Micro liquid mono-propellant propulsion

 

 

The European Union is going to ban the use of the toxic satellite propellant Hydrazine as early as 2021. Instead of the mono-Hydrozine propellant the 'green' ones can be suggested.  
The Liquid Mono-Propellant Propulsion (LMPP) has essential working principle of the mono-propellant thruster uses ADN/HAN-based propellants with catalytic decomposition. There are jet systems using thermal decomposition for ADN/HAN. The 'green' propellants have some advantages before Hydrozine: safer handling (low toxity), low freezing point (up to -30C), high density (1.4 g/cm3), higher specific impulse Isp (up to 250...260 s), less cost.
We propose the use HAN-based propellants developed in LAJP and related propulsion systems using liquid 'green' mono-propellant.

 

 Liquid Mono-Propellant Propulsion

 

 

 

 

Liquid Mono-Propellant Propulsion

Parameters     1N Motor   3N Motor   5N Motor   10N Motor
                   
Propellant     HAN-based   HAN-based   HAN-based   HAN-based
                   
Operation power consumption, W     ~8   ~16    ~24   ~50
                   
Specific impulse, s     230 … 260    230 … 260    240 … 260    240 … 260
                   
Thrust, N     1N   3N   5N   10N
                   
Dry weight of reaction
control system, kg
    ~4.5     ~11     ~16     ~30
                   

 

 
 
 
 
 
 

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