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engine.pipeline.config_schemas.ChamberGeometryConfig Class Reference
Inheritance diagram for engine.pipeline.config_schemas.ChamberGeometryConfig:
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Collaboration diagram for engine.pipeline.config_schemas.ChamberGeometryConfig:
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Static Public Attributes

float design_pressure = Field(gt=0, description="Target chamber pressure Pc [Pa]")
float design_thrust = Field(gt=0, description="Target thrust F [N]")
float design_MR = Field(gt=0, description="Design mixture ratio O/F")
float chamber_diameter = Field(gt=0, description="Inner chamber diameter [m]")
float Lstar = Field(gt=0, description="Characteristic length [m] (0.95-1.27 for LOX/RP-1)")
float exit_diameter = Field(gt=0, description="Nozzle exit diameter [m]")
float expansion_ratio = Field(gt=1, description="Area ratio A_exit/A_throat")
float nozzle_efficiency = Field(default=0.95, ge=0, le=1, description="Nozzle efficiency (0.94-0.98)")
Optional A_throat = Field(default=None, gt=0, description="Throat area [m²] - SOLVED")
Optional A_exit = Field(default=None, gt=0, description="Exit area [m²] - SOLVED")
Optional volume = Field(default=None, gt=0, description="Chamber volume [m³] - SOLVED")
Optional length = Field(default=None, gt=0, description="Total chamber length [m] - SOLVED")
Optional length_cylindrical = Field(default=None, gt=0, description="Cylindrical section length [m] - SOLVED")
Optional length_contraction = Field(default=None, gt=0, description="Contraction section length [m] - SOLVED")
Optional Cf = Field(default=None, gt=0, description="Thrust coefficient - SOLVED")

Detailed Description

Unified chamber geometry configuration for solve_chamber_geometry_with_cea.
Groups all design inputs (chamber + nozzle) in one place.

Definition at line 1321 of file config_schemas.py.

Member Data Documentation

◆ A_exit

Optional engine.pipeline.config_schemas.ChamberGeometryConfig.A_exit = Field(default=None, gt=0, description="Exit area [m²] - SOLVED")
static

Definition at line 1342 of file config_schemas.py.

◆ A_throat

Optional engine.pipeline.config_schemas.ChamberGeometryConfig.A_throat = Field(default=None, gt=0, description="Throat area [m²] - SOLVED")
static

Definition at line 1341 of file config_schemas.py.

◆ Cf

Optional engine.pipeline.config_schemas.ChamberGeometryConfig.Cf = Field(default=None, gt=0, description="Thrust coefficient - SOLVED")
static

Definition at line 1347 of file config_schemas.py.

◆ chamber_diameter

float engine.pipeline.config_schemas.ChamberGeometryConfig.chamber_diameter = Field(gt=0, description="Inner chamber diameter [m]")
static

Definition at line 1332 of file config_schemas.py.

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

◆ design_MR

float engine.pipeline.config_schemas.ChamberGeometryConfig.design_MR = Field(gt=0, description="Design mixture ratio O/F")
static

Definition at line 1329 of file config_schemas.py.

◆ design_pressure

float engine.pipeline.config_schemas.ChamberGeometryConfig.design_pressure = Field(gt=0, description="Target chamber pressure Pc [Pa]")
static

Definition at line 1327 of file config_schemas.py.

◆ design_thrust

float engine.pipeline.config_schemas.ChamberGeometryConfig.design_thrust = Field(gt=0, description="Target thrust F [N]")
static

Definition at line 1328 of file config_schemas.py.

◆ exit_diameter

float engine.pipeline.config_schemas.ChamberGeometryConfig.exit_diameter = Field(gt=0, description="Nozzle exit diameter [m]")
static

Definition at line 1336 of file config_schemas.py.

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

◆ expansion_ratio

float engine.pipeline.config_schemas.ChamberGeometryConfig.expansion_ratio = Field(gt=1, description="Area ratio A_exit/A_throat")
static

Definition at line 1337 of file config_schemas.py.

◆ length

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

Definition at line 1344 of file config_schemas.py.

◆ length_contraction

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

Definition at line 1346 of file config_schemas.py.

◆ length_cylindrical

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

Definition at line 1345 of file config_schemas.py.

◆ Lstar

float engine.pipeline.config_schemas.ChamberGeometryConfig.Lstar = Field(gt=0, description="Characteristic length [m] (0.95-1.27 for LOX/RP-1)")
static

Definition at line 1333 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().

◆ nozzle_efficiency

float engine.pipeline.config_schemas.ChamberGeometryConfig.nozzle_efficiency = Field(default=0.95, ge=0, le=1, description="Nozzle efficiency (0.94-0.98)")
static

Definition at line 1338 of file config_schemas.py.

◆ volume

Optional engine.pipeline.config_schemas.ChamberGeometryConfig.volume = Field(default=None, gt=0, description="Chamber volume [m³] - SOLVED")
static

Definition at line 1343 of file config_schemas.py.

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

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