Lunar Case 6A: Highly Elliptical Orbit – Cylinder, zero inertial rotation
Scenario 6A tests Keplerian propagation in a low-fidelity 8x8 GRAIL gravity field with Sun and Earth perturbations.
Constants and models
The gravitational constant is defined from the GRAIL model specified in the table below. The ephemerides are: DE440. Time is expressed in UTC. Although test case initial conditions may be in the future, the following constants are used: TAI − UTC = 37 sec; DUT1 = 0.0 sec Low-Fidelity GRAIL uses the GRAIL gravity model of degree and order 8 (i.e. 8x8 GRAIL).
Initial Conditions
| Scenario | Lunar Case 6A: Highly Elliptical Orbit – Cylinder, zero inertial rotation | |||
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| Body | Cylinder | |||
| Orientation | Body frame aligned with VO frame quaternionWrtVo_W/X/Y/Z should be [1,0,0,0] respectively |
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| Rotation | bodyAngularRateWrtMi: [0, 0, 0] deg/s (angular rotation rate of the body frame WRT MI presented in the body frame) |
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| Gravitation | Low-Fidelity GRAIL | Gravity Gradient Effects | Off | |
| Sun/Earth Perturbations | On | Duration | 100,800 s | |
| Output Interval | 60 s | Output Format | CSV | |
| Initial states | ||||
| Time | 2026-1-28 6:42:03.51 UTC corresponds to output j2000UtcTime_s J2000 epoch of January 1.5, 2000 = -2451545.0 days Using 37 leap seconds j2000TtTime_s = j2000UtcTime + 32.184 + 37 = j2000UtcTime + 69.184 (s) Note that delta UT1/UTC is not relevant for checkcase and is thus not specified |
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| Frame | Planet-Centered Inertial | |||
| Position (m) |
miPosition_m_X miPosition_m_Y miPosition_m_Z |
1830456.52713665 -711552.315099665 -304763.785806531 |
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| Velocity (m/s) |
miVelocity_m_s_X miVelocity_m_s_Y miVelocity_m_s_Z |
457.748608640399 335.646153516028 1965.6506408711 |
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Latest Results
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| Sim | Raw Data Link |
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Interactive Plots
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Note: pp_euler variables are Euler angles automatically calculated from sim provided quaternions.
A link to the conversion used can be accessed from the References menu in the navigation bar.
Note: All quaternions are modified to be scalar positive.
Load Data
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