Documents pertaining to the present research into nitrous oxide and paraffin-based fuels can be found bellow:
The Development of a Paraffin Based Experimental HybridSounding Rocket
Development and Testing of Paraffin-Based Hybrid Rocket Fuels
Design, Optimization, and Launch of a 3” Diameter N2O/Aluminized Paraffin Rocket
The Physics of Nitrous Oxide
SCALE-UP TESTS OF HIGH REGRESSION RATE LIQUEFYING HYBRID ROCKET FUELS
Fast Burning Hybrid Fuels
DEVELOPMENT OF HIGH-BURNING-RATE HYBRID-ROCKET-FUEL FLIGHT DEMONSTRATORS
Characterization of a family of paraffin-based solid fuels
high regression rate hybrid rocket propellants
Experimental Investigation of Paraffin-Fueled Hybrid Combustion
Development of High-Burning-Rate Hybrid-Rocket-Fuel Flight Demonstrators
Testing of Paraffin-Based Hybrid Rocket Fuel Using Hydrogen Peroxide Oxidizer
Hybrid Rocket Propulsion for Future Space Launch
Hybrid Rocket Fuel Regression Rate Data and Modeling
Non-homogeneous Hybrid Rocket Fuel for Enhanced Regression Rates Utilizing Partial Entrainment
Combustion Characteristics of a Paraffin-Based Fuel Hybrid Rocket
Fuel Regression Rate in a Paraffin-HTPB Nitrous Oxide Hybrid Rocket
WPI AIAA Research Rocket for the Investigation and Observation of Recovery and Staging WARRIORS III
Testing of LiAlH 4 as a Potential Additive to Paraffin Wax Hybrid Rocket Fuel
EXPERIMENTAL INVESTIGATION OF A PARAFFIN BASED HYBRID ROCKET
GOX / Paraffin Hybrid Motor - Nozzle Design
Epolene® Polymers as Petroleum Wax Modifiers A
STUDY OF THE OPTIMUM CONDITION TOWARDS THE INDUCING PARAFFIN WAX LDPE
Influence of Microcrystalline Wax on Properties of MIM Multi-Component Was Matrix Binder
Other documents pertaining to hybrid rocket motors can be found bellow:
NANO-SIZED ALUMINUM- AND BORON-BASED SOLID-FUEL CHARACTERIZATION IN A HYBRID ROCKET ENGINE
An Experimental Investigation of A Lithium Aluminum Hydride-Hydrogen Peroxide Hybrid Rocket
Guanidinium Azo-Tetrazolate (GAT) as a High Performance Hybrid Rocket Fuel Additive
Fuel Regression Rate Characterization Using a Laboratory Scale Nitrous Oxide Hybrid Propulsion System
Regression Rate Behavior of Hybrid Rocket Solid Fuels
A PARAMETRIC STUDY OF THE RADIANT ENERGY FLUX TO THE FUEL SURFACE DURING HYBRID COMBUSTION
Hybrid Fuel Formulation and Technology Development
INVESTIGATIONAL HYBRID ROCKET ENGINE DESIGN FOR RIT M.E.T.E.O.R. ORBITAL LAUNCH SYSTEMS
Documents pertaining to energetic fuels and additives can be found bellow:
ADN – The new oxidizer around the corner for an environmentally friendly smokeless propellant
Development of Novel Polynitrogen-based High-performance Solid Propellants
Characterization of Potassium Nitrate - Sugar Alcohol Based Solid Rocket Propellants
Characterization of Aluminum and Ice Solid Propellants
Solid Propellant Selection and Characterization
ammonia borane, N-B-H compounds properties and applications
Synthesis, Evaluation, and Formulation Studies on New Oxidizers as Alternatives to Ammonium Perchlorate in DoD Missile Propulsion Applicat
Synthesis, Characterization and thermal behavior of hydrazinium nitroformate (HNF) and its new N-alkyl Substituted derivatives
Synthesis of Ammonium Dinitramide by Nitration of Potassium and Ammonium Sulfamate. The Effect of Sulfamate Conterion on ADN Purity
Recent Advances in Development of Eco-friendly Solid Composite Propellants for Rocket Propulsion
Improvements in the Synthesis of Guanidinium Azotetrazolate (GuZT)
Bistetrazoles: Nitrogen-Rich, High-Performing, Insensitive Energetic Compounds
Application of Ionic Liquids to Space Propulsion
Analysis of Hydroxylammonium Nitrate Based Liquid Propellants
Experimental investigation on hydrazinium nitroformate (HNF) combustion and its modification
Synthesis and Characterization of 1-azido, 2,3-dihydroxy 2-azidomethylpropane (ADMP): A New Energetic Organic Azide
Recent Advances in High Nitrogen Energetic Materials
Energetic Ionic Liquids
Energetic Nitrogen-Rich Salts and Ionic Liquids: 5-aminotetrazole (AT) as a Weak Acid
HAN-Based Monopropellant Propulsion System With Applications
Decomposition and Ignition of HAN-Based Monopropellants by Electrolysis
Burn-Rate Investigation of HAN-Based Candidate Liquid Propellants
Technical Report of Hydroxylamine Nitrate
High Nitrogen Compounds For Use in Low-Erosivity Gun Propellants
Hydrazinium 5-Aminotetrazolate: an Insensitive Energetic Material Containing 83.72% Nitrogen
