The motor essentially consists of the chamber casing, a grade 431 stainless steel torispherical injector bulkhead and nozzle retainer, a fine grain graphite nozzle, and a fuel grain cartridge, as the core of the propulsion system. The combustion chamber casing and oxidiser tank were manufactured from 6082-T6 aluminium alloy. The vehicle's airframe consists of an ogive nose cone with aluminium tip, drogue and main parachute bays, a flight computer bay, four stabilizing fins, a boat-tail, and a tapered inter-stage section for encasing the feed system. The Phoenix-1A rocket is depicted in the cross-sectional view in figure 1. To date, the progress in UKZN's Programme includes the design and static tests of the PL-1 lab-scale motor, design and static test of the PV-1 flight motor, development of a Hybrid Rocket Performance Simulation (HYROPS) model, development of vehicle airframe and internal components, and the launch of Phoenix-1A. A paraffin-wax/nitrous oxide propellant combination was selected as the propulsion system.
#SPACE DROP VUII SERIES#
The programme's long-term objective is to develop a series of sub-orbital hybrid sounding rockets for customers engaged in atmospheric and space physics research, starting with a first low-altitude demonstrator, Phoenix-1A, which was designed to deliver a 1 kg payload to 10 km altitude. In 2010, the University of KwaZulu-Natal (UKZN) initiated the Phoenix Hybrid Sounding Rocket Programme to address the lack of an indigenous sub-orbital launch capability and meet the demands of the South African and African scientific research communities. In the conventional and most used hybrid rocket motors, the oxidiser and fuel are in the liquid and solid phases, respectively. It is classified as a chemical rocket due to the required energy being generated from the combustion process of the propellants, which are stored in two distinct states before undergoing the chemical reaction. These include safety, throttling capability, propellant versatility, design simplicity and lower fabrication cost. The hybrid rocket offers attractive advantages over solid and liquid variants in university-based research programmes.
Saturated vapour pressure of nitrous oxide N number of moles, regression rate bal coefficient Molar heat capacity at constant pressure The HRPC application is validated against hot-fire test data of Phoenix-lA's PV-1 flight motor and against reported performance data from the literature.Īdditional keywords: Hybrid rocket propulsion, nitrous oxide, paraffin-wax, computational modelĪ inj injector orifice cross-sectional area Ī p grain port cross-sectional area Ĭ p specific heat capacity at constant pressure Ĭ v specific heat capacity at constant volume As such, different propellant combinations can be analysed for motor performances. HRPC is coupled with NASA-CEA equilibrium chemistry program to determine the thermodynamic properties of the combustion products necessary for solving the governing ordinary differential equations. The zero-dimensional model is linked to a self-pressurising delivery tank model obtainedfrom literature to simulate the changes in physicochemical properties of nitrous oxide in the tank.
#SPACE DROP VUII CODE#
The predictive motor performance code is based on a one-dimensional unsteady gas flow model through the nozzle and, on a zero-dimensional model of the combustion chamber capturing only the filling and emptying dynamics. The Hybrid Rocket Performance Code (HRPC), programmed in MATLAB, is segregated into two individual models: i) a preliminary motor design code to analyse and design hybrid rocket motors, and ii) a predictive motor performance code to compute the instantaneous motor performance for a targeted burn time.
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E-mail: model is described to aid in the design of hybrid rockets and in the prediction of motor performance, specifically with respect to the University of KwaZulu-Natal's Phoenix-1A vehicle. Discipline of Mechanical Engineering, University of KwaZulu-Natal, Durban, South Africa. E-mail: of Mechanical Engineering, University of KwaZulu-Natal, Durban, South Africa. University of KwaZulu-Natal, Durban, South Africa. A computational tool for predicting hybrid rocket motor performanceī.
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