SolidMotor Class

class rocketpy.SolidMotor.SolidMotor(thrustSource, burnOut, grainNumber, grainDensity, grainOuterRadius, grainInitialInnerRadius, grainInitialHeight, grainSeparation=0, nozzleRadius=0.0335, throatRadius=0.0114, reshapeThrustCurve=False, interpolationMethod='linear')[source]

Class to specify characteristics and useful operations for solid motors.

Geometrical attributes
Motor.nozzleRadius

Radius of motor nozzle outlet in meters.

Type

float

Motor.throatRadius

Radius of motor nozzle throat in meters.

Type

float

Motor.grainNumber

Number of solid grains.

Type

int

Motor.grainSeparation

Distance between two grains in meters.

Type

float

Motor.grainDensity

Density of each grain in kg/meters cubed.

Type

float

Motor.grainOuterRadius

Outer radius of each grain in meters.

Type

float

Motor.grainInitialInnerRadius

Initial inner radius of each grain in meters.

Type

float

Motor.grainInitialHeight

Initial height of each grain in meters.

Type

float

Motor.grainInitialVolume

Initial volume of each grain in meters cubed.

Type

float

Motor.grainInnerRadius

Inner radius of each grain in meters as a function of time.

Type

Function

Motor.grainHeight

Height of each grain in meters as a function of time.

Type

Function

Mass and moment of inertia attributes
Motor.grainInitialMass

Initial mass of each grain in kg.

Type

float

Motor.propellantInitialMass

Total propellant initial mass in kg.

Type

float

Motor.mass

Propellant total mass in kg as a function of time.

Type

Function

Motor.massDot

Time derivative of propellant total mass in kg/s as a function of time.

Type

Function

Motor.inertiaI

Propellant moment of inertia in kg*meter^2 with respect to axis perpendicular to axis of cylindrical symmetry of each grain, given as a function of time.

Type

Function

Motor.inertiaIDot

Time derivative of inertiaI given in kg*meter^2/s as a function of time.

Type

Function

Motor.inertiaZ

Propellant moment of inertia in kg*meter^2 with respect to axis of cylindrical symmetry of each grain, given as a function of time.

Type

Function

Motor.inertiaDot

Time derivative of inertiaZ given in kg*meter^2/s as a function of time.

Type

Function

Thrust and burn attributes
Motor.thrust

Motor thrust force, in Newtons, as a function of time.

Type

Function

Motor.totalImpulse

Total impulse of the thrust curve in N*s.

Type

float

Motor.maxThrust

Maximum thrust value of the given thrust curve, in N.

Type

float

Motor.maxThrustTime

Time, in seconds, in which the maximum thrust value is achieved.

Type

float

Motor.averageThrust

Average thrust of the motor, given in N.

Type

float

Motor.burnOutTime

Total motor burn out time, in seconds. Must include delay time when the motor takes time to ignite. Also seen as time to end thrust curve.

Type

float

Motor.exhaustVelocity

Propulsion gases exhaust velocity, assumed constant, in m/s.

Type

float

Motor.burnArea

Total burn area considering all grains, made out of inner cylindrical burn area and grain top and bottom faces. Expressed in meters squared as a function of time.

Type

Function

Motor.Kn

Motor Kn as a function of time. Defined as burnArea divided by nozzle throat cross sectional area. Has no units.

Type

Function

Motor.burnRate

Propellant burn rate in meter/second as a function of time.

Type

Function

Motor.interpolate

Method of interpolation used in case thrust curve is given by data set in .csv or .eng, or as an array. Options are ‘spline’ ‘akima’ and ‘linear’. Default is “linear”.

Type

string

Initialize Motor class, process thrust curve and geometrical parameters and store results.

Parameters
  • thrustSource (int, float, callable, string, array) – Motor’s thrust curve. Can be given as an int or float, in which case the thrust will be considered constant in time. It can also be given as a callable function, whose argument is time in seconds and returns the thrust supplied by the motor in the instant. If a string is given, it must point to a .csv or .eng file. The .csv file shall contain no headers and the first column must specify time in seconds, while the second column specifies thrust. Arrays may also be specified, following rules set by the class Function. See help(Function). Thrust units are Newtons.

  • burnOut (int, float) – Motor burn out time in seconds.

  • grainNumber (int) – Number of solid grains

  • grainDensity (int, float) – Solid grain density in kg/m3.

  • grainOuterRadius (int, float) – Solid grain outer radius in meters.

  • grainInitialInnerRadius (int, float) – Solid grain initial inner radius in meters.

  • grainInitialHeight (int, float) – Solid grain initial height in meters.

  • grainSeparation (int, float, optional) – Distance between grains, in meters. Default is 0.

  • nozzleRadius (int, float, optional) – Motor’s nozzle outlet radius in meters. Used to calculate Kn curve. Optional if the Kn curve is not interesting. Its value does not impact trajectory simulation.

  • throatRadius (int, float, optional) – Motor’s nozzle throat radius in meters. Its value has very low impact in trajectory simulation, only useful to analyze dynamic instabilities, therefore it is optional.

  • reshapeThrustCurve (boolean, tuple, optional) – If False, the original thrust curve supplied is not altered. If a tuple is given, whose first parameter is a new burn out time and whose second parameter is a new total impulse in Ns, the thrust curve is reshaped to match the new specifications. May be useful for motors whose thrust curve shape is expected to remain similar in case the impulse and burn time varies slightly. Default is False.

  • interpolationMethod (string, optional) – Method of interpolation to be used in case thrust curve is given by data set in .csv or .eng, or as an array. Options are ‘spline’ ‘akima’ and ‘linear’. Default is “linear”.

Returns

Return type

None

reshapeThrustCurve(burnTime, totalImpulse, oldTotalImpulse=None, startAtZero=True)[source]

Transforms the thrust curve supplied by changing its total burn time and/or its total impulse, without altering the general shape of the curve. May translate the curve so that thrust starts at time equals 0, without any delays.

Parameters
  • burnTime (float) – New desired burn out time in seconds.

  • totalImpulse (float) – New desired total impulse.

  • oldTotalImpulse (float, optional) – Specify the total impulse of the given thrust curve, overriding the value calculated by numerical integration. If left as None, the value calculated by numerical integration will be used in order to reshape the curve.

  • startAtZero (bool, optional) – If True, trims the initial thrust curve points which are 0 Newtons, translating the thrust curve so that thrust starts at time equals 0. If False, no translation is applied.

Returns

Return type

None

evaluateTotalImpulse()[source]

Calculates and returns total impulse by numerical integration of the thrust curve in SI units. The value is also stored in self.totalImpulse.

Parameters

None

Returns

self.totalImpulse – Motor total impulse in Ns.

Return type

float

exhaustVelocity

Calculates and returns exhaust velocity by assuming it as a constant. The formula used is total impulse/propellant initial mass. The value is also stored in self.exhaustVelocity.

Parameters

None

Returns

self.exhaustVelocity – Constant gas exhaust velocity of the motor.

Return type

float

evaluateMassDot()[source]

Calculates and returns the time derivative of propellant mass by assuming constant exhaust velocity. The formula used is the opposite of thrust divided by exhaust velocity. The result is a function of time, object of the Function class, which is stored in self.massDot.

Parameters

None

Returns

self.massDot – Time derivative of total propellant mas as a function of time.

Return type

Function

evaluateMass()[source]

Calculates and returns the total propellant mass curve by numerically integrating the MassDot curve, calculated in evaluateMassDot. Numerical integration is done with the Trapezoidal Rule, given the same result as scipy.integrate. odeint but 100x faster. The result is a function of time, object of the class Function, which is stored in self.mass.

Parameters

None

Returns

self.mass – Total propellant mass as a function of time.

Return type

Function

evaluateGeometry()[source]

Calculates grain inner radius and grain height as a function of time by assuming that every propellant mass burnt is exhausted. In order to do that, a system of differential equations is solved using scipy.integrate. odeint. Furthermore, the function calculates burn area, burn rate and Kn as a function of time using the previous results. All functions are stored as objects of the class Function in self.grainInnerRadius, self.grainHeight, self. burnArea, self.burnRate and self.Kn.

Parameters

None

Returns

geometry – First element is the Function representing the inner radius of a grain as a function of time. Second argument is the Function representing the height of a grain as a function of time.

Return type

list of Functions

evaluateBurnArea()[source]

Calculates the BurnArea of the grain for each time. Assuming that the grains are cylindrical BATES grains.

Parameters

None

Returns

  • burnArea (Function)

  • Function representing the burn area progression with the time.

evaluateBurnRate()[source]

Calculates the BurnRate with respect to time. This evaluation assumes that it was already calculated the massDot, burnArea timeseries.

Parameters

None

Returns

  • burnRate (Function)

  • Rate of progression of the inner radius during the combustion.

evaluateInertia()[source]

Calculates propellant inertia I, relative to directions perpendicular to the rocket body axis and its time derivative as a function of time. Also calculates propellant inertia Z, relative to the axial direction, and its time derivative as a function of time. Products of inertia are assumed null due to symmetry. The four functions are stored as an object of the Function class.

Parameters

None

Returns

The first argument is the Function representing inertia I, while the second argument is the Function representing inertia Z.

Return type

list of Functions

importEng(fileName)[source]
Read content from .eng file and process it, in order to

return the comments, description and data points.

fileNamestring

Name of the .eng file. E.g. ‘test.eng’. Note that the .eng file must not contain the 0 0 point.

commentslist

All comments in the .eng file, separated by line in a list. Each line is an entry of the list.

description: list

Description of the motor. All attributes are returned separated in a list. E.g. “F32 24 124 5-10-15 .0377 .0695 RV

” is return as

[‘F32’, ‘24’, ‘124’, ‘5-10-15’, ‘.0377’, ‘.0695’, ‘RV

‘]
dataPoints: list

List of all data points in file. Each data point is an entry in the returned list and written as a list of two entries.

exportEng(fileName, motorName)[source]

Exports thrust curve data points and motor description to .eng file format. A description of the format can be found here: http://www.thrustcurve.org/raspformat.shtml

Parameters
  • fileName (string) – Name of the .eng file to be exported. E.g. ‘test.eng’

  • motorName (string) – Name given to motor. Will appear in the description of the .eng file. E.g. ‘Mandioca’

Returns

Return type

None

info()[source]

Prints out a summary of the data and graphs available about the Motor.

Parameters

None

Returns

Return type

None

allInfo()[source]

Prints out all data and graphs available about the Motor.

Parameters

None

Returns

Return type

None