User Manual 3.3 Force models - Historique des versions

Admin le 3 avril 2018 à 13:51

2018-04-03T13:51:52Z

← Version précédente		Version du 3 avril 2018 à 13:51
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	=== Drag force ===		=== Drag force ===
	Before implementing the drag force, one has to define a vehicle with aerodynamic properties. To do so, it is advised to consult the page about [~~SPC_FORCES_Home~~ assembly models for force models]. Given an assembly with the right aerodynamic properties, the user can create an instance of [{{JavaDoc3.3}}/fr/cnes/sirius/patrius/assembly/models/AeroModel.html AeroModel] or [{{JavaDoc3.3}}/fr/cnes/sirius/patrius/assembly/models/DragLiftModel.html DragLiftModel], and use it to create an instance of DragForce :		Before implementing the drag force, one has to define a vehicle with aerodynamic properties. To do so, it is advised to consult the page about [[User Manual 3.3 Properties and models: Mass and Forces\|assembly models for force models]]. Given an assembly with the right aerodynamic properties, the user can create an instance of [{{JavaDoc3.3}}/fr/cnes/sirius/patrius/assembly/models/AeroModel.html AeroModel] or [{{JavaDoc3.3}}/fr/cnes/sirius/patrius/assembly/models/DragLiftModel.html DragLiftModel], and use it to create an instance of DragForce :

	<syntaxhighlight lang="java">		<syntaxhighlight lang="java">
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	Please refer to the {{siteLink label="Propagation tutorial" jd="OR" suffix="tutorial/propagation.html"/}} for more information.		Please refer to the {{siteLink label="Propagation tutorial" jd="OR" suffix="tutorial/propagation.html"/}} for more information.

	Nota : The ImpulseManeuver force does not implement the ForceModel interface. It implements the EventDetector and should be handled as such (see code below). For more information about Events, please refer to the [~~MIS_EVT_Home~~ Events section].		Nota : The ImpulseManeuver force does not implement the ForceModel interface. It implements the EventDetector and should be handled as such (see code below). For more information about Events, please refer to the [[User Manual 3.3 Events detection: Presentation\|Events section]].

	<syntaxhighlight lang="java">		<syntaxhighlight lang="java">

Admin : /* Gravity potential */

2018-03-16T10:21:07Z

Gravity potential

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 === Gravity potential ===
-{{specialInclusion prefix=$theme_sub section="Gravity potential"/}}
+==== Static potential models ====
 === Tides ===

Admin : /* Available force models */

2018-03-16T09:42:31Z

Available force models

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	The acceleration derivatives implemented are :		The acceleration derivatives implemented are :

	~~\|=(% colspan="6" %)Force model\|=(% colspan="6" %)wrt Position\|=(% colspan="3" %)wrt Velocity\|=(% colspan="9" %)wrt additional parameters~~
	~~\|=(% colspan="15" %)\|=(% colspan="3" %)Parameter\|=(% colspan="3" %)ParamDiffFunction\|=(% colspan="3" %)Parameter or ParamDiffFunction from a model~~


	{\| class="wikitable"		{\| class="wikitable"

Admin : /* Available force models */

2018-03-16T09:42:17Z

Available force models

Voir les modifications

Admin : /* Solar radiation pressure with ellipsoid occulting body */

2018-03-01T13:46:40Z

Solar radiation pressure with ellipsoid occulting body

← Version précédente		Version du 1 mars 2018 à 13:46
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	===== Solar radiation pressure with ellipsoid occulting body =====		===== Solar radiation pressure with ellipsoid occulting body =====

	Before implementing the solar radiation pressure (that takes into account Earth flattening), one has to define a vehicle with radiative properties. To do so, it is advised to consult the page which describes how to build and use [[User Manual 3.3 Assemblies in PATRIUS: Presentation\|the Assembly]] ([User Manual 3.3 Assemblies in PATRIUS: Building and using an assembly\|see also...]).		Before implementing the solar radiation pressure (that takes into account Earth flattening), one has to define a vehicle with radiative properties. To do so, it is advised to consult the page which describes how to build and use [[User Manual 3.3 Assemblies in PATRIUS: Presentation\|the Assembly]] ([[User Manual 3.3 Assemblies in PATRIUS: Building and using an assembly\|see also...]]).

	The following code snippet allows the user to create an instance of the ForceModel class that can be passed to the NumericalPropagator. This instance will calculate the SRP by computing penumbra and umbra events for a flattened Earth.		The following code snippet allows the user to create an instance of the ForceModel class that can be passed to the NumericalPropagator. This instance will calculate the SRP by computing penumbra and umbra events for a flattened Earth.

Admin : /* Solar radiation pressure */

2018-03-01T13:46:07Z

Solar radiation pressure

← Version précédente		Version du 1 mars 2018 à 13:46
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	=== Solar radiation pressure ===		=== Solar radiation pressure ===
	Before implementing the solar radiation pressure or the rediffused solar radiation pressure, one has to define a vehicle with radiative properties. To do so, it is advised to consult the page about [~~SPC_FORCES_Home~~ forces models using the assembly].		Before implementing the solar radiation pressure or the rediffused solar radiation pressure, one has to define a vehicle with radiative properties. To do so, it is advised to consult the page about [[User Manual 3.3 Properties and models: Mass and Forces\|forces models using the assembly]].

	==== Direct solar radiation pressure ====		==== Direct solar radiation pressure ====
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	===== Solar radiation pressure with ellipsoid occulting body =====		===== Solar radiation pressure with ellipsoid occulting body =====

	Before implementing the solar radiation pressure (that takes into account Earth flattening), one has to define a vehicle with radiative properties. To do so, it is advised to consult the page which describes how to build and use [~~SPC_VEH_Home~~ the Assembly] ([~~SPC_VBU_Home~~ see also...]).		Before implementing the solar radiation pressure (that takes into account Earth flattening), one has to define a vehicle with radiative properties. To do so, it is advised to consult the page which describes how to build and use [[User Manual 3.3 Assemblies in PATRIUS: Presentation\|the Assembly]] ([User Manual 3.3 Assemblies in PATRIUS: Building and using an assembly\|see also...]).

	The following code snippet allows the user to create an instance of the ForceModel class that can be passed to the NumericalPropagator. This instance will calculate the SRP by computing penumbra and umbra events for a flattened Earth.		The following code snippet allows the user to create an instance of the ForceModel class that can be passed to the NumericalPropagator. This instance will calculate the SRP by computing penumbra and umbra events for a flattened Earth.
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	</syntaxhighlight>		</syntaxhighlight>

	It is also possible to compute these forces using assemblies, as seen in the [~~SPC_VEH_Home~~ spacecraft] [~~SPC_VBU_Home~~ chapter].		It is also possible to compute these forces using assemblies, as seen in the [[User Manual 3.3 Assemblies in PATRIUS: Presentation\|spacecraft]] [[User Manual 3.3 Assemblies in PATRIUS: Building and using an assembly\|chapter]].

	=== Relativistic Effects ===		=== Relativistic Effects ===

Admin : Admin a déplacé la page Force models vers User Manual 3.3 Force models sans laisser de redirection

2018-02-28T09:16:19Z

Admin a déplacé la page Force models vers User Manual 3.3 Force models sans laisser de redirection

← Version précédente		Version du 28 février 2018 à 09:16
(Aucune différence)

Admin : /* Partial derivatives with respect to the drag coefficient (Cx) */

2018-02-28T09:15:32Z

Partial derivatives with respect to the drag coefficient (Cx)

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	===== Partial derivatives with respect to the drag coefficient (Cx) =====		===== Partial derivatives with respect to the drag coefficient (Cx) =====

	The partial derivatives of the drag force with respect to the drag coefficient are computed using the exact equations.		The partial derivatives of the drag force with respect to the drag coefficient are computed using the exact equations.<br>
	Note that the ballistic coefficient for a spherical spacecraft is equal to <math>{B}_{c}=\frac{S {C}_{X}}{M}</math>, where <math>S</math> is the cross-sectional area of the sphere, <math>{C}_{X}</math> is the drag coefficient and <math>M</math> is the mass.		Note that the ballistic coefficient for a spherical spacecraft is equal to <math>{B}_{c}=\frac{S {C}_{X}}{M}</math>, where <math>S</math> is the cross-sectional area of the sphere, <math>{C}_{X}</math> is the drag coefficient and <math>M</math> is the mass.


	===== Partial derivatives with respect to k parameters =====		===== Partial derivatives with respect to k parameters =====

Admin : /* Constant thrust error */

2018-02-28T09:14:10Z

Constant thrust error

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	◦ With a start date and a duration (former method)		◦ With a start date and a duration (former method)
	◦ With event detectors, first detector for starting the thrust, second detector for stopping the thrust. Action.STOP is required to trigger (start/stop) the thrust. Any other action will be discarded.		◦ With event detectors, first detector for starting the thrust, second detector for stopping the thrust. Action.STOP is required to trigger (start/stop) the thrust. Any other action will be discarded.<br>
	When using event detectors, pay attention to events that may occur several times. If you want the thrust to perform only once, the event detectors the event detectors have to be included in a nth occurrence detector or its <code>shouldBeRemoved()</code> method have to return <code>true</code>. Otherwise the thrust may be performed more than once: if a thrust starts at the perigee (using a perigee detector) and stops at the apogee (using an apogee detector), then the thrust will start at every perigee and stop at every apogee.		When using event detectors, pay attention to events that may occur several times. If you want the thrust to perform only once, the event detectors the event detectors have to be included in a nth occurrence detector or its <code>shouldBeRemoved()</code> method have to return <code>true</code>. Otherwise the thrust may be performed more than once: if a thrust starts at the perigee (using a perigee detector) and stops at the apogee (using an apogee detector), then the thrust will start at every perigee and stop at every apogee.

Admin : /* Empirical force */

2018-02-28T09:13:36Z

Empirical force

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	The <code>EmpiricalForce</code> class provides a model describing a generic empirical force; an empirical force is a "pseudo acceleration" with the same frequency of the spacecraft orbital frequency (or a multiple of this frequency). One or more instances of this force can be added to a propagator in order to represent a more complex empirical force model.		The <code>EmpiricalForce</code> class provides a model describing a generic empirical force; an empirical force is a "pseudo acceleration" with the same frequency of the spacecraft orbital frequency (or a multiple of this frequency). One or more instances of this force can be added to a propagator in order to represent a more complex empirical force model.

	Given a local frame (usually a LOF frame), and three vectors A, B and C defined in this frame, the acceleration in this local frame due to empirical force is the following:		Given a local frame (usually a LOF frame), and three vectors A, B and C defined in this frame, the acceleration in this local frame due to empirical force is the following:<br>
	<math>\overrightarrow{a}_{local}=\overrightarrow{A}\cos(n\omega t) + \overrightarrow{B}\sin(n\omega t) + \overrightarrow{C}</math>		<math>\overrightarrow{a}_{local}=\overrightarrow{A}\cos(n\omega t) + \overrightarrow{B}\sin(n\omega t) + \overrightarrow{C}</math><br>
	n is the harmonic factor and <math>\omega</math> is the orbital period.		n is the harmonic factor and <math>\omega</math> is the orbital period. <br>
	As <math>\omega</math> is usually unknown, <math>\cos(n\omega t)</math> and <math>\sin(n\omega t)</math> are computed from the orbital position of the spacecraft:		As <math>\omega</math> is usually unknown, <math>\cos(n\omega t)</math> and <math>\sin(n\omega t)</math> are computed from the orbital position of the spacecraft:

User Manual 3.3 Force models - Historique des versions

Admin le 3 avril 2018 à 13:51

Admin : /* Gravity potential */

Admin : /* Available force models */

Admin : /* Available force models */

Admin : /* Solar radiation pressure with ellipsoid occulting body */

Admin : /* Solar radiation pressure */

Admin : Admin a déplacé la page Force models vers User Manual 3.3 Force models sans laisser de redirection

Admin : /* Partial derivatives with respect to the drag coefficient (Cx) */

Admin : /* Constant thrust error */

Admin : /* Empirical force */

Admin : /* Gravity potential */

Admin : /* Available force models */

Admin : /* Available force models */

Admin : /* Solar radiation pressure with ellipsoid occulting body */

Admin : /* Solar radiation pressure */

Admin : Admin a déplacé la page Force models vers User Manual 3.3 Force models sans laisser de redirection

Admin : /* Partial derivatives with respect to the drag coefficient (Cx) */

Admin : /* Constant thrust error */

Admin : /* Empirical force */