A5014510340- Rocket and propulsion systems research
- Energetic Materials and Combustion
- Spacecraft and Cryogenic Technologies
- Astro and Planetary Science
- Planetary Science and Exploration
- Space Exploration and Technology
- Spacecraft Design and Technology
- Atmospheric Ozone and Climate
- Combustion and flame dynamics
- Advanced Combustion Engine Technologies
- Heat transfer and supercritical fluids
- Space Satellite Systems and Control
- Laser Design and Applications
- Laser-induced spectroscopy and plasma
- Gas Dynamics and Kinetic Theory
- Particle Dynamics in Fluid Flows
- Plasma Diagnostics and Applications
- Aerospace Engineering and Control Systems
- Combustion and Detonation Processes
- Spacecraft Dynamics and Control
- Phase Equilibria and Thermodynamics
- Space Science and Extraterrestrial Life
- Fluid Dynamics and Heat Transfer
- Diamond and Carbon-based Materials Research
- Electrohydrodynamics and Fluid Dynamics
California Institute of Technology
2025
Jet Propulsion Laboratory
2016-2024
Stanford University
2012-2019
This work was undertaken in an effort to improve the understanding of combustion processes inside classical and fast-burning hybrid rocket motors. In this paper, a visualization experiment various optics were used explore mass transfer phenomena, boundary-layer growth rates, flame location above combusting fuels at atmospheric elevated chamber pressures. The results presented provide strong confirmation basic droplet formation entrainment mechanism for operating conditions representative...
The discovery of high regression rate liquefying fuels for hybrid motors has generated a renewed interest in visualization experiments. In 2012, the Stanford Combustion Visualization Facility was developed to investigate combustion these with gaseous oxygen. A major upgrade this facility recently completed. Details changes made are provided. Visual and schlieren images paraffin wax oxygen at range operating pressures presented, including first supercritical pressures. nature boundary layer...
This paper explores turbulent boundary layer development within a hybrid rocket motor. Schlieren images of the combustion typical motor fuels with gaseous oxygen in slab-burning configuration are presented. The recently upgraded Stanford Combustion Visualization Facility was used to conduct atmospheric pressure tests investigating classical such as Hydroxyl-Terminated PolyButadiene (HTPB), High Density PolyEtheylene (HDPE) and polymethyl methacrylate (PMMA) well liquefying high regression...
The performance of a diode laser igniter as restart-capable device has been assessed for single-port, poly(methyl methacrylate) (PMMA)/gaseous oxygen (GOX) hybrid motors. For this testing prototype version the designed and implemented substitute to traditional methane/GOX torch ignition system. Ignition tests have conducted at atmospheric ambient conditions using an experimental single-port motor setup. Using three PMMA fuel grains, total 46 successful ignitions restarts were achieved. These...
The capabilities of a SmallSat-class spacecraft targeting the outer solar system and using combined chemical electric propulsion are explored. development compact hybrid rockets has enabled high-thrust engines to be packaged tightly enough fit on CubeSat SmallSat spacecraft. These provide 10's-100 N thrust depending propellant load & >300 s specific impulse have been demonstrated in both ambient vacuum environments. Advancements low -power long-life Hall thruster technologies provided...
High combustion efficiency is a critical attribute of successful rocket engine. Reported results from ground tests single port hybrid engines show measured characteristic velocity ranging 55 to 97 percent. In many configurations, the starts out high at beginning burn and decreases as fuel opens up over course burn. Differences in engine interior geometry, propellents, injector design, post chamber mixing devices measurement techniques have made it difficult elucidate factors that lead...
The SkyCardinal Hybrid Rocket design team in the Department of Aeronautics and Astronautics at Stanford University designed, developed, ground-tested, intends to flight-test a medium-scale hybrid rocket. vehicle will demonstrate thrust vector control (TVC) capability as well utility paraffin (fuel) Nytrox (oxidizer) propellant combination. In addition, expects rocket launch an altitude exceeding 1500 meters while simultaneously employing TVC. Two ground tests have been performed evaluate...
This paper describes the design and development status of a hybrid CubeSat propulsion system. system is designed to be packaged within 12 U envelope deliver approximately 800 m/s ΔV 25 kg spacecraft. The motor uses green propellants, specifically gaseous oxygen as oxidizer solid Poly(Methyl MethAcrylate) (PMMA), also known acrylic, fuel. propellant combination separated by phase non-toxic non-hypergolic, making well suited for use secondary payload where safety paramount. has high...
Owing to its wide (3.4 eV) and direct-tunable band gap, gallium nitride (GaN) is an excellent material platform make UV photo detectors. GaN also stable in radiation-rich high-temperature environments, which makes detectors fabricated using this useful for in-situ flame detection combustion monitoring. In paper, we use a detector measure ultraviolet (UV) emissions from hybrid rocket motor igniter plume. The detector, built at the Stanford Nanofabrication Facility, has 5 μm regions of...
Current Mars science goals require the removal of dust from surface samples to expose rock beneath layer for imaging. A simple cold gas system is proposed fill this need. series tests were conducted investigate suspension and entrainment phenomena under influence a jet in near vacuum conditions at Mars. This paper describes experimental set-up results these tests. Data was collected more than 400 different order evaluate mass flow rate, molecular weight working gas, back pressure ambient...