def load(sheetName):
"""
loads list of constants from xls database
"""
pth = MyPaths()
output = {}
sh = ReadDatabase(pth.db.constants,sheetName)
for irow in range(1,sh.nrows):
name = sh.read_cell(irow,1)
value = sh.read_row(irow,2,False)
output[str(name)] = value
return output
def _read_db(self,sheetName='Sheet1'):
db = ReadDatabase(self.dbPath,sheetName)
nComp = db.nrows - 1
self.name = db.read_column(1,0,nComp,True)
self.desc = db.read_column(1,1,nComp,True)
self.relCD = db.read_column(1,2,nComp,True)
mode = db.read_column(1,3,nComp,True)
for m in mode:
if m=='*':
self.mode.append(True)
else:
self.mode.append(False)
def load(self,name, xlsPath=None):
""" loads turbofan engine from database file"""
path = MyPaths()
if xlsPath==None:
xlsPath = path.db.engineTurbofan
self.name = str(name)
db = ReadDatabase(xlsPath,self.name)
self.thrustMC = db.read_row(-1,1) *constants.GRAVITY_ACCEL
self.sfcMC = db.read_row(-1,1)
self.length = db.read_row(-1,1)
self.diameter = db.read_row(-1,1)
self.mass = db.read_row(-1,1,False)
self.BPR = db.read_row(-1,1)
self._calc_data()
def load_xls(self, name, xlsPath=None):
"""
Loads aircraft data from *.xls datasheet and calculates necessary
parameters:
- full geometry data set
- weight and cg
- parasite drag curve: CD0 vs Mach
- engine thrust table if it does not exist for selected engine
Parameters
----------
name : string
name of aircraft in database
xlsPath : path, optional
database path
"""
self.name = str(name)
if xlsPath == None:
xlsPath = path.db.aircraftFW
keyword = "SECTION: "
db = ReadDatabase(xlsPath, name, keyword)
idx = db.find_header(keyword + "DESIGN QUANTITIES")
self.type = db.read_row(idx + 1, 1)
self.designGoals.fuelMass = db.read_row(-1, 1)
self.designGoals.avionicsMass = db.read_row(-1, 1)
self.designGoals.grossMass = db.read_row(-1, 1)
self.designGoals.cruiseMach = db.read_row(-1, 1)
self.designGoals.cruiseAltitude = db.read_row(-1, 1)
self.designGoals.loadFactor = db.read_row(-1, 1)
self.designGoals.loadFactorLanding = db.read_row(-1, 1)
self.designGoals.staticThrust = db.read_row(-1, 1)
self.designGoals.numberOfOccupants = db.read_row(-1, 1)
idx = db.find_header(keyword + "FUSELAGE")
self.fusWidth = db.read_row(idx + 1, 1, False)
idx = db.find_header(keyword + "MAIN WING")
self.wing.segSpans = db.read_row(idx + 1, 1, True)
self.wing.chords = db.read_row(-1, 1, True)
self.wing.airfoilNames = db.read_row(-1, 1, True)
self.wing.secOffset = db.read_row(-1, 1, True)
self.wing.segDihedral = db.read_row(-1, 1, True)
self.wing.secTwist = db.read_row(-1, 1, True)
self.wing.incidence = db.read_row(-1, 1, False)
elevonLocation = db.read_row(-1, 1, True)
flapLocation = db.read_row(-1, 1, True)
self.wing.set_elevon(elevonLocation)
self.wing.set_flap(flapLocation)
self.wing.flap.type = db.read_row(-1, 1, False)
self.wing.material = db.read_row(-1, 1, False)
self.wing.fuelTankCGratio = db.read_row(-1, 1, True)
idx = db.find_header(keyword + "PROPULSION")
engineName = db.read_row(idx + 1, 1, False)
self.propulsion.load(engineName, True)
self.propulsion.sfcModel = None
self.propulsion.numberOfEngines = int(db.read_row(-1, 1, False))
self.propulsion.CGx = db.read_row(-1, 1, True)
self.propulsion.CGy = db.read_row(-1, 1, True)
self.propulsion.CGz = db.read_row(-1, 1, True)
self.propulsion.engine.deignAltitude = self.designGoals.cruiseAltitude
self.propulsion.engine.designMach = self.designGoals.cruiseMach
self.propulsion.engine.designThrust = self.designGoals.staticThrust / self.propulsion.numberOfEngines
idx = db.find_header(keyword + "LANDING GEAR")
self.landingGear.groundContactX = db.read_row(idx + 1, 1, True)
self.landingGear.groundContactY = db.read_row(-1, 1, True)
self.landingGear.groundContactZ = db.read_row(-1, 1, True)
self.landingGear.tireWidth = db.read_row(-1, 1, True)
self.landingGear.tireDiameter = db.read_row(-1, 1, True)
self.landingGear.strutLength = db.read_row(-1, 1, True)
# self.landingGear._set_right_mlg()
idx = db.find_header(keyword + "VLM PARAM")
self.vlm.panelsChordwise = db.read_row(idx + 1, 1, False)
self.vlm.panelsSpanwise = db.read_row(-1, 1, False)
self.vlm.distribution = db.read_row(-1, 1, False)
sec = db.read_section("PAYLOAD", 0)
for line in sec:
name = str(line[0])
mass = float(line[1])
CG = np.array([float(val) for val in line[2:5]])
MOI = np.array([float(val) for val in line[5:8]])
self.mass.payload.add_item(name, mass, CG, MOI)
self.mass.update_total()
self._process_data(True)
# fuelCG = self.wing.locate_on_wing(self.wing.fuelTankCGratio[0],self.wing.fuelTankCGratio[1])
# fuelCG[1] = 0.0
# self.mass.set_fuel_mass(self.designGoals.fuelMass,fuelCG)
self.designGoals._process_data()
self._update_parasite_drag()
self._update_mass()
