Arkansas Space Grant Consortium2013-4 NASA Research Infrastructure Development Team
22nd ASGC Symposium Hot Springs, April 7, 2014
Adam Huang, Principal InvestigatorUniversity of ArkansasMechanical Engineering Department863 W. Dickson St., MEEG 105Fayetteville, AR 72703479-575-7485, [email protected]
Ed Wilson, Co-InvestigatorHarding UniversityDepartment of ChemistryBox 10849/915 East Market StreetSearcy, AR 72149-0849501-279-4513, [email protected]
Yupo Chan, Co-Investigator
University of ArkansasDepartment of Systems Engineering (EIT 544)
2801 South University AveLittle Rock, AR 72204-1099
501-569-8926, [email protected]
Development of Critical Technologies for Formation and Proximity Flight with Nano-Satellites
Satellite, Space Station
ISS ~180,000 kg (Nov 2005)
MILSTAR ~4,500 kg
Femto? Pico Nano Micro100kg10kg1kg0.1kg
AFRL XSS-10 ~29 kg
Aerospace PICOSAT1~300 grams
SSTL GSTB-V2A 600 kgSSTL SNAP-1 6.5 kg
What is a Nano-satellite?
Project ObjectivesMicro-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.
University Grade Nanosats-CubeSats
Stanford
Pumpkin™ Kits
6U (ARAPAIMA)
Project Description
thrusters
thrusters
Vision Scanning
LED Beacon
LED Beacon
LED Beacon
LED Beacon
• Two cooperating nano-satellites in formation flight from 50m-1km range.• Reference CubeSat design based on NASA Marshall Space Flight Center’s
6U Bus.
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)
SPRITE Lab Proximity Ops CubeSat Demonstrator (TIP)
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).
Vapo
r/Ga
s
Vapor Membrane with Nanopores
Solenoid Valve
Aqueous Propellant
Propellant Tank
TTemperature Sensor
PPressure Sensor
Schrader Valve
MEMS 2-Phase SeparatorCoarse Filter
MEMS Heater/Temperature Sensor
Solenoid Valve Solenoid Valve
Fluid Mixer
T
Temperature Sensor
MEMS Nozzle
P
Pressure Sensor
• Water/Propylene Glycol– non-toxic– PG disrupts hydrogen bonding in
water– Theoretical Isp 85-108s
• Why not just PG?– High boiling point (188°C), affects
electronics– In-situ resource utilization
Propellant Selected
University of Arkansas 2
Previous Work
• Propylene Glycol Research
• AFM Nanolithography Research– Found/Reviewed
Manuals
• Journal Paper Review – Will be submitted Today
-55
-50
-45
-40
-35
-30
-25
-20
-15
-10
-5
00 25 50 75 100
Free
zing
Poin
t (°C
)
Weight Percent Solute
Freezing Point Depression(Mixed with Water)
Propylene Glycol
Ethylene Glycol
Specific Impulse (Water-PG Ratio)
Fraction PG
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
Acknowledgments
• Students:John Lee, Mustafa Bayraktar, Maurisa Orona, and Drew Couch.
• Arkansas Space Grant Consortium 2012-13 NASA RID
