Monopropellant
Thrusters

Standard Models
1N Model CHT 1
20N Model CHT 20
400N Model CHT 400

Heritage Thrusters
0.5N Model CHT 0.5
2N Model CHT 2
5N Model CHT 5
10N Model CHT 10

1 N Monopropellant Thruster Model No CHT - 1N

1 N Monopropellant Thruster: Model No CHT-1N

Designed for precision attitude, trajectory and orbit control of small satellites and deep space probes.

The 1 N thruster uses the storable propellant hydrazine N2O4 and is designed for both long term steady state and pulse mode operation.

The thruster was derived from the space proven 0.5 N 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, the CHT-1N may be regarded as a low cost thruster.

The thruster operates over a wide pressure range and is thus ideal for blow down propulsion systems.

The combustion chamber and nozzle are manufactured from Haynes 25 alloy. The structure is also designed to serve as a heat barrier for protecting both the propellant valve and spacecraft structure.

An internally redundant catalyst bed heater and thermal insulation guarantees optimum start up conditions. In addition, the thruster is qualified for multiple cold starts.

Thruster valves are of the dual seat solenoid type, produced by Astrium and also by external partners. The solenoids operate at a nominal valve voltage of 28 volts DC and are mechanically and electrically decoupled from each other. Thruster performance is identical for both Astrium and partner produced dual seat valves.

 

1 N Monopropellant Thruster - Model No CHT-1N

Characteristics Values Thrust, Nominal 1 N Thrust Range 0.320 - 1.1 N 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 Supplied Components   Catalyst Solvay, Belgium: KC 12 GA Catalyst Bed Heater Cartridge Heater with redundant heating elements. Power: 6.4 W Tayco Engineering, Cypress, USA Valve, 16 V DC Dual Seat Dual Solenoid Valve, Power 6.5 W MOOG, East Aurora, USA Valve, 28 V DC Dual Seat Dual Solenoid Valve, Power 9.5 W MOOG, East Aurora, USA Valve, 28 V DC Dual Seat Dual Solenoid Valve, Power 9.5 W AER France Qualification   Total Impulse 112,000 Ns Cycle Life 59,000 cycles Propellant Throughput 52 kg Single Burn Life 12 hours Accumulated Burn Life 50 hours No of Cold Starts below 10° C 10 Shock Loads, All Axes 500 g for 0.5 ms

Technical Brochure
		A brochure is available on our 1 N Monopropellant thrusters where you will find more detailed information, including: Heritage. Thruster dimensions. Technical Characteristics. Sinus and random vibration diagram. Pulse mode performance diagrams - duty cycle qualification - specific impulse - impulse bit

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