engine.pipeline.config_schemas.NozzleConfig Class Reference

Inheritance diagram for engine.pipeline.config_schemas.NozzleConfig:

Collaboration diagram for engine.pipeline.config_schemas.NozzleConfig:

Static Public Attributes
float	A_throat = Field(gt=0, description="Throat area [m²]")
float	A_exit = Field(gt=0, description="Exit area [m²]")
float	expansion_ratio = Field(gt=1, description="Expansion ratio (A_exit/A_throat)")
Optional	exit_diameter = Field(default=None, gt=0, description="Nozzle exit diameter [m]")
float	efficiency = Field(default=0.98, ge=0, le=1, description="Nozzle efficiency")

Detailed Description

Nozzle configuration

Definition at line 1372 of file config_schemas.py.

Member Data Documentation

A_exit

float engine.pipeline.config_schemas.NozzleConfig.A_exit = Field(gt=0, description="Exit area [m²]")

static

Definition at line 1375 of file config_schemas.py.

A_throat

float engine.pipeline.config_schemas.NozzleConfig.A_throat = Field(gt=0, description="Throat area [m²]")

static

Definition at line 1374 of file config_schemas.py.

efficiency

float engine.pipeline.config_schemas.NozzleConfig.efficiency = Field(default=0.98, ge=0, le=1, description="Nozzle efficiency")

static

Definition at line 1378 of file config_schemas.py.

exit_diameter

Optional engine.pipeline.config_schemas.NozzleConfig.exit_diameter = Field(default=None, gt=0, description="Nozzle exit diameter [m]")

static

Definition at line 1377 of file config_schemas.py.

Referenced by payload.cold_gas_thruster.ColdGasThrusterConfig.A_exit().

expansion_ratio

float engine.pipeline.config_schemas.NozzleConfig.expansion_ratio = Field(gt=1, description="Expansion ratio (A_exit/A_throat)")

static

Definition at line 1376 of file config_schemas.py.

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

• EngineDesign/engine/pipeline/config_schemas.py