vulcan::propulsion::rocket Namespace Reference

Functions
template<typename Scalar>
Scalar	thrust_from_mdot (const Scalar &mdot, const Scalar &Ve)
	Calculates thrust from mass flow rate and effective exhaust velocity.
template<typename Scalar>
Scalar	exhaust_velocity (const Scalar &Isp, double g0=9.80665)
	Calculates effective exhaust velocity from specific impulse.
template<typename Scalar>
Scalar	specific_impulse (const Scalar &thrust, const Scalar &mdot, double g0=9.80665)
	Calculates specific impulse from thrust, mass flow rate, and gravity.
template<typename Scalar>
Scalar	delta_v (const Scalar &Ve, const Scalar &m0, const Scalar &mf)
	Calculates Delta-V using the Tsiolkovsky rocket equation.
template<typename Scalar>
Scalar	propellant_mass (const Scalar &delta_v, const Scalar &m0, const Scalar &Ve)
	Calculates required propellant mass for a given Delta-V.
template<typename Scalar>
Scalar	mass_flow_rate (const Scalar &thrust, const Scalar &Ve)
	Calculates mass flow rate from thrust and exhaust velocity.
template<typename Scalar>
Scalar	burn_time (const Scalar &propellant_mass, const Scalar &mdot)
	Calculates burn time for a given propellant mass and flow rate.

Function Documentation

burn_time()

template<typename Scalar>

Scalar vulcan::propulsion::rocket::burn_time	(	const Scalar &	propellant_mass,
		const Scalar &	mdot )

Calculates burn time for a given propellant mass and flow rate.

t = mp / mdot

Template Parameters

Scalar

Variable type

Parameters

propellant_mass	Mass of propellant to burn [kg]
mdot	Mass flow rate [kg/s]

Returns

Burn time [s]

delta_v()

template<typename Scalar>

Scalar vulcan::propulsion::rocket::delta_v	(	const Scalar &	Ve,
		const Scalar &	m0,
		const Scalar &	mf )

Calculates Delta-V using the Tsiolkovsky rocket equation.

dV = Ve * ln(m0 / mf)

Template Parameters

Scalar

Variable type

Parameters

Ve	Effective exhaust velocity [m/s]
m0	Initial mass [kg]
mf	Final mass [kg]

Returns

Delta-V [m/s]

exhaust_velocity()

template<typename Scalar>

Scalar vulcan::propulsion::rocket::exhaust_velocity	(	const Scalar &	Isp,
		double	g0 = 9.80665 )

Calculates effective exhaust velocity from specific impulse.

Ve = Isp * g0

Template Parameters

Scalar

Variable type

Parameters

Isp	Specific impulse [s]
g0	Standard gravity [m/s^2] (default: 9.80665)

Returns

Effective exhaust velocity [m/s]

mass_flow_rate()

template<typename Scalar>

Scalar vulcan::propulsion::rocket::mass_flow_rate	(	const Scalar &	thrust,
		const Scalar &	Ve )

Calculates mass flow rate from thrust and exhaust velocity.

mdot = F / Ve

Template Parameters

Scalar

Variable type

Parameters

thrust	Thrust force [N]
Ve	Effective exhaust velocity [m/s]

Returns

Mass flow rate [kg/s]

propellant_mass()

template<typename Scalar>

Scalar vulcan::propulsion::rocket::propellant_mass	(	const Scalar &	delta_v,
		const Scalar &	m0,
		const Scalar &	Ve )

Calculates required propellant mass for a given Delta-V.

mp = m0 * (1 - exp(-dV / Ve))

Template Parameters

Scalar

Variable type

Parameters

delta_v	Target Delta-V [m/s]
m0	Initial mass [kg]
Ve	Effective exhaust velocity [m/s]

Returns

Propellant mass required [kg]

specific_impulse()

template<typename Scalar>

Scalar vulcan::propulsion::rocket::specific_impulse	(	const Scalar &	thrust,
		const Scalar &	mdot,
		double	g0 = 9.80665 )

Calculates specific impulse from thrust, mass flow rate, and gravity.

Isp = F / (mdot * g0)

Template Parameters

Scalar

Variable type

Parameters

thrust	Thrust force [N]
mdot	Mass flow rate [kg/s]
g0	Standard gravity [m/s^2] (default: 9.80665)

Returns

Specific impulse [s]

thrust_from_mdot()

template<typename Scalar>

Scalar vulcan::propulsion::rocket::thrust_from_mdot	(	const Scalar &	mdot,
		const Scalar &	Ve )

Calculates thrust from mass flow rate and effective exhaust velocity.

F = mdot * Ve

Template Parameters

Scalar

Variable type (e.g., double or casadi::MX)

Parameters

mdot	Mass flow rate [kg/s]
Ve	Effective exhaust velocity [m/s]

Returns

Thrust [N]