def add_simulations(self, num):
with orhelper.OpenRocketInstance() as instance:
# Load the document and get simulation
orh = orhelper.Helper(instance)
doc = orh.load_doc(os.path.join('examples', 'simple.ork'))
sim = doc.getSimulation(0)
# Randomize various parameters
opts = sim.getOptions()
rocket = opts.getRocket()
# Run num simulations and add to self
for p in range(num):
print('Running simulation ', p)
opts.setLaunchRodAngle(math.radians(gauss(
45, 5))) # 45 +- 5 deg in direction
opts.setLaunchRodDirection(math.radians(gauss(
0, 5))) # 0 +- 5 deg in direction
opts.setWindSpeedAverage(gauss(15, 5)) # 15 +- 5 m/s in wind
for component_name in (
'Nose cone',
'Body tube'): # 5% in the mass of various components
component = orh.get_component_named(rocket, component_name)
mass = component.getMass()
component.setMassOverridden(True)
component.setOverrideMass(mass * gauss(1.0, 0.05))
airstarter = AirStart(gauss(
1000, 50)) # simulation listener to drop from 1000 m +- 50
lp = LandingPoint(self.ranges, self.bearings)
orh.run_simulation(sim, listeners=(airstarter, lp))
self.append(lp)
def add_simulations(self, num):
with orhelper.OpenRocketInstance('../lib/build/jar/OpenRocket.jar', log_level='ERROR'):
# Load the document and get simulation
orh = orhelper.Helper()
doc = orh.load_doc(self.args.rocket)
parachute_setting = doc.getRocket().getParachute().getDeployEvent().toString()
parachuteFlag = False
# Run num simulations and add to self
print("Running {} sims".format(num))
for p in range(num):
print ('Running simulation ', p+1)
sim = doc.getSimulation(0)
# Randomize various parameters
opts = sim.getOptions()
rocket = opts.getRocket()
if (p == (num - self.args.parachute)):
doc.getRocket().getParachute().setDeployEventCustom("never")
parachuteFlag = True
# Set latitude and longitude
sim.getOptions().setLaunchLatitude(self.args.startLat)
sim.getOptions().setLaunchLongitude(self.args.startLong)
sim.getOptions().setLaunchRodAngle(math.pi/3)
opts.setLaunchRodAngle(math.radians( gauss(self.args.rodAngle, self.args.rodAngleSigma) ))
opts.setLaunchRodDirection(math.radians( gauss(self.args.rodDirection, self.args.rodDirectionSigma) ))
opts.setWindSpeedAverage( gauss(self.args.windSpeed, self.args.windSpeedSigma) )
for component_name in ('Nose cone', 'Body tube'):
component = orh.get_component_named( rocket, component_name )
mass = component.getMass()
component.setMassOverridden(True)
component.setOverrideMass( mass * gauss(1.0, 0.05) )
# Call computation listeners
ma = MaxAltitude()
lp = LandingPoint()
pu = PositionUpwind()
pp = PositionParallel()
lm = LateralMovement()
wd = WindListener(self.args.windDirection, self.args.windSpeed)
mp = MotorPerformance(self.args.motorPerformance)
rf = FinListener(self.args.pValue, self.args.iValue)
orh.run_simulation(sim, [lp, ma, pu, pp, lm,wd,mp, rf])
self.landing_points.append( lp )
self.max_altitudes.append( ma )
self.upwind.append( pu )
self.parallel.append ( pp )
self.lateral_movement.append( lm )
self.parachute_fail.append (parachuteFlag)
def run_sims(settings):
log_file = "logs/" + settings['id'] + ".cass"
points_done = -1
if not os.path.isfile(log_file):
with open(log_file,'w') as sim_file:
sim_file.write('MIT Rocket Team Cassandra v0.1 Analysis' + os.linesep)
sim_file.write('Date: ' + datetime.now().strftime("%Y-%m-%d %H:%M") + os.linesep)
sim_file.write('Params: ' + json.dumps(settings) + os.linesep + os.linesep)
else:
get_points(settings['id'],settings['points'])
points_done = len(settings['points'])
print("Current directory: " + str(os.getcwd()))
with orhelper.OpenRocketInstance('/app/req/OpenRocket.jar', log_level='DEBUG'):
# Load the document and get simulation
orh = orhelper.Helper()
doc = orh.load_doc('/app/rockets/'+settings['filename'])
sim = doc.getSimulation(0)
opts = sim.getOptions()
rocket = opts.getRocket()
for p in range(points_done,settings['iters']):
print('Running simulation ', p+1)
wind_dir = get_prop(settings['gauss'],'Wind direction')
opts.setLaunchRodAngle(math.radians(get_prop(settings['gauss'],'Rod angle',angle=True)))
opts.setLaunchRodDirection(math.radians(get_prop(settings['gauss'],'Rod direction',angle=True)-wind_dir))
opts.setWindSpeedAverage(get_prop(settings['gauss'],'Wind speed'))
opts.setLaunchTemperature(273.15+get_prop(settings['gauss'],'Launch temperature'))
opts.setLaunchPressure(get_prop(settings['gauss'],'Launch pressure'))
opts.setLaunchRodLength(get_prop(settings['gauss'],'Rod length'))
orh.run_simulation(sim)
data = orh.get_timeseries(sim,DEFAULT_STATS+settings['params'])
events = orh.get_events(sim)
for key in data:
if key == "Lateral direction":
data[key] += math.radians(wind_dir)
data[key] = data[key].tolist()
datapoint = {'data':data,'events':events}
with open(log_file,'a') as sim_file:
json.dump(datapoint, sim_file)
sim_file.write(os.linesep)
def solve_nonlinear(self, params, unknowns, resids):
# Instantiate OpenRocket if it has not been already
if self.openRocket == None:
dir = path.dirname(path.realpath(__file__))
jarpath = dir.replace("scripts", "openmeta-OpenRocket.jar")
self.openRocket = orhelper.OpenRocketInstance(jarpath)
# opens Open Rocket
orh = orhelper.Helper()
# Load document
doc = orh.load_doc('rocket.ork')
# Run OpenRocket simulation (first sim has a faulty motor)
sim = doc.getSimulation(1)
simOptions = sim.getOptions(
) # get handle for simulation options class
simOptions.setRandomSeed(0) # get rid of randomization
simOptions.setWindSpeedAverage(params['WindSpeed']) # set wind speed
orh.run_simulation(sim)
flightData = sim.getSimulatedData()
data = orh.get_timeseries(sim, [
'Time', 'Altitude', 'Stability margin calibers', 'Mass', 'Thrust'
])
events = orh.get_events(sim)
self.plot(data, events)
# derive stability and mass info
try:
launchRodCleared = events['Launch rod clearance']
index_launchRodCleared = np.where(data['Time'] == launchRodCleared)
stability_launchRodCleared = data['Stability margin calibers'][
index_launchRodCleared]
mass_launchRodCleared = data['Mass'][index_launchRodCleared]
except:
# sometimes the simulation shuts down before launch rod clearance, so set values to -1 (error)
stability_launchRodCleared = -1
mass_launchRodCleared = -1
try:
motorBurnout = events['Motor burnout']
index_motorBurnout = np.where(data['Time'] == motorBurnout)
stability_motorBurnout = data['Stability margin calibers'][
index_motorBurnout]
mass_motorBurnout = data['Mass'][index_motorBurnout]
except:
# sometimes the simulation shuts down before the motors burnout, so set burnout mass to -1 (error)
mass_motorBurnout = -1
try:
index_maxStability = np.nanargmax(
data['Stability margin calibers'])
maxStability = data['Stability margin calibers'][
index_maxStability]
except:
# sometimes the simulation doesn't record stability, so set burnout mass to -1
maxStability = -1
# export flight data
unknowns['MaxVelocity'] = flightData.getMaxVelocity()
unknowns['MaxAltitude'] = flightData.getMaxAltitude()
unknowns['MaxAcceleration'] = flightData.getMaxAcceleration()
unknowns['MaxMach'] = flightData.getMaxMachNumber()
unknowns['GroundHitVelocity'] = flightData.getGroundHitVelocity()
unknowns['LaunchRodVelocity'] = flightData.getLaunchRodVelocity()
unknowns['FlightTime'] = flightData.getFlightTime()
unknowns['MaxStability'] = maxStability
unknowns['LaunchRodClearanceStability'] = stability_launchRodCleared
unknowns['LaunchRodClearanceMass'] = mass_launchRodCleared
unknowns['BurnoutMass'] = mass_motorBurnout
import numpy as np
from matplotlib import pyplot as plt
import orhelper
with orhelper.OpenRocketInstance():
orh = orhelper.Helper()
# Load document, run simulation and get data and events
doc = orh.load_doc('estes_gnome.ork')
sim = doc.getSimulation(0)
orh.run_simulation(sim)
data = orh.get_timeseries(sim, ['Time', 'Altitude', 'Vertical velocity'])
events = orh.get_events(sim)
# Make a custom plot the simulation
events_to_annotate = ['Motor burnout', 'Apogee', 'Launch rod clearance']
fig = plt.figure()
ax1 = fig.add_subplot(111)
ax2 = ax1.twinx()
ax1.plot(data['Time'], data['Altitude'], 'b-')
ax2.plot(data['Time'], data['Vertical velocity'], 'r-')
ax1.set_xlabel('Time (s)')
ax1.set_ylabel('Altitude (m)', color='b')
ax2.set_ylabel('Vertical Velocity (m/s)', color='r')
change_color = lambda ax, col: [
x.set_color(col) for x in ax.get_yticklabels()
]
import os
import numpy as np
from matplotlib import pyplot as plt
import orhelper
from orhelper import FlightDataType, FlightEvent
with orhelper.OpenRocketInstance() as instance:
orh = orhelper.Helper(instance)
# Load document, run simulation and get data and events
doc = orh.load_doc(os.path.join('examples', 'simple.ork'))
sim = doc.getSimulation(0)
orh.run_simulation(sim)
data = orh.get_timeseries(sim, [
FlightDataType.TYPE_TIME, FlightDataType.TYPE_ALTITUDE,
FlightDataType.TYPE_VELOCITY_Z
])
events = orh.get_events(sim)
# Make a custom plot of the simulation
events_to_annotate = {
FlightEvent.BURNOUT: 'Motor burnout',
FlightEvent.APOGEE: 'Apogee',
FlightEvent.LAUNCHROD: 'Launch rod clearance'
}
fig = plt.figure()