Propulsion Overview
Parabilis engineers have extensive experience conceptualizing, designing, building, testing, and flying affordable propulsion systems and launch vehicles for manned and unmanned spaceflight. Our propulsion expertise ranges from small liquid bi-propellant RCS thrusters, to a high-performance H2O2/HTPB fueled upper-stage, to larger hybrid launch vehicles with >65,000 lbs. of thrust. Our team is committed to providing affordable space access that will help catalyze the emerging low-cost New Space industries. Learn more below about how we excel in developing affordable propulsion systems.
Over 35+ years of experience developing propulsion systems for manned and unmanned spaceflight.
- Designed and tested both bi-propellant and hybrid engines at our Test Site using:
- LOX/CH4
- N2O/HTPB
- MON3/HTPB
- N2O4/Paraffin
- H2O2/HTPB
- Successfully demonstrated variable-throttle hybrid rocket engine technologies.
- Developed custom pyrotechnic and spark ignition hardware for multiple motors.
- Developed innovative liquid injection thrust vector control technologies.
- Created Cryogenic Gelled Propellants and tested rheological properties.
- Established processes to analyze, and mitigating risks in propellant feed systems.
- Developed innovative Additive Manufactured components for rocket engines.
- Developed multi-port & complex fuel grain geometries demonstrating minimal residual.
- Experience designing and integrating launch vehicles and small spacecraft such as Atlas/Centaur, SpaceShipOne, SpaceShipTwo, DreamChaser, and Trailblazer.
Hybrid Upper Stage on Test Stand
- Various R&D of printed designs
- Small-feature and channel development, cooling & manifolds
- Direct fluid & sensor interfaces
- Multi-material incorporation (copper and graphite into Inconel base)
- Spark-driven lox/methane torch igniter for propulsion applications
- 10” diameter printed primary bulkhead, including load structure with fluid ports, manifolds, injector
- Fluid is injected into the nozzle of a rocket motor, diverting exhaust flow
- LITVC can be used to directionally steer rocket exhaust, enabling vehicle control
- Steering diverts flow but not nozzle assembly, no gimbal or fancy seals
- For hybrids, injectant can be the same liquid oxidizer (creating a more-simple system)
- Demonstration tests include a regen jacket with multi-port water cooling
- Particularly synergistic with Parabilis aft-injected center-exhaust (ACE) hybrid propulsion system.
- Tested in 2019
- 3/8” configuration is <1lb
- CV of 1.2 for 3/8” design
- 500psi rated, 200psi pneumatic supply
- Stainless steel and PTFE wetted surfaces, class 4 rating with peroxide
- Successfully demonstrated with rocket grade 90% hydrogen peroxide
- Core design scalable to accommodate alternate sizes and pressures
- 100 lbf-class, compact design
- Symbiotic RCS for deep space ops
- Single-piece monolithic design
- Integrated fluid interfaces, manifolds, cooling jacket, and injectors
- Spark-driven restartable torch igniter
- DMLS printed in Inconel 718 material
- Tested on Parabilis-created cryogenic bi-prop mobile test stand for LOx/LCH4
- Over 100 successful tests
Parabilis Space Technologies designed, developed, manufactured, and successfully hot-fire tested an additively manufactured (3D-printed) 100 lb-class reaction control system (RCS) thruster to provide a low-cost, high-performance LOX/methane thruster for NASA missions such as Mars exploration and for next-generation launch-vehicle upper stages.
Additive manufacturing enables rapid design iterations and the affordable production of highly complex geometries. It also supports in-transit component repair or replacement for spacecraft.
Parabilis Space Technologies designed, developed, manufactured, and successfully hot-fire tested an additively manufactured (3D-printed) 100 lb-class reaction control system (RCS) thruster to provide a low-cost, high-performance LOX/methane thruster for NASA missions such as Mars exploration and for next-generation launch-vehicle upper stages.
Additive manufacturing enables rapid design iterations and the affordable production of highly complex geometries. It also supports in-transit component repair or replacement for spacecraft.
Optical Scan of Hybrid Rocket Fuel Internal Surface Profile
Methods and Capabilities
- Utilize multiple industry standard software tools.
- Utilize validated in-house analysis tools.
- Dynamic fluid system analysis.
- Internal ballistic codes for various hybrid fuel ports.
- Thermal/heat transfer of propulsion system components.
- In-house machining & assembling of propulsion systems.
- Propellant handling and propulsion testing experience.
- In-house testing for all propulsion components.
- System sizing and optimization for any spacecraft/vehicle.
- Iterative design processes, increasing adaptability and optimization abilities.
- Developed custom fuel grain motor pour vacuum processes and techniques.
- Extensive propulsion FEA analysis for extreme environments.
- Non-destructive fuel regression measurement & 3D mapping system.
Manufacturing, 3D Printing, & Other Capabilities
Mars Ascent Vehicle Hot Fire