# -*- coding: cp1252 -*-
# created on May 22, 2014 by Andreas
import importlib
import krpc
from toolkit import ksp
from toolkit import nodes
cx = ksp.connect(name = 'Console')
ksp.set_globals(cx)
low_orbit = 80000
importlib.reload(nodes); nd = nodes.apoapsis(low_orbit)
importlib.reload(nodes); nodes.execute(nd)
# vec = krpc.schema.Geometry.Vector3()
# cx = krpc.connect(name = 'Console')
# print('Connected to server, version', cx.krpc.get_status().version)
space_center = cx.space_center
vessel = SC.active_vessel
orbit = vessel.orbit
control = vessel.control
auto_pilot = vessel.auto_pilot
flight = vessel.flight()
resources = vessel.resources
print(vessel.name)
print(orbit.body.name)
def ltoa(ascent_profile=DEFAULT_PROFILE):
""" launch to lko in atmosphere
target_periapsis
target_apoapsis
target_inclination
"""
vessel = SC.active_vessel
orbit = vessel.orbit
control = vessel.control
auto_pilot = vessel.auto_pilot
flight = vessel.flight()
# parts = vessel.parts
# resources = vessel.resources
# calculate pitch legs
pitch_legs = []
for i in range(len(ascent_profile) - 1):
j = i + 1
dx = ascent_profile[j][0] - ascent_profile[i][0]
dy = ascent_profile[j][1] - ascent_profile[i][1]
a = dy / dx
b = ascent_profile[i][1] - a * ascent_profile[i][0]
pitch_legs.insert(0, (ascent_profile[i][0], (a, b)))
pitch_legs.insert(0, (ascent_profile[j][0], (0, 0)))
print(pitch_legs)
# sys.exit(0)
body = orbit.body
mu = body.gravitational_parameter # gravitational parameter, mu = G mass
rb = body.equatorial_radius # radius of body [m]
ha = body.atmosphere_depth # atmospheric height [m]
# gravity turn parameters
low_orbit = 80000 # low lko altitude [m]
# velocity parameters
maxq = 8000
print("Launch program start at: {:.0}".format(SC.ut))
control.throttle = 1
auto_pilot.set_rotation(90, 90)
vsfc = vessel.velocity(vessel.surface_reference_frame)
vobt = vessel.velocity(body.non_rotating_reference_frame)
# lock steering to up + R(0, 0, -180)
print("T-1 All systems GO. Ignition!")
# control.activate_next_stage()
time.sleep(1)
print(met(vessel.met) + " Ignition.")
control.activate_next_stage()
print(met(vessel.met) + " Liftoff.")
# control speed and attitude
while orbit.apoapsis_altitude < low_orbit:
facing = flight.direction
vel = flight.velocity
speed = flight.speed
ma = flight.mean_altitude
# control attitude
# target pitch
for mina, coeff in pitch_legs:
if ma > mina:
a, b = coeff
target_pitch = a * ma + b
break
pitch = flight.pitch
auto_pilot.set_rotation(target_pitch, 90, 90)
# dynamic pressure q
q = flight.dynamic_pressure
vl = maxq * 0.9
vh = maxq * 1.1
if q < vl:
qfac = 1
if q > vl and q < vh:
qfac = (vh - q) / (vh - vl)
if q > vh:
qfac = 0
control.throttle = qfac
print("q: {:5.0f} pitch: flight {:2.1f}, target {:2.1f}".format(q, pitch, target_pitch))
#print("tta: {:3.0f} q: {:5.0f} pitch: flight {:2.1f}, target {:2.1f}".format(tta, q, pitch, target_pitch))
time.sleep(0.5)
control.throttle = 0
auto_pilot.set_direction(flight.direction, roll=90, wait=True)
print("Waiting to leave atmosphere {:.0f}km".format(body.atmosphere_depth / 1000))
while flight.mean_altitude < body.atmosphere_depth:
time.sleep(1)
nd = nodes.apoapsis(low_orbit)
nodes.execute(nd)
auto_pilot.disengage()
print("attitude control terminated.")