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HYBRID ROCKET PROPULSION STUDENT PROJECTS AT THE UNIVERSITY OF BRASÍLIA
Congresso Aeroespacial BrasileiroM. Gontijo +4 more
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Hybrid Rocket Propulsion Performance Prediction
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit, 2005The work performed in this effort used previously measured experimental subscale hybrid propellant data to develop a ground test motor in the 1000 pound-force range. This ground test motor was test fired and the test data was used to finalize a motor fuel grain geometry configuration and an oxidizer injector geometry. The ground tests were then used to
Robert Cavalleri, Richard Loehr
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Development of Student-Led Hybrid Rocket Propulsion Projects
53rd AIAA/SAE/ASEE Joint Propulsion Conference, 2017Ken E. Donathan +4 more
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A Critical Analysis of Paraffin-based Fuel Formulations for Hybrid Rocket Propulsion
, 2017 C. Paravan, L. Galfetti, F. Maggi
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Performance Analysis of Axial-Injection, End-Burning Hybrid Rocket Propulsion System
, 2020Although several investigations have been performed regarding the fundamental physics of axial-injection, end-burning hybrid rocket motors, investigations into the mission performance of a propulsi...
M. Hitt
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A NOVEL POLYETHYLENE PARTICLES/PARAFFIN-BASED SELF-DISINTEGRATION FUEL FOR HYBRID ROCKET PROPULSION
, 2018 Yue Tang +6 more
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AQUASONIC – A Sounding Rocket Based on Hybrid Propulsion
Applied Mechanics and Materials, 2016The AQUASONIC project is aimed to develop a sounding rocket including a hybrid propulsion system based on the propellant combination nitrous oxide and polyethylene. It takes place in the frame of the STERN (Student Experimental Rockets) programme founded by the German Space Agency (DLR) in order to promote students in the area of launch vehicles.
Uwe Apel +3 more
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Performance Calculations for Hybrid Nuclear-Chemical Rocket Propulsion Systems
ARS Journal, 1959 LEON GREEN, JAMES M. CARTER
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Recent developments and current status of hybrid rocket propulsion
1st Annual Meeting, 1964Efficient, high-energy hybrid motors can be designed for specific applications. High impulse and variable thrust capabilities have been proved. New propellant systems and improved motor designs have led to impulse efficiencies > 93%, nearly total fuel utilization, and burning rates approximating those of conventional solid propellants.
D. D. ORDAHL, W. A. RAINS
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