GMATとTLEデータから衛星の軌跡を描画

1. TLEデータを例えばCelesTrakから検索する。

たとえばSentinel-2を検索してみる

Sentinel-2BのTLE

SENTINEL-2B             
1 42063U 17013A   23073.15860935  .00000480  00000+0  19989-3 0  9999
2 42063  98.5691 149.0377 0001133 115.2065 244.9253 14.30818853314338

2. TLE2Keplerianをインストール

github.com
TLE2Keplerianをパスの通った適当な場所に置く(自分は/usr/local/binに置いた )

3. TLE2Keplerianを起動して上記TLEをコピペする

$ TLE2Keplerian.py

Enter TLE including object title:
SENTINEL-2B
1 42063U 17013A   23073.15860935  .00000480  00000+0  19989-3 0  9999
2 42063  98.5691 149.0377 0001133 115.2065 244.9253 14.30818853314338
Year: 2023
Day: 73.15860935
Inclination: 98.5691
RAAN: 149.0377
Eccentricity: 0.0001133
AoP: 115.2065
Mean Anomaly: 244.9253
Ecc. Anomaly: 244.91942046580596
True Anomaly: -115.08645892718607
MM: 14.30818853314338
Semi Major Axis: 7167.132035930462
Epoch: 14 Mar 2023 03:48:23.847

Create Spacecraft SENTINEL_2B;
GMAT SENTINEL_2B.Id = '42063';
GMAT SENTINEL_2B.DateFormat = UTCGregorian;
GMAT SENTINEL_2B.Epoch = '14 Mar 2023 03:48:23.847';
GMAT SENTINEL_2B.CoordinateSystem = EarthMJ2000Eq;
GMAT SENTINEL_2B.DisplayStateType = Keplerian;
GMAT SENTINEL_2B.SMA = 7167.132035930462;
GMAT SENTINEL_2B.ECC = 0.0001133;
GMAT SENTINEL_2B.INC = 98.5691;
GMAT SENTINEL_2B.RAAN = 149.0377;
GMAT SENTINEL_2B.AOP = 115.2065;
GMAT SENTINEL_2B.TA = -115.08645892718607;

Create Spacecraft DefaultSC;
GMAT DefaultSC.Id = '42063';
GMAT DefaultSC.DateFormat = UTCGregorian;
GMAT DefaultSC.Epoch = '14 Mar 2023 03:48:23.847';
GMAT DefaultSC.CoordinateSystem = EarthMJ2000Eq;
GMAT DefaultSC.DisplayStateType = Keplerian;
GMAT DefaultSC.SMA = 7167.132035930462;
GMAT DefaultSC.ECC = 0.0001133;
GMAT DefaultSC.INC = 98.5691;
GMAT DefaultSC.RAAN = 149.0377;
GMAT DefaultSC.AOP = 115.2065;
GMAT DefaultSC.TA = -115.08645892718607;

DefaultSCの箇所（以下）をコピーする

Create Spacecraft DefaultSC;
GMAT DefaultSC.Id = '42063';
GMAT DefaultSC.DateFormat = UTCGregorian;
GMAT DefaultSC.Epoch = '14 Mar 2023 03:48:23.847';
GMAT DefaultSC.CoordinateSystem = EarthMJ2000Eq;
GMAT DefaultSC.DisplayStateType = Keplerian;
GMAT DefaultSC.SMA = 7167.132035930462;
GMAT DefaultSC.ECC = 0.0001133;
GMAT DefaultSC.INC = 98.5691;
GMAT DefaultSC.RAAN = 149.0377;
GMAT DefaultSC.AOP = 115.2065;
GMAT DefaultSC.TA = -115.08645892718607;