Classes
class	ColdGasThrusterConfig
class	ColdGasThrusterResult
class	ColdGasThruster

Functions
	main ()

Variables
float	R_UNIVERSAL = 8.314462618
float	G0 = 9.80665
float	CO2_GAMMA = 1.289
float	CO2_MOLAR_MASS = 0.04401
float	PSI_TO_PA = 6894.757
float	DEFAULT_AMBIENT_PA = 12.0 * PSI_TO_PA

Detailed Description

Cold Gas Thruster (CGT) analysis module.

Design: 4 CO₂ cold-gas thrusters at the nosecone, sharing the same nozzle
geometry, firing perpendicular to the rocket's longitudinal axis (±Y, ±Z).

Given a converging-diverging nozzle geometry (throat + exit areas, bell%)
and an inlet CO₂ stagnation pressure, computes:
  - Thrust per thruster (momentum + pressure thrust)
  - Specific impulse
  - Mass flow rate
  - Nozzle exit conditions (Mach, temperature, pressure, velocity)
  - Torque and angular acceleration about the rocket CG

Reuses:
  - engine.core.mach_solver.solve_mach_robust  (isentropic area-Mach solver)
  - engine.core.nozzle_solver.rao              (Rao bell nozzle contour)

Function Documentation

◆ main()

payload.cold_gas_thruster.main ( )

Example analysis with placeholder inputs.

Definition at line 503 of file cold_gas_thruster.py.

References main().

Referenced by main().

Variable Documentation

◆ CO2_GAMMA

float payload.cold_gas_thruster.CO2_GAMMA = 1.289

Definition at line 38 of file cold_gas_thruster.py.

◆ CO2_MOLAR_MASS

float payload.cold_gas_thruster.CO2_MOLAR_MASS = 0.04401

Definition at line 39 of file cold_gas_thruster.py.

◆ DEFAULT_AMBIENT_PA

float payload.cold_gas_thruster.DEFAULT_AMBIENT_PA = 12.0 * PSI_TO_PA

Definition at line 43 of file cold_gas_thruster.py.

◆ G0

float payload.cold_gas_thruster.G0 = 9.80665

Definition at line 35 of file cold_gas_thruster.py.

◆ PSI_TO_PA

float payload.cold_gas_thruster.PSI_TO_PA = 6894.757

Definition at line 42 of file cold_gas_thruster.py.

◆ R_UNIVERSAL

float payload.cold_gas_thruster.R_UNIVERSAL = 8.314462618

Definition at line 34 of file cold_gas_thruster.py.

Classes

Functions

Variables