calculate_responses1¶

Source: userfiles/SSBJ/subsystem1/calculate_responses1.py

Response calculation module for SSBJ Subsystem 1 (Propulsion).

This module provides propulsion-related calculations for the Supersonic Business Jet (SSBJ) problem.

Functions¶

poly_approx(S, S_new, flag, S_bound)

Calculate polynomial approximation for propulsion parameters.

Args:

S: Base values for normalization.
S_new: New values to be normalized against base values.
flag: Flags controlling the polynomial coefficient calculation mode.
S_bound: Boundary values for the polynomial approximation.

Returns:

Scaled performance factor.

calculate_specific_fuel_consumption(dim_throttle: float, h: float, Mach: float)

Calculate Specific Fuel Consumption (SFC).

Args:

dim_throttle: Dimensional throttle setting [lb].
h: Altitude in feet [ft].
Mach: Mach number [-].

Returns:

Specific fuel consumption value [1/hr].

calculate_engine_scale_factor(drag: float, dim_throttle: float)

Calculate Engine Specific Force (ESF).

Args:

drag: Total drag force [lb].
dim_throttle: Dimensional throttle setting [lb].

Returns:

Engine scale factor [-].

calculate_engine_weight(engine_scale_factor: float)

Calculate engine weight based on ESF.

Args:

engine_scale_factor: Engine scale factor [-].

Returns:

Engine weight [lb].

calculate_engine_temperature(drag: float, throttle: float, h: float, Mach: float)

Calculate engine temperature and throttle adjustment.

Reproduces the original DMDO SSBJ propulsion logic, which normalizes the (non-dimensional) throttle design variable against the drag reference in the polynomial approximation.

Args:

drag: Total drag force [lb].
throttle: Throttle setting (non-dimensional design variable) [-].
h: Altitude in feet [ft].
Mach: Mach number [-].

Returns:

Engine temperature scaling factor [-].

calculate_throttle_uA(h: float, Mach: float)

Calculate upper-bound throttle value.

Args:

h: Altitude in feet [ft].
Mach: Mach number [-].

Returns:

Upper-bound throttle value [lb].