Inheritance diagram for engine.pipeline.config_schemas.PintleEngineConfig:

Collaboration diagram for engine.pipeline.config_schemas.PintleEngineConfig:

Public Member Functions
	validate_branches (cls, v)
	injector_aware_geometry_cd_default (self)
	align_expansion_ratio_with_exit_throat_areas (self)
	sync_burn_time_fields (self)

Static Public Attributes
Optional	propellant_preset = Field(default=None, description="Propellant preset to merge (e.g. 'methalox', 'ethalox', 'kerolox'); explicit fields win over preset")
Dict	fluids [str, FluidConfig]
Dict	feed_system [str, FeedSystemConfig]
Optional	regen_cooling = Field(default=None, description="Regenerative cooling configuration (fuel only)")
Optional	film_cooling = Field(default=None, description="Film cooling configuration")
Optional	ablative_cooling = Field(default=None, description="Ablative cooling configuration for chamber liner")
Optional	graphite_insert = Field(default=None, description="Graphite throat insert configuration (separate from chamber ablator)")
Optional	stainless_steel_case = Field(default=None, description="Stainless steel case configuration (structural wall behind ablative/graphite)")
Dict	discharge [str, DischargeConfig]
SprayConfig	spray = Field(default_factory=SprayConfig)
CombustionConfig	combustion = Field(default_factory=CombustionConfig)
Optional	chamber_geometry = Field(default=None, description="Unified chamber geometry config (design inputs + solver outputs)")
Optional	chamber = Field(default=None, description="Legacy chamber config (use chamber_geometry instead)")
Optional	nozzle = Field(default=None, description="Legacy nozzle config (use chamber_geometry instead)")
SolverConfig	solver = Field(default_factory=SolverConfig)
StabilityConfig	stability = Field(default_factory=StabilityConfig, description="Combustion / feed stability model inputs (calibration, regulator, acoustic damping)")
Optional	measurements = Field(default=None, description="Measured values that replace the model's assumptions (cold flow, hot fire).")
Optional	optimizer = Field(default=None, description="Optimizer configuration")
Optional	lox_tank = Field(default=None, description="LOX tank configuration for flight simulation")
Optional	fuel_tank = Field(default=None, description="Fuel tank configuration for flight simulation")
Optional	press_tank = Field(default=None, description="Pressurant tank configuration for flight simulation")
Optional	rocket = Field(default=None, description="Rocket configuration for flight simulation")
Optional	environment = Field(default=None, description="Environment configuration for flight simulation")
Optional	thrust = Field(default=None, description="Thrust configuration for flight simulation")
Optional	design_requirements = Field(default=None, description="Design requirements for optimizer")
Optional	pressure_curves = Field(default=None, description="Optimized pressure curves from Layer 2 optimization")
Optional	design_valid_for = Field(default=None, description="{'injector','propellant'} the chamber geometry was solved for (forward-mode staleness flag)")
	model_config = ConfigDict(extra="allow")

Detailed Description

Complete pintle engine configuration

Definition at line 2735 of file config_schemas.py.

Member Function Documentation

◆ align_expansion_ratio_with_exit_throat_areas()

engine.pipeline.config_schemas.PintleEngineConfig.align_expansion_ratio_with_exit_throat_areas ( self )

Nozzle thrust uses eps == A_exit/A_throat (strict); YAML often labels eps rounded.

Definition at line 2797 of file config_schemas.py.

◆ injector_aware_geometry_cd_default()

engine.pipeline.config_schemas.PintleEngineConfig.injector_aware_geometry_cd_default ( self )

FINDING F1 fix (UNIFICATION P3): ``use_geometry_cd`` schema-defaults to True (drilled
impinging orifices). For PINTLE the geometry-Cd correlation doesn't apply (annulus/orifice
Cd is fixed Cd_inf; the solver never calls it) — so when the field was NOT explicitly given,
derive False for pintle. Explicit YAML values are respected (model_fields_set check).

Definition at line 2784 of file config_schemas.py.

◆ sync_burn_time_fields()

engine.pipeline.config_schemas.PintleEngineConfig.sync_burn_time_fields ( self )

Keep thrust.burn_time and pressure_curves.target_burn_time_s aligned with design_requirements.

Definition at line 2830 of file config_schemas.py.

◆ validate_branches()

engine.pipeline.config_schemas.PintleEngineConfig.validate_branches	(		cls,
			v )

Ensure both oxidizer and fuel branches are present

Definition at line 2777 of file config_schemas.py.

Member Data Documentation

◆ ablative_cooling

Optional engine.pipeline.config_schemas.PintleEngineConfig.ablative_cooling = Field(default=None, description="Ablative cooling configuration for chamber liner")

static

Definition at line 2746 of file config_schemas.py.

◆ chamber

Optional engine.pipeline.config_schemas.PintleEngineConfig.chamber = Field(default=None, description="Legacy chamber config (use chamber_geometry instead)")

static

Definition at line 2755 of file config_schemas.py.

◆ chamber_geometry

Optional engine.pipeline.config_schemas.PintleEngineConfig.chamber_geometry = Field(default=None, description="Unified chamber geometry config (design inputs + solver outputs)")

static

Definition at line 2753 of file config_schemas.py.

◆ combustion

CombustionConfig engine.pipeline.config_schemas.PintleEngineConfig.combustion = Field(default_factory=CombustionConfig)

static

Definition at line 2751 of file config_schemas.py.

◆ design_requirements

Optional engine.pipeline.config_schemas.PintleEngineConfig.design_requirements = Field(default=None, description="Design requirements for optimizer")

static

Definition at line 2768 of file config_schemas.py.

◆ design_valid_for

Optional engine.pipeline.config_schemas.PintleEngineConfig.design_valid_for = Field(default=None, description="{'injector','propellant'} the chamber geometry was solved for (forward-mode staleness flag)")

static

Definition at line 2773 of file config_schemas.py.

◆ discharge

Dict engine.pipeline.config_schemas.PintleEngineConfig.discharge [str, DischargeConfig]

static

Definition at line 2749 of file config_schemas.py.

Referenced by feedtwin.engine.design.InjectorSide.cd_at().

◆ environment

Optional engine.pipeline.config_schemas.PintleEngineConfig.environment = Field(default=None, description="Environment configuration for flight simulation")

static

Definition at line 2766 of file config_schemas.py.

◆ feed_system

Dict engine.pipeline.config_schemas.PintleEngineConfig.feed_system [str, FeedSystemConfig]

static

Definition at line 2743 of file config_schemas.py.

◆ film_cooling

Optional engine.pipeline.config_schemas.PintleEngineConfig.film_cooling = Field(default=None, description="Film cooling configuration")

static

Definition at line 2745 of file config_schemas.py.

◆ fluids

Dict engine.pipeline.config_schemas.PintleEngineConfig.fluids [str, FluidConfig]

static

Definition at line 2741 of file config_schemas.py.

◆ fuel_tank

Optional engine.pipeline.config_schemas.PintleEngineConfig.fuel_tank = Field(default=None, description="Fuel tank configuration for flight simulation")

static

Definition at line 2763 of file config_schemas.py.

◆ graphite_insert

Optional engine.pipeline.config_schemas.PintleEngineConfig.graphite_insert = Field(default=None, description="Graphite throat insert configuration (separate from chamber ablator)")

static

Definition at line 2747 of file config_schemas.py.

◆ lox_tank

Optional engine.pipeline.config_schemas.PintleEngineConfig.lox_tank = Field(default=None, description="LOX tank configuration for flight simulation")

static

Definition at line 2762 of file config_schemas.py.

◆ measurements

Optional engine.pipeline.config_schemas.PintleEngineConfig.measurements = Field(default=None, description="Measured values that replace the model's assumptions (cold flow, hot fire).")

static

Definition at line 2759 of file config_schemas.py.

◆ model_config

engine.pipeline.config_schemas.PintleEngineConfig.model_config = ConfigDict(extra="allow")

static

Definition at line 2837 of file config_schemas.py.

◆ nozzle

Optional engine.pipeline.config_schemas.PintleEngineConfig.nozzle = Field(default=None, description="Legacy nozzle config (use chamber_geometry instead)")

static

Definition at line 2756 of file config_schemas.py.

◆ optimizer

Optional engine.pipeline.config_schemas.PintleEngineConfig.optimizer = Field(default=None, description="Optimizer configuration")

static

Definition at line 2760 of file config_schemas.py.

◆ press_tank

Optional engine.pipeline.config_schemas.PintleEngineConfig.press_tank = Field(default=None, description="Pressurant tank configuration for flight simulation")

static

Definition at line 2764 of file config_schemas.py.

◆ pressure_curves

Optional engine.pipeline.config_schemas.PintleEngineConfig.pressure_curves = Field(default=None, description="Optimized pressure curves from Layer 2 optimization")

static

Definition at line 2769 of file config_schemas.py.

◆ propellant_preset

Optional engine.pipeline.config_schemas.PintleEngineConfig.propellant_preset = Field(default=None, description="Propellant preset to merge (e.g. 'methalox', 'ethalox', 'kerolox'); explicit fields win over preset")

static

Definition at line 2740 of file config_schemas.py.

◆ regen_cooling

Optional engine.pipeline.config_schemas.PintleEngineConfig.regen_cooling = Field(default=None, description="Regenerative cooling configuration (fuel only)")

static

Definition at line 2744 of file config_schemas.py.

◆ rocket

Optional engine.pipeline.config_schemas.PintleEngineConfig.rocket = Field(default=None, description="Rocket configuration for flight simulation")

static

Definition at line 2765 of file config_schemas.py.

◆ solver

SolverConfig engine.pipeline.config_schemas.PintleEngineConfig.solver = Field(default_factory=SolverConfig)

static

Definition at line 2757 of file config_schemas.py.

◆ spray

SprayConfig engine.pipeline.config_schemas.PintleEngineConfig.spray = Field(default_factory=SprayConfig)

static

Definition at line 2750 of file config_schemas.py.

◆ stability

StabilityConfig engine.pipeline.config_schemas.PintleEngineConfig.stability = Field(default_factory=StabilityConfig, description="Combustion / feed stability model inputs (calibration, regulator, acoustic damping)")

static

Definition at line 2758 of file config_schemas.py.

◆ stainless_steel_case

Optional engine.pipeline.config_schemas.PintleEngineConfig.stainless_steel_case = Field(default=None, description="Stainless steel case configuration (structural wall behind ablative/graphite)")

static

Definition at line 2748 of file config_schemas.py.

◆ thrust

Optional engine.pipeline.config_schemas.PintleEngineConfig.thrust = Field(default=None, description="Thrust configuration for flight simulation")

static

Definition at line 2767 of file config_schemas.py.

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

EngineDesign/engine/pipeline/config_schemas.py

Public Member Functions

Static Public Attributes

Detailed Description

Member Function Documentation

◆ align_expansion_ratio_with_exit_throat_areas()

◆ injector_aware_geometry_cd_default()

◆ sync_burn_time_fields()

◆ validate_branches()

Member Data Documentation

◆ ablative_cooling

◆ chamber

◆ chamber_geometry

◆ combustion

◆ design_requirements

◆ design_valid_for

◆ discharge

◆ environment

◆ feed_system

◆ film_cooling

◆ fluids

◆ fuel_tank

◆ graphite_insert

◆ lox_tank

◆ measurements

◆ model_config

◆ nozzle

◆ optimizer

◆ press_tank

◆ pressure_curves

◆ propellant_preset

◆ regen_cooling

◆ rocket

◆ solver

◆ spray

◆ stability

◆ stainless_steel_case

◆ thrust