Functions
	area_exit_calc (diameter_exit=diameter_exit_default)
	expansion_ratio_calc (area_exit, area_throat)
	area_throat_calc (pc_design, thrust_design, force_coeffcient=force_coeffcient_default)
	chamber_volume_calc (area_throat, l_star=l_star_default)
	contraction_ratio_calc (area_chamber, area_throat)
	area_chamber_calc (diameter_inner=chamber_diameter_default)
	chamber_diameter_calc (area_chamber)
	entrance_arc_volume (R_t, theta=theta_default, steps=4000)
	chamber_length_calc (chamber_volume, area_throat, contraction_ratio, theta=theta_default)
	contraction_length_horizontal_calc (area_chamber, entrance_arc_start_y, theta=theta_default)
	generate_nozzle (area_throat, area_exit, steps=200, theta=theta_default)
	chamber_geometry_calc (pc_design, thrust_design, force_coeffcient=force_coeffcient_default, diameter_inner=chamber_diameter_default, diameter_exit=diameter_exit_default, l_star=l_star_default, do_plot=False, color_segments=False, steps=200, export_dxf=None, theta=theta_default)

Variables
bool	HAS_EZDXF = True
int	theta_default = np.pi/4
float	force_coeffcient_default = 1.4
int	diameter_exit_default = 4 / 39.37
float	l_star_default = 1.27
float	chamber_diameter_default = 3.4 / 39.37
	pts
	data
	lengths
	pc_design
	e6
	thrust_design
	do_plot
	True
	color_segments
	export_dxf

Function Documentation

◆ area_chamber_calc()

engine.core.chamber_geometry.area_chamber_calc ( diameter_inner = chamber_diameter_default )

Calculate the area of the chamber.
Parameters:
- diameter_inner: The inner diameter of the chamber. = 3.4"
Calculate the area of the chamber.

Definition at line 74 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ area_exit_calc()

engine.core.chamber_geometry.area_exit_calc ( diameter_exit = diameter_exit_default )

Calculate the area of the exit of the chamber.
Parameters:
- diameter_exit: The diameter of the exit of the chamber.
Calculate the area of the exit of the chamber.

Definition at line 20 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ area_throat_calc()

engine.core.chamber_geometry.area_throat_calc	(	pc_design,
		thrust_design,
		force_coeffcient = force_coeffcient_default )

Calculate the area of the throat of the chamber.
Parameters:
- pc_design: The design chamber pressure.
- thrust_design: The design thrust.
- force_coeffcient: The force coeffcient.
Calculate the area of the throat of the chamber.

Definition at line 39 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ chamber_diameter_calc()

engine.core.chamber_geometry.chamber_diameter_calc ( area_chamber )

Calculate the diameter of the chamber.
Parameters:
- area_chamber: The area of the chamber.
Calculate the diameter of the chamber.

Definition at line 83 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ chamber_geometry_calc()

engine.core.chamber_geometry.chamber_geometry_calc	(	pc_design,
		thrust_design,
		force_coeffcient = force_coeffcient_default,
		diameter_inner = chamber_diameter_default,
		diameter_exit = diameter_exit_default,
		l_star = l_star_default,
		do_plot = False,
		color_segments = False,
		steps = 200,
		export_dxf = None,
		theta = theta_default )

Calculate the full chamber geometry including cylindrical section, contraction, and nozzle.

Parameters:
-----------
export_dxf : str or None
    If provided, exports the contour to a DXF file at the specified path.
    Example: 'chamber/chamber_contour.dxf'

Returns:
--------
pts : numpy array
    Array of (x, y) points representing the full chamber contour
data : list of lists
    Table data with metric and imperial units. First row contains headers:
    ['Parameter', 'Metric Value', 'Metric Units', 'Imperial Value', 'Imperial Units']
    Subsequent rows contain parameter data.

Definition at line 169 of file chamber_geometry.py.

References area_chamber_calc(), area_exit_calc(), area_throat_calc(), chamber_diameter_calc(), chamber_length_calc(), chamber_volume_calc(), contraction_length_horizontal_calc(), contraction_ratio_calc(), expansion_ratio_calc(), and generate_nozzle().

◆ chamber_length_calc()

engine.core.chamber_geometry.chamber_length_calc	(	chamber_volume,
		area_throat,
		contraction_ratio,
		theta = theta_default )

Calculate the length of the chamber.
Parameters:
- chamber_volume: The volume of the chamber.
- area_throat: The area of the throat of the chamber.
- contraction_ratio: The contraction ratio of the chamber.
- theta: The angle of the chamber. = 45 degrees from -135deg nozzle entrance
Calculate the length of the chamber.

Definition at line 111 of file chamber_geometry.py.

References entrance_arc_volume().

Referenced by chamber_geometry_calc().

◆ chamber_volume_calc()

engine.core.chamber_geometry.chamber_volume_calc	(		area_throat,
			l_star = l_star_default )

Parameters:
- l_star: The characteristic length of the chamber. (Get from config)
- area_throat: The area of the throat of the chamber.
Calculate the volume of the chamber.

Definition at line 50 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ contraction_length_horizontal_calc()

engine.core.chamber_geometry.contraction_length_horizontal_calc	(	area_chamber,
		entrance_arc_start_y,
		theta = theta_default )

Definition at line 155 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ contraction_ratio_calc()

engine.core.chamber_geometry.contraction_ratio_calc	(		area_chamber,
			area_throat )

Calculate the contraction ratio of the chamber.
Parameters:
- area_chamber: The area of the chamber.
- area_throat: The area of the throat of the chamber.
Calculate the contraction ratio of the chamber.

Definition at line 64 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ entrance_arc_volume()

engine.core.chamber_geometry.entrance_arc_volume	(	R_t,
		theta = theta_default,
		steps = 4000 )

Solid-of-revolution volume of the 1.5*R_t nozzle entrance arc, face side of the throat.

The arc is centred at (0, 2.5*R_t) with radius 1.5*R_t and is swept from
t = -(pi/2 + theta) (tangent to the convergent cone) to t = -pi/2 (the throat), so

    x(t) = 1.5 R_t cos t,   y(t) = 1.5 R_t sin t + 2.5 R_t

and V = integral of pi*y^2 dx over that sweep. Integrated numerically because the closed
form is easy to get subtly wrong and this is called once per candidate, not per step.

Definition at line 92 of file chamber_geometry.py.

Referenced by chamber_length_calc().

◆ expansion_ratio_calc()

engine.core.chamber_geometry.expansion_ratio_calc	(		area_exit,
			area_throat )

Calculate the expansion ratio of the chamber.
Parameters:
- area_exit: The area of the exit of the chamber.
- area_throat: The area of the throat of the chamber.
Calculate the expansion ratio of the chamber.

Definition at line 29 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

◆ generate_nozzle()

engine.core.chamber_geometry.generate_nozzle	(	area_throat,
		area_exit,
		steps = 200,
		theta = theta_default )

Definition at line 164 of file chamber_geometry.py.

Referenced by chamber_geometry_calc().

Variable Documentation

◆ chamber_diameter_default

float engine.core.chamber_geometry.chamber_diameter_default = 3.4 / 39.37

Definition at line 18 of file chamber_geometry.py.

◆ color_segments

engine.core.chamber_geometry.color_segments

Definition at line 390 of file chamber_geometry.py.

◆ data

engine.core.chamber_geometry.data

Definition at line 390 of file chamber_geometry.py.

◆ diameter_exit_default

int engine.core.chamber_geometry.diameter_exit_default = 4 / 39.37

Definition at line 16 of file chamber_geometry.py.

◆ do_plot

engine.core.chamber_geometry.do_plot

Definition at line 390 of file chamber_geometry.py.

◆ e6

engine.core.chamber_geometry.e6

Definition at line 390 of file chamber_geometry.py.

◆ export_dxf

engine.core.chamber_geometry.export_dxf

Definition at line 390 of file chamber_geometry.py.

◆ force_coeffcient_default

float engine.core.chamber_geometry.force_coeffcient_default = 1.4

Definition at line 15 of file chamber_geometry.py.

◆ HAS_EZDXF

bool engine.core.chamber_geometry.HAS_EZDXF = True

Definition at line 8 of file chamber_geometry.py.

◆ l_star_default

float engine.core.chamber_geometry.l_star_default = 1.27

Definition at line 17 of file chamber_geometry.py.

◆ lengths

engine.core.chamber_geometry.lengths

Definition at line 390 of file chamber_geometry.py.

◆ pc_design

engine.core.chamber_geometry.pc_design

Definition at line 390 of file chamber_geometry.py.

◆ pts

engine.core.chamber_geometry.pts

Definition at line 390 of file chamber_geometry.py.

◆ theta_default

int engine.core.chamber_geometry.theta_default = np.pi/4

Definition at line 14 of file chamber_geometry.py.

◆ thrust_design

engine.core.chamber_geometry.thrust_design

Definition at line 390 of file chamber_geometry.py.

◆ True

engine.core.chamber_geometry.True

Definition at line 390 of file chamber_geometry.py.

Functions

Variables

Function Documentation

◆ area_chamber_calc()

◆ area_exit_calc()

◆ area_throat_calc()

◆ chamber_diameter_calc()

◆ chamber_geometry_calc()

◆ chamber_length_calc()

◆ chamber_volume_calc()

◆ contraction_length_horizontal_calc()

◆ contraction_ratio_calc()

◆ entrance_arc_volume()

◆ expansion_ratio_calc()

◆ generate_nozzle()

Variable Documentation

◆ chamber_diameter_default

◆ color_segments

◆ data

◆ diameter_exit_default

◆ do_plot

◆ e6

◆ export_dxf

◆ force_coeffcient_default

◆ HAS_EZDXF

◆ l_star_default

◆ lengths

◆ pc_design

◆ pts

◆ theta_default

◆ thrust_design

◆ True