FireSatelliteModel

class FireSatelliteModel

Data class for the Fire Satellite.

Examples

>>> from openturns.usecases import fireSatellitefunction
>>> # Load the FireSatellite model model
>>> m = fireSatellitefunction.FireSatelliteModel()

Attributes:

dimDimension of the problem

dim = 9

HAltitude (m), TruncatedNormal distribution

First marginal, ot.TruncatedNormal(18e6,1e6,18e6-3e6,18e6+3e6)

PotherPower other than ACS (W), TruncatedNormal distribution

Second marginal, ot.TruncatedNormal(1000.0,50.0,1000.0-150.0,1000.0+150.0)

FsAverage solar flux (W/m^2), TruncatedNormal distribution

Third marginal, ot.TruncatedNormal(1400.0,20.0,1400.0-60.0,1400.0+60.0)

thetaDeviation of moment axis (deg), TruncatedNormal distribution

Fourth marginal, ot.TruncatedNormal(15.0,1.0,15.0-3.0,15.0+3.0)

LspMoment arm for radiation torque (m), TruncatedNormal distribution

Fifth marginal, ot.TruncatedNormal(2.0,0.4,2.0-1.2,2.0+1.2)

qReflectance factor (-), TruncatedNormal distribution

Sixth marginal, ot.TruncatedNormal(0.5,0.1,0.5-0.3,0.5+0.3)

RDResidual dipole of spacecraft (A.m^2), TruncatedNormal distribution

Seventh marginal, ot.TruncatedNormal(5.0,1.0,5.0-3.0,5.0+3.0)

LalphaMoment arm for aerodynamic torque (m), TruncatedNormal distribution

Eighth marginal, ot.TruncatedNormal(2.0,0.4,2.0-1.2,2.0+1.2)

CdDrag coefficient (-), TruncatedNormal distribution

Nineth marginal, ot.TruncatedNormal(1.0,0.3,1.0-0.9,1.0+0.9)

distributionXJointDistribution

The joint distribution of the input parameters.

modelPythonFunction

The Fire Satellite model with H, Pother, Fs, theta, Lsp, q, RD, Lalpha and Cd as variables. This function retrieves three outputs : the total torque, the total power and the area of solar array

modelTotalTorquePythonFunction

The Fire Satellite model retrieving only the Total Torque as output, with H, Pother, Fs, theta, Lsp, q, RD, Lalpha and Cd as variables.

modelTotalPowerPythonFunction

The Fire Satellite model retrieving only the Total Power as output, with H, Pother, Fs, theta, Lsp, q, RD, Lalpha and Cd as variables. This function retrieves three outputs : the total torque, the total power and the area of solar array

modelSolarArrayAreaPythonFunction

The Fire Satellite model retrieving only the Solar Array Area as output, with H, Pother, Fs, theta, Lsp, q, RD, Lalpha and Cd as variables. This function retrieves three outputs : the total torque, the total power and the area of solar array

cSpeed of light, constant

c = 2.9979e8 m/s

omega_maxMaximum rotational velocity of reaction wheel, constant

omega_max = 6000 rpm

nNumber of reaction wheels that could be active, constant

n = 3

delta_theta_slewSlewing time period, constant

delta_theta_slew = 760 s

AsArea reflecting radiation, constant

As = 13.85 m^2

iSun incidence angle, constant

i = 0 deg

MMagnetic moment of earth, constant

M = 7.96e15 A.m^2

rhoAtmospheric density, constant

rho = 5.1480e-11 kg/m^3

ACross-sectional in flight direction, constant

A = 13.85 m^2

PholdHolding power, constant

Phold = 20 W

muEarth gravity constant

mu = 398600.4418e9 m^3/s^2

IdInherent degradation of array, constant

Id = 0.77

tThickness of solar panels, constant

t = 0.005 m

n_saNumber of solar arrays, constant

n_sa = 3

epsilon_degDegradation in power production capability, constant

epsilon_deg = 0.0375 percent per year

LTLifetime of spacecraft, constant

LT = 15 years

r_lwLength to width ratio of solar array, constant

r_lw = 3

DDistance between panels, constant

D = 2 m

I_bodyXInertia of body, X axis, constant

I_bodyX = 6200 kg.m^2

I_bodyYInertia of body, Y axis, constant

I_bodyY = 6200 kg.m^2

I_bodyZInertia of body, Z axis, constant

I_bodyZ = 4700 kg.m^2

rho_saAverage mass density to arrays, constant

rho_sa = 700 kg.m^3

etaPower efficiency, constant

eta = 0.22

phi_targetTarget diameter, constant

phi_target = 235000 m

REEarth radius, constant

RE = 6378140 m

tolFPITolerance on Fixed Point Iteration used in the multidisciplinary analysis

tolFPI = 1e-3 (deterministic)

maxFPIIterMaximum number of iterations of Fixed Point Iteration used in the multidisciplinary analysis

maxFPIIter = 50 (deterministic)

Methods

attitudeControl(inputs)	Function computing the attitude and control discipline outputs to retrieve the power of ACS and total torque
multidisciplinaryAnalysis(x)	Function computing the multidisciplinary analysis to retrieve the total torque, the total power and the area of solar array
orbit(inputs)	Function computing the orbit discipline outputs and retrieve the slewing angle, the velocity, the orbit duration and the eclipse duration
power(inputs)	Function computing the power discipline outputs to retrieve the inertia, the total power and the area of solar array

__init__()

attitudeControl(inputs)

Function computing the attitude and control discipline outputs to retrieve the power of ACS and total torque

Inputs:

dictionary of inputs of the Attitude and Control discipline

multidisciplinaryAnalysis(x)

Function computing the multidisciplinary analysis to retrieve the total torque, the total power and the area of solar array

X:

list of inputs

orbit(inputs)

Function computing the orbit discipline outputs and retrieve the slewing angle, the velocity, the orbit duration and the eclipse duration

Inputs:

dictionary of inputs of the Orbit discipline

power(inputs)

Function computing the power discipline outputs to retrieve the inertia, the total power and the area of solar array

Inputs:

dictionary of inputs of the Power discipline

Examples using the class

Example of multi output Kriging on the fire satellite model

Example of multi output Kriging on the fire satellite model