Vehicle - Historique des versions

Admin : /* Aerodynamic properties */

2019-09-06T08:47:07Z

Aerodynamic properties

← Version précédente		Version du 6 septembre 2019 à 08:47
Ligne 41 :		Ligne 41 :
	[[Fichier:Aerodynamic.png]]		[[Fichier:Aerodynamic.png]]

	Moreover, if the vehicle shape is a sphere and there are no solar panels, it will possible to give more sophisticated aerodynamic coefficients as used for reentry trajectories, giving coefficients depending on altitude, angle of attack (<font color=#FF8C00 title="Angle Of Attack">AOA</font>), Mach number or <font color=#FF8C00 title="Angle Of Attack">AOA</font> & Mach number. An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[:File:Stela_drag_coefficient.zip\|here]]: you just need to include it in a context file.		Moreover, if the vehicle shape is a sphere and there are no solar panels, it will possible to give more sophisticated aerodynamic coefficients as used for reentry trajectories, giving coefficients depending on altitude, angle of attack (<font color=#FF8C00 title="Angle Of Attack">AOA</font>), Mach number or <font color=#FF8C00 title="Angle Of Attack">AOA</font> & Mach number. An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[:File:Stela_drag_coefficient.zip\|here]] (you just need to include it in a context file).

Admin : /* Aerodynamic properties */

2019-09-06T08:46:31Z

Aerodynamic properties

← Version précédente		Version du 6 septembre 2019 à 08:46
Ligne 41 :		Ligne 41 :
	[[Fichier:Aerodynamic.png]]		[[Fichier:Aerodynamic.png]]

	Moreover, if the vehicle shape is a sphere and there are no solar panels, it will possible to give more sophisticated aerodynamic coefficients as used for reentry trajectories, giving coefficients depending on altitude, angle of attack (<font color=#FF8C00 title="Angle Of Attack">AOA</font>), Mach number or <font color=#FF8C00 title="Angle Of Attack">AOA</font> & Mach number.		Moreover, if the vehicle shape is a sphere and there are no solar panels, it will possible to give more sophisticated aerodynamic coefficients as used for reentry trajectories, giving coefficients depending on altitude, angle of attack (<font color=#FF8C00 title="Angle Of Attack">AOA</font>), Mach number or <font color=#FF8C00 title="Angle Of Attack">AOA</font> & Mach number. An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[:File:Stela_drag_coefficient.zip\|here]]: you just need to include it in a context file.


	[[Fichier:Aerodynamic2.png]]		[[Fichier:Aerodynamic2.png]]

	An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[:File:Stela_drag_coefficient.zip\|here]].

	The aerodynamic forces will be computed as:		The aerodynamic forces will be computed as:

Admin : /* Aerodynamic properties */

2019-09-06T08:45:32Z

Aerodynamic properties

← Version précédente		Version du 6 septembre 2019 à 08:45
Ligne 45 :		Ligne 45 :
	[[Fichier:Aerodynamic2.png]]		[[Fichier:Aerodynamic2.png]]

	An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[File::Stela_drag_coefficient.zip\|here]].		An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[:File:Stela_drag_coefficient.zip\|here]].

	The aerodynamic forces will be computed as:		The aerodynamic forces will be computed as:

Admin : /* Aerodynamic properties */

2019-09-06T08:44:51Z

Aerodynamic properties

← Version précédente		Version du 6 septembre 2019 à 08:44
Ligne 45 :		Ligne 45 :
	[[Fichier:Aerodynamic2.png]]		[[Fichier:Aerodynamic2.png]]

	An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[File:Stela_drag_coefficient.zip\|here]].		An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[File::Stela_drag_coefficient.zip\|here]].

	The aerodynamic forces will be computed as:		The aerodynamic forces will be computed as:

Admin : /* Aerodynamic properties */

2019-09-06T08:44:25Z

Aerodynamic properties

← Version précédente		Version du 6 septembre 2019 à 08:44
Ligne 45 :		Ligne 45 :
	[[Fichier:Aerodynamic2.png]]		[[Fichier:Aerodynamic2.png]]

	An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[File:Stela_drag_coefficient.zip here]].		An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[File:Stela_drag_coefficient.zip\|here]].

	The aerodynamic forces will be computed as:		The aerodynamic forces will be computed as:

Admin : /* Aerodynamic properties */

2019-09-06T08:43:22Z

Aerodynamic properties

← Version précédente		Version du 6 septembre 2019 à 08:43
Ligne 44 :		Ligne 44 :

	[[Fichier:Aerodynamic2.png]]		[[Fichier:Aerodynamic2.png]]

			An example of the <font color=#FF8C00 title="Extensible Markup Language">XML</font> structure corresponding to aerodynamic coefficients depending on altitude as used in the [https://logiciels.cnes.fr/en/content/stela STELA S/W] is available [[File:Stela_drag_coefficient.zip here]].

	The aerodynamic forces will be computed as:		The aerodynamic forces will be computed as:

Admin : /* Aerodynamic properties */

2018-10-18T13:56:46Z

Aerodynamic properties

← Version précédente		Version du 18 octobre 2018 à 13:56
Ligne 63 :		Ligne 63 :
	** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>		** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>
	*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \centerdot \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \centerdot \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \centerdot \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \centerdot \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere

	== Radiative properties ==		== Radiative properties ==

Admin : /* Aerodynamic properties */

2018-10-18T13:56:26Z

Aerodynamic properties

← Version précédente		Version du 18 octobre 2018 à 13:56
Ligne 62 :		Ligne 62 :
	** Parallelepiped (and solar panels too): <math>S_{apparent} = S_x\ cos(α_x) + S_y\ cos(α_y) + S_x\ cos(α_z)</math>		** Parallelepiped (and solar panels too): <math>S_{apparent} = S_x\ cos(α_x) + S_y\ cos(α_y) + S_x\ cos(α_z)</math>
	** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>		** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>
	*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \~~dot~~ \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \centerdot \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere

Admin : /* Aerodynamic properties */

2018-10-18T13:55:37Z

Aerodynamic properties

← Version précédente		Version du 18 octobre 2018 à 13:55
Ligne 62 :		Ligne 62 :
	** Parallelepiped (and solar panels too): <math>S_{apparent} = S_x\ cos(α_x) + S_y\ cos(α_y) + S_x\ cos(α_z)</math>		** Parallelepiped (and solar panels too): <math>S_{apparent} = S_x\ cos(α_x) + S_y\ cos(α_y) + S_x\ cos(α_z)</math>
	** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>		** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>
	*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \∙ \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \dot \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere

Admin : /* Aerodynamic properties */

2018-10-18T13:55:17Z

Aerodynamic properties

← Version précédente		Version du 18 octobre 2018 à 13:55
Ligne 62 :		Ligne 62 :
	** Parallelepiped (and solar panels too): <math>S_{apparent} = S_x\ cos(α_x) + S_y\ cos(α_y) + S_x\ cos(α_z)</math>		** Parallelepiped (and solar panels too): <math>S_{apparent} = S_x\ cos(α_x) + S_y\ cos(α_y) + S_x\ cos(α_z)</math>
	** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>		** Cylinder (sideslip angle is neglected): <math>S_{apparent} = S_x\ cos(α_x) + S_t\ sin(α_x)</math>
	*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>{\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_x) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} \∙ \vec X</math> , being <math>\vec X</math> the X satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>{\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_y) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Y</math> , being <math>\vec Y</math> the Y satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere
	*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>{\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere		*** cos(α_z) = <math>\dfrac {\overrightarrow{V_{aero}}}{\\|V_{aero}\\|} ∙ \vec Z</math> , being <math>\vec Z</math> the Z satellite unitary axis direction and <math>\overrightarrow{V_{aero}}</math> the s/c velocity wrt the atmosphere

	== Radiative properties ==		== Radiative properties ==

Vehicle - Historique des versions

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */

Admin : /* Aerodynamic properties */