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1 Lunar Lava Tube Survey Mission 4/5/2016 Rohan Deshmukh Swapnil Pujari Giovanny Guecha Advisor: Professor David Spencer

Lunar Lavatube AIAA Presentation_Final

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Page 1: Lunar Lavatube AIAA Presentation_Final

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Lunar Lava Tube Survey Mission

4/5/2016

Rohan Deshmukh

Swapnil Pujari

Giovanny Guecha

Advisor: Professor David Spencer

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About Us

Rohan Deshmukh Swapnil Pujari Giovanny Guecha

School Georgia Institute of

Technology

Georgia Institute of

Technology

Georgia Institute of

Technology

Major Aerospace Engineering Aerospace Engineering Aerospace Engineering

Hometown Fairfax, VA Alpharetta, GA Kennesaw, GA

Year 4th Year 4th Year 3rd Year

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Presentation Outline

•Concept Motivation

•Mission Overview

•Flight System Overview

•Technical Resource Budgets

•Summary

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Global Exploration Roadmap (GER)

•A vision for globally coordinated human and robotic space exploration

focused on the solar system destinations where humans may someday

live and work

•Calls for sustainable human exploration of the Moon, near-Earth

asteroids, and Mars.

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Image Source: The Global Exploration Roadmap, 2011

Option 1: Asteroid Next

Option 2: Moon Next

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Detection of Buried Empty Lava Tubes Using

GRAIL Gravity Data

•Gravity Recovery and Interior Laboratory (GRAIL) provided high-

resolution lunar gravity data through NASA’s Discovery Program

•Analysis of the GRAIL data has provided insight into the presence and

extent of empty subsurface lava tubes

–Ref: Chappaz, Melosh, Howell, and Milbury, “Detection of Buried Empty Lava Tubes

Using GRAIL Gravity Data,” 47th Lunar and Planetary Science Conference, Abstract No.

1509, 2016.

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nus Iridum. The pit itself is approximately 20 m deep

with central hole of 70 m x 33Dde m and an outer fun-

nel of 110 x 125 m. The maps overlay local topogra-

phy, and the color represents the signed magnitude

corresponding to the largest eigenvalue of the Hessian

derived from the gravitational potential. Both free-air

and

Figure 2: Local gradiometry (top), cross-correlation

(bottom) maps for free-air (left), Bouguer (center), and

free-air/Bouguer correlation (right) for Sinus Iridum

pit.

Bouguer eigenvalue maps show gravity low in the vi-

cinity of the lunar pit. The correlation map distinctively

marks the region near the pit as a region of mass deficit

with a potential access to an underground buried empty

lava tube. The cross-correlation technique applied is

shown in the second row of Figure 2. The schematic

shows that for both free-air and Bouguer cross-

correlation maps, the anomaly is detected in the same

region as via the gradiometry technique. Both tech-

niques provide evidence for a subsurface anomaly in

the vicinity of the newly found lunar pit.

Free-air and Bouguer Gravity Anomaly: Contin-

uing the validation of the subsurface anomaly, regional

free-air and Bouguer gravity maps are generated. Fig-

ure 3 illustrates local maps for the free-air gravity on

the left and Bouguer gravity on the right. On closer in-

Figure 3: Local free-air (left) and Bouguer (right) grav-

ity map for Marius Hills skylight with overlay of to-

pography.

spection, the two gravity maps demonstrate a gravity

low surrounding the rille along which the Marius Hills

skylight lies. The Bouguer low adds to the evidence

suggesting a potential buried empty lava tube along the

rille with an access through the Marius Hills skylight.

Similar free-air and Bouguer gravity analysis is car-

ried out for the newly found pit in Sinus Iridum as

shown in Figure 4. The color bar is adjusted to visually

Figure 4: Local free-air (left) and Bouguer (right) grav-

ity map for the newly found lunar pit in Sinus Iridum

with overlay of topography.

distinguish the region in proximity to the lunar pit in

Sinus Iridum. The gravity low shown in both the free-

air and Bouguer gravity suggest an underground mass

deficit in the vicinity of the pit. Although the pit itself

is relatively small, it can potentially be an access to a

larger underground structure as evident from the gravi-

ty maps and the two detection strategies. Additional

maps have also been studied to identify a possible con-

nection of this anomaly to a buried empty lava tube

structure.

Conclusions: Two strategies are employed to de-

tect small scale lunar features: one based on gradiome-

try and a second one that relies on cross-correlation of

individual tracks. The two methods have previously

been validated with a known surface rille, Schröter’s

Valley. Then, a signal suggesting an unknown buried

structure is observed in the vicinity of Marius Hills

skylight that is robust enough to persist on a map creat-

ed from an average of several hundred simulations. A

similar signal is also observed in the vicinity of the

Sinus Iridum pit suggesting a possible subsurface mass

deficit.

The technique has been extended to cover the vast

mare regions. Multiple new candidates for buried emp-

ty lava tube structures have been discovered as a part

of this study. Some of the candidates bear no surface

expression but similar signals are observed from both

the detection strategies as observed for candidates with

surface expressions, i.e., skylights/pits.

References:

[1] Zuber et al. (2013) SSR 178, 1.

[2] Chappaz et al. (2014) AIAA 2014-4371.

[3] Haruyama et al. (2009), GRL 36, L21206.

1509.pdf47th Lunar and Planetary Science Conference (2016)

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Applications to Human Exploration

• Empty lava tubes represent

potential sites for human

habitation, providing natural

protection from:

– Cosmic radiation

– Micrometeorite impacts

– Diurnal temperature

extremes

• Lunar lava tubes may be stable

up to about 5 km wide

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Image Source: Building a Lunar Base with 3D Printing, ESA 2013

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Sinuous Rilles & Skylights

•Surface features associated with

lunar lava flow include sinuous rilles

and skylights

•Sinuous rilles are channel-like

depressions formed when lava tubes

collapse

–Lunar rilles can be 30-50 times

larger than terrestrial analogs

•Skylights are collapsed openings into

empty caverns

–Potential access points to empty lava

tubes

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Schroeter Vallis sinuous rille captured from

orbit during Apollo 15 mission

Image Source: Buried Empty Lava

Tube Detection with GRAIL Data,

2014

Marius Hills Skylight

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Mission Objectives

•Survey the depth, volume, and extent of subsurface empty lunar lava

tubes

•Provide high resolution surface topography of regions containing

sinuous rilles associated with subsurface lava tubes

–Direct measurements of skylights and depth of lava tubes below skylights

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Image Source: Lava tubes safe enough for Moon base, 2015

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Mission Concept

•Orbiter/lander combination

–Orbiter equipped with visible camera, ground penetrating radar

(GPR) and LIDAR

–Lander equipped with GPR and visible camera

–Telecom relay from lander through orbiter

•Spaceflight, Inc. SHERPA 2200 (derived from ESPA Grande) is

utilized as a carrier vehicle, hosting

–Orbiter & payload

–Lunar tensegrity lander & payload

–Lunar Orbit Insertion (LOI) module

–Deorbit module

•Targeted launch on NASA EM-2

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Trans-Lunar Orbit Lunar Orbit Insertion Lunar Parking Orbit

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1) Launch

from EM-2

4) LOI

Burn

5) Orbit Trim

Maneuvers:

2 Days

2) Deployment from L/V

Duration to Lunar Orbit: 5 Days

6) Elliptical Lunar

Parking Orbit

hp: 5 km

ha: 50 km

inc: 15.4°

3) Trajectory Correction

Maneuver (TCM)

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1. Disposal State

Trajectory

2. LOI: ΔV = 493 m/s

3. Post-LOI Orbit Propagated to

Apoapsis (10,000 km)

4. Trajectory Propagated

to Periapsis

5. PLM-1: Periapsis

Anti-Velocity Burn

ΔV = 500 m/s

7. PLM-2: Periapsis Anti-

Velocity Burn ΔV = 242 m/s

6. PLM-1 Orbit with 250 km

periapsis altitude

8. PLM-2 Orbit with

50 km periapsis altitude9. PLM-3: Periapsis

Anti-Velocity Burn

ΔV = 69 m/s

10. 5 x 50 km

Science Orbit

Elliptical Capture Maneuvers – STK Analysis

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Tensegrity Lander Entry, Descent, and Landing

Altitude: 5 km

1. Orbiter & Lander

Separation

∆𝑉 = −1190 𝑚/𝑠

Altitude: 10 m

2. De-orbit Burn

4. Powered Descent

7. Backshell Flyaway

3. Backshell

Reorientation

𝑉𝐿 = 0𝑚/𝑠

5. Tensegrity Deployment

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Altitude: 3 km

∆𝑉 = −637 𝑚/𝑠

∆𝑉 = −100 𝑚/𝑠

6. Tensegrity TDZ

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Orbiter Overview

Payload•GPR•LIDAR•Visible Camera

S/C Bus•X-Band Antenna•X-Band Transceiver•UHF Antenna•UHF Transceiver•3-axis attitude control•Solar Panels•Cold Gas Thruster

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LIDAR

Visible

Camera

GPR

** CAD Model used for Visual Representation Only **Image Source: Prox-1 CAD

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Tensegrity Lander Overview

Top Plate:

•GPR Electronics

•Visible Camera

•UHF Antenna

•UHF Transceiver

•Gimbal System

•C&DH

•Battery, PDM

• IMU

•Thermal Control

Bottom Plate:

•GPR Antenna

Mass Ratio of Tensegrity to

Payload vs Impact Landing Velocity

17*CAD Model used for Visual Representations*

Image Source: Julian Rimoli

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Tensegrity Structure

•Light weight, mechanically stable, and

loadbearing structure under extreme

deformation

•Alternative to Airbag EDL system

•Reduces complexity, weight, costs, and

form factor for launch

•Currently researched/developed by Dr.

Julian Rimoli – Georgia Tech

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Ground Penetrating Radar

Orbiter GPR (Analogous to SHARAD-MRO/KAGUYA)

• Send electromagnetic waves into the ground and

detect the reflected signals to reveal subsurface

structure and composition

• Uses an FM/CW radar technique in High

Frequency range

• Survey the lunar crust up to kilometers of depth

Lander GPR (Analogous to RIMFAX-Mars 2020 Rover)

• Successfully used by Apollo 17 (1972) and the

Chinese lunar rover Yuto (2014)

• RIMFAX (Mars 2020) will image the subsurface

stratigraphy to maximum depths of 10 to 500

meters, with vertical resolutions of 5 to 20 cm

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** Images used for Visual Representations **

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SHERPA Tug - Overview

•Developed by Spaceflight, Inc.

•Built upon existing Spaceflight

Secondary Payload System

(SSPS)

–Tested on Falcon 9 in 2013

•Customized ESPA Grande Ring

–Payload Capacity: 1,500 kg

–ΔV capability: > 2.2 km/s

–Integrated ADCS, Power, Comms,

and Avionics

•Future testing in 2016/2017

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SHERPA Tug – Propulsion Performance

Sherpa ΔV Performance vs. Payload Mass

SHERPA 2200

• Bi-propellant propulsion system

• NTO/MMH Propellant

• Four 90N thrusters

734 kg

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SHERPA Tug – Payload Capabilities

• Five 24” Ports available on ESPA

Grande:

– 1 Port LOI Module

– 1 Port Deorbit Module

– 1 Port for Orbiter

– 1 Port for Tensegrity System

• Payload Constraints:

– 39” X 45” X 49” volume

constraint

– 300 kg mass constraint per port

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Orbiter

LOI

Module

Tensegrity

Lander System

Deorbit

Module

ESPA Grande Ring

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Delta-V Budget

Maneuver # Description ΔV (km/s)Propulsion

System

6 De-orbit 1.190De-orbit

Module

7Rocket Assisted

Deceleration Burn0.637 SHERPA 2200

8 Backshell Fly-away 0.100 SHERPA 2200

CBE Total (km/s) 1.927 -

Segment ΔV (km/s)

TCM, Lunar Orbit

Insertion

& Orbit Trim

1.324

Deorbit & Descent 1.927

System Margin (%) 25

MEV Total (km/s) 4.064

Maneuver # Description ΔV (km/s)Propulsion

System

1 TCM 0.020 SHERPA 2200

2 LOI 0.493 LOI Module

3 PLM-1 0.500 SHERPA 2200

4 PLM-2 0.242 SHERPA 2200

5 PLM-3 0.069 SHERPA 2200

CBE Total (km/s) 1.324 -

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Propulsion System ΔV (km/s)

SHERPA 2200 1.568

LOI Module 0.493

Deorbit Module 1.190

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Mass Equipment List

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Sherpa PayloadsUnit CBE Mass (kg)

QTYCBE Mass

(kg)Notes

Orbiter 75 1 75 ~Prox-1 Mass

LOI Module 263 1 263 Orbital ATK Star 26C (SRM)

De-orbit Module 218 1 218 Orbital ATK Star 24 (SRM)

Tensegrity 1.2 1 1.2 0.04 Payload/Tensegrity Ratio

Lander Payload 30 1 30 ~24U mass

CBE Total Mass (kg) 587

System Contingency 25%

MEV Payload Mass (kg) 734

Margin (kg) 766

MPV Sherpa Payload Mass (kg) 1500

Orbital ATK Star 24 (SRM)

Orbital ATK Star 26C (SRM)

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Summary

•The Lunar Lava Tube Survey mission will provide direct observations

to confirm the analytical finding of empty subsurface lava tubes, and

will characterize their depth, volume, and extent.

–Empty lava tubes provide natural protection from radiation,

micrometeorites, and diurnal temperature extremes, and represent

potential “safe zones” for future human habitation

•Through utilization of the SHERPA 2200 as a carrier vehicle for small

spacecraft and solid rocket propulsion modules, a highly capable

orbiter/lander combination can be delivered to the Moon at low cost

•Tensegrity lander concept offers robust landing capability for small

lunar payloads

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Image Source: Diversity of Basaltic Lunar Volcanism, Lunar Reconnaissance Orbiter, ASU

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Proposed Organizational Roles

•NASA Marshall Spaceflight Center–Project management, project system engineering, mission assurance, integration & testing,

mission operations

–SHERPA 2200 interface

–LOI & Deorbit modules

•Purdue University (Jay Melosh, Kathie Howell, Dave Spencer)–Mission design, flight system engineering, payload system engineering

–Orbiter, orbiter payload

–Lander payload

–UHF comm system (lander/orbiter)

•Georgia Tech (Julian Rimoli, Brian Gunter, Grady Tuell)–Tensegrity Lander

–LIDAR

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GER - Moon

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Image Source: The Global Exploration Roadmap, 2011

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Space Exploration Key Supporting Objectives

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Source: The Global Exploration Roadmap, 2011

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References

1. https://www.nasa.gov/pdf/284273main_Radiation_HS_Mod1.pdf

2. http://www.lpi.usra.edu/publications/books/lunar_sourcebook/pdf/Luna

rSourceBook.pdf

3. http://www.kinetics.nsc.ru/chichinin/books/spectroscopy/Stuart04.pdf

4. http://pds-smallbodies.astro.umd.edu/holdings/di-c-hrii_hriv_mri_its-6-

doc-set-

5. http://www.planetary.brown.edu/pdfs/4309.pdf

6. http://onlinelibrary.wiley.com/doi/10.1029/93JE02604/pdf

7. http://spaceflightnow.com/news/n1212/13grail/#.Vv6X0U8rJD8

8. http://www.bbc.com/news/science-environment-31953052

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