sys.path.append(os.path.join(os.path.dirname(__file__), '..', 'Aero'))
import aero_calcs as ac
import mars_standard_atmosphere as atm
mean_radius = 3389500 #[m]
reentry_altitude = 80000 #[m]
v_insertion_orbit = 3272.46591 #[m/s]
insertion_orbit_a = mean_radius + 500000 #[m]
insertion_orbit_p = mean_radius - 300000 #[m]
vehicle_mass = 38000 #[kg]
S = 350 #[m^2]
MOI = [391281.1045, 22714482.967, 22714482.967] # Ixx, Iyy, Izz
dt = 0.1
mars = astro_tools.Planet()
state = np.zeros(12)
state[0] = mars.reentry_velocity(reentry_altitude, insertion_orbit_a,
insertion_orbit_p) # velocity
state[1] = mars.reentry_angle(
reentry_altitude, insertion_orbit_p,
insertion_orbit_a) # flight path angle (1.5 arcsecs (2 sigma))
state[2] = np.radians(42.5) # heading angle (1.5 arcsecs (2 sigma))
state[3] = reentry_altitude + mean_radius # radius
state[4] = np.radians(-1.168) # lognitude 25.5 -1.168 - 0.141
state[5] = np.radians(24.322) # latitude 42.5 24.322 - 0.077
state[6] = 0 # rollrate
state[7] = 0 # pitchrate
state[8] = 0 # yawrate
state[9] = -np.radians(55) # angle of attack defined positive downwards
data = np.genfromtxt('spirit_flightpath.csv', delimiter='', dtype=None)
t = data[:, 0] - data[0, 0]
alt = data[:, 2]
gamma = data[:, 1]
lat = data[:, 4]
long = data[:, 6]
ca = data[:, 32]
cn = data[:, 34]
vx = data[:, 18]
vy = data[:, 20]
vz = data[:, 22]
v = np.sqrt(vx**2 + vy**2 + vz**2)
vrel = data[:, 24]
aaxial = data[:, 8]
aradial = data[:, 10]
mars = astro_tools.Planet(scale_height=11.1e3)
state = np.zeros(12)
state[0] = v[0] # velocity
state[1] = np.radians(-16) # flight path angle
state[2] = np.radians(86.5) # heading angle
state[3] = mars.r + 125000 # radius end at 3400300 m 3522200
state[4] = np.radians(340.9) # lognitude
state[5] = np.radians(-2.9) # latitude
state[6] = 0 # rollrate
state[7] = 0 # pitchrate
state[8] = 0 # yawrate
state[9] = np.radians(0) # angle of attack defined positive downwards
state[10] = 0 # sideslip angle
state[11] = np.radians(0) # bank angle