Propulsion systems
Stellar Exploration provides comprehensive propulsion system development and delivery, fully tailored to meet the specific needs of each customer and mission. Our team works closely with customers to select the most suitable propulsion technology be it warm gas, monopropellant, or bipropellant systems based on performance requirements, available space, mass constraints, and desired operational complexity. This includes careful selection of propellants to ensure safety in handling, storage, and launch operations.
Beyond design, we handle the development of critical hardware components such as thrusters, propellant tanks and pressurization systems, ensuring they meet all performance and environmental requirements. We also provide full integration support, ensuring mechanical, electrical, and software compatibility with the host spacecraft.
Stellar Exploration further manages rigorous qualification testing, including thermal vacuum, vibration, and pressure testing, to validate flight readiness. We also offer assistance during pre-launch activities such as fueling operations and safety documentation preparation.
Whether for CubeSats, small satellites, or more complex missions, our end-to-end propulsion system delivery ensures customers receive a fully engineered, tested, and mission-ready solution.
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
At Stellar Exploration, we design custom warm gas propulsion systems tailored to each mission’s requirements. Rather than offering a standard product, we work with customers to develop solutions that match their platform’s constraints such as size, mass, power, and thrust.
Warm gas propulsion is a simple, reliable, and cost-effective option for small satellites. Our systems support key functions like attitude control, reaction wheel desaturation, and end-of-life deorbiting, with a typical specific impulse in the range of 60–70 seconds.
We use safe, non-toxic, and non-flammable propellants, making ground handling and integration easier while lowering operational risks and costs. From early design to tested flight hardware, we provide full support throughout the development process.
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
Stellar Exploration offers custom monopropellant propulsion systems designed to meet the performance and integration needs of small satellites. We work closely with customers to develop solutions tailored to their mission profiles, from rapid orbital maneuvers to precise station-keeping and attitude control.
We have proven experience with hydrazine-based systems, including flight heritage on missions. Our past experience encompasses the design of conformal tanks and the use of electric gear pumps for pressurization.
In parallel, we are actively developing systems based on green monopropellants, offering safer handling, reduced ground support requirements, and improved environmental compatibility, while maintaining competitive performance.
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
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