RocketSolver is a Python package that helps engineers design rockets, rocket motors and rocket engines with efficiency and precision.
The following assertions were taken into consideration:
- Propellant consisting of 2D BATES grain segments
- Cylindrical combustion chamber
- Thrust chamber composed of a simple flat end cap, conical nozzle and tubular casing
- Isentropic flow through nozzle
- Non-submerged nozzle
- Structure with screws as fasteners of both end cap and nozzle
Correction factors applied:
- Divergent CD nozzle angle
- Two phase flow
- Kinetic losses
- Boundary layer losses
Propellant data was obtained from ProPEP3. This software has been used in several applications/projects and it is capable of delivering reliable information on the chemical characteristics of a specific propellant composition. Burn rate data is obtained from experiments conducted by Richard Nakka and Magnus Gudnason.
- KNDX (Nakka burn rate data)
- KNSB-NAKKA (Nakka burn rate data) and KNSB (Magnus Gudnason burn rate data)
- KNSU (Nakka burn rate data)
- KNER (Magnus Gudnason burn rate data)
Correction factors.
Chamber Pressure equation.