def main(args):
trAng5 = rad(5.0)
trAng6 = rad(6.0)
c_f_water = 1481.0
c_air = 343
c1 = c_f_water
c2 = c_air
ang5 = np.arcsin((c1 / c2) * trAng5)
ang6 = np.arcsin((c1 / c2) * trAng6)
print deg(ang5)
print deg(ang6)
d = 1.0/(tan(ang6)-tan(ang5))
print d
R = d*tan(ang5)
print R
return 0
def get_poa(self,
dates,
ghi,
dhi,
dni,
sun_zenith,
sun_azimuth,
dni_extra=None,
airmass=None,
model="haydavies"):
if self.method == "pvlib":
sun_zenith = deg(sun_zenith)
sun_azimuth = deg(sun_azimuth)
if dni_extra is None:
dni_extra = irradiance.extraradiation(DatetimeIndex(dates))
if airmass is None:
airmass = atmosphere.relativeairmass(sun_zenith)
poa = irradiance.total_irrad(self.tilt,
self.azimuth,
sun_zenith,
sun_azimuth,
dni,
ghi,
dhi,
dni_extra=dni_extra,
airmass=airmass,
model=model,
albedo=self.albedo)
self.poa = poa['poa_global']
def xcp(self, alpha):
'''wing center of pressure measured vs leading edge'''
alphaMin = -2 # deg
alphaMax = 9.5 # deg
if alpha < rad(alphaMin):
alpha = rad(alphaMin)
elif alpha > rad(alphaMax):
alpha = rad(alphaMax)
return self.xCP[0] + self.xCP[1] * deg(alpha) + self.xCP[2] * deg(alpha) ** 2 + self.xCP[3] * deg(alpha) ** 3
def draw_arc_arrow(ax, angle_, theta2_, center=(0., 0.), text="", text_offset=(0., 0.), radius=1., color='white', is_rad=True, flip=False):
if(is_rad):
angle_ = deg(angle_)
theta2_ = deg(theta2_)
#========Line
if(flip):
head_angle = 180+angle_
direction = 1.
arc = Arc([center[0],center[1]],radius*2.,radius*2.,angle=angle_,
theta1=0., theta2=theta2_-angle_, capstyle='round',
linestyle='-', lw=1, color=color)
else:
head_angle = angle_
direction = -1.
arc = Arc([center[0],center[1]],radius*2.,radius*2.,angle=theta2_,
theta1=0., theta2=angle_-theta2_, capstyle='round',
linestyle='-', lw=1, color=color)
ax.add_patch(arc)
#========Create the arrow head
arrow_scale = radius/30.
delta_angle = arrow_scale/(radius)
endX=center[0]+(radius)*(np.cos(rad(angle_) + direction*delta_angle) ) #Do trig to determine end position
endY=center[1]+(radius)*(np.sin(rad(angle_) + direction*delta_angle) )
ax.add_patch( #Create triangle as arrow head
RegularPolygon(
(endX, endY), # (x,y)
3, # number of vertices
arrow_scale, # radius
rad(head_angle), # orientation
color=color
)
)
#========text
middle_angle = theta2_ - (theta2_ - angle_)/2.
endX=center[0]+(radius*1.05)*(np.cos(rad(middle_angle)) )
endY=center[1]+(radius*1.05)*(np.sin(rad(middle_angle)) )
ax.text(endX+text_offset[0], endY+text_offset[1], text, size=20)
return
def inverse(t,tol=0.1):
target = vector(t)
if((t - joint_positions['shoulder']).length > 57.1):
print('Out of range')
return out_of_range_condition(target)
elif((t - joint_positions['wrist']).length < tol):
print('Iterations = 0')
try:
return(deg([theta_shoulder, theta_arm_ud, theta_arm_oc, theta_uturn, theta_elbow]))
except NameError:
return([0,0,0,0,0])
else:
return iteration(target,tol)
def serialize(angle, hour=False):
if not angle:
return "Nedefinisan"
angle = deg(angle)
if hour:
angle /= 15
degrees = int(angle)
minutes = (angle - degrees) * 60
seconds = (minutes - int(minutes)) * 60
minutes = int(minutes)
if hour:
return f"{degrees}h {minutes}m {seconds:.3f}s"
return f"{degrees}° {minutes}' {seconds:.3f}\""
def launch(args):
# logging.basicConfig()
#Edit params.yml here only; it is copied (read only) to results folder
# print('Backend {}, interactive {}'.format(matplotlib.get_backend(), matplotlib.is_interactive()))
#######################################################################
# path = '/media/sf_results/2021-11-15'
# path = '/media/sf_results/2021-11-24 v control'
#######################################################################
[path,ks,replacedParams] = args
os.chdir('/home/bret/winchrep/pythonModeling/launch')
# sys.stdout = Tee(sys.stdout, open(os.path.join(path,'log.txt'), "w"))
runsDir = path.replace(path.split('/')[-1],'')
if not os.path.exists(runsDir): os.mkdir(runsDir)
print ('\n',ks)
print ('**** Number of run folders: ',len( os.listdir(runsDir)))
if not os.path.exists(path): os.mkdir(path)
overwriteCopyParams(replacedParams,path)
pr = loadParams(path) # parameters
if not pr['overwriteResults'] and os.path.exists(os.path.join(path, 'results.txt')):
print('Run complete: results.txt exists')
return
g = 9.8
saveStateFile = os.path.join(path, 'savedState')
writeStatesFile = os.path.join(path, 'manyStates')
writeStateDersFile = os.path.join(path, 'manyStDers')
save = [saveStateFile,writeStatesFile, writeStateDersFile]
if os.path.exists(writeStatesFile):
os.remove(writeStatesFile)
if os.path.exists(writeStateDersFile):
os.remove(writeStateDersFile)
#--- time
tStart = pr['tStart']
tEnd = pr['tEnd']
print ('tEnd',tEnd)
dt0 = pr['dt0']
tfactor = pr['tfactor']
if pr['useTables']:
tfactor = max(30,tfactor)
dt = dt0/float(tfactor) # nominal time step, sec
ntime = int((tEnd - tStart)/dt) + 1 # number of time steps to allow for data points saved
# # Loop over parameters for study, optimization
# if loop:
# loopParams = linspace(0,8,50) #Alpha\
# else:
# loopParams = [setpoint[0]]
# #
# loopData = zeros(len(loopParams),dtype = [('alphaLoop', float),('xRoll', float),('tRoll', float),('yfinal', float),('vmax', float),('vDmax', float),('Sthmax',float),\
# ('alphaMax', float),('gammaMax', float),('thetaDmax', float),('Tmax', float),('Tavg', float),('yDfinal', float),('Lmax', float),\
# ('smRopeMin', float),('smStallMin', float),('smStructMin', float),('smRecovMin', float)])
# yminLoop = 20 #if yfinal is less than this height, the run failed, so ignore this time point
# for iloop,param in enumerate(loopParams):
# alphaLoop = param
# if len(loopParams) > 1:
# if loopWhich == 0:
# path = os.path.join(path,'loop0--{:3.1f},3'.format(param))
# setpoint = [param,3,30] # deg,speed, deg last one is climb angle to transition to final control
# elif loopWhich == 1:
# path = os.path.join(path,'loop1--3,{:3.1f}'.format(param))
# setpoint = [3,param,30] # deg,speed, deg last one is climb angle to transition to final control
# elif loopWhich == 'both':
# path = os.path.join(path,'loop01--{:3.1f},{:3.1f}'.format(param,param))
# setpoint = [param,param,30] # deg,speed, deg last one is climb angle to transition to final control
# if not os.path.exists(path): os.mkdir(path)
# else:
# path = path
control = pr['control']
setpoint = pr['setpoint']
print('\nInitial pilot control: ({},{:4.1f})'.format(control[0],setpoint[0]) )
t = linspace(tStart,tEnd,num=ntime)
# create the objects we need from classes
ti = timeinfo(tStart,tEnd,ntime)
gl = glider(pr,ntime)
ai = air(pr,gl,ntime)
rp = rope(pr,tEnd,ntime)
dr = drum(pr,ntime)
tc = torqconv(pr,ntime)
en = engine(pr,dr,ntime)
op = operator(pr,ntime)
pl = pilot(pr,control,setpoint,ntime)
##### Advanced block for air start
# loadState = True
loadState = pr['loadState']
if loadState: #
print('loading state from {}'.format(saveStateFile) )
time,gl,rp,dr,tc,en,op,pl = readState(saveStateFile,gl,rp,dr,tc,en,op,pl)
print('loaded state for time {}', time)
#Change some of the initial conditions
rp.T = op.targetT * gl.W
# v = 43
# gl.xD = v * cos(gl.theta); gl.yD = v* sin(gl.theta)
# gl.y = 1
##### End advanced block for air start
#initialize state vector to zero
S0 = zeros(9)
#integrate the ODEs
S0 = stateJoin(S0,gl,rp,dr,tc,en,op,pl)
S = odeint(stateDer,S0,t,mxstep=500, args =(pr,gl,ai,rp,dr,tc,en,op,pl,ti,save))
#Split S (now a matrix with state variables in columns and times in rows)
gl,rp,dr,tc,en,op,pl = stateSplitMat(S,gl,rp,dr,tc,en,op,pl)
#gl.x, etc are now 1-D arrays
# Integrater always goes to tEnd.
# ti.i and all data arrays stoppped being updated after release
# ti is passed to prepData and arrays are stopped after tRelease
# So tRelease = ti.data[ti.i]['t']
preppedData = prepData(pr,t,ti,gl,ai,rp,dr,tc,en,op,pl)
[t, x, y, xD, yD, v, vD, alpha, theta, thetaD, gamma, elev, Sth, omegd, omege, L, D, T, Tg, vgw, \
torqWing,torqStab, Me, Few, engP, omegrel, rdrum, tctorqueDrum, winP, ropP, gliP, gndTorq, ropeTheta, ropeTorq, \
smRope, smStall, smStruct, smRecov, vGust, gData, dData, oData, pData, eData, rData, aData, tData] = preppedData
#ground roll
if max(y) > gl.deltar:
iEndRoll = where(y > gl.deltar)[0][0] # where it's left the ground
xRoll = x[iEndRoll]
tRoll = t[iEndRoll]
iEndRollData = where(t>tRoll)[0][0]
else:
xRoll = 0 #didn't get off ground
tRoll = 0
iEndRollData = 1
#misc results
Tavg = mean(T[where(T>10)[0]])/gl.W
# final values
yfinal = y[-1]
yDfinal = yD[-1]
# if yDfinal < 0.5: yDfinal = 0
# max values
ymax = max(y)
thetaDmax = max(thetaD)
vmax = max(v)
vDmax = max(vD) #max acceleration
Sthmax = max(Sth)
Tmax = max(T)/gl.W
alphaMax = max(alpha[iEndRollData:])
Lmax = max(L)/gl.W
gammaMax = max(gamma)
# safety margin minimum values taken when glider is 1m or more above the ground
minHeight = 1 #m to be airborne
if y[-1] > minHeight:
iminHeight = where(y > minHeight)[0][0]
tminHeight = t[iminHeight]
iminHeightData = where(t>tminHeight)[0][0]
smRopeMin = min(smRope[iminHeightData:])
smStallMin = min(smStall[iminHeightData:])
smStructMin = min(smStruct[iminHeightData:])
smRecovMin = min(smRecov[iminHeightData:])
else:
iminHeight = 0
tminHeight = 0
iminHeightData = t
smRopeMin = min(smRope)
smStallMin = min(smStall)
smStructMin = min(smStruct)
smRecovMin = min(smRecov)
# Comments to user
print('Controls', control )
print('Throttle ramp up time (after slack is out)', op.tRampUp)
print('Final time: {:5.1f}s'.format(t[-1]))
print('Final vy: {:5.1f} m/s'.format(yDfinal))
if yDfinal > 0:
ymax += 0.5* yDfinal**2/g
stalledList = where(gl.data['alpha'] > gl.alphaStall)[0]
if len(stalledList) > 0:
tstalled = t[stalledList[0]]
print ('Glider stalled at {:5.1f}s'.format(tstalled))
print('Final height reached: {:5.0f} m, {:5.0f} ft. Fraction of rope length: {:4.1f}%'.format(yfinal,yfinal/0.305,100*yfinal/float(rp.lo)))
print('Maximum speed: {:3.0f} m/s, maximum rotation rate: {:3.1f} deg/s'.format(vmax,deg(thetaDmax)))
print('Maximum tension factor: {:3.1f}'.format(Tmax))
print('Average tension factor: {:3.1f}'.format(Tavg))
print('Maximum angle of attack: {:3.1f} deg'.format(deg(alphaMax)))
print('Ground roll: {:5.0f} m, {:5.1f} sec'.format(xRoll,tRoll))
# # check whether to keep this run as loop data
# if yfinal < yminLoop and iloop >0:
# print('Bad run, not saving data')
# loopData[iloop] = loopData[iloop-1] #write over this data point with the last one.
# else:
# # Store loop results
# loopData[iloop]['alphaLoop'] = alphaLoop
# loopData[iloop]['xRoll'] = xRoll
# loopData[iloop]['tRoll'] = tRoll
# loopData[iloop]['yfinal'] = yfinal
# loopData[iloop]['yDfinal'] = yDfinal
# loopData[iloop]['vmax'] = vmax
# loopData[iloop]['vDmax'] = vDmax
# loopData[iloop]['Lmax'] = Lmax
# loopData[iloop]['Tmax'] = Tmax
# loopData[iloop]['Tavg'] = Tavg
# loopData[iloop]['Sthmax'] = Sthmax
# loopData[iloop]['alphaMax'] = deg(alphaMax)
# loopData[iloop]['gammaMax'] = deg(gammaMax)
# loopData[iloop]['thetaDmax'] = deg(thetaDmax)
# loopData[iloop]['smRopeMin'] = smRopeMin
# loopData[iloop]['smStallMin'] = smStallMin
# loopData[iloop]['smStructMin'] = smStructMin
# loopData[iloop]['smRecovMin'] = smRecovMin
# Need to fix this to plot for each part of loop
# plot results for each one
close('all')
if pr['SIPlotsShow'] or pr['SIPlotsSave']:
figures = plotsSI(path,preppedData,pr,gl,ai,rp,dr,tc,en,op,pl)
if pr['impPlotsShow'] or pr['impPlotsSave']:
figures = plotsImp(figures,path,preppedData,pr,gl,ai,rp,dr,tc,en,op,pl)
# show()
writeRunResults(ks,setpoint,elev,t,v,gl,op,rp,pl,T,Sth,yfinal,stalledList,path)
return
def writeRunResults(ks, setpoint, elev, t, v, gl, op, rp, pl, T, Sth, yfinal,
stalledList, path):
print(ks)
vSet = setpoint[0]
# placesTest = where(v > vSet)[0]
# placesTest = where(t > 1)[0]
if pl.tPrepRelease:
placesTest = where((t > op.tRampUp + 1) & (t < pl.tPrepRelease))[
0] #Don't include ramp period in tests.
else:
placesTest = where(t > op.tRampUp + 1)[0]
if len(placesTest) > 0:
timesTest = t[placesTest]
testStart = timesTest[0]
flightDur = timesTest[-1] - testStart
vTest = v[placesTest]
elevTest = deg(elev[placesTest])
verr = vTest - vSet
meanv = mean(vTest)
meanvErr = mean(verr)
stdvErr = std(verr)
meanElev = mean(elevTest)
stdElev = std(elevTest)
Ttest = T[placesTest] / gl.W * 100
Terr = Ttest - op.targetT * 100
meanT = mean(Ttest)
meanTErr = mean(Terr)
stdTErr = std(Terr)
SthTest = Sth[placesTest]
# sampleElev the elevator and throttle every 0.5 sec for extreme swings
dt = 0.1 # sec
sampleElev = []
lasttime = timesTest[0]
crossElev = 0 # how many times does the elevator setting change sign?
for i, elevator in enumerate(elevTest[:-1]):
if timesTest[i] - lasttime > dt:
sampleElev.append(elevator)
for i in range(len(sampleElev) - 1):
if sign(sampleElev[i]) != sign(sampleElev[i + 1]):
crossElev += 1
sampleSth = []
fullThr = 0 # how many times does the throttle hit 100 and drop away
for i, setting in enumerate(SthTest[:-1]):
if timesTest[i] - lasttime > dt:
sampleSth.append(setting)
for i in range(len(sampleSth) - 1):
if sampleSth[i] < 1.0 and abs(sampleSth[i + 1] - 1.0) < 1e-6:
fullThr += 1
fracHeight = 100 * yfinal / float(rp.lo)
if len(stalledList) > 0:
stalled = 1.0
else:
stalled = 0
output = [
flightDur, testStart, meanv, meanvErr, stdvErr, meanElev, stdElev,
crossElev, meanT, meanTErr, stdTErr, fullThr, fracHeight, stalled
]
labels = [
'flightDur', 'testStart', 'meanv ', 'meanvErr', 'stdvErr ',
'meanElev', 'stdElev', 'crossElev', 'meanTx100', 'meanTErr',
'stdTErr', 'fullThr', 'fracHeight', 'stalled'
]
resultsLines = []
for i, label in enumerate(labels):
resultsLine = '{} \t{:4.1f}'.format(label, output[i])
print(resultsLine)
resultsLines.append(resultsLine + '\n')
writefile(resultsLines, os.path.join(path, 'results.txt'))
def plotsImp(figures, path, preppedData, pr, gl, ai, rp, dr, tc, en, op, pl):
close('all')
showPlot = pr['impPlotsShow']
save = pr['impPlotsSave']
path = os.path.join(path, 'imperial')
if not os.path.exists(path): os.mkdir(path)
lbsPernewt = 1 / 4.44822
hpPerW = 1.34102 / 1000.0
ftlbPerNm = 0.738
ktPerms = 1.94384
ftPerm = 3.28084
rpmPerRadPs = 60 / 2 / pi
g = 9.8
[t, x, y, xD, yD, v, vD, alpha, theta, thetaD, gamma, elev, Sth, omegd, omege, L, D, T, Tg, vgw, \
torqWing,torqStab, Me, Few, engP, omegrel, rdrum, tctorqueDrum, winP, ropP, gliP, gndTorq, ropeTheta, ropeTorq, \
smRope, smStall, smStruct, smRecov, vGust, gData, dData, oData, pData, eData, rData, aData, tData] = preppedData
iColor = 0 # counter for plots, so each variable has a different color
# plot engine power and torque curves from model parameters
if pr['plotPowerTorque']:
omegeng = linspace(0, 1.1 * en.omegapeakP, 100)
powr = linspace(0, 1.1 * en.omegapeakP, 100)
torq = linspace(0, 1.1 * en.omegapeakP, 100)
rpm = omegeng * 60 / 2.0 / pi
for i, omegr in enumerate(omegeng):
powr[i] = hpPerW * en.Pavail(omegr)
torq[i] = ftlbPerNm * en.torqAvail(omegr)
figures.append(
xy(False, showPlot, save, path, iColor, [rpm], [powr, torq],
'Engine speed (rpm)', 'Power (HP), Torque(Ftlbs)',
['Pistons power', 'Pistons torque'], 'Engine curves'))
if pr['plotLift']: ##plot lift curve vs alpha at v_best
alphaList = linspace(-20, 80, 100)
lift = array([gl.Lnl(gl.vb, rad(alph)) for alph in alphaList])
figures.append(xy(False, showPlot, save, path, iColor, [alphaList], [lift/gl.W], \
'Angle of attack (deg)', 'Lift/Weight', [''], 'Lift vs angle of attack'))
alphaList = linspace(-4, pr['alphaStallVsWing'], 100)
drag = array([gl.coeffDrag(rad(alph)) for alph in alphaList])
figures.append(xy(False, showPlot, save, path, iColor, [alphaList], [drag], \
'Angle of attack (deg)', 'Drag coefficient', [''], 'Drag vs angle of attack'))
if pr['plotTorqCov']:
vrelList = linspace(0, 1.5, 100)
tcGearingList = array([tc.torqMult(vrel) for vrel in vrelList])
# tcEfficiencyList = array([vrel * tc.torqMult(vrel) for vrel in vrelList])
tcInvKform = array([tc.invKform(vrel) for vrel in vrelList])
figures.append(xy(False, showPlot, save, path, iColor, [vrelList], \
[tcGearingList, tcInvKform],
'vDrum/vEngine', '' ,['torque factor','inverse capacity form'], 'Torque converter'))
# def xy(holdOpen, showPlot, save, path, iColor, xs, ys, xlbl, ylbl, legendLabels, titlestr, xmin=None, xmax=None):
#presentation figures
#height, T, L, y vs x
figures.append(
xy(False, showPlot, save, path, iColor, [ftPerm * x],
[ftPerm * y, Tg / gl.W * 1000, L / gl.W * 1000], 'x (ft)',
'y (ft), forces',
['height', 'tension/Weight x 1000', 'lift/Weight x 1000'],
'Height and forces vs x'))
# glider v, climb, alpha, elevator vs x
figures.append(xy(False, showPlot, save, path, iColor, [ftPerm * x],
[ktPerms*v, deg(alpha),deg(gamma), deg(elev)], \
'x (ft)', 'velocity (kts), angles (deg)',
['v', 'angle of attack', 'climb', 'elevator'],
'Glider speed and angles vs x'))
# engine rpm, vrel, thr vs x
figures.append(xy(False, showPlot, save, path, iColor, [ftPerm*x],
[omege * 60 / 2 / pi/10, hpPerW*engP, 10 * 100 * omegrel,
10 * 100 * Sth], \
'x (ft)', 'Speeds (rpm,kts), %',
['eng rpm/10', 'engine HP', \
'TC speed vs engine % x10', 'throttle % x10'],
'Engine vs x'))
#height, T, L, y vs t
figures.append(
xy(False, showPlot, save, path, iColor, [t],
[ftPerm * y, Tg / gl.W * 1000, L / gl.W * 1000], 't (sec)',
'y (ft), forces',
['height', 'tension/Weight x 1000', 'lift/Weight x 1000'],
'Height and forces vs t'))
# glider v, climb, alpha, elevator vs t
figures.append(xy(False, showPlot, save, path, iColor, [t],
[ktPerms*v, deg(alpha),deg(gamma), deg(elev)], \
't (sec)', 'velocity (kts), angles (deg)',
['v', 'angle of attack', 'climb', 'elevator'],
'Glider speed and angles vs t'))
# engine rpm, vrel, thr vs t
figures.append(xy(False, showPlot, save, path, iColor, [t],
[omege * 60 / 2 / pi/10, hpPerW*engP, 10 * 100 * omegrel,
10 * 100 * Sth], \
't (sec)', 'Speeds (rpm,kts), %',
['eng rpm/10', 'engine HP', \
'TC speed vs engine % x10', 'throttle % x10'],
'Engine vs t'))
# glider position vs time
figures.append(
xy(False, showPlot, save, path, iColor, [t], [ftPerm * x, ftPerm * y],
'time (sec)', 'position (ft)', ['x', 'y'],
'Glider position vs time'))
figures.append(
xy(False, showPlot, save, path, iColor, [ftPerm * x], [ftPerm * y],
'x (ft)', 'y (ft)', [''], 'Glider y vs x'))
# glider speed and angles
figures.append(xy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t],
[ktPerms*xD, ktPerms*yD, ktPerms*v, deg(alpha), deg(theta), deg(gamma), deg(elev), deg(thetaD)], \
'time (sec)', 'Velocity (kts), Angles (deg)',
['vx', 'vy', 'v', 'angle of attack', 'pitch', 'climb', 'elevator', 'pitch rate (deg/sec)'],
'Glider velocities and angles'))
# iColor = 0 #restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t, t],
[ktPerms*v, ktPerms * dr.rdrum * omegd, y/rp.lo, Tg/gl.W, L/gl.W, divide(L, D), deg(alpha), deg(gamma), deg(thetaD)], \
[0, 0, 1, 1, 1, 0, 0, 0, 0], 'time (sec)', ['Velocity (kt), Angles (deg), L/D', 'Relative forces and height'],
['v (glider)', r'$v_r$ (rope)', \
'height/' + r'$\l_o $', 'T/W at glider', 'L/W', 'L/D', 'angle of attack', 'climb angle', 'rot. rate (deg/sec)'],
'Glider and rope'))
# Forces
figures.append(xy(False, showPlot, save, path, iColor, [t, t, t, t, t], [L/gl.W, D/gl.W, T/gl.W, Tg/gl.W, Few/gl.W], \
'time (sec)', 'Forces/Weight', ['lift', 'drag', 'tension at drum', 'tension at glider', 'tc-drum'],
'Forces'))
# torques
figures.append(
xy(False, showPlot, save, path, iColor, [t], [
ftlbPerNm * ropeTorq, ftlbPerNm *
(torqWing + torqStab), ftlbPerNm * Me, ftlbPerNm * gndTorq
], 'time (sec)', 'Torque (ft-lbs)',
['rope', 'stabilizer+wing', 'elevator', 'ground'],
'Torques on glider'))
figures.append(
xy(False, showPlot, save, path, iColor, [t],
[ftlbPerNm * torqWing, ftlbPerNm * torqStab], 'time (sec)',
'Torque (ft-lbs)', ['wing', 'stabilizer'],
'Torques wing and stabilzer'))
# Engine, rope and drum
figures.append(xy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t], [ktPerms*multiply(omege,rdrum)/dr.gear/dr.diff, ktPerms*multiply(omegd,rdrum), \
ktPerms*vgw, deg(ropeTheta), ftlbPerNm * tctorqueDrum/10, -ftlbPerNm * multiply(T,rdrum)/10, 100 * Sth], 'time (sec)',
'Speeds (effective: kt), Torque/10 (Ft-lbs) Angle (deg), Throttle %',
['engine speed', 'rope speed', 'glider radial speed', 'rope angle', 'TC torque on drum', 'Rope torque on drum','throttle'], 'Engine, drum and rope'))
# Engine
figures.append(xy(False, showPlot, save, path, iColor, [t],
[omege * 60 / 2 / pi/10, hpPerW*engP, ftlbPerNm*engP/(omege + 1e-6),
ftlbPerNm*tctorqueDrum/dr.gear/ dr.diff,
10 * 100 * omegrel,
10 * 100 * Sth], \
'time (sec)', 'Speeds (rpm,kts), Torque (ft-lbs), %',
['eng rpm/10', 'engine HP', 'engine torque', 'TC torque out',\
'TC speed vs engine % x10', 'throttle % x10'],
'Engine'))
figures.append(
xy(False, showPlot, save, path, iColor, [t], [
eData['Edeliv'] / 1e6, dData['Edeliv'] / 1e6,
rData['Edeliv'] / 1e6, gData['Edeliv'] / 1e6, gData['Emech'] / 1e6
], 'time (sec)', 'Energy (MJ)',
['to engine', 'to drum', 'to rope', 'to glider', 'in glider'],
'Energy delivered and kept'))
figures.append(
xy(False, showPlot, save, path, iColor, [t],
[engP / en.Pmax, winP / en.Pmax, ropP / en.Pmax, gliP / en.Pmax],
'time (sec)', 'Power/Pmax',
['to engine', 'to drum', 'to rope', 'to glider'],
'Power delivered'))
zoom = pr['zoom']
if zoom:
# if not ai.startGust is None and 's' in ai.startGust:
# t1 = float(ai.startGust.split()[0])-0.5
# t2 = t1 + 2*ai.widthGust/2.05.0 + 2.0 -1.5
[t1, t2] = zoom
if ai.vGustPeak > 0 and not ai.startGust is None:
# without safety margins
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t],
[ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, T/gl.W, vGust], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W', 'vel gust'], 'Winch launch'))
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t],
[ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, T/gl.W, vGust], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W', 'vel gust'],
'Winch launch expanded', t1, t2))
# with safety margins (T/W is redundant)
iColor = 0 # restart color cycle
figures.append(xyy(False and not zoom, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t, t, t],
[ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, smStruct, smStall, smRope, smRecov, vGust], \
[0, 0, 0, 1, 1, 1, 1, 0, 0], 'time (sec)',
['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin', 'rope margin',
'recovery margin', 'vel gust'], 'Winch launch and safety margins'))
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t, t, t],
[ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, smStruct, smStall, smRope, smRecov, vGust], \
[0, 0, 0, 1, 1, 1, 1, 0, 0], 'time (sec)',
['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin',
'rope margin', 'recovery margin', 'vel gust'], 'Winch launch and safety margins expanded', t1,
t2))
else: # without gusts
# without safety margins
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t], [ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, T/gl.W], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W'], 'Winch launch expanded', t1, t2))
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t], [ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, T/gl.W], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W'], 'Winch launch'))
# with safety margins
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t],
[ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, smStruct, smStall, smRope, smRecov], \
[0, 0, 0, 1, 1, 1, 1, 0], 'time (sec)',
['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin',
'rope margin', 'recovery margin'], 'Winch launch and safety margins expanded', t1, t2))
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t],
[ktPerms*v,ftPerm/10.0*y, deg(gamma), L/gl.W, smStruct, smStall, smRope, smRecov], \
[0, 0, 0, 1, 1, 1, 1, 0], 'time (sec)', ['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin', 'rope margin',
'recovery margin'], 'Winch launch and safety margins'))
# safety margins alone
if zoom:
iColor = 6 # choose color cycle start
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t], [smStruct, smStall, smRope, smRecov], \
[1, 1, 1, 0], 'time (sec)', ['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['struct margin', 'stall margin', 'rope margin', 'recovery margin'], 'Safety margins expanded', t1,
t2))
iColor = 6 # choose color cycle start
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t], [smStruct, smStall, smRope, smRecov], \
[1, 1, 1, 0], 'time (sec)', ['Velocity (kt), Height/10 (ft), Angle (deg)', "Relative forces"], \
['struct margin', 'stall margin', 'rope margin', 'recovery margin'], 'Safety margins'))
#############
'''Looping over parameters is now done with multiprocessor pool. Below are plots from old looping'''
# plot loop results (saved in last parameter's folder
# if loop:
# heightDiff = loopData['yfinal'] - min(loopData['yfinal']) # vs minimum in loop
# iColor = 0 # restart color cycle
# figures.append(xyy(False, showPlot, save, path, iColor, [loopData['alphaLoop']] * 12,
# [loopData['xRoll'], 10 * loopData['tRoll'], loopData['yfinal']/rp.lo * 100, heightDiff, loopData['vmax'],
# loopData['vDmax']/g, loopData['Sthmax'], loopData['Tmax'], loopData['Lmax'], loopData['alphaMax'],
# loopData['gammaMax'],
# loopData['thetaDmax']], \
# [0, 0, 0, 0, 0, 1, 1, 1, 1, 0, 0, 0], 'Angle of attack setting (deg)',
# ['Velocity (kt), Angles (deg), m, sec, %', "Relative forces,g's"], \
# ['x gnd roll', 't gnd roll x 10', 'height/rope %', 'height diff', r'$v_{max}$', "max g's", 'max throttle',
# r'$T_{max}/W$', r'$L_{max}/W$', r'$\alpha_{max}$', r'$\gamma_{max}$', 'rot. max (deg/sec)'],
# 'Flight (all) vs target angle of attack'))
# # fewer results, for presentation
# iColor = 0 # restart color cycle
# figures.append(xyy(False, showPlot, save, path, iColor, [loopData['alphaLoop']] * 4,
# [loopData['vmax'], heightDiff, loopData['gammaMax'], loopData['Lmax']], \
# [0, 0, 0, 1], 'Angle of attack target (deg)',
# ['Velocity (kt), Angle (deg), Height/10 (ft), %', "Relative forces"], \
# [r'$v_{max}$', 'height diff', 'climb angle max', r'$L_{max}/W$'], 'Flight vs target angle of attack'))
# # With safety margins for presentation
# iColor = 4 # match colors in previous plot
# figures.append(xyy(False, [loopData['alphaLoop']] * 4,
# [loopData['smStructMin'], loopData['smStallMin'], loopData['smRopeMin'], loopData['smRecovMin']], \
# [1, 1, 1, 0], 'Target angle of attack (deg)', ['Recovery height margin (ft)', "Safety margin (g's)"], \
# ['struct margin', 'stall margin', 'rope margin', 'recovery margin'],
# 'Safety margins vs target angle of attack'))
# print('Stop program to close plots!')
return figures
def get_aoi(self, sun_zenith, sun_azimuth):
if self.method == "pvlib":
self.aoi = rad(self.syst.get_aoi(deg(sun_zenith),
deg(sun_azimuth)))
def stateDer(S, t, pr, gl, ai, rp, dr, tc, en, op, pl, ti, save):
'''First derivative of the state vector'''
g = 9.8
[saveStateFile, writeStatesFile, writeStateDersFile] = save
saveStateTime = pr['saveStateTime']
writeStatesTimes = pr['writeStatesTimes']
if rp.data[ti.i][
'theta'] > rp.thetaMax: # glider released but the integrator must finish to specified tEnd
return zeros(len(S))
else:
gl, rp, dr, tc, en, op, pl = stateSplitVec(S, gl, rp, dr, tc, en, op,
pl)
# if gl.xD < 1e-6:
# gl.xD = 1e-6 # to handle v = 0 initial
if en.omeg < 1e-6:
en.omeg = 1e-6 # to handle v = 0 initial
# ----algebraic and logic functions----#
# gear
dr.checkGear(t)
# rope and crash
gl.max = max(gl.y, gl.ymax)
thetarope = arctan(gl.y / float(rp.lo - gl.x))
if gl.y < 0 and gl.ymax > 1:
print('Glider crashed at {:4.1f} s.'.format(t))
else:
if thetarope < -1e-6:
thetarope += pi # to handle overflight of winch
if not rp.broken: # break rope if chosen for simulation:
if not rp.breakAngle is None and (thetarope > rp.breakAngle
or t > rp.breakTime):
rp.broken = True
rp.tRelease = t
print('Rope broke at rope angle {:4.1f} deg, {:4.1f} s.'.
format(deg(thetarope), t))
print('Horizontal velocity {:4.1f} m/s.'.format(gl.xD))
else:
rp.T = 0.0
lenrope = sqrt((rp.lo - gl.x)**2 + gl.y**2)
# steady wind
vwx = ai.vhead
if gl.y > ai.heightupdraft:
vwy = ai.vupdraft
else:
vwy = 0.0
# glider
v = sqrt(gl.xD**2 + gl.yD**2) # speed
vecAir = array(
[gl.xD + vwx, gl.yD - vwy]
) # note minus sign for y, similar to above for vwy. Vy reduces glider speed vs air
vAir = norm(vecAir) # speed vs air
vgw = (gl.xD * (rp.lo - gl.x) - gl.yD * gl.y) / float(
lenrope) # velocity of glider toward winch
vtrans = sqrt(
v**2 - vgw**2 +
1e-6) # velocity of glider perpendicular to straight line rope
rp.thetaRG = rp.thetaRopeGlider(
t, ti, thetarope, vtrans, lenrope,
pr) # rope angle at glider corrected for rope weight and drag
Tg = rp.Tglider(thetarope,
lenrope) # tension at glider corrected for rope weight
if gl.freeFlight: Tg = 0
if gl.xD > 1: # avoid initial zeros problem
gamma = arctan(gl.yD / gl.xD) # climb angle.
gammaAir = arctan(
(gl.yD - vwy) / (gl.xD + vwx)) # climb angle vs air
else:
gamma = 0
gammaAir = 0
# gusts -- only one 1-cos gust per simulation
vgx, vgy, d, vgxStab, vgyStab = ai.gustDynamic(t, gammaAir, gl.x, gl.y)
vecGustWing = array(
[vgx, -vgy]) # note minus sign for y, similar to above for vwy
gammaAirWing = gammaAir
vAirWing = vAir
if norm(vecGustWing) > 0:
vecAirWing = vecAir + vecGustWing
vAirWing = norm(vecAirWing) # speed vs air
gammaAirWing = arctan(
vecAirWing[1] / vecAirWing[0]) # climb angle vs air with gust
alpha = gl.theta - gammaAirWing # angle of attack for wing
vecGustStab = array(
[vgxStab,
-vgyStab]) # note minus sign for y, similar to above for vwy
gammaAirStab = gammaAir
vAirStab = vAir
if norm(vecGustStab) > 0:
vecAirStab = vecAir + vecGustStab
vAirStab = norm(vecAirStab)
gammaAirStab = arctan(vecAirStab[1] / vecAirStab[0])
alphaStab = gl.theta - gammaAirStab # angle of attack for elevator
# forces on glider
Lwing = gl.Lnl(vAirWing, alpha) # lift
Lstab = gl.W * (gl.rsw0 + gl.ralphas * alphaStab) * (vAirStab /
gl.vb)**2
L = Lwing + Lstab
D = gl.W * gl.coeffDrag(alpha) / gl.Co * (vAirWing / gl.vb) ** 2 \
+ 0.5 * 1.22 * (gl.Agear * vAirWing ** 2 + rp.Apara * vgw ** 2)
torqWing = Lwing * (gl.xCG - gl.xcp(alpha))
torqStab = -gl.ls * Lstab
[Fmain, Ftail, Ffric] = gl.gndForces(ti, rp)
gndTorq = Fmain * gl.d_m - Ftail * gl.d_t
M = torqWing + torqStab + pl.Me + gndTorq # torque of air and ground on glider
ropetorq = Tg * sqrt(rp.a**2 + rp.b**2) * sin(
arctan(rp.b / float(rp.a)) - gl.theta -
rp.thetaRG) # torque of rope on glider
# Torques on drum and engine
dr.rdrum = dr.newRadius(rp, lenrope) #increasing drum radius with time
# if t>14.95:
# print(t)
# dummy = True
omegrel = dr.gear * dr.diff * dr.omeg / en.omeg # dr.gear can vary with time
if abs(en.dotomeg) > 1e-6:
omegrelD = dr.gear * dr.diff * dr.dotomeg / en.dotomeg
else:
omegrelD = 0
powerPistons = op.Sth * en.Pavail(en.omeg)
torqPistons = powerPistons / float(en.omeg)
# if op.Sth>0: # Then it's in gear...but we start with idle at beginning to take up slack
slipTorq = tc.invK(
omegrel)**2 * en.omeg**2 #- tc.tcdamp * omegrel * omegrelD
# torqtcd = tc.torqMult(omegrel) * dr.gear * dr.diff * slipTorq
torqtcd = tc.torqMult(omegrel) * dr.gear * dr.diff * slipTorq * (
1 - pr['winchLossFactor'])
torqtce = slipTorq
#testing:
# if t>3.7:
# print('test',t,torqtcd)
# dummy=1
# if t>7.3:
# print('test', t, 'dr.dotomeg', dr.dotomeg,'en.dotomeg', en.dotomeg, 'omegrelD', omegrelD, 'TM', tc.torqMult(omegrel), 'ik',
# tc.invK(omegrel))
# if t>7.5:
# sys.exit('stop')
# if t> 0 and abs(ti.temp - torqtcd)/abs(torqtcd) > 0.4:
# dummy = 1
ti.temp = torqtcd
# print (t,'throttle',op.Sth, 'omegrel',omegrel,'torqtcd',torqtcd)
#
# print('{:10.8f} rpm {:8.0f} omegrel {:8.5f} veng {:8.5f} Sth {:8.5f} P>drum {:8.5f} P<eng {:8.5f} P<pistons {:8.5f}'\
# .format(t,en.omeg*60/2/pi, omegrel,en.omeg*dr.omeTov(),op.Sth, \
# dr.omeg*torqtcd/en.Pmax, en.omeg*torqtce/en.Pmax,
# en.omeg*torqPistons/en.Pmax))
powerToEngine = powerPistons
powerToDrum = dr.omeg * torqtcd
if t > 0.4:
dummy = True
# ----derivatives of state variables----#
dotx = gl.xD
dotxD = 1 / float(gl.m) * (Tg * cos(rp.thetaRG) - D * cos(gamma) -
L * sin(gamma) - Ffric) # x acceleration
doty = gl.yD
dotyD = 1 / float(
gl.m) * (L * cos(gamma) - Tg * sin(rp.thetaRG) - D * sin(gamma) -
gl.W + Fmain + Ftail) # y acceleration
dottheta = gl.thetaD
dotthetaD = 1 / float(gl.I) * (
ropetorq + M - sign(dottheta) * gl.dampThetaDot * dottheta**2)
dotT = rp.chgT(dr.omeg * dr.rdrum, vgw, lenrope)
if dotT < 0 and rp.T < 0.01: #don't allow tension to be negative
dotT = 0
if gl.freeFlight: dotT = 0
dotomege = 1 / float(
en.Iengine) * (torqPistons - torqtce - en.damp * en.omeg)
#rpm limiter
if en.omeg > en.omegaLimit and dotomege > 0:
dotomege = 0.0
dotomegd = 1 / float(
dr.Idrum) * (torqtcd - dr.rdrum * rp.T - dr.damp * dr.omeg)
# dotomegd = 1 / float(dr.Idrum) * (torqtcd)
# print ('turned off rope tension')
if t > 7.2:
dummy = True
# The ode solver enters this routine usually two or more times per time step.
# We advance the time step counter only if the time has changed by close to a nominal time step
if t - ti.oldt > 1.0 * ti.dt:
ti.i += 1
if t > pr['timeForceFullElev']:
pl.elev = gl.elevLimits[1]
print('FORCING ELEVATOR TO FULL!!')
if saveStateTime is not None:
if t > saveStateTime:
saveState(t, gl, rp, dr, tc, en, op, pl, saveStateFile)
if writeStatesTimes is not None:
if writeStatesTimes[0] < t < writeStatesTimes[1]:
writeStates(t, gl, rp, dr, tc, en, op, pl, writeStatesFile)
writeStateDers(t, gl, dotx, dotxD, doty, dotyD, dottheta,
dotthetaD, dotT, dotomegd, dotomege,
writeStateDersFile)
ti.data[ti.i]['t'] = t
gl.data[ti.i]['x'] = gl.x
gl.data[ti.i]['xD'] = gl.xD
gl.data[ti.i]['y'] = gl.y
gl.data[ti.i]['yD'] = gl.yD
gl.data[ti.i]['v'] = v
gl.data[ti.i]['vD'] = sqrt(dotxD**2 + dotyD**2)
gl.data[ti.i]['yDD'] = dotyD
gl.data[ti.i]['theta'] = gl.theta
gl.data[ti.i]['thetaD'] = gl.thetaD
gl.data[ti.i]['gamma'] = gamma
gl.data[ti.i]['alpha'] = alpha
gl.data[ti.i][
'alphaStall'] = gl.alphaStall # constant stall angle include just for comparison
if gl.y > 0.01:
sm, Vball, gammaBall, ygainDelay, type = gl.smRecov(
v, L, alpha, gamma, pl)
# print('t:{:8.3f} type:{:8s} x:{:8.3f} y:{:8.3f} ygnDelay:{:8.3f} sm:{:8.3f} v:{:8.3f} vball:{:8.3f} gam:{:8.3f} gamball:{:8.3f} '.format(t,type,gl.x,gl.y,ygainDelay,sm,v,Vball,deg(gamma),deg(gammaBall)))
if gl.y > 0.3 or sm > 0:
gl.data[
ti.i]['smRecov'] = sm # gl.smRecov(v,L,alpha,gamma,pl)
ngust = ai.gustLoad(gl, v)
if Lwing > 0:
gl.data[ti.i]['smStall'] = (
vAirWing / gl.vStall
)**2 - Lwing / gl.W - ngust # safety margin vs stall (g's)
gl.data[ti.i]['smStruct'] = gl.n1 * sqrt(
(1 - gl.mw * gl.yG / gl.m / gl.yL * (1 - 1 / gl.n1))
) - Lwing / gl.W - ngust # safety margin vs structural damage (g's)
else:
gl.data[ti.i]['smStall'] = (
vAirWing / gl.vStall
)**2 - ngust # safety margin vs stall (g's). No negative lift is considered.
gl.data[ti.i]['smStruct'] = gl.n4 * sqrt(
(1 - gl.mw * gl.yG / gl.m / gl.yL * (1 - 1 / gl.n1))
) - abs(
Lwing
) / gl.W - ngust # safety margin vs structural damage (g's)
# gl.data[ti.i]['smStruct'] = gl.n1*(1-0) - Lglider/gl.W - ngust #safety margin vs structural damage (g's)
gl.data[ti.i]['vgw'] = vgw
gl.data[ti.i]['L'] = L
gl.data[ti.i]['D'] = D
gl.data[ti.i]['gndTorq'] = gndTorq
gl.data[ti.i]['torqWing'] = torqWing
gl.data[ti.i]['torqStab'] = torqStab
gl.data[ti.i]['Emech'] = 0.5 * (
gl.m * v**2 + gl.I *
gl.thetaD**2) + gl.m * g * gl.y # only glider energy here
gl.data[ti.i]['Pdeliv'] = Tg * v * cos(rp.thetaRG + gl.theta)
gl.data[ti.i]['Edeliv'] = gl.data[ti.i - 1]['Edeliv'] + gl.data[
ti.i]['Pdeliv'] * (t - ti.oldt) # integrate
ai.data[ti.i]['vGust'] = norm(vecGustWing)
op.data[ti.i]['Sth'] = op.Sth
rp.data[ti.i]['Pdeliv'] = rp.T * dr.omeg * dr.rdrum
rp.data[ti.i]['Edeliv'] = rp.data[ti.i - 1]['Edeliv'] + rp.data[
ti.i]['Pdeliv'] * (t - ti.oldt) # integrate
rp.data[ti.i]['T'] = rp.T
rp.data[ti.i]['Tglider'] = Tg
rp.data[ti.i][
'torq'] = ropetorq #torque of rope on glider (on rp. for labeling simplicty
rp.data[ti.i]['theta'] = thetarope
rp.data[ti.i]['sm'] = (rp.Twl - Tg) / gl.W
if rp.T > 0:
rp.data[ti.i]['stretch'] = rp.data[ti.i - 1]['stretch'] + (
dr.omeg * dr.rdrum - vgw) * (t - ti.oldt)
dr.data[ti.i]['v'] = dr.omeg * dr.rdrum
dr.data[ti.i]['omegrel'] = omegrel
dr.data[ti.i]['rdrum'] = dr.rdrum
dr.data[ti.i]['Pdeliv'] = powerToDrum
dr.data[ti.i]['Edeliv'] = dr.data[ti.i - 1]['Edeliv'] + dr.data[
ti.i]['Pdeliv'] * (t - ti.oldt) # integrate
dr.data[ti.i]['torq'] = torqtcd
en.data[ti.i]['torqTC'] = torqtce
en.data[ti.i]['Pdeliv'] = powerToEngine
# en.data[ti.i]['torq'] = # doesn't have much meaning on engine since we don't have a defined radius
en.data[ti.i]['Edeliv'] = en.data[ti.i - 1]['Edeliv'] + en.data[
ti.i]['Pdeliv'] * (t - ti.oldt) # integrate
dr.dotomeg = dotomegd
en.dotomeg = dotomege
# op.data[ti.i]['Sth'] = op.Sth
ti.oldt = t
# ---update things that don't affect stateDer
gl.findState(t, ti, rp, pl)
# Update controls
pl.control(pr, t, ti, gl)
op.control(pr, t, ti, gl, rp, dr, en)
#don't print state variables or derivatives, use writeStatesFile, writeStateDersFile
return [
dotx, dotxD, doty, dotyD, dottheta, dotthetaD, dotT, dotomegd,
dotomege
]
def out_of_range_condition(t):
b = (t - joint_positions['shoulder']).length
c = (31/b)*(t - joint_positions['shoulder']) + joint_positions['shoulder'] # new_elbow
joint_positions['elbow'] = c
theta_shoulder = arcsin(joint_positions['shoulder'][1]/13.7) # theta_shoulder = 0
# new_elbow judgement
theta3, theta_arm_oc = get_oc_angle()
theta_arm_ud = get_ud_angle(theta3)
if((deg(theta_arm_ud) > 32) or (deg(theta_arm_ud) < 0) or (deg(theta_arm_oc) > 30) or (deg(theta_arm_oc) < 0)):
if(deg(theta_arm_ud) > 32):
theta_arm_ud = rad(32)
elif(deg(theta_arm_ud < 0)):
theta_arm_ud = 0
if(deg(theta_arm_oc) > 30):
theta_arm_oc = rad(30)
elif(deg(theta_arm_oc) < 0):
theta_arm_oc = 0
arr = get_elbow_position([theta_shoulder, theta_arm_ud, theta_arm_oc])
joint_positions['elbow']= vector(arr)
c = joint_positions['elbow']
e = (t - c).length
f = (26.1/e)*(t - c) + c # new_wrist
joint_positions['wrist'] = f
# new_wrist judgement
theta_elbow = get_elbow_angle()
theta_uturn = get_uturn_angle(theta_shoulder, theta_arm_ud, theta_arm_oc, theta_elbow)
if ((deg(theta_uturn) > 90) or (deg(theta_uturn < 0))):
if(deg(theta_uturn) > 90):
theta_uturn = rad(90)
else:
theta_uturn = 0
arr = get_wrist_position([theta_shoulder, theta_arm_ud, theta_arm_oc, theta_uturn, theta_elbow])
f = vector(arr)
joint_positions['wrist'] = f
return(deg([theta_shoulder, theta_arm_ud, theta_arm_oc, theta_uturn, theta_elbow]))
def iteration(t,tolerance):
iterations = 0
need_test = False
if ((t - joint_positions['elbow']).length < 0.001):
arr = get_elbow_position([0, 0.1, 0.1])
joint_positions['elbow'] = vector(arr)
arr = get_wrist_position([0, 0.1, 0.1, 0.1, 1])
joint_positions['wrist'] = vector(arr)
while((need_test) or ((joint_positions['wrist'] - t).length > tolerance)):
# _______________________________________________________________________________________________
#________________________ Forward reaching, from target to reference_____________________________
# _______________________________________________________________________________________________
joint_positions['wrist'] = t
len_share = 26.1 / (joint_positions['wrist'] - joint_positions['elbow']).length
joint_positions['elbow'] = (1-len_share)*joint_positions['wrist'] + len_share*joint_positions['elbow']
len_share = 31 / (joint_positions['elbow'] - joint_positions['shoulder']).length
joint_positions['shoulder'] = (1-len_share)*joint_positions['elbow'] + len_share*joint_positions['shoulder']
# ________________________________________________________________________________________________
# ____________________________Forward reaching ends here__________________________________________
# ________________________________________________________________________________________________
# -------------------------------------------------------------------------------------------------------------------------------
#_________________________________________________________________________________________________
#_________________________Backward reaching, from reference to target_____________________________
# ________________________________________________________________________________________________
len_share = 13.7 / (joint_positions['origin'] - joint_positions['shoulder']).length
joint_positions['shoulder'] = (1-len_share)*joint_positions['origin'] + len_share*joint_positions['shoulder']
# ____________________________________________________________________________________________
# __________________test if shoulder is away from x-y plane___________________________________
# ____________________________________________________________________________________________
if(joint_positions['shoulder'][2] != 0):
# rotate shoulder about y-axis, so that it stays in x-y plane
rotation = np.arctan(joint_positions['shoulder'][2]/joint_positions['shoulder'][0])
x = joint_positions['shoulder'][0]*cos(rotation) + joint_positions['shoulder'][2]*sin(rotation)
z = joint_positions['shoulder'][2]*cos(rotation) - joint_positions['shoulder'][0]*sin(rotation)
y = joint_positions['shoulder'][1]
joint_positions['shoulder'] = vector(x,y,z)
theta_shoulder = arcsin(joint_positions['shoulder'][1]/13.7)
# ____________________________________________________________________________________________
# __________________test if shoulder is out of the boundary___________________________________
# ____________________________________________________________________________________________
if((deg(theta_shoulder) > 9) or (deg(theta_shoulder) < 0)):
if(deg(theta_shoulder) > 9): theta_shoulder = rad(9)
elif(deg(theta_shoulder) < 0): theta_shoulder = rad(0)
# rotate about z-axis, so that it stays within hardware limit
x = 13.7*cos(theta_shoulder)
y = 13.7*sin(theta_shoulder)
joint_positions['shoulder'] = vector(x,y,0)
# _______________________________________________________________________________________________
# ____________________________________Adjustment of shoulder ends here___________________________
# _______________________________________________________________________________________________
# --------------------------------------------------------------------------------------------------------------------------------
# _______________________________________________________________________________________________
# ____________________________________Starts adjustment of elbow_________________________________
# _______________________________________________________________________________________________
len_share = 31 / (joint_positions['shoulder'] - joint_positions['elbow']).length
joint_positions['elbow'] = (1-len_share)*joint_positions['shoulder'] + len_share*joint_positions['elbow']
theta3, theta_arm_oc = get_oc_angle()
theta_arm_ud = get_ud_angle(theta3)
# _______________________________________________________________________________________________
# _________________________________Test if position of elbow is out of boundary__________________
# _______________________________________________________________________________________________
if((deg(theta_arm_ud) > 32) or (deg(theta_arm_ud) < 0) or (deg(theta_arm_oc) > 30) or (deg(theta_arm_oc) < 0)):
if(deg(theta_arm_ud) > 32):
theta_arm_ud = rad(32)
elif(deg(theta_arm_ud < 0)):
theta_arm_ud = 0
if(deg(theta_arm_oc) > 30):
theta_arm_oc = rad(30)
elif(deg(theta_arm_oc) < 0):
theta_arm_oc = 0
arr = get_elbow_position([theta_shoulder, theta_arm_ud, theta_arm_oc])
joint_positions['elbow'] = vector(arr)
# _______________________________________________________________________________________________
# _________________________________Adjustment of elbow ends here_________________________________
# _______________________________________________________________________________________________
# _________________________________Starts adjustment of wrist____________________________________
# _______________________________________________________________________________________________
len_share = 26.1 / (joint_positions['elbow'] - joint_positions['wrist']).length
joint_positions['wrist'] = (1-len_share)*joint_positions['elbow'] + len_share*joint_positions['wrist']
theta_elbow = get_elbow_angle()
theta_uturn = get_uturn_angle(theta_shoulder, theta_arm_ud, theta_arm_oc, theta_elbow)
need_test = False
# _______________________________________________________________________________________________
# ________________________________Test if wrist is out of boundary_______________________________
# _______________________________________________________________________________________________
if(deg(theta_uturn)<0 and abs(deg(theta_uturn))>0.00001):
V = joint_positions['elbow'] - joint_positions['wrist']
k = joint_positions['shoulder'] - joint_positions['elbow']
k = k/(k.length)
Vrot = V*cos(-theta_uturn) + (k.cross(V))*sin(-theta_uturn) + k*(k.dot(V))*(1-cos(-theta_uturn))
joint_positions['elbow'] = joint_positions['wrist'] + Vrot
need_test = True
if(deg(theta_uturn)>90):
theta_uturn = np.pi/2
theta_arm_ud = theta_arm_ud - rad(1)
iterations += 1
if(iterations > 100):
print('Target is unreachable (iterations > 100)')
return(deg([theta_shoulder, theta_arm_ud, theta_arm_oc, theta_uturn, theta_elbow]))
print('Iterations = ',iterations)
return(deg([theta_shoulder, theta_arm_ud, theta_arm_oc, theta_uturn, theta_elbow]))
def plotsSI(path, preppedData, pr, gl, ai, rp, dr, tc, en, op, pl):
showPlot = pr['SIPlotsShow']
save = pr['SIPlotsSave']
figures = []
g = 9.8
[t, x, y, xD, yD, v, vD, alpha, theta, thetaD, gamma, elev, Sth, omegd, omege, L, D, T, Tg, vgw, \
torqWing,torqStab, Me, Few, engP, omegrel, rdrum, tctorqueDrum, winP, ropP, gliP, gndTorq, ropeTheta, ropeTorq, \
smRope, smStall, smStruct, smRecov, vGust, gData, dData, oData, pData, eData, rData, aData, tData] = preppedData
iColor = 0 # counter for plots, so each variable has a different color
# plot engine power and torque curves from model parameters
figures.append(
xy(False, showPlot, save, path, iColor, [t],
[oData['err'], oData['derr'], oData['interr']], 't (sec)',
'error quantities', ['err', 'derr', 'interr'], 'Errors operator'))
figures.append(
xy(False, showPlot, save, path, iColor, [t],
[pData['err'], pData['derr'], pData['interr']], 't (sec)',
'error quantities', ['err', 'derr', 'interr'], 'Errors pilot'))
if pr['plotPowerTorque']:
omegeng = linspace(0, 1.1 * en.omegapeakP, 100)
powr = linspace(0, 1.1 * en.omegapeakP, 100)
torq = linspace(0, 1.1 * en.omegapeakP, 100)
rpm = omegeng * 60 / 2.0 / pi
for i, omegar in enumerate(omegeng):
powr[i] = en.Pavail(omegar) / 1000
torq[i] = en.torqAvail(omegar)
figures.append(
xy(False, showPlot, save, path, iColor, [rpm], [powr, torq],
'Engine speed (rpm)', 'Power (kW), Torque(Nm)',
['Pistons power', 'Pistons torque'], 'Engine curves'))
if pr['plotLift']: ##plot lift curve vs alpha at v_best
alphaList = linspace(-20, 80, 100)
lift = array([gl.Lnl(gl.vb, rad(alph)) for alph in alphaList])
figures.append(xy(False, showPlot, save, path, iColor, [alphaList], [lift / gl.W], \
'Angle of attack (deg)', 'Lift/Weight', [''], 'Lift vs angle of attack'))
alphaList = linspace(-4, pr['alphaStallVsWing'], 100)
drag = array([gl.coeffDrag(rad(alph)) for alph in alphaList])
figures.append(xy(False, showPlot, save, path, iColor, [alphaList], [drag], \
'Angle of attack (deg)', 'Drag coefficient', [''], 'Drag vs angle of attack'))
if pr['plotTorqCov']:
vrelList = linspace(0, 1.5, 100)
tcGearingList = array([tc.torqMult(vrel) for vrel in vrelList])
# tcEfficiencyList = array([vrel * tc.torqMult(vrel) for vrel in vrelList])
tcInvKform = array([tc.invKform(vrel) for vrel in vrelList])
figures.append(xy(False, showPlot, save, path, iColor, [vrelList], \
[tcGearingList, tcInvKform],
'vDrum/vEngine', '' ,['torque factor','inverse capacity form'], 'Torque converter'))
# glider position vs time
figures.append(
xy(False, showPlot, save, path, iColor, [t], [x, y], 'time (sec)',
'position (m)', ['x', 'y'], 'Glider position vs time'))
figures.append(
xy(False, showPlot, save, path, iColor, [x], [y], 'x (m)', 'y (m)',
[''], 'Glider y vs x'))
# glider speed and angles
figures.append(xy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t],
[xD, yD, v, deg(alpha), deg(theta), deg(gamma), deg(elev), deg(thetaD)], \
'time (sec)', 'Velocity (m/s), Angles (deg)',
['vx', 'vy', 'v', 'angle of attack', 'pitch', 'climb', 'elevator', 'pitch rate (deg/sec)'],
'Glider velocities and angles'))
# iColor = 0 #restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t, t, t],
[v, rData['stretch'], dr.rdrum * omegd, y / rp.lo, Tg / gl.W, L / gl.W, divide(L, D), deg(alpha), deg(gamma), deg(thetaD)], \
[0, 0, 0, 1, 1, 1, 0, 0, 0, 0], 'time (sec)', ['Velocity (m/s), stretch (m), Angles (deg), L/D', 'Relative forces and height'],
['v (glider)', 'stretch', r'$v_r$ (rope)', \
'height/' + r'$\l_o $', 'T/W at glider', 'L/W', 'L/D', 'angle of attack', 'climb angle', 'rot. rate (deg/sec)'],
'Glider and rope'))
# Forces
figures.append(xy(False, showPlot, save, path, iColor, [t, t, t, t, t], [L / gl.W, D / gl.W, T / gl.W, Tg / gl.W, Few / gl.W], \
'time (sec)', 'Forces/Weight', ['lift', 'drag', 'tension at drum', 'tension at glider', 'tc-drum'],
'Forces'))
# torques
figures.append(
xy(False, showPlot, save, path, iColor, [t],
[ropeTorq, torqWing + torqStab, Me, gndTorq], 'time (sec)',
'Torque (Nm)', ['rope', 'stabilizer+wing', 'elevator', 'ground'],
'Torques on glider'))
figures.append(
xy(False, showPlot, save, path, iColor, [t], [torqWing, torqStab],
'time (sec)', 'Torque (Nm)', ['wing', 'stabilizer'],
'Torques wing and stabilizer'))
# Engine, rope and drum
figures.append(xy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t], [multiply(omege,rdrum)/dr.gear/dr.diff, multiply(omegd,rdrum), \
vgw, deg(ropeTheta), tctorqueDrum/10, -multiply(T,rdrum)/10, 100 * Sth], 'time (sec)',
'Speeds (effective: m/s), Torque/100 (Nm) Angle (deg), Throttle %',
['engine speed', 'rope speed', 'glider radial speed', 'rope angle', 'TC torque on drum', 'Rope torque on drum','throttle'], 'Engine, drum and rope'))
figures.append(xy(False, showPlot, save, path, iColor, [t],
[omege * 60 / 2 / pi/10, engP/1000, engP/(omege + 1e-6),
tctorqueDrum / dr.gear / dr.diff,
10 * 100 * omegrel, \
10 * 100 * Sth], \
'time (sec)', 'Speeds (rpm,m/s), Power (KW)Torque (Nm), Throttlex10 %',
['eng rpm/10', 'engine power', 'engine torque','TC torque out', 'TC speed vs engine % x10', 'throttle % x10'],
'Engine'))
figures.append(
xy(False, showPlot, save, path, iColor, [t], [
eData['Edeliv'] / 1e6, dData['Edeliv'] / 1e6,
rData['Edeliv'] / 1e6, gData['Edeliv'] / 1e6, gData['Emech'] / 1e6
], 'time (sec)', 'Energy (MJ)',
['to engine', 'to drum', 'to rope', 'to glider', 'in glider'],
'Energy delivered and kept'))
figures.append(
xy(False, showPlot, save, path, iColor, [t],
[engP / en.Pmax, winP / en.Pmax, ropP / en.Pmax, gliP / en.Pmax],
'time (sec)', 'Power/Pmax',
['to engine', 'to drum', 'to rope', 'to glider'],
'Power delivered'))
# zoom in on a time range same plot as above
# Specialty plots for presentations
# zoom = True
# if zoom:
# t1 = 6 ; t2 = 17
# figures.append(xyy(False, showPlot, save, path, iColor,[t,t,t,t,t,t,t,t,t,t,t],[1.94*v,1.94*omegd,y/0.305/10,Tg/gl.W,L/gl.W,10*deg(alpha),10*deg(gData['alphaStall']),deg(gamma),10*deg(elev),Sth,omege/dr.rdrum*60/2/pi*dr.diff*dr.gear/100],\
# [0,0,0,1,1,0,0,0,0,1,0],'time (sec)',['Velocity (kts), Height/10 (ft), Angle (deg)','Relative forces'],\
# ['v (glider)',r'$v_r$ (rope)','height/10','T/W', 'L/W', 'angle of attack','stall angle','climb angle','elev deflection','throttle','rpm/100'],'Glider and engine expanded',t1,t2)
# iColor = 0 #restart color cycle
# figures.append(xyy(False, showPlot, save, path, iColor,[t,t,t,t,t,t,t,t],[1.94*v,y/0.305,deg(gamma),L/gl.W,smStruct,smStall,smRope,smRecov/0.305],\
# [0,0,0,1,1,1,1,0],'time (sec)',['Velocity (kts), Height (ft), Angle (deg)',"Relative forces"],\
# ['v','height','Climb angle','L/W','Struct margin','Stall margin','Rope margin','Recovery margin'],'Glider and safety margins',t1,t2)
# iColor = 0 #restart color cycle
# figures.append(xyy(False, showPlot, save, path, iColor,[t,t,t,t,t,t,t,t,t,t,t],[1.94*v,1.94*omegd,y/0.305/10,Tg/gl.W,L/gl.W,10*deg(alpha),10*deg(gData['alphaStall']),deg(gamma),10*deg(elev),Sth,omege/dr.rdrum*60/2/pi*dr.diff*dr.gear/100],\
# [0,0,0,1,1,0,0,0,0,1,0],'time (sec)',['Velocity (kts), Height/10 (ft), Angle (deg)','Relative forces'],\
# ['v (glider)',r'$v_r$ (rope)','height/10','T/W', 'L/W', 'angle of attack','stall angle','climb angle','elev deflection','throttle','rpm/100'],'Glider and engine')
# iColor = 0 #restart color cycle
# figures.append(xyy(True,[t,t,t,t,t,t,t,t],[1.94*v,y/0.305/10,deg(gamma),L/gl.W,smStruct,smStall,smRope,smRecov/0.305/10],\
# [0,0,0,1,1,1,1,0],'time (sec)',['Velocity (kts), Height (ft), Angle (deg)',"Relative forces"],\
# ['v','height/10','climb angle','L/W','Struct margin','Stall margin','Rope margin','Recovery margin'],'Glider and safety margins')
# Imperial units:
# if vGustPeak > 0 and ymax > hGust:
# figures.append(xyy(False, showPlot, save, path, iColor,[t,t,t,t,t,t,t,t,t],[1.94*v,y/0.305,deg(gamma),L/gl.W,smStruct,smStall,smRope,smRecov/0.305, 1.94*vGust*10],\
# [0,0,0,1,1,1,1,0,0],'time (sec)',['Velocity (kts), Height (ft), Angle (deg)',"Relative forces"],\
# ['velocity','height','climb angle','L/W','struct margin','stall margin','rope margin','recovery margin','vel gust'],'Glider and safety margins')
# else:
# figures.append(xyy(False, showPlot, save, path, iColor,[t,t,t,t,t,t,t,t],[1.94*v,y/0.305,deg(gamma),L/gl.W,smStruct,smStall,smRope,smRecov/0.305],\
# [0,0,0,1,1,1,1,0],'time (sec)',['Velocity (kts), Height (ft), Angle (deg)',"Relative forces"],\
# ['velocity','height','climb angle','L/W','struct margin','stall margin','rope margin','recovery margin'],'Glider and safety margins')
zoom = pr['zoom']
if zoom:
# if not ai.startGust is None and 's' in ai.startGust:
# t1 = float(ai.startGust.split()[0])-0.5
# t2 = t1 + 2*ai.widthGust/25.0 + 2.0 -1.5
[t1, t2] = zoom
if ai.vGustPeak > 0 and not ai.startGust is None:
# without safety margins
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t],
[v, y/10.0, deg(gamma), L / gl.W, T / gl.W, vGust], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W', 'vel gust'], 'Winch launch'))
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t],
[v, y/10.0, deg(gamma), L / gl.W, T / gl.W, vGust], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W', 'vel gust'],
'Winch launch expanded', t1, t2))
# with safety margins (T/W is redundant)
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t, t, t],
[v, y/10.0, deg(gamma), L / gl.W, smStruct, smStall, smRope, smRecov, vGust], \
[0, 0, 0, 1, 1, 1, 1, 0, 0], 'time (sec)',
['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin', 'rope margin',
'recovery margin', 'vel gust'], 'Winch launch and safety margins'))
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t, t, t],
[v, y/10.0, deg(gamma), L / gl.W, smStruct, smStall, smRope, smRecov, vGust], \
[0, 0, 0, 1, 1, 1, 1, 0, 0], 'time (sec)',
['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin',
'rope margin', 'recovery margin', 'vel gust'], 'Winch launch and safety margins expanded', t1,
t2))
else: # without gusts
# without safety margins
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t], [v, y/10.0, deg(gamma), L / gl.W, T / gl.W], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W'], 'Winch launch expanded', t1, t2))
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t], [v, y/10.0, deg(gamma), L / gl.W, T / gl.W], \
[0, 0, 0, 1, 1, 0], 'time (sec)', ['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'T/W'], 'Winch launch'))
# with safety margins
if zoom:
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t],
[v, y/10.0, deg(gamma), L / gl.W, smStruct, smStall, smRope, smRecov], \
[0, 0, 0, 1, 1, 1, 1, 0], 'time (sec)',
['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin',
'rope margin', 'recovery margin'], 'Winch launch and safety margins expanded', t1, t2))
iColor = 0 # restart color cycle
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t, t, t, t, t],
[v, y/10.0, deg(gamma), L / gl.W, smStruct, smStall, smRope, smRecov], \
[0, 0, 0, 1, 1, 1, 1, 0], 'time (sec)', ['Velocity (m/s), Height/10 (m), Angle (deg)', "Relative forces"], \
['velocity', 'height', 'climb angle', 'L/W', 'struct margin', 'stall margin', 'rope margin',
'recovery margin'], 'Winch launch and safety margins'))
# safety margins alone
if zoom:
iColor = 6 # choose color cycle start
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t], [smStruct, smStall, smRope, smRecov], \
[1, 1, 1, 0], 'time (sec)', ['Velocity (m/s), Height (m), Angle (deg)', "Relative forces"], \
['struct margin', 'stall margin', 'rope margin', 'recovery margin'], 'Safety margins expanded', t1,
t2))
iColor = 6 # choose color cycle start
figures.append(xyy(False, showPlot, save, path, iColor, [t, t, t, t], [smStruct, smStall, smRope, smRecov], \
[1, 1, 1, 0], 'time (sec)', ['Velocity (m/s), Height (m), Angle (deg)', "Relative forces"], \
['struct margin', 'stall margin', 'rope margin', 'recovery margin'], 'Safety margins'))
return figures
def coeffDrag(self,alpha):
return self.CD[0] + self.CD[1] * deg(alpha) + self.CD[2] * deg(alpha) ** 2 + self.CD[3] * deg(alpha) ** 3
def wobj_error_x(self):
if (self.parser.yaml_wobj is None):
return numpy.NaN
acos_val = acos(
normalize(self.wobj_ori_x).dot(self.parser.yaml_wobj_ori_x))
return deg(acos_val)
