K]

Tm_d = 220; % Temperature outside day [K]

Tm_n = 170; % Temperature outside night [K]

Tm = linspace(Tm_n,Tm_d,12);

day1_m = (1:12); %hours

day1_n = (12:23); %hours

day2_m = (23:34); %hours

day2_n = (34:45); %hours

T_diff = zeros(1,12);

T_diff(1) = Th - Tm(1);

for i = 2:12

T_diff(i) = Tm(i) - Tm(i-1);

end

T_des = Th - Tm(1); % Temperature difference

v_hab = 330; % volume of habitat [m^3]

d_air = 1.3; % density of air [kg/m^3]

m_air = d_air * v_hab; % mass of air in hab [kg]

cp_air = 1.005; % specific heat of air [kJ/(kg.K)]

h = 9.45; % [m]

r = 3.334; % [m]

A_surf = (2 * pi * r * h) + (2 * pi * r^2); %

BACK UP SLIDES k = 0.167; % k of material (aluminum)

[Watts/m*K]

t = 0.0127; % Thickness of Aluminum [m]

n = 40; % Layers of material

d = t * n; % total thickness of Aluminum

cp_alum = 0.91; % Specific Heat Capacity

Aluminum [kJ/kg.K]

rho = 2.7e3; % Mass density of Aluminum

[kg/m^3]

A_cyl = (2 * pi * r * h) + (2 * pi * r^2);

e = 0.04; % emissivity

boltz = 1.38064852e-23; % Boltzman constant

h1= 5; % conduction coefficient

h2= 5;

Rcv1 = 1/h1; % Resistance of convection

between inside hab and inside wall

Rcn = d/k;

Rcv2 = 1/h2; % Resistance of convection

between outside wall and moon atmosphere

Rtot = Rcv1 + Rcn + Rcv2; % Total

Resistance

q1 = (T_diff) ./ (Rtot); % estimated total

heat transfer used to find temperature of

walls

Tyler Murray

Ts1 = Th - Rcv1*q1; % Surface Temperature of Inside

Wall [K]

Ts2 = Tm - Rcv2*q1; % Surface Temperature of Outside

Wall [K]

k1 = 1.67;

Q_v = cp_air * m_air * (Th - Tm_n) / (3600*3); % kW

needed to increase to desired temp (60 needed to

convert from kJ to kW)

Q_lc = (A_surf * k1 .* (Th - Tm)) ./ (d * 1000); %

kW needed from losses by conduction

Q_r = (e./((n+1).*(2-e))).*boltz.*(Ts2.^4-

Tm.^4).*A_cyl/1000; % kW needed from losses by

radiation

Q_t = Q_lc + Q_r; % kW needed to regulate power

Q_t(1) = Q_t(1) + Q_v;

Q_t(2) = Q_t(2) + Q_v;

Q_t(3) = Q_t(3) + Q_v;

Q_t1 = fliplr(Q_t);

figure(1)

plot(day1_m,Q_t)

xlabel('Time (hour)')

ylabel('Power (kW)')

title('Power Required to Heat Hab 1 Day')

axis([1 12 0 85])

BACK UP SLIDES figure(2)

plot(day1_m,Q_t, 'b')

xlabel('Time (hour)')

ylabel('Power (kW)')

title('Power Required to Account for

Conduction & Radiation')

hold on

plot(day1_n,Q_t1, 'b')

hold on

plot(day2_m,Q_t, 'b')

hold on

plot(day2_n,Q_t1, 'b')

v_impact = 1480; %volume excavated from

impact [m^3]

m_impact = 2219; %mass excavated from

impact [Mg]

r_length = 24; %length of rectangle portion

of base [m]

r_width = 32; %width of rectangle portion

of base [m]

height = 3; %triangle height [m]

angle = 16; %ramp angle [deg]

t_side = height/tand(angle); %width of

triangle portion of base

density = 1500; %density of lunar regolith

[kg/m^3]

Tyler Murray

scoop_v = 0.5; %volume of scoop collecting regolith

[m^3]

scoop_m = density * scoop_v; %mass of regolith

collected [kg]

power = 480; %power needed to pick up, transport,

and drop regolith [W]

charge = (24 + 28.8)/24; %days needed to charge

battery

per_day = 10; %desired power used per day for

construction [kW]

r_vol = r_length * r_width * height; %volume of

rectangle portion of base [m^3]

t_vol = t_side * height * r_width * .5; %volume of

triangle portion of base [m^3]

b_vol = r_vol + t_vol; %volume of base

b_mass = b_vol * density / 1000; %total mass of

lunar regolith in area

dig_v = b_vol - v_impact; %volume needed to dig by

rover [m^3]

dig_m = b_mass - m_impact; %mass needed to dig by

rover [Mg]

scoops = dig_m / scoop_m * 1000; %number of scoops

to dig base

total_p = power * scoops / 1000; %power needed to

dig entire base [kWh]

days = total_p / per_day * charge; %number of days

to complete construction

REFERENCES "Battery Charge Time Calculator." Battery Charge Time Calculator. CSG Network, n.d. Web. 02 Mar. 2016. . Lunar regolith: density = 1500 kg/m3

Tyler Murray

Unified Rover System for Astronauts and Habitat Modules

ARIEL DIMSTON STRUCTURES

AIRLOCKS AND WHEEL ASSEMBLY

Objective Stress Analysis of

Wheels, Airlocks, Hab Analysis

Reasoning To design the airlocks

for the rover, estimate mass for

wheels and hab modules.

Fig. 1: Hula-Hoop Stress Condition Rim & Tire

Fig. 2 Airlock Open Fig. 3: Airlock Shut

Ariel Dimston

Airlock Door Specifications

Length 1 [m]

Width 0.6 [m]

Thickness 88.3 [mm]

Max Pressure Differential

27 [psi]

HABITAT STRUCTURE

Ariel Dimston

Fig. 5: Stress of Habitat Modules

Fig. 6: Displacement

Specification Value

Diameter 7 [m]

Height 10 [m]

Pressure 14.7 [PSI]

Structural Mass 5.3 [Mg]

FEA Parameter Result

Safety Factor 7.5

Max Displacement

1.2 [mm]

Wall Thickness 33.5 [mm]

Regolith Mass 55.0 [Mg]

ADDITIONAL AIRLOCK PICTURES

Ariel Dimston

SEATING AREA IN ROVER

AIRLOCK DESIGN DETAILS

There are a total of six hydraulic lock

assemblies in the door.

Each assembly contains two physical

locks.

The door is designed to be safe to the

astronauts should three locks fail.

The locks are designed to fail without

jamming.

Should the locks become jammed they

can be disassembled from the door when

docked to the habitat system.

The locks can be unlocked from the

outside with a specially designed wrench

but it is impossible to open the door if

there is a pressure differential.

CONTROLS MAO KONISHI

Rover video and light attachments

March 3, 2016

CREWED/UNCREWED ROVER VIEWS APPROACH

Objective: Control uncrewed rover remotely from Earth; increase visibility from crewed

rover for driving

Requirements: Uncrewed

• Operate from Earth

• Send images/videos for drivers

• See 35+ m ahead of rover

• Clear views of attachments

Requirements: Crewed

• Clear views of rover surroundings

• Front, back

• Clear view of attachments

Mao Konishi

Rover CAD by Ariel Dimston

CREWED/UNCREWED ROVER VIEWS INSTRUMENTS

Attachments (C - crewed, U – uncrewed)

• Video camera – 2 on C, 1+ on U

• M = 0.6 kg, P = 8 W, V = 5.493*10-4 m3 each1

• LED headlights – 2 on C, 1 on U

• M = 10.89 kg, P = 12.8~25.6 W, V = 0.0565 m3 each2

• On-board monitor – 1 on C

• M = 0.700 kg, P = 8 W, V = 6.967*10-4 m3

Control Instruments (Uncrewed - TBD)

• Actuators

Total Mass (C/U): 23.68 kg, 11.58 kg

Total Power (C/U): 75.20 W, 33.60 W

Total Volume (C/U): 0.1148 m3, 0.0570 m3

Mao Konishi

Example camera/light placement

(Rover CAD by Ariel Dimston)

BACKUP SLIDES CALCULATIONS – VISIBILITY REQUIREMENT

Mao Konishi

BACKUP SLIDES CODE – TORQUE CALCULATION

Mao Konishi

Sample calculation with mrover = 100 kg

BACKUP SLIDES REFERENCES

1 HDTV Digital Camera HV-HD30. Hitachi Kokusai Electric (March 2008).

http://www.hitachi-

keu.com/test/broadcast/hdtv_box_pov_cameras/pdf/hv_hd30_datasheet.pdf 2 NH LED 200 RECT. GE Lighting (2015). http://consumer.gelighting.com/catalog/p/69822 3 VM-7X Customizable LCD Monitor. Tru-Vu Monitors Inc.

http://www.tru-vumonitors.com/images/7_LCD_Monitor_VM-7X.pdf

4 Dagnelie, G. (2011). Visual prosthetics: Physiology, bioengineering, and rehabilitation.

New York: Springer. 5 Drive Wheel Motor Torque Calculations. MAE Design and Manufacturing Laboratory.

http://www2.mae.ufl.edu/designlab/motors/EML2322L%20Drive%20Wheel%20Motor

%20Torque%20Calculations.pdf

Mao Konishi

SCIENCE GROUP RACHEL MAXWELL

3 March 2016 STM Updates (Justifications, Instrumentation)

Location of Instruments

47

USES OF EXPERIMENTS / INSTRUMENTS UNDERSTANDING THE SCIENCE RETURNS

Objective: Provide a clear context for the experiments and instruments with regard to the mission

Reasoning: Optimize science return of the mission

Lunar Sample Dating

Late Heavy Bombardment

Understand melt differentiation

Spectrometers

Locate volatiles

Measure volatiles

Understand composition and mineralogy

Measure abundance of elements

Cameras

Characterize landscape geomorphology, processes, and the geologic record

Provide operational support and scientific context

48 Rachel Maxwell

Artist’s concept of SuperCam (Mars 2020) Image Credit: NASA

INSTRUMENT PLACEMENT NECESSARY LAB SETTINGS FOR INSTRUMENTS

Mass: 18.75 kg

Power: 53 W

Volume: 0.419 m3

Autonomous Rover

• Spectrometers

• APXS

• DAN

• SuperCam

• CheMin

• NIRVSS

• Mastcam-Z

• RAD

Crewed Rover

• Spectrometers

• Same as

above

49

Lunar Laboratory*

• SAM

• Gas Chromatograph

• Quadrupole Mass Spectrometer

• Tunable Laser Spectrometer

• ALSEP

• Passive seismometer

• Magnetometer

• Lunar dust detector

• Heat flow experiment

Earth-based Laboratories

• Alternative dating methods (Sm-Nd, Rb-Sr)

Rachel Maxwell

Mass: 24.85 kg

Power: 69 W

Volume: 0.429 m3 Mass: 65 kg

Power: TBD

Volume: TBD

*Not a complete list of instruments

BACKUP SLIDES

50

DESCRIPTION AND USE OF EACH INSTRUMENT

Sample Analysis at Mars (SAM): Gas Chromatograph, Quadrupole Mass Spectrometer, Tunable Laser Spectrometer.

What are the chemical and isotopic states of the lighter elements in rocks and regolith?

Alpha Particle X-Ray Spectrometer (APXS): Highly sensitive X-Ray detector

Measure the abundance of chemical elements in rocks and regolith

Near-Infrared Volatiles Spectrometer System (NIRVSS): Near-Infrared Spectrometer

Measure the volatiles in regolith samples

Mastcam-Z: Multispectral and stereoscopic imaging

Characterize the overall landscape geomorphology, processes, and the geologic record

Provide operational support and scientific context

SuperCam: Laser Induced Breakdown Spectroscopy (LIBS), Raman Spectroscopy, Time Resolved Fluorescence Spectroscopy, Visible and Infrared Spectroscopy, Remote-Micro Imager

Remote optical measurements and laser spectroscopy to determine fine-scale mineralogy, chemistry, and atomic and molecular composition of samples

Chemistry and Camera (ChemCam): LIBS, Remote-Micro Imager

Analyze the elemental composition of vaporized materials from areas smaller than 1 millimeter (Precursor to SuperCam)

Rachel Maxwell

BACKUP SLIDES

51

DESCRIPTION AND USE OF EACH INSTRUMENT

Radiation Assessment Detector (RAD): Stack of silicon detectors

Measure and identify all high-energy radiation on the surface

Chemistry and Mineralogy Instrument (CheMin): X-Ray diffraction

Identify and measure various minerals on the surface

Apollo Lunar Surface Experiments Package (ALSEP): Passive seismometer; Lunar

Surface Magnetometer; Solar Wind Spectrometer; Suprathermal Ion Detector; Cold

Cathode Ion Gauge; Lunar Dust Detector; Heat Flow Experiment

Measure seismic activity; Magnetic Field at surface; flux and spectra of electrons and

protons from the sun; Flux, composition, energy, velocity of positive ions; atmosphere

and variations over time or solar activity; dust accumulation; radiation damage to

solar cells; rate of heat loss from lunar interior and thermal properties of lunar

material

Dynamic Albedo of Neutrons (DAN): Active/Passive Neutron Spectrometer

Measure the abundance and depth distribution of H- and OH-bearing materials (e.g.,

adsorbed water, hydrated minerals) in a shallow layer (~1 m) of subsurface along

rover path

Rachel Maxwell

BACKUP SLIDE: AUTONOMOUS ROVER

52

MASS, POWER, VOLUME

Instrument Model from Mass (kg) Power (W) Volume (m3)

DAN MSL 2.6 13 0.0019025

NIRVSS Resource Prospector Unavailable*

Mastcam-Z Mars 2020 4.5 11.8 0.009

RAD MSL 1.6 4.2 0.00024

ChemCam MSL 5.778 Unavailable 0.1327

SuperCam Mars 2020 Unavailable**

APXS MER / Mars 2020 0.37 Unavailable 0.000368

CheMin MSL 10 40 0.027

Total per Rover 24.848 69 0.17122

Rachel Maxwell

*NIRVSS is an instrument designed for launch in 2020. Mass, Power, Volume not yet available, but instrument has been tested as of August 2015. **SuperCam is the Mars 2020 version of ChemCam with more instruments. Mass, Power, Volume not yet available

BACKUP SLIDE: CREWED ROVER

53

MASS, POWER, VOLUME


DAN MSL 2.6 13 0.0019025

NIRVSS Resource Prospector Unavailable*

ChemCam MSL 5.778 Unavailable 0.1327

SuperCam Mars 2020 Unavailable**

APXS MER / Mars 2020 0.37 Unavailable 0.000368

CheMin MSL 10 40 0.027

Total per Rover 18.748 53 0.16198

Rachel Maxwell

*NIRVSS is an instrument designed for launch in 2020. Mass, Power, Volume not yet available, but instrument has been tested as of August 2015. **SuperCam is the Mars 2020 version of ChemCam with more instruments. Mass, Power, Volume not yet available

BACKUP SLIDE: INSTRUMENTS ON BASE

54


SAM MSL 40 max 990 ~size of a microwave

oven

ASLEP Apollo 15 25 max 65.41 0.0348

Base Total 65 TBD TBD

NOTE:

SAM will go in the lunar laboratory inside the hab

ASLEP will go outside the hab

Rachel Maxwell

REFERENCES

55

http://mars.nasa.gov/msl/mission/instruments/

http://mars.nasa.gov/mars2020/mission/science/for-scientists/instruments/

Andrews, D. R., “Resource Prospector (RP) - Early Prototyping and Development,” AIAA SPACE 2014 Conference and Exposition, 2015, pp. 1–15.

Blake, D., Vaniman, D., Anderson, R., Bish, D., Chipera, S., Chemtob, S., Crisp, J., DesMarais, D., Downs, R., Farmer, J., and Others, “The CheMin mineralogical instrument on the Mars Science Laboratory

mission,” Lunar and Planetary Institute Science Conference Abstracts, vol. 40, 2009, p. 1484.

Campbell, J. L., “The instrumental blank of the Mars Science Laboratory alpha particle X-ray spectrometer,” Nuclear Instruments and Methods in Physics Research, Section B: Beam Interactions with

Materials and Atoms, vol. 288, 2012, pp. 102–110.

Campbell, J. L., Perrett, G. M., Gellert, R., Andrushenko, S. M., Boyd, N. I., Maxwell, J. A., King, P. L., and Schofield, C. D. M., “Calibration of the Mars Science Laboratory alpha particle X-ray spectrometer,”

Space Science Reviews, vol. 170, 2012, pp. 319–340.

Bell, J.F. III, Maki, J.N., Mehall, G.L., Ravine, M.A., Caplinger, M.A., and the Mastcam-Z Science Team. “Mastcam-Z: A Geologic, Stereoscopic, and Multispectral Investigation on the NASA Mars-2020

Rover,”

Grotzinger, J. P., Crisp, J., Vasavada, A. R., Anderson, R. C., Baker, C. J., Barry, R., Blake, D. F., Conrad, P., Edgett, K. S., Ferdowski, B., Gellert, R., Gilbert, J. B., Golombek, M., Gómez-Elvira, J.,

Hassler, D. M., Jandura, L., Litvak, M., Mahaffy, P., Maki, J., Meyer, M., Malin, M. C., Mitrofanov, I., Simmonds, J. J., Vaniman, D., Welch, R. V., and Wiens, R. C., Mars Science Laboratory

mission and science investigation, 2012.

Hassler, D. M., Zeitlin, C., Wimmer-Schweingruber, R. F., Böttcher, S., Martin, C., Andrews, J., Böhm, E., Brinza, D. E., Bullock, M. A., Burmeister, S., Ehresmann, B., Epperly, M., Grinspoon, D., Köhler, J.,

Kortmann, O., Neal, K., Peterson, J., Posner, A., Rafkin, S., Seimetz, L., Smith, K. D., Tyler, Y., Weigle, G., Reitz, G., and Cucinotta, F. A., “The Radiation Assessment Detector (RAD)

investigation,” Space Science Reviews, vol. 170, 2012, pp. 503–558.

Jet Propulsion Laboratory, “Sample Analysis at Mars (SAM),” 2012.

Mahaffy, P. R., Webster, C. R., Cabane, M., Conrad, P. G., Coll, P., Atreya, S. K., Arvey, R., Barciniak, M., Benna, M., Bleacher, L., Brinckerhoff, W. B., Eigenbrode, J. L., Carignan, D., Cascia, M.,

Chalmers, R. A., Dworkin, J. P., Errigo, T., Everson, P., Franz, H., Farley, R., Feng, S., Frazier, G., Freissinet, C., Glavin, D. P., Harpold, D. N., Hawk, D., Holmes, V., Johnson, C. S., Jones, A.,

Jordan, P., Kellogg, J., Lewis, J., Lyness, E., Malespin, C. A., Martin, D. K., Maurer, J., McAdam, A. C., McLennan, D., Nolan, T. J., Noriega, M., Pavlov, A. A., Prats, B., Raaen, E., Sheinman, O.,

Sheppard, D., Smith, J., Stern, J. C., Tan, F., Trainer, M., Ming, D. W., Morris, R. V., Jones, J., Gundersen, C., Steele, A., Wray, J., Botta, O., Leshin, L. A., Owen, T., Battel, S., Jakosky, B. M.,

Manning, H., Squyres, S., Navarro-Gonz??lez, R., McKay, C. P., Raulin, F., Sternberg, R., Buch, A., Sorensen, P., Kline-Schoder, R., Coscia, D., Szopa, C., Teinturier, S., Baffes, C., Feldman, J.,

Flesch, G., Forouhar, S., Garcia, R., Keymeulen, D., Woodward, S., Block, B. P., Arnett, K., Miller, R., Edmonson, C., Gorevan, S., and Mumm, E., “The sample analysis at mars investigation and

instrument suite,” Space Science Reviews, vol. 170, 2012, pp. 401–478.

Maurice, S., Wiens, R. C., Saccoccio, M., Barraclough, B., Gasnault, O., Forni, O., Mangold, N., Baratoux, D., Bender, S., Berger, G., Bernardin, J., Berth, M., Bridges, N., Blaney, D., Bouye, M., Ca??s, P.,

Clark, B., Clegg, S., Cousin, A., Cremers, D., Cros, A., Deflores, L., Derycke, C., Dingler, B., Dromart, G., Dubois, B., Dupieux, M., Durand, E., D’Uston, L., Fabre, C., Faure, B., Gaboriaud, A.,

Gharsa, T., Herkenhoff, K., Kan, E., Kirkland, L., Kouach, D., Lacour, J. L., Langevin, Y., Lasue, J., Le Moulic, S., Lescure, M., Lewin, E., Limonadi, D., Manh??s, G., Mauchien, P., McKay, C.,

Meslin, P. Y., Michel, Y., Miller, E., Newsom, H. E., Orttner, G., Paillet, A., Pares, L., Parot, Y., Perez, R., Pinet, P., Poitrasson, F., Quertier, B., Sall, B., Sotin, C., Sautter, V., S??ran, H.,

Simmonds, J. J., Sirven, J. B., Stiglich, R., Striebig, N., Thocaven, J. J., Toplis, M. J., and Vaniman, D., “The ChemCam instrument suite on the Mars Science Laboratory (MSL) rover: Science

objectives and mast unit description,” Space Science Reviews, vol. 170, 2012, pp. 95–166.

Maurice, S., Wiens, R. C., Anderson, R., Beyssac, O., Bonal, L., Clegg, S., DeFlores, L., Dromard, G., Fischer, W., Forni, O., Gasnault, O., Grotzinger, J., Johnson, J., Martinez-Frias, J., Mangold, N.,

McLennan, S., Montmessin, F., Rull, F., Sharma, S., Fouchet, T., Poulet, F., and Team, T. S., “Science Objectives of the SuperCam Instrument for th Mars2020 rover,” Lunar Planetary Sciences

Conference, vol. 10, 2015, pp. 6–7.

Mitrofanov, I. G., Litvak, M. L., Varenikov, A. B., Barmakov, Y. N., Behar, A., Bobrovnitsky, Y. I., Bogolubov, E. P., Boynton, W. V., Harshman, K., Kan, E., Kozyrev, A. S., Kuzmin, R. O., Malakhov, A. V.,

Mokrousov, M. I., Ponomareva, S. N., Ryzhkov, V. I., Sanin, A. B., Smirnov, G. A., Shvetsov, V. N., Timoshenko, G. N., Tomilina, T. M., Tret’Yakov, V. I., and Vostrukhin, A. A., “Dynamic Albedo

of Neutrons (DAN) experiment onboard NASA’s Mars Science Laboratory,” Space Science Reviews, vol. 170, 2012, pp. 559–582.

NASA, “Apollo Lunar Surface Experiment Package,” 1972.

Rieder, R., Gellert, R., Brückner, J., Klingelhöfer, G., Dreibus, G., Yen, A., and Squyres, S. W., “The new Athena alpha particle X-ray spectrometer for the Mars Exploration Rovers,” Journal of Geophysical

Research, vol. 108, 2003, p. 8066.

http://mars.nasa.gov/msl/mission/instruments/http://mars.nasa.gov/msl/mission/instruments/http://mars.nasa.gov/mars2020/mission/science/for-scientists/instruments/http://mars.nasa.gov/mars2020/mission/science/for-scientists/instruments/http://mars.nasa.gov/mars2020/mission/science/for-scientists/instruments/http://mars.nasa.gov/mars2020/mission/science/for-scientists/instruments/

PROPULSION CLAIRE ALEXANDER

• Science Probe Design

• Recommended Final Design and ACS

56 Claire Alexander

SCIENCE PROBE DESIGN CURRENT DESIGN AND GUIDELINES FOR RE-DESIGN

57 Claire Alexander

Mass (kg) Power (W) Volume (m^3)

Propulsion 110 46 0.4

Total 174.1 107.6 1.123

Prop. Percentage 63.1% 42.7% 35.6%

New Total Payload Mass Needed: 64.31 kg

NEW RECOMMENDED MAIN PROPULSION

SYSTEM:

• Aerojet Rocketdyne R-6D (x3) • Power: 36 Watts • 111 N • TRL = 9

* old design configuration

PROPULSION SYSTEM REDESIGN

58 Claire Alexander

RECOMMENDED FINAL DESIGN

ACS Requirements: • Accommodate Precision Landing • Efficient use of fuel

ACS Recommendation: • Use variable thrust main engine • Use Control Moment Gyroscope

(CMG) system Overall Propulsion System:

Mass (kg) Volume (m^3)

Propulsion 89.54 0.069

Total 149.6 0.783

* CAD by Jay Millane and Claire Alexander

* for one probe

BACKUP SLIDE 1 REFERENCES

59 Claire Alexander

“Aerojet Rocketdyne Capabilities”. Bipropellant Fact Sheet. http://www.rocket.com/files/aerojet/documents/Capabilities/PDFs/Bipropellant%20Data%20Sheets.pdf. [Retrieved 13 February 2016]. “Design Considerations for Reaction control Systems”. https://solarsystem.nasa.gov/docs/Dyakonov%20RCS%20Design%20Considerations.pdf. [Retrieved 1 March 2016]. “Robotic Lunar Landers for Science and Exploration”. https://solarsystem.nasa.gov/docs/pr412.pdf. [Retrieved 1 March 2016].

http://www.rocket.com/files/aerojet/documents/Capabilities/PDFs/Bipropellant Data Sheets.pdfhttp://www.rocket.com/files/aerojet/documents/Capabilities/PDFs/Bipropellant Data Sheets.pdfhttps://solarsystem.nasa.gov/docs/pr412.pdfhttps://solarsystem.nasa.gov/docs/pr412.pdfhttps://solarsystem.nasa.gov/docs/pr412.pdf

BACKUP SLIDE 2 MATLAB CODE

60 Claire Alexander

% Landing on Lunar Surface for Science Probes % Author: Claire Alexander clear all close all clc mpay = 64.05; deltav = 2183; % (km/s) from LLO to surface g = 9.80655; % (m/s^2) for Earth x = [1:1:9]; Isp = [294 280 315.5 323 329 303 327 333 293]; % Isp of engines (sec) mi = [0.454 2 4.31 5.44 5.44 4.53 7.3 5.4 6.8]; % mass of engines (kg) p = [5 36 46 46 46 46 45 45 70]; % power required to operate the valve (W) t = [22 111 490 445 445 890 890 623 4000]; % Thrust avaliable for engines mg = 9.80655/6; % gravitational acceleration of the Moon (m/s^2) ACSmass = mi(1)*6; % Calculations to narrow down engine options MR = exp(deltav./(g.*Isp)); mprop = MR.*(mi+mpay)-mpay-mi; mfull = mprop+mpay+mi+ACSmass; mempty = mi+mpay; T = mfull*mg/3; % thrust required for each engine figure(1) set(gcf,'color','w'); subplot(3,1,1) plot(x,mfull) xlabel('Engine number') ylabel('Mass (kg)') title('Total Mass of Probe') subplot(3,1,2) plot(x,p) xlabel('Engine number') ylabel('Power (W)')

title('Power Required') subplot(3,1,3) plot(x,T,'b') hold on plot(x,t,'r') xlabel('Engine number') ylabel('Thrust (N)') title('Comparrison of Thrust Provded and Required by Engine') legend('Required','Provided') MEthrust = t(2)/3; MEmass = mprop(2)/3; MEOF = 1.65; % Choosen Engine O/F ratio fd = 880; % Density of Fuel (kg/m^3) od = 1440; % Density of Oxidizer (kg/m^3) MEmfuel = MEmass/2.65; % Mass of fuel needed (kg) MEmox = 1.65*MEmfuel; % Mass of oxidizer needed (kg) MEvfuel = MEmfuel/fd; % Volume required for fuel (m^3) MEvox = MEmox/od; % Volume required for oxidizer (m^3) Tmass = mprop(2)+mi(2)*3; Tvolume = MEvfuel+MEvox; fprintf('--------------------------\n') fprintf('----ME System Specs------\n') fprintf('Number of Engines: 3\n') fprintf('Initial Mass of each: %d Total Initial Mass: %d \n',mi(2),mi(2)*3) fprintf('Fuel Mass of each: %4.2d Total Fuel Mass: %4.2d \n',MEmfuel,MEmfuel*3) fprintf('OX Mass of each: %4.2d Total OX Mass: %4.2d \n',MEmox,MEmox*3) fprintf('OX Volume of each: %4.2d Total Volume OX: %4.2d \n',MEvox,MEvox*3) fprintf('Fuel Volume of each: %4.2d Total Volume Fuel: %4.2d \n',MEvfuel,MEvfuel*3) fprintf('----Total Prop System Specs------\n') fprintf('Total Mass: %d\n',Tmass) fprintf('Total Propellant Volume: %d\n',Tvolume)

BACKUP SLIDE 3 MATLAB CODE

61 Claire Alexander

-------------------------- ----ME System Specs------ Number of Engines: 3 Initial Mass of each: 2 Total Initial Mass: 6 Fuel Mass of each: 1.01e+01 Total Fuel Mass: 3.03e+01 OX Mass of each: 1.66e+01 Total OX Mass: 4.99e+01 OX Volume of each: 1.16e-02 Total Volume OX: 3.47e-02 Fuel Volume of each: 1.15e-02 Total Volume Fuel: 3.44e-02 ----Total Prop System Specs------ Total Mass: 8.621713e+01 Total Propellant Volume: 2.302784e-02

POWER/THERMO BRIAN O’NEILL

Ideal location for Fuel Depot

PROBLEM DESCRIPTION OBJECTIVES/REASONING

Objective: Determine ideal location for Fuel depot

Reasoning: To minimize energy required and prepare for extreme temperatures

Landing Pad = 312.25 ⁰ E,-83.68 ⁰ Fuel Depot = 312.10 ⁰ E,-83.82 ⁰ Base = 315.567 ⁰ E, -84.083 ⁰ Mining/ISRU = 314.95 ⁰ E,-84.29 ⁰ [longitude, latitude]

RESULTS OF ANALYSIS LOCATION, METHOD, M/P/V

Power required: .60 KW (±.18KW) Mass for Insulation: 1.92 Kg (±.576Kg) Volume for Insulation: 29.15 m^3 (±8.75m^3)

AAAS Report

BACK UP SLIDES

Full Shade Full Illumination

Illumination Phase Power Required [KW]

Full Sun 0.6

Average 0.403

Full Shade 0.404

ILLUMINATION VARIANCE

BACK UP SLIDES

%LCH4

%% Heat Transfer Analysis for Fuel Tanks

%% Weronika Juszczak(Modified by Brian O'Neill for fuel tank simulations)

close all

%% Defining Variables

d1 = 147E9 %meters from earth to sun

d2 = d1

viewfactor = 1/(4*pi)*atan(sqrt((1/(d1^2+d2^2+d1^2*d2^2))))

sun_fluct = linspace(0,100,100);

n = 40; % number of layers

ks = 0.00004; % Thermal conductivity of MLI spencer [W/m*K]

Tw1 = 95; % Temperature of Inside Wall [K]

Volume = 20 %m^3

Tw2 = linspace(50,400,100)% Temperature of Outside Wall [K] now the temp of Permenately shadowed region

% Tw2 = 40

L = .002; % length between layers of MLI [m]

emm = 0.9; % average emissivity of lunar regolith

e = 0.04; % emissivity of MLI aluminum

em = 0.3; % emissivity of mylar

boltz = 5.67e-8; % Boltzman constant W/m^2*K^-4

Tsun = 5779; % Temperature of sun [K]

%% Heat Transfer Across MLI with Varying n

% Conduction Heat Transfer of Spacer

qc_MLI = ks*(Tw1-Tw2)./(n*L);

% Radiation Heat Transfer

qr1_MLI = (e./((n+1).*(2-e))).*boltz.*(Tw1.^4-Tw2.^4); % heat transfer per unit area for radiation heat transfer through layers [Watts/m^2]

qr2_MLI = e*boltz*(Tsun.^4 - Tw2.^4)%*.216;

qtot_MLI = qr1_MLI+qr2_MLI+qc_MLI;

% figure

% plot(n, qtot_MLI,n,qr1_MLI+qr2_MLI,n,qc_MLI)

% legend('total','radiation','conduction')

% title('Heat Transfer per Unit Area','FontSize',20)

% xlabel('Number of MLI layers (n)')

% ylabel('Heat Flux [Watts/m^2]')

% figure

% plot(L.*n,qtot_MLI)

% title('Heat Transfer vs. Thickness of MLI','FontSize',20)

% xlabel('Thickness [m]')


% Effective Emmitance of MLI (test of efficiency)

e1 = e;% emissivity of surface 1

e2 = e; % emissivity of surface 2

eff = (((2.*n)./emm)-n-1+(1/e1)+(1/e2)).^-1*sun_fluct/100;

% plot(n,eff)

% title('Effective Emittance of MLI','FontSize',20)

% xlabel('Number of Layers')

% ylabel('Eff')

%% Heat Transfer Through Regolith of Varying Thickness

k = .015; % Thermal conductivity of Lunar Regolith 1 M thick [W/m*K]

x = .08; % Thickness

qc = 0; % Heat flux of regolith of varying thickness

qr = boltz*e*(Tsun^4-Tw2.^4) * 3.68260778129241e-24.*sun_fluct/100*viewfactor

qr2 = boltz*e*(Tw1.^4-Tw2.^4)*.271;

q_tot = qc + qr + qr2;

%% FOR CYLINDER

%Brian O'Neill

MATLAB SCRIPT

%LOX %% Heat Transfer Analysis for Fuel Tanks %% Weronika Juszczak(Modified by Brian O'Neill for fuel tank simulations) %% Defining Variables d1 = 147E9 %meters from earth to sun d2 = d1 viewfactor = 1/(4*pi)*atan(sqrt((1/(d1^2+d2^2+d1^2*d2^2)))) sun_fluct = linspace(0,100,100); n = 40; % number of layers ks = 0.00004; % Thermal conductivity of MLI spencer [W/m*K] Tw1 = 90; % Temperature of Inside Wall [K] Volume = 28 %m^3 Tw2 = linspace(50,400,100)% Temperature of Outside Wall [K] now the temp of Permenately shadowed region % Tw2 = 40 L = .002; % length between layers of MLI [m] emm = 0.9; % average emissivity of lunar regolith e = 0.04; % emissivity of MLI aluminum em = 0.3; % emissivity of mylar boltz = 5.67e-8; % Boltzman constant W/m^2*K^-4 Tsun = 5779; % Temperature of sun [K] %% Heat Transfer Across MLI with Varying n % Conduction Heat Transfer of Spacer % qc_MLI = ks*(Tw1-Tw2)./(n*L); % Radiation Heat Transfer qr1_MLI = (e./((n+1).*(2-e))).*boltz.*(Tw1.^4-Tw2.^4); % heat transfer per unit area for radiation heat transfer through layers [Watts/m^2] qr2_MLI = e*boltz*(Tsun.^4 - Tw2.^4)%*.216; qtot_MLI = qr1_MLI+qr2_MLI+qc_MLI; % figure % plot(n, qtot_MLI,n,qr1_MLI+qr2_MLI,n,qc_MLI) % legend('total','radiation','conduction') % title('Heat Transfer per Unit Area','FontSize',20) % xlabel('Number of MLI layers (n)') % ylabel('Heat Flux [Watts/m^2]') % figure % plot(L.*n,qtot_MLI) % title('Heat Transfer vs. Thickness of MLI','FontSize',20) % xlabel('Thickness [m]') % ylabel('Heat Flux [Watts/m^2]') % Effective Emmitance of MLI (test of efficiency) e1 = e;% emissivity of surface 1 e2 = e; % emissivity of surface 2 eff = (((2.*n)./emm)-n-1+(1/e1)+(1/e2)).^-1*sun_fluct/100; % plot(n,eff) % title('Effective Emittance of MLI','FontSize',20) % xlabel('Number of Layers') % ylabel('Eff') %% Heat Transfer Through Regolith of Varying Thickness k = .015; % Thermal conductivity of Lunar Regolith 1 M thick [W/m*K] x = .08; % Thickness qc = 0; % Heat flux of regolith of varying thickness qr = boltz*e*(Tsun^4-Tw2.^4) * 3.68260778129241e-24.*sun_fluct/100 qr2 = boltz*e*(Tw1.^4-Tw2.^4)*.271; q_tot = qc + qr + qr2; %% FOR CYLINDER %Brian O'Neill

BACKUP SLIDES

%m^3

Cyl_length = .9 %axial length of cylinder in meters

% Thickness = n*L

Thickness = .08;

ri = sqrt(Volume./(pi*(Cyl_length-2*Thickness))) %meters INSIDE RADIUS OF CYLINDER

OSA = 2*pi*(ri+Thickness)*Cyl_length+2*pi*(ri+Thickness).^2 ;%OUTSIDE SURFACE AREA

ISA = 2*pi*(ri)*Cyl_length-(2.*Thickness)+2*pi*(ri).^2; %INSIDE SURFACE AREA

ASA = (OSA + ISA)/2; %AVERAGE BETWEEN INSIDE AND OUTSIDE SURFACE AREAS

t = 1:.1:28.5;

day_night_cycle = (1-.213)/2*sin(2*pi*t/28.5)+1.213/2; %CHECK WITH SCIENCE IF YOU WANT TO USE THIS

% figure

% plot(t,day_night_cycle)

% title('Moon cycle','FontSize',20)


% ylabel('Heat transfer [Watts]')

Q = ASA.*qtot_MLI%(.08/.002)

%

% figure

% plot(Thickness,Q)

% title('Heat Transfer vs. Thickness of MLI, For Super Assembly','FontSize',15)



%

% figure

% plot(n,Q)

% title('Heat Transfer vs. Layers of MLI,For Super Assembly','FontSize',15)

% xlabel('Layers of MLI')


%% Volume calculator

ri2 = 3.5; %m

Cyl_length = 2; %m

Thickness = .08; %m

Volume = pi*(ri2+Thickness)^2*Cyl_length-pi*ri2^2*(Cyl_length-2*Thickness);

density = (95+37)/2; %[kg/m^3]for MLI A144 cyrostat

Mass = density*Volume/1000;

massm = Mass

volumem = Volume

Qo = ASA.*q_tot;

n = 1:1:100;

figure

plot(Tw2,Qo)

title('Q vs. temperature level LOX')

xlabel('Temperature [K]')

ylabel('Q [watts]')

qtot1 = q_tot

%Sabatier

%% Heat Transfer Analysis for Fuel Tanks

%% Weronika Juszczak(Modified by Brian O'Neill for fuel tank simulations)

%% Defining Variables

d1 = 147E9 %meters from earth to sun

d2 = d1

viewfactor = 1/(4*pi)*atan(sqrt((1/(d1^2+d2^2+d1^2*d2^2))))

sun_fluct = linspace(0,100,100);

n = 40; % number of layers

ks = 0.00004; % Thermal conductivity of MLI spencer [W/m*K]

Tw1 = 673.15; % Temperature of Inside Wall [K]

Volume = .3 %m^3

Tw2 = linspace(50,400,100)% Temperature of Outside Wall [K] now the temp of Permenately shadowed region

% Tw2 = 40

L = .002; % length between layers of MLI [m]

emm = 0.9; % average emissivity of lunar regolith

e = 0.04; % emissivity of MLI aluminum

em = 0.3; % emissivity of mylar

boltz = 5.67e-8; % Boltzman constant W/m^2*K^-4

Tsun = 5779; % Temperature of sun [K]

%% Heat Transfer Across MLI with Varying n

% Conduction Heat Transfer of Spacer

% qc_MLI = ks*(Tw1-Tw2)./(n*L);

% Radiation Heat Transfer

qr1_MLI = (e./((n+1).*(2-e))).*boltz.*(Tw1.^4-Tw2.^4); % heat transfer per unit area for radiation heat transfer through layers [Watts/m^2]

qr2_MLI = e*boltz*(Tsun.^4 - Tw2.^4)%*.216;

qtot_MLI = qr1_MLI+qr2_MLI+qc_MLI;

% figure

% plot(n, qtot_MLI,n,qr1_MLI+qr2_MLI,n,qc_MLI)

% legend('total','radiation','conduction')

% title('Heat Transfer per Unit Area','FontSize',20)

% xlabel('Number of MLI layers (n)')


% figure

% plot(L.*n,qtot_MLI)

% title('Heat Transfer vs. Thickness of MLI','FontSize',20)



% Effective Emmitance of MLI (test of efficiency)

e1 = e;% emissivity of surface 1

e2 = e; % emissivity of surface 2

eff = (((2.*n)./emm)-n-1+(1/e1)+(1/e2)).̂ -1*sun_fluct/100;

% plot(n,eff)

% title('Effective Emittance of MLI','FontSize',20)

% xlabel('Number of Layers')

% ylabel('Eff')

%% Heat Transfer Through Regolith of Varying Thickness

k = .015; % Thermal conductivity of Lunar Regolith 1 M thick [W/m*K]

x = .08; % Thickness

qc = 0; % Heat flux of regolith of varying thickness

qr = boltz*e*(Tsun^4-Tw2.^4) * 3.68260778129241e-24.*sun_fluct/100

qr2 = boltz*e*(Tw1.^4-Tw2.^4)*.271;

q_tot = qc + qr + qr2;

%% FOR CYLINDER

%Brian O'Neill

%% FOR CYLINDER

%Brian O'Neill

%m^3

Cyl_length = .9 %axial length of cylinder in meters

% Thickness = n*L

Thickness = .08;

ri = sqrt(Volume./(pi*(Cyl_length-2*Thickness))) %meters INSIDE RADIUS OF CYLINDER

OSA = 2*pi*(ri+Thickness)*Cyl_length+2*pi*(ri+Thickness).^2 ;%OUTSIDE SURFACE AREA

ISA = 2*pi*(ri)*Cyl_length-(2.*Thickness)+2*pi*(ri).^2; %INSIDE SURFACE AREA

ASA = (OSA + ISA)/2; %AVERAGE BETWEEN INSIDE AND OUTSIDE SURFACE AREAS

t = 1:.1:28.5;

day_night_cycle = (1-.213)/2*sin(2*pi*t/28.5)+1.213/2; %CHECK WITH SCIENCE IF YOU WANT TO USE THIS

% figure

% plot(t,day_night_cycle)

% title('Moon cycle','FontSize',20)



Q = ASA.*qtot_MLI%(.08/.002)

%

% figure

% plot(Thickness,Q)

% title('Heat Transfer vs. Thickness of MLI, For Super Assembly','FontSize',15)



%

% figure

% plot(n,Q)

% title('Heat Transfer vs. Layers of MLI,For Super Assembly','FontSize',15)

% xlabel('Layers of MLI')


%% Volume calculator

ri2 = 3.5; %m

Cyl_length = 2; %m

Thickness = .08; %m

Volume = pi*(ri2+Thickness)^2*Cyl_length-pi*ri2^2*(Cyl_length-2*Thickness);

density = (95+37)/2; %[kg/m^3]for MLI A144 cyrostat

Mass = density*Volume/1000;

masss = Mass

volumes = Volume

Qs = ASA.*q_tot;

n = 1:1:100;

figure

plot(Tw2,Qs)

title('Q vs. temperature level Sabatier')


ylabel('Q [watts]')

Qn = abs(Qm) + abs(Qo) + abs(Qs)

figure

plot(Tw2,Qn)

title('Q vs. temperature level Sabatier, LOX, LCH4')


ylabel('Q [watts]')

total_mass = masso + massm + masss

total_volume = volumeo + volumem + volumes

Qn

References:

David A. Paige, M. A. (2010). Diviner Lunar Radiometer Observations of Cold Traps in the Moon’s South Polar Region. AAAS. Retrieved from http://science.sciencemag.org/content/330/6003/479.figures-only

BACKUPSLIDES MAX/MIN CHART

AAAS Report

PROPULSION DAYLE ALEXANDER

• ISRU Fuel Depot Overview

• ISRU Design, Mass and Volume

69

ISRU/FUEL DEPOT SYSTEM

70 Dayle Alexander

ISRU • Function: generates usable materials for

base/fuel depot • Located at the mining site in the

permanently shadowed region • Mining rover needed to mine the regolith

Fuel Depot • Function: generates fuel/ox for reusable

lander (stores 2 launches worth) • Located at the reusable lander

launch/landing site, in between ISRU and base

• Fuel rover needed to transport materials from the ISRU

Fuel Depot Model from Austin Black

ISRU REQUIREMENTS/MASS

71 Dayle Alexander

MASS OF REQUIRED MATERIALS PER DAY FOR FUEL DEPOT

H2O [Mg] 0.0071 CH4 [Mg] 0.0200

CO2 [Mg] 0.0087

MASS OF MATERIALS GENERATED PER DAY

H2O [Mg] 3.0769 CH4 [Mg] 0.0200 CO2 [Mg] 0.0668

REGOLITH [Mg] 102.5600

EXCESS MATERIALS GENERATED PER DAY H2O [Mg] 0.0031

CO2 [Mg] 0.0001

MINIMUM TANK VOLUMES H2O [m^3] 3.0769

CH4 [m^3] 1.3887 CO2 [m^3] 1.5236

REGOLITH [m^3] 68.3761

TANK MASSES H2O [Mg] 2.1219

CH4 [Mg] 1.2840 CO2 [Mg] 1.3548

REGOLITH [Mg] 15.8720

Regolith Tank

Smaller tanks (H2O, CH4 & CO2)

Shell

REFERENCES • “The Sabatier System: Producing Water on the Space Station”, NASA Space

Station Research,

http://www.nasa.gov/mission_pages/station/research/news/sabatier.html

[retrieved 15 February 2016]

• “Compact and Lightweight Sabatier Reactor for Carbon Dioxide Reduction”,

NASA Marshall Space Flight Center,

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120016419.pdf

[retrieved 2 March 2016]

• “Compact, Lightweight Adsorber and Sabatier Reactor for CO2 Capture and

Reduction for Consumable and Propellant Production”, NASA Marshall Space

Flight Center

http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120015003.pdf

[retrieved 2 March 2016]

• “Mars Return Fuel Production Using Table Top Electrolysis and Sabatier

Reaction”, Colorado State University Space Research Symposium,

http://spacegrant.colorado.edu/COSGC_Projects/symposium/2012/16_MARS

_Return_Fuel_Production.pdf [retrieved 2 March 2016]

72 Dayle Alexander

http://www.nasa.gov/mission_pages/station/research/news/sabatier.htmlhttp://www.nasa.gov/mission_pages/station/research/news/sabatier.htmlhttp://www.nasa.gov/mission_pages/station/research/news/sabatier.htmlhttp://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120016419.pdfhttp://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120016419.pdfhttp://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120016419.pdfhttp://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120015003.pdfhttp://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120015003.pdfhttp://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20120015003.pdfhttp://spacegrant.colorado.edu/COSGC_Projects/symposium/2012/16_MARS_Return_Fuel_Production.pdfhttp://spacegrant.colorado.edu/COSGC_Projects/symposium/2012/16_MARS_Return_Fuel_Production.pdfhttp://spacegrant.colorado.edu/COSGC_Projects/symposium/2012/16_MARS_Return_Fuel_Production.pdfhttp://spacegrant.colorado.edu/COSGC_Projects/symposium/2012/16_MARS_Return_Fuel_Production.pdf

BACKUP SLIDE 1

– LAUNCH/LANDING

73

REASONING FOR REUSABLE LANDER LAUNCH/LANDING SITE AT FUEL DEPOT SITE

• Need to transport fuels to a separate site: will waste time, rovers

• Keeping the landers in a warmer site will cause boil off in the cryogens, which would

require more fluids and more energy

• Fuel depot site will be in between the mining site and base, not too far for rovers to

travel

Dayle Alexander

BACKUP SLIDE 2 – MATLAB CODE PG1

74 Dayle Alexander

% -MODEL FOR ISRU INFO- % AUTHOR: DAYLE ALEXANDER % LAST UPDATED: 3/2/2016 % ASSUMPTIONS: - 1 LAUNCH INCLUDES UP AND DOWN % - LUNAR SURFACE TO LUNAR ORBIT (DV 2200KM/S) % - WILL NEED TO LAUNCH FROM THE SURFACE MIN ONCE EVERY 2 % YEARS % - NEED 1 LAUNCH WORTH OF EMERGENCY FUEL IN HOLDING TANK % - USING 10 MG LANDER % - INERT MASS FRACTION OF 0.15 % - USING 6061AL WITH YIELD STRENGTH 40000PSI clear all; close all; % -CONSTANTS- % co2=0.0087; % [Mg] h2o=0.0071; % [Mg] ch4=0.0200; % [Mg] per_co2=0.0217; per_ch4=0.0065; per_h2o=0.03; p_ch4=14.402; % at 300 psi [kg/m^3]

p_co2=43.822; % at 300 psi [kg/m^3] p_h2o=1000; % [kg/m^3] p_reg=1500; % [kg/m^3] h2o1=ch4/per_ch4; co21=h2o1*per_co2; m_reg=h2o1/per_h2o; v_ch4=ch4*1000/p_ch4; v_co2=co21*1000/p_co2; v_h2o=h2o1*1000/p_h2o; v_reg=m_reg*1000/p_reg; mch4=linspace(0,100,1000); th_1atm=101.35*2.55/(2*275790.28*0.85-0.2*101.35) th_press1=2000*0.023/(2*275790.28*0.85-0.2*2000) th_2atm=101.35*0.023/(2*275790.28*0.85-0.2*101.35) m_smallW=(4/3*pi*0.98^3-4/3*pi*0.91^3)*2700; m_smallM=(4/3*pi*0.77^3-4/3*pi*0.7^3)*2700; m_smallC=(4/3*pi*0.79^3-4/3*pi*0.72^3)*2700; m_large=(4/3*pi*2.62^3-4/3*pi*2.55^3)*2700;

ISRU CODE PG1


75

ISRU CODE PG2

Dayle Alexander

fprintf(' MASSES REQUIRED PER DAY\n'); fprintf('--------------------------------------------------\n'); fprintf('-Mass of H2O Required [Mg] %.4f-\n',h2o); fprintf('-Mass of CH4 Required [Mg] %.4f-\n',ch4); fprintf('-Mass of CO2 Required [Mg] %.4f-\n',co2); fprintf('--------------------------------------------------\n'); fprintf(' MINIMUM MASSES PRODUCED PER DAY\n'); fprintf('--------------------------------------------------\n'); fprintf('-Mass of H2O Produced [Mg] %.4f-\n',h2o1); fprintf('-Mass of CH4 Produced [Mg] %.4f-\n',ch4); fprintf('-Mass of CO2 Produced [Mg] %.4f-\n',co21); fprintf('-Mass of Regolith Required [Mg] %.2f-\n',m_reg); fprintf('--------------------------------------------------\n'); fprintf(' EXCESSES PRODUCED PER DAY\n'); fprintf('--------------------------------------------------\n'); fprintf('-Mass of Excess H2O Produced [Mg] %.4f-\n',(h2o1-h2o)/1000); fprintf('-Mass of Excess CO2 Produced [Mg] %.4f-\n',(co21-co2)/1000); fprintf('--------------------------------------------------\n'); fprintf(' REQUIRED VOLUMES OF TANKS\n'); fprintf('--------------------------------------------------\n'); fprintf('-Volume of H2O Tank [m^3] %.4f-\n',v_h2o); fprintf('-Volume of CH4 Tank [m^3] %.4f-\n',v_ch4);

fprintf('-Volume of CO2 Tank [m^3] %.4f-\n',v_co2); fprintf('-Volume of Regolith Tank [m^3] %.4f-\n',v_reg); fprintf('-Volume of Total ISRU [m^3] %.4f-\n',v_reg); fprintf('--------------------------------------------------\n'); fprintf(' TANK MATERIAL THICKNESS/MASSES\n'); fprintf('--------------------------------------------------\n'); fprintf('-Wall Thickness of H2O Tank [m] %.4f-\n',th_2atm+0.08); fprintf('-Wall Thickness of CH4 Tank [m] %.4f-\n',th_press1+0.08); fprintf('-Wall Thickness of CO2 Tank [m] %.4f-\n',th_press1+0.08); fprintf('-Wall Thickness of Regolith Tank [m] %.4f-\n',th_1atm+0.08); fprintf('-Mass of H2O Tank (Empty) [Mg] %.4f-\n',m_smallW/1000); fprintf('-Mass of CH4 Tank (Empty) [Mg] %.4f-\n',m_smallM/1000); fprintf('-Mass of CO2 Tank (Empty) [Mg] %.4f-\n',m_smallC/1000); fprintf('-Mass of Regolith Tank (Empty) [Mg] %.3f-\n',m_large/1000); fprintf('--------------------------------------------------\n');

BACKUP SLIDE 4 – MATLAB OUTPUT

76 Dayle Alexander

ISRU CODE OUTPUT

MASSES REQUIRED PER DAY -------------------------------------------------- -Mass of H2O Required [Mg] 0.0071- -Mass of CH4 Required [Mg] 0.0200- -Mass of CO2 Required [Mg] 0.0087- -------------------------------------------------- MINIMUM MASSES PRODUCED PER DAY -------------------------------------------------- -Mass of H2O Produced [Mg] 3.0769- -Mass of CH4 Produced [Mg] 0.0200- -Mass of CO2 Produced [Mg] 0.0668- -Mass of Regolith Required [Mg] 102.56- -------------------------------------------------- EXCESSES PRODUCED PER DAY -------------------------------------------------- -Mass of Excess H2O Produced [Mg] 0.0031- -Mass of Excess CO2 Produced [Mg] 0.0001- -------------------------------------------------- REQUIRED VOLUMES OF TANKS -------------------------------------------------- -Volume of H2O Tank [m^3] 3.0769- -Volume of CH4 Tank [m^3] 1.3887- -Volume of CO2 Tank [m^3] 1.5236-

-Volume of Regolith Tank [m^3] 68.3761- -Volume of Total ISRU [m^3] 68.3761- -------------------------------------------------- TANK MATERIAL THICKNESS/MASSES -------------------------------------------------- -Wall Thickness of H2O Tank [m] 0.0800- -Wall Thickness of CH4 Tank [m] 0.0801- -Wall Thickness of CO2 Tank [m] 0.0801- -Wall Thickness of Regolith Tank [m] 0.0806- -Mass of H2O Tank (Empty) [Mg] 2.1219- -Mass of CH4 Tank (Empty) [Mg] 1.2840- -Mass of CO2 Tank (Empty) [Mg] 1.3548- -Mass of Regolith Tank (Empty) [Mg] 15.872- --------------------------------------------------


77

% -MODEL FOR FUEL DEPOT INFO-

% AUTHOR: DAYLE ALEXANDER

% LAST UPDATED: 3/2/2016

% ASSUMPTIONS: - 1 LAUNCH INCLUDES UP AND DOWN

% - LUNAR SURFACE TO LUNAR ORBIT (DV 2200KM/S)

% - WILL NEED TO LAUNCH FROM THE SURFACE MIN ONCE

EVERY 2

% YEARS

% - NEED 1 LAUNCH WORTH OF EMERGENCY FUEL IN

HOLDING TANK

% - USING 10 MG LANDER

% - CAN HARVEST 20 KG OF CH4 A DAY FROM ISRU

% - INERT MASS FRACTION OF 0.15

clear all; close all;

% -CONSTANTS- %

% GENERAL

boiloff=0.1; % Boiloff rate for cryogens in space in %/day

freq_l=1; % Frequency of launch (with 1 extra) [launch/year]

days_y=365; % Number of days in a year [days]

% DENSITIES

p_gh2=0.0899; % Density of GH2 at 350C [kg/m^3]

p_gh2o=575; % Density of GH2O at 350C [kg/m^3]

p_gco2=1.977; % Density of GCO2 at 350C [kg/m^2]

p_gch4=0.6797; % Density of GCH4 [kg/m^2]

p_gox=1.35; % Density of GOX [kg/m^3]

p_lox=1141; % Density of LOX [kg/m^3]

p_lch4=421; % Density of LCH4 [kg/m^3]

p_lh2o=1000; % Density of LH2O [kg/m^3]

p_lco2=1101; % Density of LCO2 [kg/m^3]

% MOLAR MASSES

mm_h2=0.002; % Molar mass of H2 [kg/mol]

mm_h2o=0.018; % Molar mass of H2O [kg/mol]

mm_co2=0.044; % Molar mass of CO2 [kg/mol]

mm_ch4=0.016; % Molar mass of CH4 [kg/mol]

mm_o2=0.032; % Molar mass of O2[kg/mol]

% METHANE ENGINE VALUES

m_prop=10*2; % Mass of Propellants needed to launch 10 Mg lander [Mg]

of=3.8; % O/F ratio for the Raptor engine

m_lch4=m_prop/(of+1); % Mass of CH4 needed to launch 10Mg lander [Mg]

m_lox=m_lch4*of; % Mass of O2 needed to launch [Mg]

% -EQUATIONS- %

% GENERAL

mol_lch4=m_lch4*1000/mm_ch4; % Mols of CH4 required [mols]

mol_lox=m_lox*1000/mm_o2; % Mols of LOX required [moles]

% SABATIER PROCESS

mol_h2_s=mol_lch4*4; % Mols of H2 required in Sabatier Process [mols]

mol_h2o_s=mol_lch4*2; % Mols of H2O generated in Sabatier Process [mols]

mol_co2=mol_lch4; % Mols of CO2 required [mols]

m_h2_s=mol_h2_s*mm_h2; % Mass of H2 required in Sabatier Process [kg]

m_h2o_s=mol_h2o_s*mm_h2o; % Mass of H2O generated in Sabatier

Process[kg]

m_co2=mol_co2*mm_co2; % Mass of CO2 required [kg]

FUEL DEPOT PG1

Dayle Alexander


78

% ELECTROLYSIS

mol_h2o_e=mol_h2_s; % Moles of H2O required from electrolysis H2 [moles]

mol_o2_e=mol_h2_s/2; % Moles of O2 generated from electrolysis [moles]

m_h2o_e=(mol_h2o_e*mm_h2o)/1000; % Mass of H2O in electrolysis H2 [Mg]

m_o2_e=mol_o2_e*mm_o2; % Mass of O2 generated from electrolysis [kg]

% -RESULTS- %

% HOLDING TANK VOLUMES

v_lox=(m_lox*1000)/p_lox; % Min volume of LOX needed [m^3]

v_ch4=(m_lch4*1000)/p_lch4; % Min volume of LCH4 needed [m^3]

excess_lox=m_o2_e-m_lox; % Extra O2 generated [kg]

excess_h2o=m_h2o_s-m_h2o_e*1000; % Extra H2O generated [kg]

% GENERATION RATES

days_ch4=180; % Number of days given to make required propellants [days]

ch4h_perday=20; % Mass of CH4 provided from ISRU per day [kg/day]

ch4g_perday=m_lch4*1000/days_ch4-ch4h_perday; % Mass of CH4 required per day [kg/day]

co2r_perday=(ch4g_perday/mm_ch4)*1*mm_co2; % Mass of CO2 required per day [kg/day]

h2r_perday=(ch4g_perday/mm_ch4)*4*mm_h2; % Mass of H2 required per day [kg/day]

h2ogs_perday=(ch4g_perday/mm_ch4)*2*mm_h2o; % Mass of H2O generated in Sabatier per day [kg/day]

h2ore_perday=(h2r_perday/mm_h2)*1*mm_h2o; % Mass of H2O required in electrolysis per day [kg/day]

h2or_perday=h2ore_perday-h2ogs_perday; % Mass of H2O required from the ISRU per day [kg/day]

o2g_perday=(h2r_perday/mm_h2)*0.5*mm_o2; % Mass of O2 generated per day [kg/day]

% ISRU TANK VOLUMES

vh_ch4=ch4g_perday/14.402; % Volume of gas CH4 tank from ISRU [m^3]

vh_h2o=h2ore_perday/p_lh2o; % Volume of liquid H2O tank from ISRU [m^3]

vh_co2=co2r_perday/43.822; % Volume of gas CO2 tank from ISRU [m^3]

% SABATIER REACTOR SIZING

h2o_perhour=h2ogs_perday/24; % H2O required per hour [kg/hr]

h2o_refrate=0.01/1.34*3; % H2O generated in experimental reactor [kg/hr]

hrs_h2o=h2o_perhour/h2o_refrate; % Hours to make required H2O[hr]

vh_refsize=18*18*18*0.0254^3; % Size of experimental reactor [m^3]

vh_size=vh_refsize*3; % Size needed for our reactor [m^3]

vh_rt=h2r_perday/p_gh2+co2r_perday/p_gco2; % Volume of Sabatier reactor [m^3]

% % PRINT RESULTS

fprintf(' MASS/VOLUME PER LAUNCH\n');

fprintf('--------------------------------------------------\n');

fprintf('-Mass of Methane Required [Mg] %.0f -\n',m_lch4);

fprintf('-Volume of Methane Holding Tank [m^3] %.0f-\n',v_ch4*2);

fprintf('--------------------------------------------------\n');

fprintf('-Mass of LOX Required [Mg] %.0f-\n',m_lox);

fprintf('-Volume of LOX Holding Tank [m^3] %.0f-\n',v_lox*2);

fprintf('--------------------------------------------------\n');

fprintf(' RAW MATERIALS REQUIRED/GENERATED\n');

fprintf('--------------------------------------------------\n');

fprintf('-Mass of H2O Required [Mg] %.0f-\n',m_h2o_e);

fprintf('-Mass of CO2 Required [Mg] %.0f-\n',m_co2/1000);

fprintf('--------------------------------------------------\n');

fprintf('-Mass of Excess LOX Generated [Mg] %.0f-\n',excess_lox/1000);

fprintf('--------------------------------------------------\n');

fprintf(' VOLUME OF RAW MATERIAL TANKS\n');

fprintf('--------------------------------------------------\n');

fprintf('-Volume of GCH4 Tank (300psi) [m^3] %.4f-\n',vh_ch4);

fprintf('-Volume of LH2O Tank [m^3] %.4f-\n',vh_h2o);

fprintf('-Volume of GCO2 Tank (300psi) [m^3] %.4f-\n',vh_co2);

fprintf('--------------------------------------------------\n');

fprintf(' ISRU REQUIREMENTS PER DAY\n');

fprintf('--------------------------------------------------\n');

fprintf('-Mass of Gas CH4 Required [Mg/day] %.4f-\n',ch4h_perday/1000);

fprintf('-Mass of Liquid H2O Required [Mg/day] %.4f-\n',h2or_perday/1000);

fprintf('-Mass of Gas CO2 Required [Mg/day] %.4f-\n',co2r_perday/1000);

fprintf('--------------------------------------------------\n');

fprintf(' POWER REQUIREMENTS\n');

fprintf('--------------------------------------------------\n');

fprintf('-Gas CH4 Heated/Kept at 6.85C [m^3] %.4f-\n',vh_ch4);

fprintf('-Liquid H2O Heated/Kept at 6.85C [m^3] %.4f-\n',vh_h2o);

fprintf('-Gas CO2 Heated/Kept at 6.85C [m^3] %.4f-\n',vh_co2);

fprintf('-Gas H2 and CO2 Heated to 350C in RT [m^3] %.4f-\n',vh_size);

fprintf('-Reactants tank kept at 350C for [hrs/day] %.3f-\n',hrs_h2o);

fprintf('-Liquid CH4 Heated/Kept at -178.15C [m^3] %.3f-\n',v_ch4*2);

fprintf('-Liquid O2 Heated/Kept at -183.15C [m^3] %.3f-\n',v_lox*2);

fprintf('-Current to process ? water in 1 day [kg] %.3f-\n',h2ore_perday);

fprintf('--------------------------------------------------\n');

fprintf('-*RT: Reaction Tank: Sabatier process tank where -\n- CO2 and H2 react -\n');

fprintf('-*Cold temps are heated due to -233.15C temp of -\n- PSR (Permanently Shadowed Reigon)

-\n');

fprintf('--------------------------------------------------\n');

FUEL DEPOT CODE PG2

Dayle Alexander

BACKUP SLIDE 7 – CODE OUTPUT

79

FUEL DEPOT CODE OUTPUT

MASS/VOLUME PER LAUNCH -------------------------------------------------- -Mass of Methane Required [Mg] 4 - -Volume of Methane Holding Tank [m^3] 20- -------------------------------------------------- -Mass of LOX Required [Mg] 16- -Volume of LOX Holding Tank [m^3] 28- -------------------------------------------------- RAW MATERIALS REQUIRED/GENERATED -------------------------------------------------- -Mass of H2O Required [Mg] 19- -Mass of CO2 Required [Mg] 11- -------------------------------------------------- -Mass of Excess LOX Generated [Mg] 17- -------------------------------------------------- VOLUME OF RAW MATERIAL TANKS -------------------------------------------------- -Volume of GCH4 Tank (300psi) [m^3] 0.2186- -Volume of LH2O Tank [m^3] 0.0142- -Volume of GCO2 Tank (300psi) [m^3] 0.1976- -------------------------------------------------- ISRU REQUIREMENTS PER DAY

-------------------------------------------------- -Mass of Gas CH4 Required [Mg/day] 0.0200- -Mass of Liquid H2O Required [Mg/day] 0.0071- -Mass of Gas CO2 Required [Mg/day] 0.0087- -------------------------------------------------- POWER REQUIREMENTS -------------------------------------------------- -Gas CH4 Heated/Kept at 6.85C [m^3] 0.2186- -Liquid H2O Heated/Kept at 6.85C [m^3] 0.0142- -Gas CO2 Heated/Kept at 6.85C [m^3] 0.1976- -Gas H2 and CO2 Heated to 350C in RT [m^3] 0.2867- -Reactants tank kept at 350C for [hrs/day] 13.183- -Liquid CH4 Heated/Kept at -178.15C [m^3] 19.794- -Liquid O2 Heated/Kept at -183.15C [m^3] 27.753- -Current to process ? water in 1 day [kg] 14.167- -------------------------------------------------- -*RT: Reaction Tank: Sabatier process tank where - - CO2 and H2 react - -*Cold temps are heated due to -233.15C temp of - - PSR (Permanently Shadowed Region) - --------------------------------------------------

Dayle Alexander

BACKUP SLIDE 8 – COMPONENTS LIST

80

COMPONENTS LIST OF THE FUEL DEPOT, UPDATED FROM LAST PRESENTATION

COMPONENTS LIST

COMPONENT REQUIRED TEMP

[°C] REQUIRED

VOLUME [m^3] REQUIRED

PRESSURE [atm/psi] INLET FLUIDS EXIT FLUIDS LH2O Tank 6.85 0.014 1/14.7 LH2O (From ISRU) GH2, GO2 GCO2 Tank 6.85 0.198 20/300 GCO2 (From ISRU) GCO2 GCH4 Tank 6.85 0.219 20/300 GCH4 (From ISRU) GCH4

Reactants Tank 350/100 0.287 1/14.7 GH2,GCO2 LH2O,GCH4 O2 Heat

Exchanger -233.15 (no

insulation/heat) ? 1/14.7 GO2 LOX CH4 Heat Exchanger

-233.15 (no insulation/heat) ? 1/14.7 GCH4 LCH4

LOX Storage Tank -183.15 28 1/14.7 LOX LOX (To lander)

LCH4 Storage Tank -178.15 20 1/14.7 LCH4

LCH4 (To lander)

Dayle Alexander

BACKUP SLIDE 9 – FD REQUIREMENTS

81

REQUIREMENTS OF THE FUEL DEPOT, UPDATED FROM LAST PRESENTATION

Dayle Alexander

ISRU REQUIREMENTS PER DAY [Mg]

Liquid Water 0.0071

Gas Methane 0.0200

Gas Carbon Dioxide 0.0087

PROPELLANT REQUIREMENTS (PER LAUNCH) MASSES [Mg]

CH4 4 LOX 16

STORAGE TANK VOLUMES [m^3]

CH4 20 LOX 28

POWER REQUIREMENTS

SABATIER PROCESS [m^3]

Reaction tank (350/100C) 0.287

ELECTROLYSIS [Mg]

Water to process per day 0.0141

STORAGE [m^3]

Methane storage (-178.15C) 20

LOX storage (-183.15C) 28

BACKUP SLIDE 10 – FD FLUID DIAGRAM

82

FUEL DEPOT FLUIDS DIAGRAM, UPDATED FROM LAST PRESENTATION

Dayle Alexander

Changes from this diagram • 21C now 6.85C • LOX Storage now -183.15C • Methane Storage now -178.15C

STRUCTURES ROBERT WHITE

Cargo Lander

CARGO LANDER DESIGN ITERATION 1: MAX INERT MASS POINT

Objective: Design a 20 Mg lander for the moon that can be launched with its cargo within

the SLS Fairing and be sent to the moon by the EUS.

• Payload Mass: 20 Mg

• Maximum Initial Mass: 45 Mg

• RL10B-2 Engine

• ISP: 462s

• O/F: 5.88

• Inert Mass: 277 Kg

• Delta-V for Landing: 3 km/s

• SLS 8.4 Meter Payload Fairing

• Must launch attached to HAB

Above: HAB and Lander in SLS Fairing

CARGO LANDER DESIGN ITERATION 1: MAX INERT MASS POINT

• Inert Mass: 3.2 Mg

• Propellant Mass: 21.8 Mg

• Propellant Volume: 75 m^3

• 8 meters tall in landing Configuration

• 6 meters tall in compact Configuration

• HABs remain 10 meters tall and 7.4

meters in diameter

• First Iteration of Design, further

iterations will reduce mass

Mass: 25 Mg Wet Lander + 20 Mg Cargo

Power:

Volume: SLS 8.4 meter Payload Fairing

Recommendation:

Below: Landing Configuration

BACKUP SLIDES NOTES ABOUT THE DESIGN PROCESS

Design was done at the maximum

allowable inert mass and propellant mass

for the allowable Initial mass. The mass

fraction comes out to 1.93. from historical

examination the Apollo lander had a mass

ratio of 1.8. Since we are operating with

more powerful engines and lighter

materials reducing the mass in further

iterations under a more detailed analyses

is very likely. The design started at this

point since this was the maximum mass

fraction that would allow the mission to

succeed. By making sure a design would

satisfy the greatest possible volumetric

requirements further iterations where the

mass decreases are guaranteed to fit

within the SLS fairing

BACKUP SLIDES EXTRA NUMBERS

• Not pictured are struts connecting to the legs at indicated point

• After landing the engine and legs can both retract again bringing the height down to 6 meters from the bottom of the legs to the top of the lander

• Fuel tank uses a common wall between LOX and LH to reduce volume.

• Volume LOX: 20 m^3

• Volume LH: 55 m^3

• Landing Legs each support 5800 kg

• Assume 1g force to account for extra stress during landing impact

• 56,833 Newton per leg

• Thickness of 10 cm as determined by Buckling of legs at 5.5 meters long (Distance to connecting strut not shown)

LH

LOX

BACKUP SLIDES CODE AND EXTRA PICTURES

%Standard Rocket Design Space

clc

clear

close all

%Design Space Inputs

m_0_max = 45000;

m_pay = 20000;

Delta_V = 3000;

Isp = 462;

%Constants

g_0 = 9.8;

%Design Space Limit Points

Inert_min = 0;

Inert_max = 0;

Inert_mid = m_0_max./(exp(Delta_V./(Isp.*g_0))) - m_pay;

Prop_min = m_pay.*(exp(Delta_V./(Isp.*g_0))-1);

Prop_max = m_0_max - m_pay;

Prop_mid = m_0_max - m_pay - Inert_mid;

%Inert Mass

%Graph by using m_prop

Prop = Prop_min:1:Prop_max;

%Indepedent

M_engine = 277 + 0*Prop;

M_coms = 0;

M_power = 0;

M_controls = 0;

%m_prop Dependent

m_ox = (5.88./6.88).*Prop;

m_hy = (1./6.88).*Prop;

[m_ox_tank,r_ox] = sphere_tank(m_ox,1141,3*g_0,.1013*10^6);

[m_hy_tank,r_hy] = sphere_tank(m_hy,70,3*g_0,.1013*10^6);

M_tank = m_ox_tank + m_hy_tank;

%m_inert Dependent

%Inert Mass

M = M_engine + M_tank;

figure(1)

plot([Inert_min,Inert_mid,Inert_max,Inert_min],...

[Prop_min,Prop_mid,Prop_max,Prop_min],...

M,Prop)

axis equal

xlabel('Inert Mass [kg]')

ylabel('Propellant Mass [kg]')

figure(2)

inert_mass = Inert_min:1:Inert_mid;

prop_mass = m_0_max - m_pay - inert_mass;

f_inert = inert_mass./(prop_mass + inert_mass);

plot(inert_mass,f_inert)

MR = (Inert_mid + m_pay + Prop_mid)/(Inert_mid + m_pay)

function [m,r]=sphere_tank(m_prop,d_prop,g_max,P_vapor)

S = 200*10^6; %Maximum Allowable Stress of Tank Structural Material

d_s = 2700; %Density of Tank Structural Material

P_ext = 0; %External Atmospheric Pressure

U = 5/100; %Ullage Percentage

T = 0; %Trapped Volume

B = 0; %Boiled Off Volume

e_w = 100/100; %Weld Efficiency Percentage

v_prop = m_prop./d_prop;

V = v_prop + T + B + U.*v_prop;

%Spherical Tank

r = (3.*V./(4.*pi)).^(1/3);

H = 2.*r;

P = d_prop.*g_max.*H + P_vapor - P_ext;

t_s = P.*r./(2.*S.*e_w);

A_s = 4.*pi.*r.^2;

m = A_s.*t_s.*d_s;

end

BACKUP SLIDES REFERENCES

• http://www.astronautix.com/engines/rl10b2.htm

• https://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdf

http://www.astronautix.com/engines/rl10b2.htmhttp://www.astronautix.com/engines/rl10b2.htmhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdfhttps://www.nasa.gov/sites/default/files/files/NAC-July2014-Hill-Creech-Final.pdf

PROPULSION ZACHARY RADY

Crewed Ferry Methalox Engine

90

CREWED FERRY ENGINE

Objective: Update Mass/Volume Numbers for Lower G’s/Smaller Engine

Reasoning: Propulsion Mass/Volume Numbers for Crewed Ferry

91 Zachary Rady

ISP 389.9 s

Expansion Ratio 136

Throat Size 12 in

O/F Ratio 3.6

Initial Throttle Levels: 70%-100% Based on Merlin 1D

CREWED FERRY PROP MASS/VOLUME

IMLEO: 30.163 Mg - For filling Propellant Tanks to 50% Capacity for single Landing

Total Volume: 72.513 m3

92 Zachary Rady

Crewed Ferry Lander Propulsion Stats Initial Mass 47.930 Mg Payload Mass 10.000 Mg Intert Mass 2.397 Mg Methane Mass 27.809 Mg LOX Mass 7.725 Mg Methane Volume 65.743 m^3 LOX Volume 6.770 m^3 Required Thrust 292.218 kN Required Engines 3 Required deltaV 5.171 km/s Initial G Force 0.1704 G's Final G Force 0.6381 G's Propellent Mass 35.534 Mg

based on code by Alexander Burton, Hakusho Chin, Zachary Rady, Andrew Cull

BACKUP SLIDE 1

93 Zachary Rady

NASA CEA Outputs AR=136 O/F 3.5 3.6 3.7 3.8 3.9 4 4.1 4.2 ISPvac [m/s] 3820.7 3823.7 3823 3818 3807.6 3791 3770.9 3749.4 CSTAR [m/s] 1838.1 1829.5 1820.6 1811.6 1802.5 1793.4 1784.4 1775.5 CF 2.0029 2.0111 2.0173 2.0211 2.0219 2.0219 2.022 2.0218

5 Mg Crewed Capsule Payload Option Initial Mass 23.877 Mg Payload Mass 5.000 Mg Intert Mass 1.194 Mg Methane Mass 13.839 Mg LOX Mass 3.844 Mg Methane Volume 32.717 m^3 LOX Volume 3.369 m^3

Required Thrust 292.218 kN Required Engines 3 Required deltaV 5.160 km/s

Initial G Force 0.9747 G's Final G Force 1.4405 G's Propellent Mass 35.534 Mg

Future Work • Look at Expandable Nozzle as

possibility to reduce nozzle length • Work with Structures on refining

design for Landing Strut Compatibility and fitting overall structure in Payload Faring for initial Launch

• More in depth analysis for Throttling capability

BACKUP SLIDE 2

94 Zachary Rady

Dimensions in m

REFERENCES

95

"Merlin (Rocket Engine Family)." Wikipedia. Wikimedia Foundation, n.d. Web. 10 Feb. 2016. Sutton, G. P., & Oscar, B. (2010). Rocket Propulsion Elements. John Wiley & Sons Inc. Cengel, Y. A., Cimbala, J. M., & Turner, R. H. (2012). Fundimentals of Thermal-Fluid Sciences. McGraw Hill. Bergin, C. (2013, March 20). Falcon 9 boost as Merlin 1D engine achieves major milestone. Retrieved from nasaspaceflight.com: http://www.nasaspaceflight.com/2013/03/falcon-9-boost-merlin-1d-engine-achieves-milestone/

Zachary Rady

PROPULSION ANDREW CULL

XM Module ACS Thruster

96 Andrew Cull

ACS THRUSTERS ENGINE & PROPELLANT SELECTION Objective: Propellant & Engine Selection, Determine # and placement of ACS thrusters

Reasoning: Need attitude control for XM Modules

Assumptions

• ΔV = 100 m/s/year

• XM Module weight = 20 tons

• 20 year life span of BA330

Requirements

• Ability to pulse

• Quick start up

• High ISP

• 6 DOF control

Propellant/Engine Selection

• MR-107 (220 N)

• Monopropellant Hydrazine

• Catalyst S405/LCH-202

• ISP = 229 sec

97 Andrew Cull

ACS THRUSTERS THRUSTER PLACEMENT AND # OF THRUSTERS Need

• 12 Thrusters to satisfy 6 DOF

Recommend

• 16 Thrusters in clusters of 4

• 90 Degrees between clusters

98 Andrew Cull

System Parameters – 20 years

Propellant Mass 18 – 28 Mg

Inert Mass 20.01 Mg

Power 552 W

Propellant Volume 17 – 28 m3

Resupply after 10 years Propellant Mass = 11.23 Mg Propellant Volume = 11 m3

BACK UP SLIDE 01 REFUELING INTERVAL

99 Andrew Cull

Recommend refueling ACS Thruster tank once every 10 years. This will only add 11.2 Mg of Fuel to the initial vehicle with a tank volume of 11 m3. Will need to adjust a mission’s cargo to replace needed fuel.

BACK UP SLIDE 02

100

VOLUME OF HYDRAZINE

Andrew Cull

MATLAB CODE % ACS Thruster Code

% Primary use: XM Modules

% Andrew Cull

clear;clc;

%Constants

g0 = 9.80665; %m/s^2

rho_N2H2 = 1021; %kg/m^3

yearsOperationmax = 20;

%Memory Allocation

mp = zeros(1,yearsOperationmax);

N2H2w = zeros(1,yearsOperationmax);

%Define Requirements:

dV = 100; %m/s/year

mpay = 20e3; %kg

numThrusters = 16; %Need 12 for 6 DOF control

%Engine Selection

%MR-107 (220 N)

%Properties

Wt = 1.01; %kg/thruster

ISP = 229; %s

totalWt = Wt*numThrusters; %kg

%Rocket Equation for 1 year of thrust

c = g0*ISP; %effective exhaust velocity

MR = exp(-dV/c); %mass ratio

mf = mpay+totalWt; %final mass

%Calculate Mass of Hydrazine needed without refueling

for year = 1:1:yearsOperationmax

MR = exp(-dV*year/c);

syms mprop;

mp(year) = double(solve(MR==mf/(mf+mprop)));

end

yearOperation = 1:1:yearsOperationmax;

plot(yearOperation,mp/1000)

title('Mass of Hydrazine needed for # Years w/o Refueling','FontSize',17)

xlabel('Years of Continuous Operation [years]','FontSize',18)

ylabel('Mass Hydrazine [Mg]','FontSize',18)

%Calculate Total Mass of Hydrazine needed as function of refuel interval

for refueltime = 1:1:yearsOperationmax

N2H2w(refueltime) = mp(refueltime)*(yearsOperationmax)/refueltime;

end

refueltime = 1:1:yearsOperationmax;

figure(2)

plot(refueltime,N2H2w/1000)

title('Total Mass of Hydrazine Needed vs Refueling Interval','FontSize',18)

xlabel('Refuel Interval [year]','FontSize',18)

ylabel('Total Mass of Hydrazine [Mg]','FontSize',18)

VolContinuous = mp/rho_N2H2;

Volrefuel = N2H2w/rho_N2H2;

figure(3)

plot(yearOperation,VolContinuous)

title('Volume of Hydrazine needed for # years w/o Refueling','FontSize',18)

xlabel('Years of Continuous Operation [years]','FontSize',18)

ylabel('Volume Hydrazine [m^3]','FontSize',18)

figure(4)

plot(refueltime,Volrefuel)

title('Volume of Hydrazine Needed vs Refueling Interval','FontSize',18)

xlabel('Refuel Interval [year]','FontSize',18)

ylabel('Total Volume of Hydrazine','FontSize',18)

101 Andrew Cull

REFERENCES

102

"Hydrazine." Wikipedia. Wikimedia Foundation, n.d. Web. 20 Feb. 2016.

.

Monopropellant Data Sheets. Redmond, WA: Aerojet, 24 Apr. 2006. PDF.

Andrew Cull

HUMAN FACTORS KATE FOWEE

Crew Selection

Radiation Shielding – Dose, Budget

Life support systems

Pressurized Rover

CREW SELECTION Objective: Describe the selection criteria and psychological considerations for

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