https://github.com/cuspaceflight/novus

Joe's Hybrid Simulation
https://github.com/cuspaceflight/novus

Last synced: about 2 months ago
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Joe's Hybrid Simulation

• Host: GitHub
• URL: https://github.com/cuspaceflight/novus
• Owner: cuspaceflight
• License: gpl-3.0
• Created: 2021-02-08T20:33:54.000Z (almost 4 years ago)
• Default Branch: master
• Last Pushed: 2021-04-01T23:20:04.000Z (over 3 years ago)
• Last Synced: 2024-10-07T18:02:44.608Z (3 months ago)
• Language: Python
• Size: 5.01 MB
• Stars: 5
• Watchers: 3
• Forks: 2
• Open Issues: 1
• Metadata Files:
  • Readme: README.txt
  • License: LICENSE.txt

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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.