Arkansas Space Grant Consortium 2013-4 NASA Research Infrastructure Development Team 22 nd ASGC...
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Arkansas Space Grant Consortium 2013-4 NASA Research Infrastructure Development Team 22 nd ASGC Symposium Hot Springs, April 7, 2014 Adam Huang, Principal
Arkansas Space Grant Consortium 2013-4 NASA Research
Infrastructure Development Team 22 nd ASGC Symposium Hot Springs,
April 7, 2014 Adam Huang, Principal Investigator University of
Arkansas Mechanical Engineering Department 863 W. Dickson St., MEEG
105 Fayetteville, AR 72703 479-575-7485, [email protected] Ed Wilson,
Co-Investigator Harding University Department of Chemistry Box
10849/915 East Market Street Searcy, AR 72149-0849 501-279-4513,
[email protected] Yupo Chan, Co-Investigator University of
Arkansas Department of Systems Engineering (EIT 544) 2801 South
University Ave Little Rock, AR 72204-1099 501-569-8926,
[email protected] Development of Critical Technologies for Formation
and Proximity Flight with Nano-Satellites
Slide 2
Satellite, Space Station ISS ~180,000 kg (Nov 2005) MILSTAR
~4,500 kg Femto?PicoNanoMicro 100kg 10kg1kg0.1kg AFRL XSS-10 ~29 kg
Aerospace PICOSAT1 ~300 grams SSTL GSTB-V2A 600 kg SSTL SNAP-1 6.5
kg What is a Nano-satellite?
Slide 3
Project Objectives Micro-Propulsion System (MPS): UAF is tasked
to develop a micro-propulsion system for nano-satellites that is
non- toxic, non-flammable, and low- or non-pressurized at launch
conditions. SAtellite Detection And Ranging Systems (SADARS):
Harding U. is tasked to design and implement a satellite detection
system, using light emitting diodes (LEDs), that will be used to
locate and uniquely identify each agent of a fleet of cooperative
nano-satellites. UALR is tasked to design a vision-based system for
the nano-satellite fleet for ranging and formation keeping.
Slide 4
University Grade Nanosats-CubeSats Stanford Pumpkin Kits 6U
(ARAPAIMA)
Slide 5
Project Description thrusters Vision Scanning LED Beacon Two
cooperating nano-satellites in formation flight from 50m-1km range.
Reference CubeSat design based on NASA Marshall Space Flight
Centers 6U Bus.
Slide 6
NASA MSFC/UA 6U CubeSat testbed with 3-axis propulsion system
3-axis DOF (Yaw, Side, Axial) 8 Nozzles 6U SPRITE Lab Proximity Ops
CubeSat Demonstrator (TIP)
Slide 7
Slide 8
Atmospheric Pressure Cold-Gas Thruster The thruster pressure is
driven by the surface tension at the nanopore membrane, which can
be controlled by the electrolyte pressure and the heating of the
membrane. Propellant pressure at launch and storage is atmospheric
(vapor pressure). Vapor/Gas Vapor Membrane with Nanopores Solenoid
Valve Aqueous Propellant
Slide 9
Water/Propylene Glycol non-toxic PG disrupts hydrogen bonding
in water Theoretical I sp 85-108s Why not just PG? High boiling
point (188C), affects electronics In-situ resource utilization
Propellant Selected
Slide 10
Specific Impulse (Water-PG Ratio) Fraction PG
Slide 11
SADAR Processing Unit http://www.logicsupply.com Need to remove
fan and add thermal management devices for space applications.
Currently being repackaged as a BallonSat payload for flight test
demonstration. Intel Next Unit of Computing (NUC, D54250WYB) as the
SADAR subsystem processor. http://techreport.com
Slide 12
Acknowledgments Students: John Lee, Mustafa Bayraktar, Maurisa
Orona, and Drew Couch. Arkansas Space Grant Consortium 2012-13 NASA
RID
