Delta 50-820 User Manual Page 5

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Mueller, Ziemer, Hofer, Wirz, O’Donnell 5
Survey of Micro-Thrust Propulsion Options
Cube Sat - 5’th Annual Developers Workshop 2008
Description:
Status:Application:
JPL Hydrazine Milli-Newton Thruster (HmNT)
Miniature hydrazine thruster development by JPL.
Drops minimum I-bit over conventional MR-103 by factor
of >100 to 50 μN-s by mating very small thruster with
small flow passages to a fast acting valve.
Significant mass (5x) and size (10x) reduction over SoA
hydrazine thruster technology.
Performance data (compared to Aerojet MR-103):
TRL 3-4. Laboratory development.>20-30 kg S/C attitude control
Pulsed mode operation demonstrated in 2007 in
relevant environment (vacuum) on JPL micro-Newton
thrust stand. Continuous firing testing planned for
2008.
Application for attitude control on conventional
spacecraft requiring ultra-fine attitude control
(reaction wheel replacement), or microsats (approx. >
20-30 kg) depending on mission deadband
requirements.
Well suited for > 20-30 kg spacecraft ACS where I-bit
requirements may be low (depending on deadband
requirement) and a liquid system is needed (low
leakage concerns, low tank mass).
Thruster may not be usable on very small
microspacecraft (< 20-30 kg) where power is limited.
HmNT Feedsystem
installed
on JPL
Milli-Newton
Thrust Stand
Comparison
Parameter
Aerojet MR103H
Current SOA
HmNT
Thrust 0.9 N 0.020 N
Envelope Volume 94 cc 8 cc
Valve Power 5/1 W 8/2 W
Cat Bed Heater 1.9 0.25 W (est.)
Mass 195 g 40 g
Min. Impulse 5,000 µNįsec 50 µN įSec
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