payload.cold_gas_thruster.ColdGasThrusterResult Class Reference

Public Member Functions
str	summary (self)

Static Public Attributes
float	thrust = 0.0
float	mass_flow = 0.0
float	specific_impulse = 0.0
float	momentum_thrust = 0.0
float	pressure_thrust = 0.0
float	exit_mach = 0.0
float	exit_velocity = 0.0
float	exit_temperature = 0.0
float	exit_pressure = 0.0
float	inlet_pressure = 0.0
float	ambient_pressure = 0.0
float	throat_mach = 1.0
bool	is_choked = True
float	critical_pressure_ratio = 0.0
float	throat_area = 0.0
float	exit_area = 0.0
float	expansion_ratio = 0.0
float	chamber_diameter = 0.0
float	chamber_length = 0.0
float	total_thrust = 0.0
float	total_mass_flow = 0.0
float	moment_arm = 0.0
float	torque = 0.0
float	moi_estimate = 0.0
float	angular_accel = 0.0
Optional	nozzle_contour = None

Detailed Description

Full output of one CGT analysis.

Definition at line 163 of file cold_gas_thruster.py.

Member Function Documentation

summary()

str payload.cold_gas_thruster.ColdGasThrusterResult.summary

(

self

)

Human-readable summary of results.

Definition at line 208 of file cold_gas_thruster.py.

Member Data Documentation

ambient_pressure

float payload.cold_gas_thruster.ColdGasThrusterResult.ambient_pressure = 0.0

static

Definition at line 179 of file cold_gas_thruster.py.

Referenced by engine.layerx.card._ExpansionScaling.evaluate(), and feedtwin.engine.card.EngineCard.install().

angular_accel

float payload.cold_gas_thruster.ColdGasThrusterResult.angular_accel = 0.0

static

Definition at line 203 of file cold_gas_thruster.py.

chamber_diameter

float payload.cold_gas_thruster.ColdGasThrusterResult.chamber_diameter = 0.0

static

Definition at line 192 of file cold_gas_thruster.py.

chamber_length

float payload.cold_gas_thruster.ColdGasThrusterResult.chamber_length = 0.0

static

Definition at line 193 of file cold_gas_thruster.py.

critical_pressure_ratio

float payload.cold_gas_thruster.ColdGasThrusterResult.critical_pressure_ratio = 0.0

static

Definition at line 184 of file cold_gas_thruster.py.

exit_area

float payload.cold_gas_thruster.ColdGasThrusterResult.exit_area = 0.0

static

Definition at line 188 of file cold_gas_thruster.py.

exit_mach

float payload.cold_gas_thruster.ColdGasThrusterResult.exit_mach = 0.0

static

Definition at line 174 of file cold_gas_thruster.py.

exit_pressure

float payload.cold_gas_thruster.ColdGasThrusterResult.exit_pressure = 0.0

static

Definition at line 177 of file cold_gas_thruster.py.

exit_temperature

float payload.cold_gas_thruster.ColdGasThrusterResult.exit_temperature = 0.0

static

Definition at line 176 of file cold_gas_thruster.py.

exit_velocity

float payload.cold_gas_thruster.ColdGasThrusterResult.exit_velocity = 0.0

static

Definition at line 175 of file cold_gas_thruster.py.

expansion_ratio

float payload.cold_gas_thruster.ColdGasThrusterResult.expansion_ratio = 0.0

static

Definition at line 189 of file cold_gas_thruster.py.

inlet_pressure

float payload.cold_gas_thruster.ColdGasThrusterResult.inlet_pressure = 0.0

static

Definition at line 178 of file cold_gas_thruster.py.

is_choked

bool payload.cold_gas_thruster.ColdGasThrusterResult.is_choked = True

static

Definition at line 183 of file cold_gas_thruster.py.

Referenced by feedtwin.comps.regulator.Regulator.diagnostics().

mass_flow

float payload.cold_gas_thruster.ColdGasThrusterResult.mass_flow = 0.0

static

Definition at line 168 of file cold_gas_thruster.py.

moi_estimate

float payload.cold_gas_thruster.ColdGasThrusterResult.moi_estimate = 0.0

static

Definition at line 202 of file cold_gas_thruster.py.

moment_arm

float payload.cold_gas_thruster.ColdGasThrusterResult.moment_arm = 0.0

static

Definition at line 200 of file cold_gas_thruster.py.

momentum_thrust

float payload.cold_gas_thruster.ColdGasThrusterResult.momentum_thrust = 0.0

static

Definition at line 170 of file cold_gas_thruster.py.

nozzle_contour

Optional payload.cold_gas_thruster.ColdGasThrusterResult.nozzle_contour = None

static

Definition at line 206 of file cold_gas_thruster.py.

pressure_thrust

float payload.cold_gas_thruster.ColdGasThrusterResult.pressure_thrust = 0.0

static

Definition at line 171 of file cold_gas_thruster.py.

specific_impulse

float payload.cold_gas_thruster.ColdGasThrusterResult.specific_impulse = 0.0

static

Definition at line 169 of file cold_gas_thruster.py.

throat_area

float payload.cold_gas_thruster.ColdGasThrusterResult.throat_area = 0.0

static

Definition at line 187 of file cold_gas_thruster.py.

Referenced by feedtwin.engine.design.EngineDesign.throat_diameter().

throat_mach

float payload.cold_gas_thruster.ColdGasThrusterResult.throat_mach = 1.0

static

Definition at line 182 of file cold_gas_thruster.py.

thrust

float payload.cold_gas_thruster.ColdGasThrusterResult.thrust = 0.0

static

Definition at line 167 of file cold_gas_thruster.py.

torque

float payload.cold_gas_thruster.ColdGasThrusterResult.torque = 0.0

static

Definition at line 201 of file cold_gas_thruster.py.

total_mass_flow

float payload.cold_gas_thruster.ColdGasThrusterResult.total_mass_flow = 0.0

static

Definition at line 197 of file cold_gas_thruster.py.

total_thrust

float payload.cold_gas_thruster.ColdGasThrusterResult.total_thrust = 0.0

static

Definition at line 196 of file cold_gas_thruster.py.

---

The documentation for this class was generated from the following file:

• EngineDesign/payload/cold_gas_thruster.py