Current Programs & Technology Development Areas

Hybrid Upper Stage
  • Hydrogen Peroxide/HTPB Launch Vehicle Stage
  • Uses Parabilis-proprietary Aft-injection Center Exhaust (ACE) configuration
  • Compact form factor
  • 3d printed aft bulkhead integrates igniters, fluid manifold, and injector
  • Resilient ablative nozzle
  • Lightweight aluminum frame & tank, integrated pressurization system
  • Successfully demonstrated May 2019
  • 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
  • ACE: Aft-injection, Center Exhaust
  • Unique design enables compact form factor; important for rover fitment
  • Leverages additive manufacturing to reduce weight and increase performance
  • Metal 3D-printed aft bulkhead functions as fluid manifold and distributed injector
  • Aft-injection allows for simpler implementation of regenerative jacket
  • Demonstrated in multiple hotfires across several designs and propellants
  • Currently teamed with USC to develop a family of modular high-performance orbital transfer stage vehicles dedicated to Nanosats and Microsats
  • Designed for maneuvering and to move secondary payloads to their desired orbits
  • Based on Parabilis’ proven hybrid engine technologies using benign environmentally safe “green” propellants
  • Nitrous oxide and acrylic motors have been demonstrated at <5lbf scale
  • Utilizes self-pressurizing nitrous oxide tank in a rectilinear design Low-cost high-performance (Isp ~275s)
  • Additively manufactured, dynamically-adjustable, in-line, cavitating flow-control and measurement venturi
  • For use in advanced propulsion system ground testing
  • Isolates combustion chambers or other downstream process fluctuations from upstream feed pressure conditions
  • Greatly simplifies propulsion testing when desired liquid flow conditions involve a range of high-precision flow rates
  • Power systems engineering and flight support for SwRI
  • Eight micro-satellites measure wind speeds over Earth’s oceans
  • Data from constellation improves the ability of scientists to predict hurricanes
  • AstroDigital Landmapper is a small satellite constellation designed for high-frequency global imaging
  • Mission planning, mission operations support, groundstation software development, and imager calibration consultation
  • Constellation will provide highest-quality pixels for lowest cost-per-bit of any satellite constellation in the world
  • Landmapper satellites first launched in 2016; additional launches continued through 2017 and 2018
  • 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
  • Performed testing of Mars Ascent Vehicle (MAV) motor for JPL
  • MAV intended to lift off from Mars surface to transport soil samples to orbiter, and return to Earth
  • Traditional single-port hybrid
  • MON3 oxidizer, paraffin wax fuel
  • On-site storage and handling of nitrogen tetroxide-based oxidizer
  • Multiple test fires in 2016
  • 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
  • Hermetically sealed, additively manufactured torque transmission device for propulsion ground test facilities
  • Suitable for valves with very low leak rate requirements
  • Eliminates the need for leak-prone stem seals and allows for extremely low external leak rates for helium, hydrogen, and toxic propellants such as hydrazine and nitrogen tetroxide.
  • 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

Parabilis develops space technologies.

Are you interested in our space endeavors?