Commit 88e08e2a authored by Bryan Cazabonne's avatar Bryan Cazabonne
Browse files

Merge branch 'issue-838' into release-11.0

parents 6427ccba 65a09196
......@@ -45,12 +45,19 @@ import org.orekit.utils.PVCoordinates;
* can also be a more elaborate {@link
* org.orekit.propagation.events.ApsideDetector apside event} for apogee
* maneuvers for example.</p>
* <p>The maneuver is defined by a single velocity increment in satellite
* frame. The current attitude of the spacecraft, defined by the current
* spacecraft state, will be used to compute the velocity direction in
* inertial frame. A typical case for tangential maneuvers is to use a
* {@link org.orekit.attitudes.LofOffset LOF aligned} attitude provider for state propagation and a
* velocity increment along the +X satellite axis.</p>
* <p>The maneuver is defined by a single velocity increment.
* If no AttitudeProvider is given, the current attitude of the spacecraft,
* defined by the current spacecraft state, will be used as the
* {@link AttitudeProvider} so the velocity increment should be given in
* the same pseudoinertial frame as the {@link SpacecraftState} used to
* construct the propagator that will handle the maneuver.
* If an AttitudeProvider is given, the velocity increment given should be
* defined appropriately in consideration of that provider. So, a typical
* case for tangential maneuvers is to provide a {@link org.orekit.attitudes.LofOffset LOF aligned}
* attitude provider along with a velocity increment defined in accordance with
* that LOF aligned attitude provider; e.g. if the LOF aligned attitude provider
* was constructed using LOFType.VNC the velocity increment should be
* provided in VNC coordinates.</p>
* <p>Beware that the triggering event detector must behave properly both
* before and after maneuver. If for example a node detector is used to trigger
* an inclination maneuver and the maneuver change the orbit to an equatorial one,
......
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