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V6.1
Simulation program for vapour pressure fed nitrous oxide hybrid rocket motors
Joe Hunt
Changelog:
-- v6.2 H. Franks
--- General refactor
-- v6.1 D. Gibbons (dug20)
--- Now stores and exports additional data that is needed for a
more complex moment of inertia model in the 6DOF simulator.
--- Additional properties added to motor_out.csv:
- Vapour Density
- Vapour Mass
- Liquid Density
- Liquid Mass
- Solid Fuel Mass
- Solid Fuel Density
- Solid Fuel Outer Diameter
- Solid Fuel Length
Instructions:
Modify inputs at top of motor_sim.py and run using python 3.
Program outputs file motor_out.csv (used as an input to trajectory_sim.py).
Other dependencies: numpy, scipy, matplotlib
Files:
motor_sim.py simulation program for motor
motor_out.csv motor performance output file generated by motor_sim.py
hybrid.rasp output .rasp file for RAS aero*
trajectory_sim.py simuluation program for rocket trajectory
hybrid_functions.py contains functions governing motor behaviour
and material properties
Additional input data:
atmosphere_data.csv 1976 standard atmosphere
drag_coefficient_data.csv drag coefficient to mach data (RAS Aero)
L_Nitrous_S_HDPE.propep propep frozen and shifting outputs for
a range of pressures and O/F ratios
*Note that a perennial problem with RASP data is the rate of decrease of mass
is always assumed to be proportional to thrust, which is invalid as a nitrous
hybrid's ISP changes with time. Hence further use of this file introduces error
from this approximation.