ConstraintSets should contain non-ConstraintSets

docs/source/examples/performance_modeling_output.txt

@@ -6,41 +6,41 @@ Cost
 Constraints
 -----------
  Mission
-   "definition of Wburn":
-     Wfuel[:-1] >= Wfuel[1:] + Wburn[:-1]
-   "require fuel for the last leg":
-     Wfuel[3] >= Wburn[3]
-   
-   FlightSegment
-     AircraftP
-       "fuel burn rate":
-         Wburn[:] >= 0.1·D[:]
-       "lift":
-         Aircraft.W + Wfuel[:] <= 0.5·rho[:]·CL[:]·S·V[:]²
-       "performance":
-         WingAero
-         "definition of D":
-           D[:] >= 0.5·rho[:]·V[:]²·CD[:]·S
-         "definition of Re":
-           Re[:] = rho[:]·V[:]·c/mu[:]
-         "drag model":
-           CD[:] >= 0.074/Re[:]^0.2 + CL[:]²/π/A/e[:]
-     
-     FlightState
-       (no constraints)
- 
+  "definition of Wburn":
+    Wfuel[:-1] >= Wfuel[1:] + Wburn[:-1]
+  "require fuel for the last leg":
+    Wfuel[3] >= Wburn[3]
+
+  FlightSegment
+   AircraftP
+    "fuel burn rate":
+      Wburn[:] >= 0.1·D[:]
+    "lift":
+      Aircraft.W + Wfuel[:] <= 0.5·rho[:]·CL[:]·S·V[:]²
+    "performance":
+      WingAero
+       "definition of D":
+         D[:] >= 0.5·rho[:]·V[:]²·CD[:]·S
+       "definition of Re":
+         Re[:] = rho[:]·V[:]·c/mu[:]
+       "drag model":
+         CD[:] >= 0.074/Re[:]^0.2 + CL[:]²/π/A/e[:]
+
+   FlightState
+    (no constraints)
+
  Aircraft
-   "definition of W":
-     Aircraft.W >= Aircraft.Fuselage.W + Aircraft.Wing.W
-   "components":
-     Fuselage
-       (no constraints)
-     
-     Wing
-       "definition of mean chord":
-         c = (S/A)^0.5
-       "parametrization of wing weight":
-         Aircraft.Wing.W >= S·Aircraft.Wing.rho
+  "definition of W":
+    Aircraft.W >= Aircraft.Fuselage.W + Aircraft.Wing.W
+  "components":
+    Fuselage
+     (no constraints)
+
+    Wing
+     "definition of mean chord":
+       c = (S/A)^0.5
+     "parametrization of wing weight":
+       Aircraft.Wing.W >= S·Aircraft.Wing.rho
 
 Optimal Cost
 ------------
@@ -108,9 +108,9 @@ Constraint Differences
 +++ added in argument
 
 @@ -41,4 +41,3 @@
-          c = (S/A)^0.5
-        "parametrization of wing weight":
-          Aircraft.Wing.W >= S·Aircraft.Wing.rho
+        c = (S/A)^0.5
+      "parametrization of wing weight":
+        Aircraft.Wing.W >= S·Aircraft.Wing.rho
 - Wburn[:] >= 0.2·D[:]
 
 **********************

docs/source/examples/relaxation_output.txt

@@ -19,11 +19,11 @@ Cost
 
 Constraints
 -----------
-   "minimum relaxation":
-     C >= 1
-   "relaxed constraints":
-     x <= C·x_max
-     x_min <= C·x
+ "minimum relaxation":
+   C >= 1
+ "relaxed constraints":
+   x <= C·x_max
+   x_min <= C·x
 
 Optimal Cost
 ------------
@@ -61,11 +61,11 @@ Cost
 
 Constraints
 -----------
-   "minimum relaxation":
-     C[:] >= 1
-   "relaxed constraints":
-     x <= C[0]·x_max
-     x_min <= C[1]·x
+ "minimum relaxation":
+   C[:] >= 1
+ "relaxed constraints":
+   x <= C[0]·x_max
+   x_min <= C[1]·x
 
 Optimal Cost
 ------------
@@ -105,18 +105,18 @@ Cost
 Constraints
 -----------
  Relax2
-   "original constraints":
-     x <= x_max
-     x >= x_min
-   "relaxation constraints":
-     "x_max":
-       Relax2.x_max >= 1
-       x_max >= Relax2.OriginalValues.x_max/Relax2.x_max
-       x_max <= Relax2.OriginalValues.x_max·Relax2.x_max
-     "x_min":
-       Relax2.x_min >= 1
-       x_min >= Relax2.OriginalValues.x_min/Relax2.x_min
-       x_min <= Relax2.OriginalValues.x_min·Relax2.x_min
+  "original constraints":
+    x <= x_max
+    x >= x_min
+  "relaxation constraints":
+    "x_max":
+      Relax2.x_max >= 1
+      x_max >= Relax2.OriginalValues.x_max/Relax2.x_max
+      x_max <= Relax2.OriginalValues.x_max·Relax2.x_max
+    "x_min":
+      Relax2.x_min >= 1
+      x_min >= Relax2.OriginalValues.x_min/Relax2.x_min
+      x_min <= Relax2.OriginalValues.x_min·Relax2.x_min
 
 Optimal Cost
 ------------

gpkit/constraints/array.py

@@ -1,9 +1,8 @@
 "Implements ArrayConstraint"
-from .set import ConstraintSet
 from .single_equation import SingleEquationConstraint
 
 
-class ArrayConstraint(SingleEquationConstraint, ConstraintSet):
+class ArrayConstraint(SingleEquationConstraint, list):
     """A ConstraintSet for prettier array-constraint printing.
 
     ArrayConstraint gets its `sub` method from ConstrainSet,
@@ -14,10 +13,16 @@ class ArrayConstraint(SingleEquationConstraint, ConstraintSet):
     """
     def __init__(self, constraints, left, oper, right):
         SingleEquationConstraint.__init__(self, left, oper, right)
-        ConstraintSet.__init__(self, constraints)
+        list.__init__(self, constraints)
+        self.constraints = constraints
+
+    def __iter__(self):
+        yield from self.constraints.flat
+
+    def lines_without(self, excluded):
+        "Returns lines for indentation in hierarchical printing."
+        return self.str_without(excluded).split("\n")
 
     def __bool__(self):
         "Allows the use of '=' NomialArrays as truth elements."
-        if self.oper != "=":
-            return NotImplemented
-        return all(bool(p) for p in self.flat())
+        return False if self.oper != "=" else bool(self.constraints.all())

gpkit/constraints/gp.py

@@ -90,7 +90,7 @@ def __init__(self, cost, constraints, substitutions,
         cost_hmap = cost.hmap.sub(self.substitutions, cost.varkeys)
         if any(c <= 0 for c in cost_hmap.values()):
             raise InvalidPosynomial("cost must be a Posynomial")
-        self.hmaps = [cost_hmap] + list(self.flathmaps(self.substitutions))
+        self.hmaps = [cost_hmap] + list(self.as_hmapslt1(self.substitutions))
         ## Generate various maps into the posy- and monomials
         # k [j]: number of monomials (rows of A) present in each constraint
         self.k = [len(hm) for hm in self.hmaps]