trajectory

# SI units

3 # dimensions

# gravity
constant 0.0 0.0 -9.81

# environment
constant 1.0 # rho(r) Function3D
constant 0.0 constant 0.0 constant 0.0 # u_i(r) Function3D[3]

# hard deck
plane 0 0 1   0 # nowhere

# rocket
constant 0.9 # Cd(u,t)
constant 1.267e-4 # frontal area (mass,time): 0.5" dia
constant 0.0 # volume (mass, time)
table 4 0.0 5.0 0.8 5.0 0.8 0.0 1.0 0.0 # F(t)
# 5.6 g propellant in 0.8 s at 5 N:
# F Dt = D(mv) = v Dm => v = F Dt/Dm = 5 0.8 / 5.6e-3 = 714.286
constant 714.286 # alpha: F = -alpha dm/dt cf F Dt=D(m u_x) => F = u_x dm/dt => alpha = u_x
constant 1.0e8 # max structural pressure (mass,time), ~2 x strength for uniform body
constant 0.0 # ablation rate (fdrag = pdrag * area, gas rho, rocket mass)

# launcher
none

# initial state
0.0   0.0 0.0 0.0   0.0 0.0 1.0e-6  0.01822 # t r u m

# integration
30.0 0.01 # dt dtsub

end