Splitting markdown files into sections

[mjburton11]

@bqpd, @whoburg: essentially what I want my pdf to look like is:

Weight Model:
Assumptions
List of all my assumptions
Variables
List of all my variables
Constraints
List of all my constraints

Aero Model:
Same thing

Then the solution table.

Any idea on how to do this? You can look at my latest commit in 1682master to see my md file.

---

SOLAR HIGH ALTITUDE LONG ENDURANCE AIRCRAFT

#inPDF: skip

from gpkit import Variable, Model, units
import numpy as np
import matplotlib.pyplot as plt

class SolarHALE(Model):
    """High altitude long endurance solar UAV"""
    def __init__(self, **kwargs):
        """Setup method should return objective, list of constraints"""
        constraints = []

Steady level flight variables

#inPDF: replace with slfvars.generated.tex
        CD = Variable('C_D', '-', 'Drag coefficient')
        CL = Variable('C_L', '-', 'Lift coefficient')
        P_shaft = Variable('P_{shaft}', 'W', 'Shaft power')
        S = Variable('S', 'm^2', 'Wing reference area')
        V = Variable('V', 'm/s', 'Cruise velocity')
        W = Variable('W', 'lbf', 'Aircraft weight')

        eta_prop = Variable(r'\eta_{prop}', 0.7, '-', 'Propulsive efficiency')
        rho = Variable(r'\rho', 'kg/m^3')

#inPDF: replace with slfcnstrs.generated.tex

        constraints.extend([P_shaft >= V*W*CD/CL/eta_prop,   # eta*P = D*V
                            W == 0.5*rho*V**2*CL*S])

Aerodynamics model

#inPDF: replace with aerovars.generated.tex

        Cd0 = Variable('C_{d0}', 0.002, '-', "non-wing drag coefficient")
        cdp = Variable("c_{dp}", "-", "wing profile drag coeff")
        CLmax = Variable('C_{L-max}', 1.5, '-', 'maximum lift coefficient')
        e = Variable('e', 0.9, '-', "spanwise efficiency")
        AR = Variable('AR', 27, '-', "aspect ratio")
        b = Variable('b', 'ft', 'span')
        mu = Variable(r'\mu', 1.5e-5, 'N*s/m^2', "dynamic viscosity")
        Re = Variable("Re", '-', "Reynolds number")
        Re_ref = Variable("Re_{ref}", 3e5, "-", "Reference Re for cdp")
        Cf = Variable("C_f", "-", "wing skin friction coefficient")
        Kwing = Variable("K_{wing}", 1.3, "-", "wing form factor")

#inPDF: replace with aerocnstrs.generated.tex

        constraints.extend([
            CD >= (Cd0 + cdp + CL**2/(np.pi*e*AR))*1.3,
            cdp >= ((0.006 + 0.005*CL**2 + 0.00012*CL**10)*(Re/Re_ref)**-0.3),
            b**2 == S*AR,
            CL <= CLmax,
            Re == rho*V/mu*(S/AR)**0.5,
            ])

Weight model

#inPDF: replace with weightvars.generated.tex
        W_batt = Variable('W_{batt}', 'lbf', 'Battery weight')
        W_airframe = Variable('W_{airframe}', 'lbf', 'Airframe weight')
        W_solar = Variable('W_{solar}', 'lbf', 'Solar panel weight')
        W_pay = Variable(r'W_{pay}', 4, 'lbf', 'Aircraft weight')

        E_batt = Variable('E_{batt}', 'J', 'Battery energy')
        rho_solar = Variable(r'\rho_{solar}', 1.2, 'kg/m^2',
                             'Solar cell area density')
        f_airframe = Variable('f_{airframe}', 0.20, '-',
                              'Airframe weight fraction')
        h_batt = Variable('h_{batt}', 250, 'W*hr/kg', 'Battery energy density')
        g = Variable('g', 9.81, 'm/s^2', 'Gravitational acceleration')

#inPDF: replace with weightcnstrs.generated.tex

        constraints.extend([W_airframe >= W*f_airframe,
                            W_batt >= E_batt/h_batt*g,
                            W_solar >= rho_solar*g*S,
                            W >= W_pay + W_solar + W_airframe + W_batt])

[mjburton11]

@bqpd, I don't have class today so if it would help to meet up to talk about what I'm envisioning then let me know.

[whoburg]

was this resolved by using individual ConstraintSets?

[mjburton11]

Yes it was.