Merge branch 'develop' into docs/star-2023-flight-sim

.vscode/settings.json

@@ -245,6 +245,7 @@
         "pytest",
         "pytz",
         "quantile",
+        "Radau",
         "Rdot",
         "referece",
         "relativetoground",

CHANGELOG.md

@@ -32,7 +32,11 @@ Attention: The newest changes should be on top -->
 
 ### Added
 
-- DOC: Lince Flight Example [#734](https://github.com/RocketPy-Team/RocketPy/pull/734)
+- DOC: Lince Flight Example [#752](https://github.com/RocketPy-Team/RocketPy/pull/752)
+- ENH: create a dataset of pre-registered motors. See #664 [#744](https://github.com/RocketPy-Team/RocketPy/pull/744)
+- DOC: add Defiance flight example [#742](https://github.com/RocketPy-Team/RocketPy/pull/742)
+- ENH: Allow for Alternative and Custom ODE Solvers. [#748](https://github.com/RocketPy-Team/RocketPy/pull/748)
+
 
 ### Changed
 
@@ -44,6 +48,7 @@ Attention: The newest changes should be on top -->
 
 ## [v1.7.1] - 2024-12-07
 
+
 ### Changed
 
 - REL: update version to 1.7.1 in configuration files [#750](https://github.com/RocketPy-Team/RocketPy/pull/750)

data/motors/aerotech/AeroTech_HP-L1000W.eng

@@ -0,0 +1,26 @@
+; per AT announcement 5/8/14
+L1000 54 635 18 1.4000000000000001 2.194 AT
+   0.004 10.664
+   0.011 1268.961
+   0.04 1322.279
+   0.195 1226.307
+   0.249 1268.961
+   0.296 1242.303
+   0.372 1252.966
+   0.416 1215.644
+   0.6 1226.307
+   0.788 1215.644
+   1.066 1183.653
+   1.261 1167.658
+   1.507 1125.004
+   1.746 1087.681
+   1.865 1050.359
+   1.995 1045.027
+   2.093 911.733
+   2.158 746.448
+   2.263 554.504
+   2.389 405.215
+   2.577 191.944
+   2.693 85.308
+   2.761 42.654
+   3.0 0.0

data/motors/aerotech/AeroTech_K1000T.eng

@@ -0,0 +1,36 @@
+; Based on AT Instruction Sheet by C. Kobel  3/17/2010
+K1000T-P 75 396 P 1.182 2.575 AT
+   0.0040 895.149
+   0.015 1119.762
+   0.025 1093.337
+   0.095 1096.640
+   0.200 1109.853
+   0.300 1116.459
+   0.400 1123.065
+   0.500 1132.975
+   0.600 1139.581
+   0.700 1136.278
+   0.800 1136.278
+   0.900 1136.278
+   1.000 1139.581
+   1.100 1132.975
+   1.200 1129.672
+   1.300 1126.369
+   1.400 1119.762
+   1.500 1109.853
+   1.600 1096.640
+   1.700 1063.609
+   1.800 1017.365
+   1.900 971.121
+   2.000 914.968
+   2.100 868.724
+   2.180 865.421
+   2.200 878.634
+   2.218 858.815
+   2.269 670.536
+   2.300 578.048
+   2.332 445.923
+   2.356 336.920
+   2.389 224.613
+   2.436 105.7
+   2.500 0.0

data/motors/aerotech/AeroTech_K400C.eng

@@ -0,0 +1,25 @@
+; Aerotech K400C DMS
+K400C 54 359 14 0.493 1.194 AT
+   0.008 376.374
+   0.025 526.181
+   0.034 548.466
+   0.063 500.182
+   0.178 527.419
+   0.394 522.467
+   0.69 502.658
+   1.003 487.801
+   1.494 446.944
+   2.002 402.374
+   2.243 377.612
+   2.501 363.994
+   2.658 354.089
+   2.772 337.994
+   2.844 304.566
+   2.882 268.662
+   2.929 177.044
+   2.963 116.379
+   3.001 99.046
+   3.064 94.094
+   3.123 61.904
+   3.208 18.571
+   3.259 0.0

data/motors/aerotech/AeroTech_K480W.eng

@@ -0,0 +1,44 @@
+; From AT Instruction Sheet by C. Kobel 3/12/10
+K480W-P 54 568 P 1.232 2.059 AT
+   0.030 535.684
+   0.045 860.341
+   0.057 915.996
+   0.098 830.194
+   0.159 832.513
+   0.246 795.409
+   0.307 811.642
+   0.398 793.090
+   0.492 809.323
+   0.557 823.237
+   0.621 811.642
+   0.689 779.176
+   0.735 795.409
+   0.845 767.581
+   0.989 718.883
+   1.091 707.288
+   1.250 684.098
+   1.307 667.865
+   1.500 653.952
+   1.606 656.271
+   1.742 651.633
+   1.909 628.443
+   2.000 605.253
+   2.250 586.701
+   2.500 565.830
+   2.750 547.279
+   2.886 544.960
+   3.000 524.089
+   3.064 491.623
+   3.144 417.416
+   3.250 394.226
+   3.292 338.571
+   3.451 271.320
+   3.500 231.898
+   3.625 178.561
+   3.700 143.777
+   3.871 132.182
+   4.000 88.121
+   4.133 41.742
+   4.246 23.190
+   4.500 18.552
+   4.800 0.0

data/motors/aerotech/AeroTech_K990DM.eng

@@ -0,0 +1,34 @@
+; Aerotech K990DM 54/2800
+K990DM 54 598 14 1.224 2.109 AT
+   0.016 35.558
+   0.024 223.805
+   0.028 868.03
+   0.036 1068.828
+   0.044 895.222
+   0.048 863.847
+   0.06 840.839
+   0.228 966.337
+   0.286 953.788
+   0.369 964.246
+   0.407 993.529
+   0.423 976.796
+   0.498 989.345
+   0.694 1024.903
+   0.865 1043.728
+   0.962 1054.186
+   1.117 1054.186
+   1.282 1029.087
+   1.51 983.071
+   1.589 960.063
+   1.688 953.788
+   1.732 968.429
+   1.748 1001.895
+   1.778 957.971
+   1.802 891.038
+   1.857 671.416
+   1.913 447.611
+   1.97 223.805
+   2.006 129.682
+   2.063 46.016
+   2.097 14.641
+   2.137 0.0

data/motors/aerotech/AeroTech_L1040DM.eng

@@ -0,0 +1,29 @@
+; L1040 Dark Matter
+L1040DM-P 75 681 P 2.602 4.7170000000000005 AT
+   0.018 1126.167
+   0.042 1036.413
+   0.053 1002.543
+   0.116 988.995
+   0.504 1049.961
+   0.794 1095.685
+   1.002 1146.489
+   1.252 1192.213
+   1.499 1237.937
+   1.753 1261.646
+   1.912 1268.42
+   2.095 1254.872
+   2.511 1134.635
+   2.772 1056.734
+   3.012 966.98
+   3.153 933.11
+   3.217 863.677
+   3.291 817.953
+   3.34 758.681
+   3.488 438.613
+   3.552 284.505
+   3.598 220.153
+   3.657 167.655
+   3.746 118.544
+   3.88 42.337
+   3.996 6.774
+   4.127 0.0

data/motors/aerotech/AeroTech_L1940X.eng

@@ -0,0 +1,22 @@
+; from TMT document and posted thrust curve
+L1940X 75 560.4 P 1.8234317999999998 3.855515 AT
+   0.02 48.137
+   0.04 2107.333
+   0.055 2289.184
+   0.073 2150.122
+   0.156 2101.985
+   0.397 2150.122
+   0.691 2155.47
+   0.982 2118.03
+   1.41 2000.362
+   1.696 1898.739
+   1.935 1839.905
+   2.06 1818.511
+   2.103 1652.705
+   2.116 1374.58
+   2.133 935.998
+   2.163 534.856
+   2.214 240.685
+   2.244 112.32
+   2.296 5.349
+   2.309 0.0

data/motors/aerotech/AeroTech_L2200G.eng

@@ -0,0 +1,39 @@
+; Curvefit of Aerotech Instructions by C. Kobel  11/19/08
+L2200G 75 665 0-6-10-14-18 2.516 4.751 AT
+   0.011 1195.177
+   0.024 2029.903
+   0.037 2380.868
+   0.050 2542.122
+   0.100 2570.578
+   0.150 2561.093
+   0.200 2523.151
+   0.250 2485.208
+   0.300 2523.151
+   0.350 2570.578
+   0.400 2674.919
+   0.500 2912.057
+   0.600 3073.311
+   0.700 3073.311
+   0.800 3101.768
+   0.900 3092.282
+   1.000 3092.282
+   1.100 2959.485
+   1.186 2807.716
+   1.227 2437.781
+   1.270 2257.556
+   1.300 2162.701
+   1.400 1991.961
+   1.500 1878.135
+   1.600 1792.765
+   1.700 1688.424
+   1.800 1612.54
+   1.900 1584.083
+   2.000 1536.656
+   2.048 1498.714
+   2.084 1403.858
+   2.102 1166.72
+   2.134 796.784
+   2.186 455.305
+   2.237 237.138
+   2.300 94.855
+   2.400 0.0