Design and performance simulation of a hybrid sounding rocket.
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Date
2012
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Abstract
Sounding rockets find applications in multiple fields of scientific research including
meteorology, astronomy and microgravity. Indigenous sounding rocket technologies are absent
on the African continent despite a potential market in the local aerospace industries. The UKZN
Phoenix Sounding Rocket Programme was initiated to fill this void by developing inexpensive
medium altitude sounding rocket modeling, design and manufacturing capacities. This
dissertation describes the development of the Hybrid Rocket Performance Simulator (HYROPS)
software tool and its application towards the structural design of the reusable, 10 km apogee
capable Phoenix-1A hybrid sounding rocket, as part of the UKZN Phoenix programme.
HYROPS is an integrated 6–Degree of Freedom (6-DOF) flight performance predictor for
atmospheric and near-Earth spaceflight, geared towards single-staged and multi-staged hybrid
sounding rockets. HYROPS is based on a generic kinematics and Newtonian dynamics core.
Integrated with these are numerical methods for solving differential equations, Monte Carlo
uncertainty modeling, genetic-algorithm driven design optimization, analytical vehicle structural
modeling, a spherical, rotating geodetic model and a standard atmospheric model, forming a
software framework for sounding rocket optimization and flight performance prediction. This
framework was implemented within a graphical user interface, aiming for rapid input of model
parameters, intuitive results visualization and efficient data handling. The HYROPS software
was validated using flight data from various existing sounding rocket configurations and found
satisfactory over a range of input conditions. An iterative process was employed in the aerostructural
design of the 1 kg payload capable Phoenix-1A vehicle and CFD and FEA numerical
techniques were used to verify its aerodynamic and thermo-structural performance. The design
and integration of the Phoenix-1A‟s hybrid power-plant and onboard electromechanical systems
for recovery parachute deployment and motor oxidizer flow control are also discussed. It was
noted that use of HYROPS in the design loop led to improved materials selection and vehicle
structural design processes. It was also found that a combination of suitable mathematical
techniques, design know-how, human-interaction and numerical computational power are
effective in overcoming the many coupled technical challenges present in the engineering of
hybrid sounding rockets.
Description
Thesis (M.Sc.)-University of KwaZulu-Natal, Durban, 2012.
Keywords
Sounding rockets--KwaZulu-Natal., Hybrid propellant rockets., Rockets (Aeronautics)--Performance--KwaZulu-Natal., Rockets (Aeronautics)--KwaZulu-Natal--Computer programs., Rockets (Aeronautics)--KwaZulu-Natal--Launching., Theses--Mechanical engineering.