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
3D Printed Lox/Methane Thruster
- 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
Sample Return
- 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
Nanosat Maneuvering and Orbital Transfer System (OTS)
- 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)
Adjustable Venturi
- 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
CYGNSS Micro-Satellite Constellation
- 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
Landmapper Small Satellite Constellation
- 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
3D Printed Research & Development
- 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
Propulsion Testing - Mars Ascent Vehicle
- 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
Liquid Injection Thrust Vector Control
- 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
Rotary Bellows
- 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.
Ultra-Compact, High-Flow Hydrogen Peroxide Pneumatic Valve
- 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
