Propulsion systems

Full Propulsion delivery based on mission requirements. Stellar Exploration provides development and design of the propulsion system according to customer and mission requirements, including:

– Analysis

– Testing

– Filling operations before launch

Flight Propulsion Test Campaign

Propulsion - Warm Gas propulsion

The Warm Gas propulsion system is an efficient, robust solution designed for small satellites, including CubeSats.
– Non-toxic, non-corrosive, and non-flammable, making it safe to handle and store
– Isp = 60 - 70 sec

Deorbit

– Capable of deorbiting maneuvers, allowing controlled re-entry or deorbiting at the end of the mission to meet space debris mitigation requirements (5 years)

Reaction control, proximity and precise maneuvers

– Provides 6-DOF reaction control, enabling precise maneuvers in all directions.

Pearl White 1 & 2 missions

– 6U spacecraft in LEO
– Manufacturing, cleaning, welding integration of components (tank, heating chamber, and thrusters)

Rogue space missions

– 1000 Ns of impulse, 40 mN thrusters

Propulsion - Monopropellant propulsion

NASA - CAPSTONE mission

– Conformal (cubical) tank
– Δv 140 m/s
– Electric gear pump pressurization
– Delivery in one year since ATP
– Verifying the calculated orbital stability planned for the Lunar Gateway space station

EG-3 mission

– Conformal (cubical) tank
– Δv 260 m/s
– Electric gear pump pressurization
– Most Rapid Altitude Change Ever Accomplished By A Nano-Satellite & 1.5 degree inclination change

Jackal 1, 2, 3 and 4

– ESPA-class
– Mass of propellant ~50 kg
– 12 thrusters are located around the vehicle to support 6-DOF propulsion for rendezvous and proximity operations
– Transporter 10 and 12; Jackal 4 will launch on a Falcon 9 in April 2025

Monopropellant thruster properties
Propellant	Hydrazine (HPH)
Thrust	0.25 N / 0.5 N / 1 N
Steady state Isp	200 sec (measured 208 - 217 sec)
Pulsed Isp	175 sec

Propulsion - Bipropellant propulsion

Harley

– 6U CubeSat
– Dual mode (monoprop & biprop)
– High-degree of miniaturization
– Electric gear pump pressurization

MSO

– ESPA-class
– Dual mode (monoprop & biprop)
– Δv 3200 m/s
– Optimized tank volume vs. mass vs. achieved Δv
– Electric gear pump pressurization

Bipropellant thruster properties
Fuel	Hydrazine (HPH)
Oxidiser	NTO (MON-3)
Thrust	5 N
Steady state Isp	285 sec
Pulsed Isp	230 - 260 sec

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Flight Propulsion Test Campaign​

Propulsion - Warm Gas propulsion

Deorbit

Reaction control, proximity and precise maneuvers​

Pearl White 1 & 2 missions​

Rogue space missions​

Propulsion - Monopropellant propulsion​

NASA - CAPSTONE mission​

EG-3 mission​

Jackal 1, 2, 3 and 4​

Monopropellant thruster properties​