R2-S2: ROBOTIC REMOTE-SENSING SCOUT
Dan Brogan
dbrogan@usc.edu
M.S. Astronautical Engineering (Expected Dec. 2021)
ASTE 527: Space Concept Architectures
CONTEXT: THE U.S. LEADS COMMERCIAL HUMAN SPACEFLIGHT TO THE MOON
Signatures from Artemis Accords [1]
R2-S2: Robotic Remote-Sensing Scout
CONTEXT: ROBOTS FOR SUPPORTING CREWED MISSIONS
R2-S2: Robotic Remote-Sensing Scout
PROBLEM: THE NEED FOR A ROBOT TO ASSIST CREWED LUNAR OPERATIONS
Space Policy Document 1 (2018):
Moon Village Association (2020):
NEEDS:
GOALS:
OBJECTIVES:
RATIONALE: HOW R2-S2 FULFILLS THE NGO
What is R2-S2?:
High-Level Problems from NGO:
How R2-S2 Addresses These Problems:
R2-S2: Robotic Remote-Sensing Scout
ASSUMPTIONS
TELEOPERATED MODE: HIGH-LEVEL CONOPS
R2-S2: Robotic Remote-Sensing Scout
COMMUNICATION ARCHITECTURE
Moon Base <-> R2-S2:
Moon Base <-> Earth:
Earth <-> R2-S2:
OPERATIONS
TELEOPERATED MODE: LUNAR CONTROL STATION
Display Interfaces:
Control Interfaces:
R2-S2: Robotic Remote-Sensing Scout
TELEOPERATED APPLICATIONS
MISSION RECONNAISSANCE
REMOTE EXPLORATION
INSPECTION
R2-S2: Robotic Remote-Sensing Scout
AUTONOMOUS CREW-ASSIST MODE: HIGH-LEVEL CONOPS
R2-S2: Robotic Remote-Sensing Scout
COMMUNICATION ARCHITECTURE
EVA Crew <-> R2-S2:
Moon Base <-> R2-S2:
Moon Base <-> Earth:
Earth <-> R2-S2:
OPERATIONS
AUTONOMOUS CREW-ASSIST MODE APPLICATIONS
R2-S2: Robotic Remote-Sensing Scout
R2-S2 OVERVIEW: POLAR & EQUATORIAL EDITION
R2-S2: Robotic Remote-Sensing Scout
Same incident solar area (same charging time)
Polar
Equatorial
R2-S2 OVERVIEW: CAPABILITIES (PART 1/2)
R2-S2: Robotic Remote-Sensing Scout
R2-S2 OVERVIEW: CAPABILITIES (PART 2/2)
R2-S2: Robotic Remote-Sensing Scout
MERITS, LIMITATIONS, & FUTURE STUDIES
MERITS:
LIMITATIONS:
FUTURE STUDIES:
R2-S2: Robotic Remote-Sensing Scout
REFERENCES
[1] “Artemis Accords: Principles for Cooperation in the Civil Exploration and Use of the Moon, Mars, Comets, and Asteroids for Peaceful Purposes”. NASA. June 2021.
[2] Chang, Kenneth. “Highlights from Richard Branson's Virgin Galactic Flight.” The New York Times, 15 Sept. 2021, https://www.nytimes.com/live/2021/07/11/science/virgin-galactic-launch-richard-branson.
[3] Wall, Mike. “Jeff Bezos Launches into Space on Blue Origin's 1st Astronaut Flight.” Space.com, 20 July 2021, https://www.space.com/jeff-bezos-blue-origin-first-astronaut-launch.
[4] Stein, Vicky. “Inspiration4: The FIRST All-Civilian Spaceflight on SpaceX Dragon.” Space.com, 23 Sept. 2021, https://www.space.com/inspiration4-spacex.html.
[5] Lueders, Kathryn. “Appendix H: Human Landing System, Option A Next Space Technologies for Explorations Partnerships-2.” NASA. April 16, 2021.
[6] Potter, Sean. “NASA Awards Contract to Deliver Science, Tech to Moon.” NASA, 8 Apr. 2020, https://www.nasa.gov/press-release/nasa-awards-contract-to-deliver-science-tech-to-moon-ahead-of-human-missions.
[7] Coleshill, Elliott, et al. "Dextre: Improving maintenance operations on the international space station." Acta Astronautica 64.9-10 (2009): 869-874.
[8] Hiltz, Michael, et al. "Canadarm: 20 years of mission success through adaptation." (2001).
[9] Netti, Vittorio. "Design of an autonomous and teleoperated modular robotic free-flyer for EVA operations." ASCEND 2020. 2020. 4257.
[10] “Presidential Memorandum on Reinvigorating America’s Human Space Exploration Program”. The White House. Dec. 11, 2018.
[11] “Best Practices for Sustainable Lunar Activities.” Moon Village Association. October 19, 2020.
[12] Boroson, Don M., and Bryan S. Robinson. “The Lunar Laser Communication Demonstration: NASA’s First Step Toward Very High Data Rate Support of Science and Exploration Missions.” Space Science Reviews, vol. 185, no. 1, Springer Netherlands, 2014, pp. 115–28, doi:10.1007/s11214-014-0122-y.
[13] Moskowitz, Clara. “Shadows of the Moon Hide 'Fluffy' Dirt & Water Ice.” Space.com, 19 Jan. 2012, https://www.space.com/14284-moon-permanently-shadowed-regions-water-ice.html.
[14] "Radiation Assessment Detector (RAD)." NASA. 22 Apr. 2020. Web. 21 Sept. 2021.
[15] "Velodyne's HDL-32E SURROUND Lidar Sensor." Velodyne Lidar. 15 Sept. 2021. Web. 21 Sept. 2021.
[16] "Quantum 360 Rover Camera." Defender. Web. 21 Sept. 2021.
[17] “Mast-Mounted Camera System (MASTCAM-Z).” NASA, https://mars.nasa.gov/mars2020/spacecraft/instruments/mastcam-z/.
[18] Fong, Terry. "Volatiles Investigating Polar Exploration Rover (VIPER)." West Virginia University Robotics Seminar.
[19] “Mahli.” NASA, 22 Apr. 2020, https://mars.nasa.gov/msl/spacecraft/instruments/mahli/.
[20] "Right-Angle Shaft DC Gearmotor." McMaster-Carr. Web. 21 Sept. 2021.
[21] “Radar Imager for Mars' Subsurface Exploration (RIMFAX).” NASA. Retrieved September 21, 2021, from https://mars.nasa.gov/mars2020/spacecraft/instruments/rimfax/.
BACKUP SLIDES
R2-S2: Robotic Remote-Sensing Scout
R2-S2 TERRAIN HAZARD DETECTION SYSTEM
R2-S2: Robotic Remote-Sensing Scout
ANTENNA SIZING & POWER BUDGET
R2-S2: Robotic Remote-Sensing Scout
R2-S2 Power Budget | |||
Item | Quantity | Power(W) | Source |
Motors | 2 | 0.25 | |
Antenna | 1 | 300 | Calculations |
360 Degree Camera | 1 | 120 | |
LiDAR | 1 | 12 | |
Radiation Sensor | 1 | 4.2 | |
Subsurface Radar | 1 | 9.5 | |
Regolith Drill | 1 | 358 | |
Neutron Spectrometer | 1 | 1.6 | |
Infrared Camera | 1 | 29.56 | |
MastCam-Z | 1 | 17.4 | |
Microscope | 1 | 17.4 | Estimate |
Total | 869.91 | | |
Link Budget for R2-S2 Direct-to-Earth Communications | ||
Parameter | Linear Value | dB Value |
R2-S2 Antenna (Transmitting) |
|
|
Diameter (m) | 0.221257 | - |
Efficiency | 0.7 | - |
Frequency (Hz) | 9.00E+09 | - |
Data Rate (bps) | 4.50E+08 | 86.532 |
Gain (W) | 304.819 | 24.840 |
Transmitted Power (W) | 90 | 19.542 |
Space, Atmospheric, and Line Loss |
|
|
Range (m) | 3.76E+08 | - |
Space Loss | - | -223.043 |
Atmospheric Loss | - | 2.000 |
Line Loss | 0.8 | -0.969 |
DSN Antenna (Receiving) |
|
|
Diameter (m) | 34 | - |
Efficiency | 0.7 | - |
Frequency (Hz) | 9.00E+09 | - |
Gain (W) | 7188 | 68.572 |
Attenuation Loss | - | 3.000 |
Temperature Noise (K) | 200 | 23.010 |
Signal to Noise Ratio |
|
|
Desired Eb/No | - | 10 |
*Green Highlighted Cells are backed-out of Eb/No equation | ||
*Some of these values are estimates to get a rough idea of transmitting antenna diameter | ||
RADIO VS. LASER COMMUNICATION
R2-S2: Robotic Remote-Sensing Scout
Feature | Radio | Lunar Laser Communication Demonstration (LLCD) [12] |
Sensitivity to Atmospheric and Physical Obstruction | Less sensitive (Longer ʎ) | More sensitive (Shorter ʎ) |
Sensitivity to long-distance communication | More Sensitive (Greater diffraction) | Less Sensitive (Less diffraction) |
Beamwidth | Easier to point (Wider beamwidth) | Stricter pointing requirements; however, it has been demonstrated that vibration control systems increase pointing accuracy (Narrower beam width) |
Data Rate/Mass Ratio | Smaller | Larger (Higher frequency means higher data rate, shorter ʎ means smaller apertures and less mass) |
Power Requirements | Larger | Smaller |
Ground Infrastructure | Complete coverage (Deep Space Network) | Complete coverage |
Green = Pros
Red = Cons
RATIONALE FOR COMMS ARCHITECTURE SELECTION
R2-S2: Robotic Remote-Sensing Scout
R2-S2 Rover
Moon Base
Earth
BATTERY PACK DESIGN: APPROXIMATE HEAT TRANSFER MODELS
R2-S2: Robotic Remote-Sensing Scout
EQUATORIAL NIGHTTIME & POLAR OPERATIONS:
EQUATORIAL DAYTIME OPERATIONS:
BATTERY PACK DESIGN: INSULATION SIZING (EQUATORIAL DAYTIME)
R2-S2: Robotic Remote-Sensing Scout
# Batteries & Projected Battery Area | |||
Parameter | Value | Unit | Description |
P | 870 | W | Power required by rover |
t_EVA | 8 | Hrs | EVA time |
b_cap | 111 | Amp-Hrs | Battery capacity |
V | 12 | V | Voltage |
A1 | 0.0516 | m^2 | Area of one battery |
N | 5.2252 | Batteries | Number of batteries needed |
N_ceiling | 6 | Batteries | N rounded up to integer value |
A | 0.3093 | m^2 | Projected area of entire battery pack |
Heat Capacity | |||
Molecule | Mi (g/mol) | mi (kg) | ci (J/kgK) |
Li | 7 | 1.1624E-26 | 3582 |
Fe | 55.84 | 9.27267E-26 | 450 |
P | 30.974 | 5.14347E-26 | 770 |
O4 | 64 | 1.06277E-25 | 920 |
LiFePO4 | 157.814 | 2.62062E-25 | 842.333 |
Daytime Energy Balance | ||||
Parameter | Value | Unit | Description | Source |
Fs | 1368 | W/m^2 | Solar Radiation | - |
A | 0.3093 | m^2 | A_rad = A_cond in this case | Calculation |
Tg | 390 | K | Temperature of the ground | |
Tb,max | 333.15 | K | Max temperature of the battery | |
k_ins | 0.035 | W/mK | Thermal conductivity of insulation | |
eps_ins | 0.9 | - | Emissivity of insulation | |
Sigma | 5.67E-08 | W/m^2K^4 | Stefan-Boltzmann Constant | - |
c_b | 842.333 | J/K | Specific heat capacity of LiFePO4 | Calculation |
t_EVA | 28800 | s | EVA time | - |
m_b | 79.8 | kg | Mass of battery pack | |
L_ins | 0.00040094 | m | Thickness of insulation | Calculation |
| 0.0159 | in | | |
R2-S2: Robotic Remote-Sensing Scout
BATTERY PACK DESIGN: INSULATION SIZING (EQUATORIAL NIGHTTIME)
Nighttime Energy Balance | ||||
Parameter | Value | Unit | Description | Source |
Fs | 1368 | W/m^2 | Solar Radiation | - |
A | 0.3093 | m^2 | A_rad = A_cond in this case | Calculation |
Tg | 95 | K | Temperature of the ground | |
Tb,min | 253.15 | K | Min temperature of the battery | |
k_ins | 0.035 | W/mK | Thermal conductivity of insulation | |
eps_ins | 0.9 | - | Emissivity of insulation | |
Sigma | 5.67E-08 | W/m^2K^4 | Stefan-Boltzmann Constant | - |
c_b | 842.333 | J/K | Specific heat capacity of LiFePO4 | Calculation |
t_EVA | 28800 | s | EVA time | - |
m_b | 79.8 | kg | Mass of battery pack | |
L_ins | 0.00291823 | m | Thickness of insulation | Calculation |
| 0.1159 | in | | |
# Batteries & Projected Battery Area | |||
Parameter | Value | Unit | Description |
P | 870 | W | Power required by rover |
t_EVA | 8 | Hrs | EVA time |
b_cap | 111 | Amp-Hrs | Battery capacity |
V | 12 | V | Voltage |
A1 | 0.0516 | m^2 | Area of one battery |
N | 5.2252 | Batteries | Number of batteries needed |
N_ceiling | 6 | Batteries | N rounded up to integer value |
A | 0.3093 | m^2 | Projected area of entire battery pack |
Heat Capacity | |||
Molecule | Mi (g/mol) | mi (kg) | ci (J/kgK) |
Li | 7 | 1.1624E-26 | 3582 |
Fe | 55.84 | 9.27267E-26 | 450 |
P | 30.974 | 5.14347E-26 | 770 |
O4 | 64 | 1.06277E-25 | 920 |
LiFePO4 | 157.814 | 2.62062E-25 | 842.333 |
BATTERY PACK DESIGN: EQUATORIAL CHARGE TIME
R2-S2: Robotic Remote-Sensing Scout
Solar Power Charge Time (Equatorial) | |||
Parameter | Value | Description | Source |
A (m^2) | 0.724 | Solar Panel Area | CAD Model |
Fs (W/m^2) | 1370 | Solar constant on the Moon | - |
fp | 0.95 | Packing factor | Estimate |
e | 0.2 | Efficiency | Estimate |
d | 0.05 | Various other losses | Estimate |
g (˚C^-1) | 0.001 | Thermal losses | Estimate |
Tref (˚C) | 28 | Reference Temperature | - |
To (˚C) | 116.85 | Max Lunar Surface Temperature | |
P (W) | 163.13 | Power produced | Calculation |
Cap (A-hrs) | 666 | Battery pack capacity | Calculation |
V (V) | 12 | Battery Voltage | |
t (hrs) | 48.992 | Charge time | Calculation |
*Charge time represents when the Sun is directly overhead | |||
BATTERY PACK DESIGN: INSULATION SIZING (POLAR)
R2-S2: Robotic Remote-Sensing Scout
South Pole Energy Balance | ||||
Parameter | Value | Unit | Description | Source |
Fs | 1368 | W/m^2 | Solar Radiation | - |
A | 0.3093 | m^2 | A_rad = A_cond in this case | Calculation |
Tg | 25.15 | K | Temperature of the ground | |
Tb,min | 253.15 | K | Min temperature of the battery | |
k_ins | 0.035 | W/mK | Thermal conductivity of insulation | |
eps_ins | 0.9 | - | Emissivity of insulation | |
Sigma | 5.67E-08 | W/m^2K^4 | Stefan-Boltzmann Constant | - |
c_b | 842.333 | J/K | Specific heat capacity of LiFePO4 | Calculation |
t_EVA | 28800 | s | EVA time | - |
m_b | 79.8 | kg | Mass of battery pack | |
L_ins | 0.00417767 | m | Thickness of insulation | Calculation |
| 0.1659 | in | | |
# Batteries & Projected Battery Area | |||
Parameter | Value | Unit | Description |
P | 870 | W | Power required by rover |
t_EVA | 8 | Hrs | EVA time |
b_cap | 111 | Amp-Hrs | Battery capacity |
V | 12 | V | Voltage |
A1 | 0.0516 | m^2 | Area of one battery |
N | 5.2252 | Batteries | Number of batteries needed |
N_ceiling | 6 | Batteries | N rounded up to integer value |
A | 0.3093 | m^2 | Projected area of entire battery pack |
Heat Capacity | |||
Molecule | Mi (g/mol) | mi (kg) | ci (J/kgK) |
Li | 7 | 1.1624E-26 | 3582 |
Fe | 55.84 | 9.27267E-26 | 450 |
P | 30.974 | 5.14347E-26 | 770 |
O4 | 64 | 1.06277E-25 | 920 |
LiFePO4 | 157.814 | 2.62062E-25 | 842.333 |
BATTERY PACK DESIGN: POLAR CHARGE TIME
R2-S2: Robotic Remote-Sensing Scout
Solar Power Charge Time (Polar) | |||
Parameter | Value | Description | Source |
A (m^2) | 0.746 | Solar Panel Area | CAD Model |
Fs (W/m^2) | 1370 | Solar constant on the Moon | - |
fp | 0.95 | Packing factor | Estimate |
e | 0.2 | Efficiency | Estimate |
d | 0.05 | Various other losses | Estimate |
g (˚C^-1) | 0.001 | Thermal losses | Estimate |
Tref (˚C) | 28 | Reference Temperature | - |
To (˚C) | 116.85 | Max Lunar Surface Temperature | |
P (W) | 168.08 | Power produced | Calculation |
Cap (A-hrs) | 666 | Battery pack capacity | Calculation |
V (V) | 12 | Battery Voltage | |
t (hrs) | 47.548 | Charge time | Calculation |
*Charge time represents when the Sun is directly on the lunar horizon | |||