ORBITAL_MANEUVER_CANCELED¶
event_output for ORBITAL_MANEUVER_CANCELED.
Format¶
<time> ORBITAL_MANEUVER_CANCELED <platform> ID: <unique id>
Type: <maneuver type> Constraint: <maneuver constraint> Duration: <time>
Orbital Elements: SMA: <length> ECC: <angle> INC: <angle> RAAN: <angle> ARGP: <angle> MA: <angle> TA: <angle> { (Circular) | (Equatorial) | (Circular, Equatorial) }
Delta-V: <speed>
Breakdown¶
- <time>
The current simulation time
- <platform>
The name of the platform initiating the maneuver.
- ID: <unique id>
The unique identifier for this maneuver.
- Type: <maneuver type>
The maneuver type being executed.
- Constraint: <maneuver constraint>
The constraint condition on the maneuver.
- Duration <time>
The maneuver duration. If the maneuver is impulsive, this value will be zero.
- Orbital Elements: The orbital elements at completion of the maneuver.
- SMA: <length>
Semi-major axis (km)
- ECC: <double>
Eccentricity
- INC: <angle>
Inclination (degrees)
- RAAN: <angle>
Right ascension of the ascending node (degrees)
- ARGP: <angle>
Argument of periapsis (degrees)
- MA: <angle>
Mean anomaly (degrees)
- TA: <angle>
True anomaly (degrees)
- { (Circular) | (Equatorial) | (Circular, Equatorial) }
Whether the orbit is circular (eccentricity = 0), equatorial (inclination = 0), or both. If neither, nothing is output.
- Delta-V <speed>
The cumulative delta-V expended by this maneuver.
How it Appears in Output¶
109.00000 ORBITAL_MANEUVER_CANCELED proton-m ID: 8 \
Type: CHANGE_SEMI_MAJOR_AXIS Constraint: AT_RELATIVE_TIME 100 s Duration: 0 s \
Orbital Elements: SMA: 39628.31548 km ECC: 0.06399014304 INC: 1.707547293e-06 deg RAAN: 169.5628846 deg ARGP: 0.4267192466 deg MA: 180.0288817 deg TA: 180.0254599 deg (Equatorial) \
Delta-V: 100 m/s
How to Show Event Messages¶
event_output file replay.evt # write event messages to file "replay.evt" enable ORBITAL_MANEUVER_CANCELED end_event_output
