plot payload contours

solar/payloadcon.py

@@ -0,0 +1,108 @@
+" contour plots "
+import matplotlib.pyplot as plt
+import numpy as np
+import pandas as pd
+import sys
+from solar import Mission, Aircraft
+from plotting import labelLines
+from gpkit.tools.autosweep import autosweep_1d
+
+N = 100
+plt.rcParams.update({'font.size':15})
+
+def payloadcon(latitudes):
+    time = 0
+    numsolves = 0
+    etamax = []
+    lines = []
+    midx = []
+    data = {}
+    passing = True
+    wmin = 0.01
+    pmin = 0.01
+    for lat in latitudes:
+        if passing:
+            V = Aircraft(sp=True)
+            M = Mission(V, latitude=[lat])
+            del M.substitutions["Wpay"]
+            M.substitutions.update({"Ppay": pmin})
+            M.cost = 1./M["Wpay"]
+            try:
+                sol = M.localsolve("mosek")
+            except RuntimeWarning:
+                break
+            time += sol["soltime"]
+            numsolves += 1
+            wmax = sol("Wpay").magnitude - 1e-3
+            if wmin >= wmax:
+                break
+            del M.substitutions["Ppay"]
+            M.cost = 1./M["Ppay"]
+            wpays = np.linspace(wmin, wmax, 10)
+            tol = 0.01
+            notpassing = True
+            ppays = []
+            for w in wpays:
+                M.substitutions["Wpay"] = w
+                try:
+                    sol = M.localsolve("mosek")
+                    time += sol["soltime"]
+                    numsolves += 1
+                    ppays.append(sol("Ppay").magnitude)
+                except RuntimeWarning:
+                    ppays.append(np.NaN)
+            data["%d-W" % lat] = wpays
+            data["%d-P" % lat] = ppays
+
+    df = pd.DataFrame(data)
+    return df
+
+def plot_payloadcon(df, lats):
+
+    lats = np.array(lats)
+    maxlat = int(df.columns[-1][0:2])
+    lats = lats[lats <= 30]
+    fig, ax = plt.subplots()
+    lines = []
+    midx = []
+    maxps = []
+    for la in lats:
+        wpays, ppays= df["%d-W" % la], df["%d-P" % la]
+        maxps.append(max(ppays))
+        if la % 4 == 0:
+            l = ax.plot(wpays, ppays, "k", label="%d$^{\\circ}$ Lat" % la)
+            if la is not 20:
+                lines.append(l[0])
+            midx.append(np.median(wpays))
+        elif la % 2 == 0:
+            l = ax.plot(wpays, ppays, "--", c="0.5", label="%d$^{\\circ}$ Lat" % la)
+
+    labelLines(lines, align=False, xvals=midx, zorder=[10]*len(lines))
+    ax.set_ylabel("Payload Power [W]")
+    ax.set_xlabel("Payload Weight [lbf]")
+    ax.set_xlim([0, 500])
+    ax.set_ylim([0, max(maxps)])
+    ax.grid()
+    return fig, ax
+
+def test():
+    _, _ = plot_battsolarcon()
+
+if __name__ == "__main__":
+    if len(sys.argv) > 1:
+        path = sys.argv[1]
+        GENERATE = True if sys.argv[2] == "GEN" else False
+    else:
+        path = ""
+        GENERATE = False
+
+    Lats = range(16, 30, 2)
+    if GENERATE:
+        DF = payloadcon(Lats)
+        DF.to_csv("payloadcon.generated.csv")
+    else:
+        DF = pd.read_csv("payloadcon.generated.csv")
+        del DF["Unnamed: 0"]
+
+    fig, ax = plot_payloadcon(DF, Lats)
+    fig.savefig(path + "paycon.pdf", bbox_inches="tight")

solar/sens_chart.py

@@ -17,6 +17,8 @@ def get_highestsens(model, res, varnames=None, N=10):
         for vname in varnames:
             sen = res["sensitivities"]["constants"][vname]
             if hasattr(sen, "__len__"):
+                print vname
+                print sen
                 val = max(np.abs(sen.values()))
                 vk = [svk for svk in sen if abs(sen[svk]) == val][0]
                 sen = sum(sen.values())
@@ -118,9 +120,9 @@ def test():
            M.aircraft.battery.etadischarge: "$\\eta_{\\mathrm{discharge}}$",
            M.aircraft.battery.hbatt: "$h_{\\mathrm{batt}}$",
            M.aircraft.solarcells.etasolar: "$\\eta_{\\mathrm{solar}}$",
-           "Nmax": "$N_{\\mathrm{max}}$",
-           "e": "$e$", "etaprop": "$\\eta_{\\mathrm{prop}}$"}
+           M.mission[1].winggust.Nmax: "$N_{\\mathrm{load}}$",
+           M.mission[1].aircraftPerf.drag.wing.e: "$e$"}
 
-    sd = get_highestsens(M, sol, N=10)
+    sd = get_highestsens(M, sol, vns)
     f, a = plot_chart(sd)
     f.savefig(path + "sensbar.pdf", bbox_inches="tight")

solar/solar.py

@@ -71,7 +71,6 @@ class AircraftDrag(Model):
     mfac        1.05    [-]     drag margin factor
     Pshaft              [hp]    shaft power
     Pavn        200     [W]     avionics power draw
-    Ppay        100     [W]     payload power draw
     Poper               [W]     operating power
     mpower      1.05    [-]     power margin
     T                   [lbf]     thrust
@@ -119,6 +118,7 @@ def setup(self, static, state, onDesign = False):
         Qmotor = self.motor.Q
         RPMmotor = self.motor.omega
         Pelec = self.motor.Pelec
+        Ppay = static.Ppay
 
 
         self.wing.substitutions[e] = 0.95
@@ -153,6 +153,7 @@ class Aircraft(Model):
     Variables
     ---------
     Wpay        11      [lbf]   payload weight
+    Ppay        100     [W]     payload power draw
     Wavn        22      [lbf]   avionics weight
     Wtotal              [lbf]   aircraft weight
     Wwing               [lbf]   wing weight
@@ -678,7 +679,7 @@ def test():
     post_process(s)
 
 if __name__ == "__main__":
-    SP = False
+    SP = True
     Vehicle = Aircraft(Npod=0, sp=SP)
     M = Mission(Vehicle, latitude=[20])
     M.cost = M[M.aircraft.Wtotal]