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Path: Orbit/OrbitMechanics
% Computes a fuel budget from a list of events.
You need only fill in the data structure with the data needed for the types of
maneuver used. The first event should always be 'initial'.
For delta-V maneuvers if some of the delta-V thrusters are chosen for acs use,
those thrusters will be off-pulsed.
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Form:
b = FBudget( event, x, file, title, html )
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Inputs
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event (:) Event data structure
event.description (1,:) String describing the event
event.type (1,:) 'initial', 'delta-v', 'delta-h', 'acs','pulses', 'circular'
event.aCSThruster (1,:) List of ACS thrusters to use <- all
event.dVThruster (1,:) List of deltaV thrusters to use <- 'delta-V'
event.dVTotal (1,1) Total delta-V <- 'delta-V'
event.dTControl (1,1) Control period <- 'delta-V', 'acs'
event.burnEff (1,1) Burn efficiency <- 'delta-V'
event.dHTotal (1,1) Total delta-H <- 'delta-H'
event.disturbance (3,1) Attitude disturbance <- 'acs'
event.pulsewidth (1,1) Pulsewidth to be used <- all
event.nPulses (1,1) Number of pulses <- pulse
event.duration (1,1) Used for attitude control <- 'acs'
event.regulated (1,1) 1 if regulated at following level
event.cM (3,1) Center of mass
event.circular (1,1) struct('period',p,'radius',r,'duration',t) <- 'circular'
x (1,1) Spacecraft data
x.regulatedPressure(1,:) Regulated pressure (if any)
x.systemTemp (1,:) Temperature of each system
x.systemVol (1,:) Volume of each system
x.systemFuel (1,:) Fuel per system
x.pressurantMass (1,:) Pressurant mass per system
x.pressurantR (1,1) Pressurant gas constant
x.thrusterData (:) Data
.systemID (1,1) System it is attached to
.iSP (1,:) ISP coefficients*
.thrust (1,:) Thrust coefficients*
.riseTime (1,:) Thruster pulse rise time
.fallTime (1,:) Thruster pulse fall time
.u (3,1)
.r (3,1)
x.dryMass (1,1) Dry mass
x.fuelDensity (1,1) Fuel density
x.controlDT (1,1) Control period
file (1,:) File name
title (1,:) Budget title
html (1,:) Any argument here gives html
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Outputs
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b (:) b.description (1,:) String describing the event
b.massTotal (1,1) Total mass
b.massFuel (1,:) Mass of fuel per system
b.fuelUsed (1,:) Fuel used per system
b.pressure (1,:) Pressure per system
b.iSpACS (1,:) Average ACS Isp
by.iSpDV (1,:) Average DV Isp
* Note: These coefficients model the thrust an Isp for short pulses. Please see
the functions ISp and Thrust below.
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Common: General/CreateHTMLTable Common: General/CreateLatexTable Common: General/StringToTokens Math: Analysis/Simplex Math: Linear/Cross Math: Linear/Mag Math: Linear/SumV Orbit: OrbitManeuver/CircularManeuver SC: Actuator/BloDown
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