def execute(self):
""" Executes the program.
:return: None
"""
super(Program11, self).execute()
utils.log("Program 11 executing", log_level="INFO")
# test if KSP is connected
try:
get_telemetry("universalTime")
except KSPNotConnected:
self.terminate()
return
# --> call average G integration with ΔV integration
gc.run_average_g_routine = True
# --> terminate gyrocompassing
if "02" in gc.running_programs:
gc.programs["02"].terminate()
# --> compute initial state vector
# gc.routines["average_g"]()
# --> Display on DSKY:
# --> V06 N62 (we are going to use V16N62 though, so we can have a updated display
# --> R1: Velocity
# --> R2: Rate of change of vehicle altitude
# --> R3: Vehicle altitude in km to nearest .1 km
gc.execute_verb(verb="16", noun="62")
def delta_v(departure_altitude, destination_altitude, departure_body="Kerbin"):
"""
Given a circular orbit at altitude departure_altitude and a target orbit at altitude
destination_altitude, return the delta-V budget of the two burns required for a Hohmann
transfer.
departure_altitude and destination_altitude are in meters above the surface.
returns a float of the burn delta-v required, positive means prograde, negative means retrograde
:param departure_body:
:param departure_altitude: departure orbit altitude
:param destination_altitude: destination orbit altitude
"""
departure_planet_radius = get_telemetry("body_radius", body_number=TELEMACHUS_BODY_IDS[departure_body])
r1 = departure_altitude + departure_planet_radius
r2 = destination_altitude + departure_planet_radius
mu = float(get_telemetry("body_gravParameter", body_number=TELEMACHUS_BODY_IDS[departure_body]))
sqrt_r1 = math.sqrt(r1)
sqrt_r2 = math.sqrt(r2)
sqrt_2_sum = math.sqrt(2 / (r1 + r2))
sqrt_mu = math.sqrt(mu)
delta_v_1 = sqrt_mu / sqrt_r1 * (sqrt_r2 * sqrt_2_sum - 1)
delta_v_2 = sqrt_mu / sqrt_r2 * (1 - sqrt_r1 * sqrt_2_sum)
return delta_v_1, delta_v_2
def _check_target(self):
"""Checks if a target exists, it not, returns the default target, else returns the selected target number
Returns: octal target code
:rtype: str
"""
if get_telemetry("target_name") == u"No Target Selected.":
utils.log("No target selected in KSP, defaulting to Mun", log_level="WARNING")
return "Mun"
else:
return get_telemetry("target_name")
def _begin_burn(self):
self.initial_speed = get_telemetry("orbitalVelocity")
# start thrusting
telemachus.set_throttle(100)
gc.main_loop_table.append(self._thrust_monitor)
def check_paused_state(self):
""" Checks the paused state of KSP, and illuminates STBY annunciator and logs state as necessary.
:return: None
"""
if self.is_ksp_connected:
paused_state = get_telemetry("paused")
# if the paused state hasn't changed, skip any annunciator changes
if paused_state != self.ksp_paused_state:
if paused_state == 0:
self.dsky.annunciators["stby"].off()
utils.log("KSP unpaused, all systems go", log_level="INFO")
elif paused_state == 1:
self.dsky.annunciators["stby"].on()
utils.log("KSP paused", log_level="INFO")
elif paused_state == 2:
self.dsky.annunciators["stby"].on()
utils.log("No power to Telemachus antenna", log_level="WARNING")
elif paused_state == 3:
self.dsky.annunciators["stby"].on()
utils.log("Telemachus antenna off", log_level="WARNING")
elif paused_state == 4:
self.dsky.annunciators["stby"].on()
utils.log("No Telemachus antenna found", log_level="WARNING")
self.ksp_paused_state = paused_state
def calculate_time_to_ignition(self):
""" Calculates the time to ignition in seconds
:return: time to ignition in seconds
:rtype : float
"""
current_time = get_telemetry("missionTime")
return self.time_of_ignition - current_time
def execute(self):
""" Entry point for the program
:return: None
"""
super(Program15, self).execute()
self.departure_body = get_telemetry("body")
self.orbiting_body = get_telemetry("body")
if not self._check_orbital_parameters():
return
self.target_name = self._check_target()
gc.noun_data["30"] = config.OCTAL_BODY_IDS[self.target_name]
gc.execute_verb(verb="01", noun="30")
gc.dsky.request_data(requesting_object=self._accept_target_input, display_location=dsky.registers[1],
is_proceed_available=True)
def _check_orbital_parameters(self):
""" Checks to see if current orbital parameters are within an acceptable range to plot maneuver
:return: Bool
"""
# check if orbit is circular
if get_telemetry("eccentricity") > 0.001:
gc.poodoo_abort(224)
return False
# check if orbit is excessively inclined
target_inclination = float(get_telemetry("target_inclination"))
vessel_inclination = get_telemetry("inclination")
if (vessel_inclination > (target_inclination - 0.5)) and (vessel_inclination > (target_inclination + 0.5)):
gc.poodoo_abort(225)
return False
else:
return True
def recalculate_phase_angles(self):
""" This function is to be placed in the GC main loop to recalculate maneuver parameters.
:return: nothing
"""
# update current phase angle
telemachus_body_id = config.TELEMACHUS_BODY_IDS[config.OCTAL_BODY_NAMES[self.target_name]]
current_phase_angle = get_telemetry("body_phaseAngle",
body_number=telemachus_body_id)
# recalculate phase angle difference
phase_angle_difference = current_phase_angle - self.phase_angle_required
if phase_angle_difference < 0:
phase_angle_difference = 180 + abs(phase_angle_difference)
self.delta_time_to_burn = phase_angle_difference / ((360 / self.orbital_period) - (360 /
self.departure_body_orbital_period))
delta_time = utils.seconds_to_time(self.delta_time_to_burn)
velocity_at_cutoff = get_telemetry("orbitalVelocity") + self.delta_v_first_burn
def terminate(self):
""" Terminates the burn, disabling autopilot if running
:return: None
"""
self._disable_directional_autopilot()
# if the throttle is open, close it
if telemachus.get_telemetry("throttle") > 0:
telemachus.cut_throttle()
gc.remove_burn(self)
def _calculate_accumulated_delta_v(self):
current_speed = get_telemetry("orbitalVelocity")
return current_speed - self.initial_speed
def _calculate_velocity_at_cutoff(self):
return get_telemetry("orbitalVelocity") + self.delta_v_required
def calculate_maneuver(self):
""" Calculates the maneuver parameters and creates a Burn object
:return: Nothing
"""
# load target
telemachus_target_id = config.TELEMACHUS_BODY_IDS[self.target_name]
target_apoapsis = float(get_telemetry("body_ApA", body_number=telemachus_target_id))
# set destination altitude
self.destination_altitude = target_apoapsis + 500000
# if target == "Mun":
# self.destination_altitude = 12750000
# obtain parameters to calculate burn
self.departure_altitude = get_telemetry("altitude")
self.orbital_period = get_telemetry("period")
self.departure_body_orbital_period = get_telemetry("body_period", body_number=config.TELEMACHUS_BODY_IDS[
"Kerbin"])
self.grav_param = get_telemetry("body_gravParameter", body_number=config.TELEMACHUS_BODY_IDS[
self.orbiting_body])
current_phase_angle = get_telemetry("body_phaseAngle", body_number=telemachus_target_id)
# calculate the first and second burn Δv parameters
self.delta_v_first_burn, gc.moi_burn_delta_v = hohmann_transfer.delta_v(self.departure_altitude,
self.destination_altitude)
print(gc.moi_burn_delta_v)
# calculate the time to complete the Hohmann transfer
self.time_to_transfer = hohmann_transfer.time_to_transfer(self.departure_altitude, self.destination_altitude,
self.grav_param)
# calculate the correct phase angle for the start of the burn
# note that the burn impulse is calculated as a instantaneous burn, to be correct the burn should be halfway
# complete at this calculated time
self.phase_angle_required = hohmann_transfer.phase_angle(self.departure_altitude, self.destination_altitude,
self.grav_param)
# calculate the current difference in phase angle required and current phase angle
self.phase_angle_difference = current_phase_angle - self.phase_angle_required
# if self.phase_angle_difference < 0:
# self.phase_angle_difference = 180 + abs(self.phase_angle_difference)
# calculate time of ignition (TIG)
self.delta_time_to_burn = self.phase_angle_difference / ((360 / self.orbital_period) -
(360 / self.departure_body_orbital_period))
# if the time of ignition is less than 120 seconds in the future, schedule the burn for next orbit
if self.delta_time_to_burn <= 120:
utils.log("Time of ignition less that 2 minutes in the future, starting burn during next orbit")
self.delta_time_to_burn += get_telemetry("period")
# convert the raw value in seconds to HMS
delta_time = utils.seconds_to_time(self.delta_time_to_burn)
# log the maneuver calculations
utils.log("P15 calculations:")
utils.log("Phase angle required: {}, Δv for burn: {} m/s, time to transfer: {}".format(
round(self.phase_angle_required, 2),
int(self.delta_v_first_burn),
utils.seconds_to_time(self.time_to_transfer)))
utils.log("Current Phase Angle: {}, difference: {}".format(
current_phase_angle,
self.phase_angle_difference))
utils.log("Time to burn: {} hours, {} minutes, {} seconds".format(
int(delta_time["hours"]),
int(delta_time["minutes"]),
delta_time["seconds"]))
# calculate the Δt from now of TIG for both burns
self.time_of_ignition_first_burn = get_telemetry("missionTime") + self.delta_time_to_burn
# create a Burn object for the outbound burn
self.first_burn = Burn(delta_v=self.delta_v_first_burn,
direction="prograde",
time_of_ignition=self.time_of_ignition_first_burn,
calling_program=self)
# load the Burn object into computer
gc.add_burn_to_queue(self.first_burn, execute=False)
# display burn parameters and go to poo
gc.execute_verb(verb="06", noun="95")
gc.go_to_poo()