Package org.orekit.forces

Class BoxAndSolarArraySpacecraft

java.lang.Object
org.orekit.forces.BoxAndSolarArraySpacecraft
All Implemented Interfaces:
DragSensitive, RadiationSensitive
public class BoxAndSolarArraySpacecraft extends Object implements RadiationSensitive, DragSensitive
Class representing the features of a classical satellite with a convex body shape.

The body can be either a simple parallelepipedic box aligned with spacecraft axes or a set of panels defined by their area and normal vector. Some panels may be moving to model solar arrays (or antennas that could point anywhere). This should handle accurately most spacecraft shapes. This model does not take cast shadows into account.

The lift component of the drag force can be optionally considered. It should probably only be used for reentry computation, with much denser atmosphere than in regular orbit propagation. The lift component is computed using a ratio of molecules that experience specular reflection instead of diffuse reflection (absorption followed by outgassing at negligible velocity). Without lift (i.e. when the lift ratio is set to 0), drag force is along atmosphere relative velocity. With lift (i.e. when the lift ratio is set to any value between 0 and 1), the drag force depends on both relative velocity direction and panels normal orientation. For a single panel, if the relative velocity is head-on (i.e. aligned with the panel normal), the force will be in the same direction with and without lift, but the magnitude with lift ratio set to 1.0 will be twice the magnitude with lift ratio set to 0.0 (because atmosphere molecules bounces backward at same velocity in case of specular reflection).

Each panel has its own set of radiation and drag coefficients. In orbit determination context, it would not be possible to estimate each panel individually, therefore getDragParametersDrivers() returns a single parameter driver representing a global drag multiplicative factor that applies to all panels drag coefficients and the getRadiationParametersDrivers() returns a single parameter driver representing a global radiation multiplicative factor that applies to all panels radiation coefficients.

Author:
Luc Maisonobe, Pascal Parraud

  • Constructor Details

    • BoxAndSolarArraySpacecraft

      public BoxAndSolarArraySpacecraft(List<Panel> panels)
      Build a spacecraft model.
      Parameters:
      panels - panels composing the body, solar arrays and antennas (only the panels with strictly positive area will be stored)
      Since:
      12.0

    • BoxAndSolarArraySpacecraft

      public BoxAndSolarArraySpacecraft(double xLength, double yLength, double zLength, ExtendedPositionProvider sun, double solarArrayArea, Vector3D solarArrayAxis, double dragCoeff, double liftRatio, double absorptionCoeff, double reflectionCoeff)
      Build a spacecraft model with best lighting of solar array.

      Solar arrays orientation will be such that at each time the Sun direction will always be in the solar array meridian plane defined by solar array rotation axis and solar array normal vector.

      Parameters:
      xLength - length of the body along its X axis (m)
      yLength - length of the body along its Y axis (m)
      zLength - length of the body along its Z axis (m)
      sun - sun model
      solarArrayArea - area of the solar array (m²)
      solarArrayAxis - solar array rotation axis in satellite frame
      dragCoeff - drag coefficient (used only for drag)
      liftRatio - lift ratio (proportion between 0 and 1 of atmosphere modecules that will experience specular reflection when hitting spacecraft instead of experiencing diffuse reflection, hence producing lift)
      absorptionCoeff - absorption coefficient between 0.0 an 1.0 (used only for radiation pressure)
      reflectionCoeff - specular reflection coefficient between 0.0 an 1.0 (used only for radiation pressure)
      Since:
      12.0

    • BoxAndSolarArraySpacecraft

      public BoxAndSolarArraySpacecraft(int n, double diameter, double dragCoeff, double liftRatio, double absorptionCoeff, double reflectionCoeff)
      Build a spacecraft model in the shape of a disco ball.

      This shape is intended either for comparison with isotropic models or as a model for geodesy satellites like Starlette or Lageos. All facets are fixed, there are no solar arrays. The facets are arranged in a spiral that attempts to preserve area.

      Parameters:
      n - number of facets (must be an odd number)
      diameter - diameter of the spherical body
      dragCoeff - drag coefficient for each facet (used only for drag)
      liftRatio - lift ratio for each facet (proportion between 0 and 1 of atmosphere modecules that will experience specular reflection when hitting spacecraft instead of experiencing diffuse reflection, hence producing lift)
      absorptionCoeff - absorption coefficient between 0.0 an 1.0 for each facet (used only for radiation pressure)
      reflectionCoeff - specular reflection coefficient between 0.0 an 1.0 for each facet (used only for radiation pressure)
      Since:
      14.0
      See Also:

  • Method Details

    • getPanels

      public List<Panel> getPanels()
      Get the panels composing the body.
      Returns:
      unmodifiable view of the panels composing the body
      Since:
      12.0

    • getDragParametersDrivers

      public List<ParameterDriver> getDragParametersDrivers()
      Get the drivers for supported parameters.
      Specified by:
      getDragParametersDrivers in interface DragSensitive
      Returns:
      parameters drivers

    • getRadiationParametersDrivers

      public List<ParameterDriver> getRadiationParametersDrivers()
      Get the drivers for supported parameters.
      Specified by:
      getRadiationParametersDrivers in interface RadiationSensitive
      Returns:
      parameters drivers

    • dragAcceleration

      public Vector3D dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity, double[] parameters)
      Compute the acceleration due to drag.

      The computation includes all spacecraft specific characteristics like shape, area and coefficients.

      Specified by:
      dragAcceleration in interface DragSensitive
      Parameters:
      state - current state
      density - atmospheric density at spacecraft position
      relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)
      parameters - values of the force model parameters
      Returns:
      spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

    • dragAcceleration

      public <T extends CalculusFieldElement<T>> FieldVector3D<T> dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)
      Compute the acceleration due to drag.

      The computation includes all spacecraft specific characteristics like shape, area and coefficients.

      Specified by:
      dragAcceleration in interface DragSensitive
      Type Parameters:
      T - instance of a CalculusFieldElement
      Parameters:
      state - current state
      density - atmospheric density at spacecraft position
      relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)
      parameters - values of the force model parameters
      Returns:
      spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

    • radiationPressureAcceleration

      public Vector3D radiationPressureAcceleration(SpacecraftState state, Vector3D flux, double[] parameters)
      Compute the acceleration due to radiation pressure.
      Specified by:
      radiationPressureAcceleration in interface RadiationSensitive
      Parameters:
      state - current state
      flux - radiation flux in the same inertial frame as spacecraft orbit
      parameters - values of the force model parameters
      Returns:
      spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

    • radiationPressureAcceleration

      public <T extends CalculusFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration(FieldSpacecraftState<T> state, FieldVector3D<T> flux, T[] parameters)
      Compute the acceleration due to radiation pressure.

      This method implements equation 8-44 from David A. Vallado's Fundamentals of Astrodynamics and Applications, third edition, 2007, Microcosm Press.

      Specified by:
      radiationPressureAcceleration in interface RadiationSensitive
      Type Parameters:
      T - extends CalculusFieldElement
      Parameters:
      state - current state
      flux - radiation flux in the same inertial frame as spacecraft orbit
      parameters - values of the force model parameters
      Returns:
      spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

    • buildBox

      public static List<Panel> buildBox(double xLength, double yLength, double zLength, double drag, double liftRatio, double absorption, double reflection)
      Build the panels of a simple parallelepipedic box.
      Parameters:
      xLength - length of the body along its X axis (m)
      yLength - length of the body along its Y axis (m)
      zLength - length of the body along its Z axis (m)
      drag - drag coefficient
      liftRatio - drag lift ratio (proportion between 0 and 1 of atmosphere modecules that will experience specular reflection when hitting spacecraft instead of experiencing diffuse reflection, hence producing lift)
      absorption - radiation pressure absorption coefficient (between 0 and 1)
      reflection - radiation pressure specular reflection coefficient (between 0 and 1)
      Returns:
      surface vectors array
      Since:
      12.0

    • buildPanels

      public static List<Panel> buildPanels(double xLength, double yLength, double zLength, ExtendedPositionProvider sun, double solarArrayArea, Vector3D solarArrayAxis, double drag, double liftRatio, double absorption, double reflection)
      Build the panels of a simple parallelepiped box plus one solar array panel.
      Parameters:
      xLength - length of the body along its X axis (m)
      yLength - length of the body along its Y axis (m)
      zLength - length of the body along its Z axis (m)
      sun - sun model
      solarArrayArea - area of the solar array (m²)
      solarArrayAxis - solar array rotation axis in satellite frame
      drag - drag coefficient
      liftRatio - drag lift ratio (proportion between 0 and 1 of atmosphere modecules that will experience specular reflection when hitting spacecraft instead of experiencing diffuse reflection, hence producing lift)
      absorption - radiation pressure absorption coefficient (between 0 and 1)
      reflection - radiation pressure specular reflection coefficient (between 0 and 1)
      Returns:
      surface vectors array
      Since:
      12.0

    • buildDiscoBall

      public static List<Panel> buildDiscoBall(int n, double diameter, double dragCoeff, double liftRatio, double absorptionCoeff, double reflectionCoeff)
      Build the panels of a disco ball.
      Parameters:
      n - number of facets (must be an odd number)
      diameter - diameter of the spherical body
      dragCoeff - drag coefficient for each facet (used only for drag)
      liftRatio - lift ratio for each facet (proportion between 0 and 1 of atmosphere modecules that will experience specular reflection when hitting spacecraft instead of experiencing diffuse reflection, hence producing lift)
      absorptionCoeff - absorption coefficient between 0.0 an 1.0 for each facet (used only for radiation pressure)
      reflectionCoeff - specular reflection coefficient between 0.0 an 1.0 for each facet (used only for radiation pressure)
      Returns:
      panels for the complete ball
      Since:
      14.0
      See Also: