Public Member Functions
None	__init__ (self, *, float mass_kg, float reference_area_m2, float nozzle_exit_area_m2, float elevation_m, Optional[float] reference_pressure_pa, Any drag=None, float dt_max=0.01)
"InlineAscent"	from_config (cls, Any config, float liftoff_mass_kg, float ambient_pa, *, Any drag=None, float dt_max=0.01)
float	specific_force (self)
bool	held (self)
float	advance (self, float t, float thrust_N, float mdot_kg_s)

Public Attributes
	A_ref = float(reference_area_m2)
	A_e = float(nozzle_exit_area_m2)
	elevation = float(elevation_m)
	p_ref = None if reference_pressure_pa is None else float(reference_pressure_pa)
	dt_max = float(dt_max)
	drag = drag
Optional[float]	t = None
float	z = 0.0
float	v = 0.0
float	m = float(mass_kg)
float	thrust = 0.0
float	mdot = 0.0
Optional[float]	liftoff_time_s = None
	held

Protected Member Functions
Tuple[float, bool]	_specific (self, float z, float v, float m, float thrust)
Tuple[float, float, float]	_rhs (self, float z, float v, float m, float thrust, float mdot)
None	_integrate (self, float t0, float t1, float f0, float f1, float md0, float md1)

Protected Attributes
	_isa = isa_troposphere
	_mach = np.asarray(drag.mach, dtype=float)
	_cd_on = np.asarray(drag.cd_power_on, dtype=float)
	_cd_off = np.asarray(drag.cd_power_off, dtype=float)

Detailed Description

A vertical 1-DOF ascent advanced sample by sample, for a burn pass to read the specific force
a liquid column feels at each step without flying the whole burn first (D5-C).

Same equations, drag and atmosphere as ``engine.pipeline.flight_1dof`` (which matches RocketPy's
specific force to 0.002 % on LE4, AUDIT 9.3, 5). Thrust and mass flow are linear between the
samples given to :meth:`advance`; the state is integrated by RK4 in substeps of at most
``dt_max``. Mass leaves only as propellant: the pressurant moves from the COPV into the ullages
and stays aboard.

**Held.** At rest on the pad (z = 0, v = 0) with thrust, pressure thrust and drag below the
weight, the stand (or rail) carries the rest and the vehicle does not move. Its specific force
is then exactly ``G0``: the pad's one g, ``Setup.body_acceleration``'s default. Pressure thrust
acts only while the thrust sample is positive, so a lead-in sample with no thrust is held.

Definition at line 472 of file flight.py.

Constructor & Destructor Documentation

◆ init()

None engine.layerx.flight.InlineAscent.__init__	(		self,
		*	,
		float	mass_kg,
		float	reference_area_m2,
		float	nozzle_exit_area_m2,
		float	elevation_m,
		Optional[float]	reference_pressure_pa,
		Any	drag = None,
		float	dt_max = 0.01 )

Definition at line 488 of file flight.py.

Member Function Documentation

◆ _integrate()

None engine.layerx.flight.InlineAscent._integrate	(		self,
		float	t0,
		float	t1,
		float	f0,
		float	f1,
		float	md0,
		float	md1 )

protected

Definition at line 573 of file flight.py.

References _rhs(), at(), dt_max, liftoff_time_s, detail::exception.m, m, time.m, max, __iar_u32.v, detail::output_vector_adapter< CharType, AllocatorType >.v, v, gui.App.v, lc_calibration_gui.LCPlotWindow.v, Adafruit_LIS3DH.z, and z.

Referenced by advance().

◆ _rhs()

Tuple[float, float, float] engine.layerx.flight.InlineAscent._rhs	(		self,
		float	z,
		float	v,
		float	m,
		float	thrust,
		float	mdot )

protected

Definition at line 544 of file flight.py.

References _specific().

Referenced by _integrate().

◆ _specific()

Tuple[float, bool] engine.layerx.flight.InlineAscent._specific	(		self,
		float	z,
		float	v,
		float	m,
		float	thrust )

protected

(the specific force the motor and the air give [m/s^2], held) at this state.

Definition at line 526 of file flight.py.

References _cd_off, _cd_on, _isa, _mach, A_e, A_ref, drag, backend.routers.flight.EnvironmentConfig.elevation, elevation, feedtwin.comps.manifold.ManifoldPort.elevation, max, p_ref, and feedtwin.engine.design.DischargeModel.p_ref.

Referenced by _rhs(), held(), and specific_force().

◆ advance()

float engine.layerx.flight.InlineAscent.advance	(		self,
		float	t,
		float	thrust_N,
		float	mdot_kg_s )

Move the ascent to ``t`` with the thrust and total propellant flow sampled there, linear
from the previous sample, and return the specific force at ``t`` [m/s^2]. The first call
only places the vehicle on the pad at ``t``.

Definition at line 557 of file flight.py.

References _integrate(), feedtwin.session.core.Session._integrate(), mdot, feedtwin.comps.base.InfeasibleOperatingPoint.mdot, feedtwin.engine.balance.SideBalance.mdot, feedtwin.session.network_trace.NetworkTrace.mdot, feedtwin.vessels.vapour.VapourExchange.mdot, anonymous_namespace{idle_e2e.cpp}::Beat.t, anonymous_namespace{idle_e2e.cpp}::World::Ground.t, t, feedtwin.model.component.EvalContext.t, feedtwin.session.burn.BurnTrace.t, feedtwin.session.core.Session.t, feedtwin.session.diagnostics.SolverRecord.t, fsw::calibration::CaptureQuality.t, fsw::calibration::CubicPoint.t, gui.App.t, lc_calibration_gui.LCPlotWindow.t, rec_t.t, and thrust.

◆ from_config()

"InlineAscent" engine.layerx.flight.InlineAscent.from_config	(		cls,
		Any	config,
		float	liftoff_mass_kg,
		float	ambient_pa,
		*	,
		Any	drag = None,
		float	dt_max = 0.01 )

The vehicle the RocketPy flight flies: body radius, nozzle exit, pad elevation and drag
from ``config``; ``ambient_pa`` is the pressure the thrust curve was computed against (the
site's, as Layer X burns it).

Definition at line 517 of file flight.py.

References engine.layerx.flight._vehicle_terms().

◆ held()

bool engine.layerx.flight.InlineAscent.held ( self )

Definition at line 554 of file flight.py.

References _specific(), detail::exception.m, m, time.m, thrust, __iar_u32.v, detail::output_vector_adapter< CharType, AllocatorType >.v, v, gui.App.v, lc_calibration_gui.LCPlotWindow.v, Adafruit_LIS3DH.z, and z.

◆ specific_force()

float engine.layerx.flight.InlineAscent.specific_force ( self )

The axial specific force at the current sample [m/s^2]: exactly ``G0`` while held.

Definition at line 548 of file flight.py.

References _specific(), detail::exception.m, m, time.m, thrust, __iar_u32.v, detail::output_vector_adapter< CharType, AllocatorType >.v, v, gui.App.v, lc_calibration_gui.LCPlotWindow.v, Adafruit_LIS3DH.z, and z.

Member Data Documentation

◆ _cd_off

engine.layerx.flight.InlineAscent._cd_off = np.asarray(drag.cd_power_off, dtype=float)

protected

Definition at line 507 of file flight.py.

Referenced by _specific().

◆ _cd_on

engine.layerx.flight.InlineAscent._cd_on = np.asarray(drag.cd_power_on, dtype=float)

protected

Definition at line 506 of file flight.py.

Referenced by _specific().

◆ _isa

engine.layerx.flight.InlineAscent._isa = isa_troposphere

protected

Definition at line 503 of file flight.py.

Referenced by _specific().

◆ _mach

engine.layerx.flight.InlineAscent._mach = np.asarray(drag.mach, dtype=float)

protected

Definition at line 505 of file flight.py.

Referenced by _specific().

◆ A_e

engine.layerx.flight.InlineAscent.A_e = float(nozzle_exit_area_m2)

Definition at line 496 of file flight.py.

Referenced by _specific().

◆ A_ref

engine.layerx.flight.InlineAscent.A_ref = float(reference_area_m2)

Definition at line 495 of file flight.py.

Referenced by feed_line_K.Run._refer(), and _specific().

◆ drag

engine.layerx.flight.InlineAscent.drag = drag

Definition at line 500 of file flight.py.

Referenced by _specific().

◆ dt_max

engine.layerx.flight.InlineAscent.dt_max = float(dt_max)

Definition at line 499 of file flight.py.

Referenced by _integrate().

◆ elevation

engine.layerx.flight.InlineAscent.elevation = float(elevation_m)

Definition at line 497 of file flight.py.

Referenced by _specific().

◆ held

engine.layerx.flight.InlineAscent.held

Definition at line 569 of file flight.py.

◆ liftoff_time_s

Optional[float] engine.layerx.flight.InlineAscent.liftoff_time_s = None

Definition at line 514 of file flight.py.

Referenced by _integrate().

◆ m

engine.layerx.flight.InlineAscent.m = float(mass_kg)

Definition at line 511 of file flight.py.

Referenced by _integrate(), test_timeseries_fill_levels._Runner.evaluate_arrays(), held(), and specific_force().

◆ mdot

engine.layerx.flight.InlineAscent.mdot = 0.0

Definition at line 513 of file flight.py.

Referenced by advance(), engine.pipeline.stability.chug.ChugStream.resistance(), and feed_line_K.Run.straight().

◆ p_ref

engine.layerx.flight.InlineAscent.p_ref = None if reference_pressure_pa is None else float(reference_pressure_pa)

Definition at line 498 of file flight.py.

Referenced by _specific().

◆ t

engine.layerx.flight.InlineAscent.t = None

Definition at line 508 of file flight.py.

Referenced by engine.pipeline.cea_cache.CEAAuxTables._bilinear(), engine.pipeline.cea_cache.CEAAuxTables._build(), engine.pipeline.cea_cache.CEAAuxTables._exit(), engine.pipeline.cea_cache.CEAAuxTables._load(), and advance().

◆ thrust

engine.layerx.flight.InlineAscent.thrust = 0.0

Definition at line 512 of file flight.py.

Referenced by advance(), held(), and specific_force().

◆ v

engine.layerx.flight.InlineAscent.v = 0.0

Definition at line 510 of file flight.py.

Referenced by _integrate(), held(), and specific_force().

◆ z

engine.layerx.flight.InlineAscent.z = 0.0

Definition at line 509 of file flight.py.

Referenced by _integrate(), held(), and specific_force().

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

EngineDesign/engine/layerx/flight.py

Public Member Functions

Public Attributes

Protected Member Functions

Protected Attributes

Detailed Description

Constructor & Destructor Documentation

◆ __init__()

Member Function Documentation

◆ _integrate()

◆ _rhs()

◆ _specific()

◆ advance()

◆ from_config()

◆ held()

◆ specific_force()

Member Data Documentation

◆ _cd_off

◆ _cd_on

◆ _isa

◆ _mach

◆ A_e

◆ A_ref

◆ drag

◆ dt_max

◆ elevation

◆ held

◆ liftoff_time_s

◆ m

◆ mdot

◆ p_ref

◆ t

◆ thrust

◆ v

◆ z

◆ init()