def maneuver_list(self):
if lsu.altitude(self.telemetry.position) > 30000:
self.vehicle.pitch = m.radians(0)
elif lsu.altitude((self.telemetry.position)) <= 30000:
self.vehicle.pitch = m.radians(90)
frame_angle = m.atan(self.vehicle.position[0] /
self.vehicle.position[1])
theta = self.vehicle.pitch - frame_angle
return np.array([m.cos(theta), -m.sin(theta)])
def maneuver_list(vehicle):
if lsu.altitude(vehicle.position) > 25000:
vehicle.pitch = m.radians(0)
elif lsu.altitude(vehicle.position) <= 25000:
vehicle.pitch = m.radians(90)
try:
frame_angle = m.atan(vehicle.position[0] / vehicle.position[1])
except RuntimeWarning: # TODO hack on this...
frame_angle = 0
theta = vehicle.pitch - frame_angle
return np.array([m.cos(theta), -m.sin(theta)])
def drag(self, R, V):
'''returns the drag force exerted on a certain stage.'''
if lsu.altitude(R) > 200000:
return 0
else:
if np.linalg.norm(V) == 0:
return 0
else:
vhat = V / np.linalg.norm(
V
) # reduce the velocity vector to its components to accurately point the drag vector
V = np.linalg.norm(V)
return (-0.5 * lsu.density(R) * (V**2) * self.dragCoefficient *
self.crossSection) * vhat
def drag(
self, R, V
): # TODO: remove the portion of drag from theta velocity corresponding to earthly rotation
"""returns the drag force exerted on a certain stage."""
if lsu.altitude(R) > 200000:
return np.array([0, 0])
else:
if np.linalg.norm(V) == 0:
return np.array([0, 0])
else:
vhat = V / np.linalg.norm(
V) # correct for speed of rotation of Earth
V = np.linalg.norm(V)
return (-0.5 * lsu.density(R) * (V**2) *
self.drag_coefficient * self.cross_section) * vhat
def Isp(self, R):
if lsu.altitude(R) < 80000:
return self.Isp_sea + (1 / lsu.pressure(0)) * (lsu.pressure(
0) - lsu.pressure(R)) * (self.Isp_vac - self.Isp_sea)
else:
return self.Isp_vac