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Diffstat (limited to 'main2.py')
| -rw-r--r-- | main2.py | 353 |
1 files changed, 0 insertions, 353 deletions
diff --git a/main2.py b/main2.py deleted file mode 100644 index 7776d9e..0000000 --- a/main2.py +++ /dev/null @@ -1,353 +0,0 @@ -# import modules -import bpy -import matplotlib.pyplot as plt -import urllib -import math -import numpy as np -from timeit import default_timer as timer - -class TLE: - def get(value, category, satNr): - with open('TLE/' + category + '.txt') as data: - content = data.readlines() - - if value == "name": - return content[(satNr)*3][0:15] - elif value == "LineNumber": - return content[((satNr)*3)+1][0:1] - elif value == "Classification": - return content[((satNr)*3)+1][7:8] - elif value == "LaunchYear": - return content[((satNr)*3)+1][9:11] - elif value == "LaunchNumber": - return content[((satNr)*3)+1][11:14] - elif value == "LaunchPiece": - return content[((satNr)*3)+1][14:17] - elif value == "EpochYear": - return content[((satNr)*3)+1][18:20] - elif value == "EpochDayFraction": - return content[((satNr)*3)+1][20:32] - elif value == "EpochDay": - return content[((satNr)*3)+1][20:23] - elif value == "EpochTime": - return content[((satNr)*3)+1][24:32] - elif value == "FirstTimeDerivative": - return content[((satNr)*3)+1][33:43] - elif value == "SecondTimeDerivative": - return content[((satNr)*3)+1][44:52] - elif value == "BSTARDragTerm": - return content[((satNr)*3)+1][53:61] - elif value == "Num0": - return content[((satNr)*3)+1][62:63] - elif value == "ElementSetNumber": - return content[((satNr)*3)+1][64:68] - elif value == "Checksum1": - return content[((satNr)*3)+1][68:69] - - elif value == "LineNumber2": - return content[((satNr)*3)+2][0:1] - elif value == "Number2": - return content[((satNr)*3)+2][2:7] - elif value == "Inclination": - return content[((satNr)*3)+2][8:16] - elif value == "RAAN": - return content[((satNr)*3)+2][17:25] - elif value == "Eccentricity": - return content[((satNr)*3)+2][26:33] - elif value == "ArgumentOfPerigee": - return content[((satNr)*3)+2][34:42] - elif value == "MeanAnomaly": - return content[((satNr)*3)+2][43:51] - elif value == "MeanMotion": - return content[((satNr)*3)+2][52:63] - elif value == "Revloution": - return content[((satNr)*3)+2][63:68] - elif value == "Checksum2": - return content[((satNr)*3)+2][68:69] - - # downlaod specific categeory - def download(category): - webx_loc = 'http://celestrak.com/NORAD/elements/' + category + '.txt' - disk_loc = 'TLE/' + category + '.txt' - urllib.request.urlretrieve(webx_loc, disk_loc) - - # get number of satellites in specific ategory - def numOfSat(category): - with open('TLE/' + category + '.txt') as data: - content = data.readlines() - return int(len(content) / 3) - - # print specified category - def printTLE(category, satNr): - with open('TLE/' + category + '.txt') as data: - content = data.readlines() - print(content[((satNr)*3)+1], end="") - print(content[((satNr)*3)+2], end="") - -start = timer() - -# controll values -category = "iridium" -globalScale = 1 -satSize = 0.5 -orbitSubDivs = 256 -resolution = 100 # get position of sat each x frames -threshold = 0.001 - -# if internet connection available: -TLE.download(category) - -# define -sce = bpy.context.scene -n = TLE.numOfSat(category) -numOfSat = TLE.numOfSat(category) -rotate = bpy.ops.transform.rotate - -# static -earthRadius = 6371 -daylengthsec = 86400 - -# create list -xyz = list( [[], [], []] for _ in range(0, numOfSat) ) - -# select all -> delete -bpy.ops.object.select_all(action='SELECT') -bpy.ops.object.delete(use_global=False) - -# cycle through every satellite in one category -for i in range(0, numOfSat): - - # define - satNr = i - name = TLE.get("name", category, satNr).rstrip("\n") - - # get inclination and convert - inc_deg = float(TLE.get("Inclination", category, satNr)) - inc_rad = inc_deg / 180 * math.pi - - # get RAAN and convert - RAAN_deg = float(TLE.get("RAAN", category, satNr)) - RAAN_rad = RAAN_deg * math.pi / 180 - - # get AoP and convert - AoP_deg = float(TLE.get("ArgumentOfPerigee", category, satNr)) - AoP_rad = AoP_deg * math.pi / 180 - - # get Mean Motion - n0 = float(TLE.get("MeanMotion", category, satNr)) - - # define duration (time for one rotation around earth) - duration = int(daylengthsec / n0) - - # calculate apogee / perigee - semimajoraxis = ((6.6228 / pow(n0, 2/3)) * earthRadius) - orbitheight = semimajoraxis - earthRadius - - # calculate Eccentricity and convert ("decimal point assumed") - e0_a = str(TLE.get("Eccentricity", category, satNr)) - e0 = float("0." + e0_a) - - # define apogee and perigee - apogee = abs(semimajoraxis * (1 + e0) - earthRadius) - perigee = abs(semimajoraxis * (1 - e0) - earthRadius) - - # print values to user - - print("") - - print("{:<10}{:<80}".format("name:", name)) - print("{:<4}/{:<4}".format(i, numOfSat)) - - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "", "|", "deg", "|", "rad")) - - print("{:+<1}{:-<5}{:+<1}{:-<40}{:+<1}{:-<40}".format("+", "-", "+", "-", "+", "-")) - - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "inc", "|", str(inc_deg), "|", str(inc_rad))) - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "RAAN", "|", str(RAAN_deg), "|", str(RAAN_rad))) - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "AoP", "|", str(AoP_deg), "|", str(AoP_rad))) - - print("{:+<1}{:-<5}{:+<1}{:-<40}{:+<1}{:-<40}".format("+", "-", "+", "-", "+", "-")) - print("") - print("{:+<1}{:-<5}{:+<1}{:-<40}{:+<1}{:-<40}".format("+", "-", "+", "-", "+", "-")) - - - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "smi", "|", str(semimajoraxis), "|", "")) - - print("{:+<1}{:-<5}{:+<1}{:-<40}{:+<1}{:-<40}".format("+", "-", "+", "-", "+", "-")) - - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "Apo", "|", str(apogee), "|", "")) - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "Per", "|", str(perigee), "|", "")) - print("{:<1}{:<5}{:<1}{:<40}{:<1}{:<40}".format("|", "e0", "|", str(e0), "|", "")) - - print("{:+<1}{:-<5}{:+<1}{:-<40}{:+<1}{:-<40}".format("+", "-", "+", "-", "+", "-")) - - TLE.printTLE(category, satNr) - - print("") - - # blender - # Creating th Satellites in blender - # Add orbit - # Add Satellite to orbit - # Transform orbit - # Get Values - - # define - orbitname = name - satname = name + "sat" - - - # add orbit, rename orbit - bpy.ops.mesh.primitive_circle_add(radius=1, vertices=orbitSubDivs) - bpy.context.object.name = orbitname - - # add sat, rename sat - bpy.ops.mesh.primitive_cube_add(radius=satSize) - bpy.context.object.name = satname - - # define object names - orbit = bpy.context.scene.objects[name] - sat = bpy.context.scene.objects[name + "sat"] - - # convert orbit to curve and attach sat - sat.select = False - orbit.select = True - sce.objects.active = orbit - bpy.ops.object.convert(target='CURVE') - - # set orbit duration - # bpy.data.curves[name].path_duration = duration - - # resize orbit - orbit.scale[0] = apogee - orbit.scale[1] = perigee - - # move sat to perigee - sat.location[1] = perigee - - # make sat follow orbit - sat.select = True - sce.objects.active = orbit - bpy.ops.object.parent_set(type='FOLLOW') - - # set duration for 1 revolution - bpy.data.curves[orbitname].path_duration = duration - - # rotate orbit - orbit.select = True - - rotate(value=RAAN_rad, axis=(0, 0, 1)) - rotate(value=inc_rad, axis=(1, 0, 0)) - rotate(value=AoP_rad, axis=(0, 0, 1)) - - # Getting the position of a satellite: - # 1. jump to specific frame - # 2. clear parent (keep transform) - # 3. get position value and append it to a list - # 4. reset parent - - for t in range(0, duration, resolution): - # jump to frame - sce.frame_set(t) - - # clear parent - bpy.ops.object.parent_clear(type='CLEAR_KEEP_TRANSFORM') - - # append sat location to list xyz - xyz[satNr][0].append(sat.location[0]) - xyz[satNr][1].append(sat.location[1]) - xyz[satNr][2].append(sat.location[2]) - - # reset parent - bpy.ops.object.parent_set(type="FOLLOW") - - -# plot x, y and z values ove every satellite for every moment -for i in range(0, numOfSat, 1): - plt.plot(xyz[i][0], '-ro') - plt.plot(xyz[i][1], '-go') - plt.plot(xyz[i][2], '-bo') - -plt.show() - -# Collision Detect -# https://hanemile.github.io/docs/master.pdf -# p. 8 - 11 - -# create an array filled with 0 -# array[t, y, x] - -dure = int(duration/resolution) -# dure = 5 -array = np.zeros((int(dure), numOfSat + 3, numOfSat + 3)) - -satNr = 1 - -print(dure) - -# for every moment in time -for time in range(0, dure, 1): - x = 0 - y = 0 - - for sat in range(0, numOfSat, 1): - array[time, y+0, sat+3] = xyz[sat][0][time] - array[time, y+1, sat+3] = xyz[sat][1][time] - array[time, y+2, sat+3] = xyz[sat][2][time] - - for sat in range(0, numOfSat, 1): - array[time, sat+3, y+0] = xyz[sat][0][time] - array[time, sat+3, y+1] = xyz[sat][1][time] - array[time, sat+3, y+2] = xyz[sat][2][time] - - # loop through array - - - for y in range(3, (numOfSat + 3), 1): - for x in range(3, (numOfSat + 3), 1): - if x != y: - a_x = array[time, 0, x] - a_y = array[time, 1, x] - a_z = array[time, 2, x] - - b_x = array[time, y, 0] - b_y = array[time, y, 1] - b_z = array[time, y, 2] - - a = pow((abs(a_x)-abs(b_x)), 2) - b = pow((abs(a_y)-abs(b_y)), 2) - c = pow((abs(a_z)-abs(b_z)), 2) - - d = math.sqrt(a + b + c) - array[time, y, x] = d - - # print Warning - if d < threshold: - xname = TLE.get("name", category, x-3) - yname = TLE.get("name", category, y-3) - - a_x = array[time, 0, x] - a_y = array[time, 1, x] - a_z = array[time, 2, x] - - b_x = array[time, y, 0] - b_y = array[time, y, 1] - b_z = array[time, y, 2] - - print("") - print("BUM !!!") - print("{:<20}{:<20}{:<10}{:<20}".format("sat A", "sat B", "time", "distance")) - print("") - print("{:<20}{:<20}{:<10}{:<20}".format(xname, yname, time, d)) - print("{:<30}{:<30}{:<30}".format(a_x, a_y, a_z)) - print("{:<30}{:<30}{:<30}".format(b_x, b_y, b_z)) - -# print horizontal "line" -print("{:#<80}".format("#")) -# print array -print(array) - -end = timer() - -print("") -print("{:<10}{:<10}".format("Total duration (sek.): ", end - start)) |
