engine.pipeline.config_schemas.ChamberConfig Class Reference

Inheritance diagram for engine.pipeline.config_schemas.ChamberConfig:

Collaboration diagram for engine.pipeline.config_schemas.ChamberConfig:

Static Public Attributes
float	volume = Field(gt=0, description="Chamber volume [m³]")
float	A_throat = Field(gt=0, description="Throat area [m²]")
Optional	length = Field(default=None, gt=0, description="Total chamber length [m]")
Optional	length_cylindrical = Field(default=None, gt=0, description="Cylindrical section length [m]")
Optional	length_contraction = Field(default=None, gt=0, description="Contraction section length [m]")
Optional	Lstar
Optional	chamber_inner_diameter = Field(default=None, gt=0, description="Chamber inner diameter [m]")
Optional	exit_diameter = Field(default=None, gt=0, description="Nozzle exit diameter [m] for geometry solver")
Optional	design_pressure = Field(default=None, gt=0, description="Design chamber pressure [Pa] (Pc_design)")
Optional	design_thrust = Field(default=None, gt=0, description="Design thrust [N] (F_design)")
Optional	design_MR = Field(default=None, gt=0, description="Design mixture ratio O/F for CEA solver")
Optional	design_force_coefficient = Field(default=None, gt=0, description="Solved thrust coefficient Cf (output from solver)")

Detailed Description

Chamber geometry configuration

Definition at line 1350 of file config_schemas.py.

Member Data Documentation

A_throat

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

static

Definition at line 1353 of file config_schemas.py.

chamber_inner_diameter

Optional engine.pipeline.config_schemas.ChamberConfig.chamber_inner_diameter = Field(default=None, gt=0, description="Chamber inner diameter [m]")

static

Definition at line 1362 of file config_schemas.py.

design_force_coefficient

Optional engine.pipeline.config_schemas.ChamberConfig.design_force_coefficient = Field(default=None, gt=0, description="Solved thrust coefficient Cf (output from solver)")

static

Definition at line 1369 of file config_schemas.py.

design_MR

Optional engine.pipeline.config_schemas.ChamberConfig.design_MR = Field(default=None, gt=0, description="Design mixture ratio O/F for CEA solver")

static

Definition at line 1368 of file config_schemas.py.

design_pressure

Optional engine.pipeline.config_schemas.ChamberConfig.design_pressure = Field(default=None, gt=0, description="Design chamber pressure [Pa] (Pc_design)")

static

Definition at line 1366 of file config_schemas.py.

design_thrust

Optional engine.pipeline.config_schemas.ChamberConfig.design_thrust = Field(default=None, gt=0, description="Design thrust [N] (F_design)")

static

Definition at line 1367 of file config_schemas.py.

exit_diameter

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

static

Definition at line 1363 of file config_schemas.py.

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

length

Optional engine.pipeline.config_schemas.ChamberConfig.length = Field(default=None, gt=0, description="Total chamber length [m]")

static

Definition at line 1354 of file config_schemas.py.

length_contraction

Optional engine.pipeline.config_schemas.ChamberConfig.length_contraction = Field(default=None, gt=0, description="Contraction section length [m]")

static

Definition at line 1356 of file config_schemas.py.

length_cylindrical

Optional engine.pipeline.config_schemas.ChamberConfig.length_cylindrical = Field(default=None, gt=0, description="Cylindrical section length [m]")

static

Definition at line 1355 of file config_schemas.py.

Lstar

Optional engine.pipeline.config_schemas.ChamberConfig.Lstar

static

Initial value:

=  Field(
        default=None,
        gt=0,
        description="Characteristic length [m] = V_chamber / A_throat. If not specified, calculated from volume and A_throat."
    )

Definition at line 1357 of file config_schemas.py.

Referenced by test_combustion_stability_audit.TestNyquistAllCrossings.case(), test_combustion_stability_audit.TestNyquistAllCrossings.L_indep(), and engine.pipeline.stability.chug.ChugChamber.theta_c().

volume

float engine.pipeline.config_schemas.ChamberConfig.volume = Field(gt=0, description="Chamber volume [m³]")

static

Definition at line 1352 of file config_schemas.py.

Referenced by feedtwin.session.core.BottleSim._air(), and feedtwin.session.core.BottleSim.advance().

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

• EngineDesign/engine/pipeline/config_schemas.py