def getCombination(args):
reqCruiseSpeed = args[0]
reqThrust = args[1]
altitude = args[2]
currFlightTime = None
while currFlightTime is None or math.isnan(currFlightTime):
#Fetch prop data
prop = s.Propeller(dbcur)
#Fetch motor data
motor = s.Motor(dbcur)
#Fetch ESC data
esc = s.ESC(dbcur)
#Fetch battery data
batt = s.Battery(dbcur)
if batt.R == 0 and esc.R == 0 and motor.R == 0:
continue
currUnit = s.PropulsionUnit(prop, motor, batt, esc, altitude)
currFlightTime = currUnit.CalcBattLife(reqCruiseSpeed, reqThrust)
return currFlightTime, currUnit
def __init__(self, prop, motor, battery, numCells, esc, altitude,
showData):
#Open database and read records from database
db = sql.connect("Database/components.db")
dbcur = db.cursor()
#Fetch prop data
formatString = """select * from Props where Name = "{propName}" """
command = formatString.format(propName=prop)
dbcur.execute(command)
propRecord = dbcur.fetchall()
propInfo = np.asarray(propRecord[0])
if showData:
print("----Propeller Data----\n", propInfo)
self.prop = s.Propeller(propInfo[1], propInfo[2], propInfo[3],
propInfo[4:])
#Fetch motor data
formatString = """select * from Motors where Name = "{motorName}" """
command = formatString.format(motorName=motor)
dbcur.execute(command)
motorRecord = dbcur.fetchall()
motorInfo = np.asarray(motorRecord[0])
if showData:
print("----Motor Data----\n", motorInfo)
self.motor = s.Motor(motorInfo[1], motorInfo[2], motorInfo[3],
motorInfo[5], motorInfo[4], motorInfo[6])
#Fetch battery data
formatString = """select * from Batteries where Name = "{batteryName}" """
command = formatString.format(batteryName=battery)
dbcur.execute(command)
batteryRecord = dbcur.fetchall()
batteryInfo = np.asarray(batteryRecord[0])
if showData:
print("----Battery Data----\n", batteryInfo)
self.batt = s.Battery(batteryInfo[1], numCells, batteryInfo[3],
batteryInfo[6], batteryInfo[5], batteryInfo[4])
#Fetch ESC data
formatString = """select * from ESCs where Name = "{escName}" """
command = formatString.format(escName=esc)
dbcur.execute(command)
escRecord = dbcur.fetchall()
escInfo = np.asarray(escRecord[0])
if showData:
print("----ESC Data----\n", escInfo)
self.esc = s.ESC(escInfo[1], escInfo[5], escInfo[2], escInfo[4])
#Initialize exterior parameters to be set later
self.prop.vInf = 0
self.prop.angVel = 0
_, _, _, self.airDensity = coesa.table(altitude)
db.close()
def getCombination(args):
v_req = args[0]
T = args[1]
h = args[2]
optimizeForRatio = args[3]
W_frame = args[4]
names = args[5]
manufacturers = args[6]
if optimizeForRatio:
R_tw_req = T
else:
T_req = T
t_flight_curr = None
while t_flight_curr is None or math.isnan(t_flight_curr):
#Fetch prop data
prop = s.Propeller(dbcur, name=names[0], manufacturer=manufacturers[0])
#Fetch motor data
motor = s.Motor(dbcur, name=names[1], manufacturer=manufacturers[1])
#Fetch ESC data
esc = s.ESC(dbcur, name=names[2], manufacturer=manufacturers[2])
#Fetch battery data
batt = s.Battery(dbcur, name=names[3], manufacturer=manufacturers[3])
if batt.R == 0 and esc.R == 0 and motor.R == 0:
continue
currUnit = s.PropulsionUnit(prop, motor, batt, esc, h)
if optimizeForRatio:
T_req = (currUnit.GetWeight() + W_frame) * R_tw_req
with warnings.catch_warnings():
warnings.simplefilter("ignore")
t_flight_curr = currUnit.CalcBattLife(v_req, T_req)
thr_curr = currUnit.CalcCruiseThrottle(v_req, T_req)
return t_flight_curr, thr_curr, currUnit
#Fetch prop data
propC = s.Propeller(dbcur, name=prop)
propC.printInfo()
propC.PlotCoefs()
#Fetch motor data
motorC = s.Motor(dbcur, name=motor)
motorC.printInfo()
#Fetch battery data
battC = s.Battery(dbcur)
battC.printInfo()
#Fetch ESC data
escC = s.ESC(dbcur, name=esc)
escC.printInfo()
test = s.PropulsionUnit(propC, motorC, battC, escC, altitude)
print("Initialization complete. Plotting thrust curves.")
minAirspeed = 0
maxAirspeed = 30
numVelocities = 11
numThrottles = 1001
thrust = test.GetWeight() + weight * thrust
test.PlotThrustCurves(minAirspeed, maxAirspeed, numVelocities,
numThrottles)
print("Flight time (thrust=", thrust, ", cruiseSpeed=", cruiseSpeed, ")",
test.CalcBattLife(thrust, cruiseSpeed), "min")
db.close()
motorC = s.Motor(motorInfo[1], motorInfo[2], motorInfo[3], motorInfo[5],
motorInfo[4], motorInfo[6])
#Fetch battery data
formatString = """select * from Batteries where Name = "{batteryName}" """
command = formatString.format(batteryName=battery)
dbcur.execute(command)
batteryRecord = dbcur.fetchall()
batteryInfo = np.asarray(batteryRecord[0])
battC = s.Battery(batteryInfo[1], numCells, batteryInfo[3], batteryInfo[6],
batteryInfo[5], batteryInfo[4], batteryInfo[2])
#Fetch ESC data
formatString = """select * from ESCs where Name = "{escName}" """
command = formatString.format(escName=esc)
dbcur.execute(command)
escRecord = dbcur.fetchall()
escInfo = np.asarray(escRecord[0])
escC = s.ESC(escInfo[1], escInfo[5], escInfo[2], escInfo[4])
test = unit.PropulsionUnit(propC, motorC, battC, escC, altitude)
print("Initialization complete. Plotting thrust curves.")
maxAirspeed = 30
numVelocities = 11
numThrottles = 101
test.PlotThrustCurves(maxAirspeed, numVelocities, numThrottles)
print("Flight time (thrust=", thrust, ", cruiseSpeed=", cruiseSpeed, ")",
test.CalcBattLife(thrust, cruiseSpeed), "min")
db.close()