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1N Hydrazine
Thruster

Close Overview 1 N Hydrazine Thruster 20 N Hydrazine Thruster 400 N Hydrazine Thruster

 

1N Monopropellant Hydrazine Thruster

For precision attitude, trajectory and orbit control of small and medium size satellites and spacecraft.

 

4N Bipropellant Thruster
1N Hydrazine Thruster
 

General Description

The 1N monopropellant hydrazine thruster is used for attitude, trajectory and orbit control of small and mid-size satellites and spacecraft.

 

The thruster is typically used in our own propulsion systems and is also available separately for use in our customers' propulsion systems. More than 500 units of this thruster operate successfully in space.

 

The 1N thruster was derived from the space proven 0.5N thruster, of which some 165 units were flown on OTS-2, ECS, Marecs, Telecom-1, Skynet 4 and NATO-IV. Since these applications, the thruster has undergone multiple refinements, especially in achieving a minimum possible production cost. Today, this unit may be regarded as a low cost thruster

 

Propellant supply to the thruster is provided by a two stage flow control valve comprising two identical monostable, normally closed valves placed in series within a single housing.

 

Additionally each thruster is equipped with an internal redundant catalyst bed heater and with thermal insulation to guarantee optimum start up. All materials used in the valve and thrust chamber assembly have been selected for compatibility with hydrazine propellant.

 

Thrust is generated when the control valve is commanded to open causing propellant to be fed to the thrust chamber where a  decomposition reaction takes place within the catalyst bed.

 

The thruster is also designed to serve as a heat barrier for protecting the flow control valve and the spacecraft structure from improper high temperatures. In addition, the thruster is qualified for multiple cold starts.

 

Thruster Dimensions and Interfaces

Thruster dimensions and interfaces drawings can be found from the links below:

 

Elevation
Plan
Cut-Out

 

 

Integrated 1N hydrazine thruster
Integrated 1N Hydrazine Thruster

 

1N Monopropellant Thruster Characteristics
Characteristics
Values
Thrust, Nominal
1N
Thrust Range
0.320 - 1.1N
Specific Impulse, Nominal
220 s
Specific Impulse, Range
200 - 223 s
Mass Flow Rate, Nominal
0.44 g/s
Mass Flow Rate, Range
0.142 - 0.447 g/s
Inlet Pressure Range
5.5 - 22 bar
Minimum Impulse Bit
0.01 - 0.043 N
Nozzle Expansion Ratio (by area)
80
Mass Thruster with Valve
290 g
Propellant
Hydrazine (N2H4), High Purity Grade


Characteristics
Values
Total Impulse
135,000 Ns
Cycle Life
59,000 cycles
Propellant Throughput
67 kg
Single Burn Life
12 hours
Accumulated Burn Life
50 hours
No of Cold Starts < 10° C
10

 

 

 

HERITAGE - 1N Hydrazine Thrusters
Spacecraft
Launch
Globalstar
1997 -2000
Jason 1 (Proteus)
2001
Rocsat - 2
2004
Cosmo - Skymed 1
2005
Galileo GSTB
2006
Corot (Proteus)
2006
Calipso (Proteus)
2006
Cosmo - Skymed 2
2006
TerraSAR - X
2007
Radarsat - 2
2007
Cosmo - Skymed 3
2007
Jason 2 (Proteus)
2008
Theos
2008
Herschel Planck
2009
SMOS (Proteus)
2009
Tandem-X
2010
Spacecraft
Launch
Alsat 2A
2010
Alsat 2B
2010
Cosmo - Skymed 4
2010
Elisa - 1
2011
Elisa - 2
2011
Elisa - 3
2011
Elisa - 4
2011
Pleiades HR1
2011
SSOT
2011
AstroTerra 1
2012
Pleiades HR2
2012
Jason 3
2013
Vietnam - 1
2013
AstroTerra 2
2014
KRS
2014
Sentinal 2A
2015
Spacecraft
Launch
Perusat-1
2017
Merlin
2018
MN-35-1
2017
SEOSAR (paz)
2018
SEOSAT (Ingenio)
2018
Taranis
2018
Sentinel 2B
2017
Sentinel 5P
2018
CSO - 1
2018
CSO - 2
*
CSO - 3
*
 
 
 
 
 
 
 
 
 
 
Hydrazine Thrusters
(PDF Brochure)

Hydrazine Thruster Brochure (pdf)

This brochure is available to view online from where it may be downloaded.

 

Get the latest version of the free Adobe Acrobat Reader  Adobe Reader


 If you require the printed version of this brochure, or more detailed information about this product please contact us.

 

See the complete list of our space propulsion brochures available for download.