Propulsion utilities for rocket, air-breathing, and electric systems. More...

Namespaces
namespace	air_breathing
namespace	electric
namespace	rocket

Functions
template<typename Scalar>
Scalar	altitude_thrust (const Scalar &F_vac, const Scalar &P_atm, double P_exit, double A_exit)
	Calculates thrust adjusted for ambient pressure (altitude).
template<typename Scalar>
Scalar	thrust_coefficient (const Scalar &thrust, const Scalar &P_chamber, double A_throat)
	Calculates the thrust coefficient.

Detailed Description

Propulsion utilities for rocket, air-breathing, and electric systems.

This module provides clean, functional, symbolic-compatible implementations of core propulsion equations.

Function Documentation

◆ altitude_thrust()

template<typename Scalar>

Scalar vulcan::propulsion::altitude_thrust	(	const Scalar &	F_vac,
		const Scalar &	P_atm,
		double	P_exit,
		double	A_exit )

Calculates thrust adjusted for ambient pressure (altitude).

Standard correction: F = F_vac - P_atm * A_e

Note: The implementation plan proposed F = F_vac - (P_atm - P_e) * A_e. However, since F_vac = F_mom + P_e * A_e, substituting into the standard equation: F = F_mom + (P_e - P_atm) * A_e = (F_mom + P_e * A_e) - P_atm * A_e = F_vac - P_atm * A_e

The P_exit parameter is kept in the signature for compatibility with the plan but is not used in the standard calculation derived from F_vac.

Template Parameters

Scalar Variable type

Parameters

F_vac	Thrust in vacuum [N]
P_atm	Ambient atmospheric pressure [Pa]
P_exit	Nozzle exit pressure [Pa] (Unused for F_vac based calculation)
A_exit	Nozzle exit area [m^2]

Returns: Altitude-compensated thrust [N]

◆ thrust_coefficient()

template<typename Scalar>

Scalar vulcan::propulsion::thrust_coefficient	(	const Scalar &	thrust,
		const Scalar &	P_chamber,
		double	A_throat )

Calculates the thrust coefficient.

C_F = F / (P_c * A_t)