PIRARUCU MARS MOONS PROSPECTOR

AE427 SECTION 02

PRELIMINARY SPACECRAFT DESIGN

ERAU AEROSPACE ENGINEERING

2 OCTOBER 2014

TEAM

• Attitude and Orbit Control Systems Allen, Brett

• Communications Williams, Sarah

• Mission Planning Bourke, Justin

Casariego, Gabriela

Smith, Gregory

• Power Maier, Margaret

• Propulsion Gosselin, Steven

• Science and instrumentation Melchert, Jeanmarie

• Command and data handling Reis, Leslie

• Structures Hiester, Evan

Patel, Chitrang

Snow, Travis

• Teaching Assistant Franquiz, Francisco

• Instructor Udrea, Bogdan

OUTLINE

• RASC-AL competition

• Mars Moons Prospector

• Science and science traceability matrix

• Concept of operations

• Preliminary mission configuration

• Open questions

REVOLUTIONARY AEROSPACE SYSTEMS CONCEPT – ACADEMIC LINKAGE1 (RASC-AL) • Goals:

• Looking for innovation in NASA exploration approaches and strategies

• Looking for evolutionary architecture development to:

• Reduce costs

• Promote future human space exploration

• Improve safety

• Sustainable space exploration programs

• Collaboration with commercial and international partners

1 http://nia-cms.nianet.org/RASCAL/Program-Info/RASC-AL-THEMES.aspx

MARS MOON PROSPECTOR MISSION

• Theme:

• Design a robotic mission that interrogates one or both [Martian] moons to fill in strategic knowledge gaps

• Support of an ISRU driven human Mars architecture, including manned missions to the moons

• Constraints:

• Must be launched on a single launch vehicle in 2022

• Cost no more than $300 million, exclusive of launch vehicle

• Primary mission must be completed by 2025

• Extended missions are encouraged if practical

SCIENCE TRACEABILITY MATRIX (1/3) Strategic Knowledge Gaps

Science/Engineering Objectives

Measurement Requirements

What are the origins of Phobos?

Objective 1: Survey general composition

Determine the density, composition, elemental make-up and radiation concentration

What are the environmental characteristics of Phobos?

Objective 2: Topography and stratigraphy

Determine the surface topography, internal substructures and geological history

Is human exploration feasible?

Objective 3: Space operational hazards

Determine dust density in orbit, gravitational field, radiation from surface scattering and regolith mechanical properties

References Darlene, L. (2012). MEPAG 2012 Goal IV update. Britt, D. T. (2014, March 03). Planetary and Space Science. Retrieved September 26, 2014, from Science Direct: http://www.sciencedirect.com/science/article/pii/S0032063314001123 NASA. (n.d.). Small Body Assesment Group. Retrieved October 2, 2014, from http://www.lpi.usra.edu/sbag/findings/

SCIENCE TRACEABILITY MATRIX (2/3) Measurements Candidate Instrumentation

Densities and composition Sample Analysis at Mars (SAM)

Composition and concentration of elements and minerals

Chemistry and Mineralogy instrument (ChemMin)

Planetary Instrument for X-Ray Lithochemistry (PIXL)

Energetic particle spectral analysis Radiation Assessment Detector (RAD)

Surface topography/landing sights Cameras

Laser rangefinder

Radar

Geological underground structures Radar Imager for Mars Sub-Surface Exploration (RIMFAX)

Global shape and rotational state Laser rangefinder

University of Arizona’s Surface Stereo Imager (SSI)

SCIENCE TRACEABILITY MATRIX (3/3) Measurements Candidate Instrumentation

Particle density Cosmic Dust Analyzer (CDA)

Gravitational field Radio Science Subsystem

Accelerometer

3-axis gradiometer

Regolith composition Chemistry and Mineralogy instrument (ChemMin)

Sample Analysis at Mars (SAM)

Planetary Instrument for X-Ray Lithochemistry (PIXL)

Passive ground radiation detection Radiation Assessment Detector (RAD)

CONCEPT OF OPERATIONS

• Multi-spacecraft mission:

• Mothership:

• Bus provides power, propulsion, comms, attitude control

• Carries 12 CubeSats

• Carries instruments

• CubeSats:

• A Team

• Surface science instruments

• Seven Dwarves

• Surface sample retrieval and carrier to mothership

• Dock and refuel with the mothership

PRELIMINARY MISSION CONFIGURATION

• Launch vehicle selection: • Falcon Heavy (Projected Values):

• 12,000kg Payload

• $85 million

• Structure design: • Evolved Expendable Launch Vehicle Secondary Payload

Adapter Ring (ESPA):

• CubeSat ring

• Propulsive and power ring

• Instrument ring

• Communications: • Ka-band for Earth communications

• Net-T network for inter-spacecraft communications

PRELIMINARY STRUCTURE

CubeSat 24cmx23cmx26cm

ESPA ring: 157.48 cm (Diameter)

Lightband ring: 20.32cm (Diameter)

PIRARUCU MARS MOONS PROSPECTOR

Open Questions