Aero.spacecraft.NumericalPropagatorOptions

Numerical orbit propagator options used by propagateOrbit

Since R2024b

expand all in page

    Description

    Options used by numerical orbit propagator in propagateOrbit.

    Creation

    Description

    options = Aero.spacecraft.NumericalPropagatorOptions creates an Aero.spacecraft.NumericalPropagatorOptions object, options, using default properties.

    options = Aero.spacecraft.NumericalPropagatorOptions(Name=Value) creates an Aero.spacecraft.NumericalPropagatorOptions object using additional parameters specified by one or more name-value arguments.

    Properties

    expand all

    Specify these properties as name-value arguments.

    Ordinary differential equation (ODE) solver used by the numerical orbit propagator, specified as "ode45", "ode23", "ode78", "ode89", "ode113", "ode15s", "ode23s","ode23t", or "ode23tb".

    Options structure for ODE solver, specified as a structure returned by odeset function.

    Data Types: struct

    Gravitational potential model of central body, specified as "spherical-harmonics", "point-mass", or "oblate-ellipsoid".

    Default Values

    The default value is

    Dependencies

    To set the value of GravitationalPotentialModel to "spherical-harmonics", ensure that the CentralBody property of Aero.spacecraft.CentralBodyOptions object set by the CentralBodyOptions property is set to one of Earth, Moon, or Mars.

    Spherical harmonic model of gravitational potential of the central body, when GravitationalPotentialModel is set to "spherical-harmonics", specified as one of:

    Default Values

    The default value is:

    Dependencies

    To use this property, GravitationalPotentialModel must be set to 'spherical-harmonics'.

    Degree of the spherical harmonic gravitational potential model, when GravitationalPotentialModel is set to "spherical-harmonics", specified as one of:

    Dependencies

    To use this property, SphericalHarmonicModel must be set to 'spherical-harmonics'.

    Data Types: double

    Option to indicate whether the numerical orbit propagator must account for atmospheric drag, specified as false or true. When set to true, the propagator calculates atmospheric drag based on the NRLMSISE-00 model for atmospheric density.

    Dependencies

    To set this property to true, the Aero.spacecraft.CentralBodyOptions object set by the CentralBodyOptions property must be set to Earth. Otherwise, this property is hidden, read-only, and set to false.

    Option to use MAT file containing consolidated space weather data file in atmospheric density calculation, specified as false or true. For more information on how to generate this MAT file, see aeroReadSpaceWeatherData.

    Dependencies

    To use this property, IncludeAtmosDrag must be set to true.

    MAT file containing consolidated space weather data file in atmospheric density calculation, specified as a character vector or string. See aeroReadSpaceWeatherData for more information on how to generate this MAT file.

    Dependencies

    To use this property, IncludeAtmosDrag and UseSpaceWeatherDataFile must be set to true.

    Method used for extrapolating F10.7 solar flux for times outside range of space weather data file, specified as one of these values:

    • 'none-clip' — F10.7 value is set to the nearest data point available in the space weather data file.

    • 'constant' — F10.7 value is set to a constant value specified by the F107ExtrapValue property.

    • 'least-squares-fit' — F10.7 value is approximated using a least-squares fit of the space weather data from October 1, 1957 to December 1, 2040, using the trigonometric function a+bcos(ct + dsin(et)).

    Dependencies

    To use this property, IncludeAtmosDrag and UseSpaceWeatherDataFile must be set to true.

    Extrapolation value for the F10.7 solar flux for times outside the date range of the space weather data file, specified as a nonnegative scalar.

    Dependencies

    To use this property:

    • IncludeAtmosDrag, and UseSpaceWeatherDataFile must be set to true.

    • 'F107ExtrapMethod' must be set to 'constant'.

    Centered 81-day average value of the F10.7 solar flux, specified as a nonnegative scalar.

    Dependencies

    To use this property:

    • IncludeAtmosDrag must be set to true.

    • UseSpaceWeatherDataFile must be set to false.

    Daily value of the F10.7 solar flux, specified as a nonnegative scalar.

    Dependencies

    To use this property:

    • IncludeAtmosDrag must be set to true.

    • UseSpaceWeatherDataFile must be set to false.

    Method used for extrapolating magnetic index for times outside range of space weather data file, specified as one of these values:

    • 'none-clip' — Magnetic index is set to the nearest data point available in the space weather data file.

    • 'constant' — Magnetic index is set to a constant value specified by the MagneticIndexExtrapValue property.

    • 'igrf' — Magnetic index is calculated using International Geomagnetic Reference Field. Because this model is defined for times between January 1, 1900, 12:00 AM UTC and January 1, 2025, 12:00 AM UTC, the predictions for times outside this range are clipped to values at these time limits.

    Dependencies

    To use this property, IncludeAtmosDrag and UseSpaceWeatherDataFile must be set to true.

    Extrapolation value for the magnetic index for times outside the date range in space weather data file, specified as a nonnegative scalar.

    Dependencies

    To use this property:

    • MagneticIndexExtrapMethod is set to 'constant'.

    • IncludeAtmosDrag and UseSpaceWeatherDataFile must be set to true.

    Magnetic index information, specified as a 7-element row vector. This value consists of magnetic index representing a daily value (AP), 3-hour AP for a reference time, 3-hour AP for three hours before the reference time, 3-hour AP for six hours before the reference time, 3-hour AP for nine hours before the reference time, average of eight 3-hour AP indices from 12 to 33 hours prior to the reference time, and average of eight 3-hour AP indices from 36 to 57 hours prior to the reference time. This vector is constant for the entire orbit propagation.

    Dependencies

    To use this property:

    • UseSpaceWeatherDataFile must be set to false.

    • IncludeAtmosDrag must be true.

    Option to specify whether anomalous oxygen must be included in atmospheric mass density calculation, specified as true or false.

    Dependencies

    To use this property, IncludeAtmosDrag must be set to true.

    Option to activate or deactivate particular variations in atmospheric mass density calculation, specified as a double vector of 23 elements. The elements are defined in this order.

    AtmosFlags elements

    ElementValue
    1

    F10.7 effect on mean

    2

    Independent of time

    3

    Symmetrical annual

    4

    Symmetrical semiannual

    5

    Asymmetrical annual

    6

    Asymmetrical semiannual

    7

    Diurnal

    8

    Semidiurnal

    9

    Daily AP. If you set this value to -1, the atmospheric mass density computation uses the entire magnetic index information that includes the 3-hour averages, as opposed to just the daily value

    10

    All UT seconds, longitudinal effects

    11

    Longitudinal

    12

    UT seconds and mixed UT seconds, longitudinal

    13

    Mixed AP, UT seconds, longitudinal

    14

    Terdiurnal

    15

    Departures from diffusive equilibrium

    16

    All exospheric temperature variations

    17

    All variations from 120,000 meter temperature (TLB)

    18

    All lower thermosphere (TN1) temperature variations

    19

    All 120,000 meter gradient (S) variations

    20

    All upper stratosphere (TN2) temperature variations

    21

    All variations from 120,000 meter values (ZLB)

    22

    All lower mesosphere temperature (TN3) variations

    23

    Turbopause scale height variations

    With the exception of element 9 (daily AP), the elements are specified as 0 or 1. Element 9 is specified as -1, 0 or 1.

    Dependencies

    To use this property, IncludeAtmosDrag must be set to true.

    Option to include third body gravity, specified as false or true.The third body gravity sources are assumed to be point masses.

    Third body gravity source, specified as a string containing a combination of 'Sun', 'Moon', 'Mercury', 'Venus', 'Mars', 'Jupiter', 'Saturn', 'Uranus', 'Neptune', or 'Pluto'.

    Default Values

    The default values are:

    Dependencies

    To use this property, set the IncludeThirdBodyGravity property to true.

    Option to include solar radiation pressure, specified as false (0) or true (1).

    Solar flux pressure acting on the satellite, specified as a nonnegative scalar, in W*s/m3.

    Dependencies

    To use this property, IncludeSRP must be set to true.

    Data Types: double

    Eclipse model used in solar radiation pressure computation, specified as 'dual-cone' or 'cylindrical'.

    Dependencies

    To use this property, IncludeSRP must be set to true and the CentralBody property of the Aero.spacecraft.CentralBodyOptions object set by the CentralBodyOptions property is not set to Sun.

    Option to include lunar eclipse in solar radiation pressure calculation, specified as false or true.

    Dependencies

    To use this property, IncludeSRP must be set to true, and the CentralBody property of Aero.spacecraft.NumericalPropagatorOptions object set by the CentralBodyOptions property is set to Earth.

    Celestial body ephemeris model used in the computation of third body gravity and solar radiation pressure, specified as one of these ephemerides defined by the Jet Propulsion Laboratory:

    • 'de405' — Released in 1998. This ephemerides takes into account the Julian date range 2305424.50 (December 9, 1599) to 2525008.50 (February 20, 2201).

    • 'de421' — Released in 2008. This ephemerides takes into account the Julian date range 2414992.5 (December 4, 1899) to 2469808.5 (January 2, 2050).

    • 'de423' — Released in 2010. This ephemerides takes into account the Julian date range 2378480.5 (December 16, 1799) to 2524624.5 (February 1, 2200).

    • 'de430' — Released in 2013. This ephemerides takes into account the Julian date range 2287184.5 (December 21, 1549) to 2688976.5 (January 25, 2650).

    • 'de432t' — Released in April 2014. This ephemerides takes into account the Julian date range 2287184.5, (December 21, 1549 ) to 2688976.5, (January 25, 2650).

    Dependencies

    To use this property, IncludeThirdBodyGravity or IncludeSRP must be set to true.

    Data Types: string

    Central body options used by the numerical orbit propagator, specified as an Aero.spacecraft.CentralBodyOptions scalar object.

    Default Values

    The default value is

    Version History

    Introduced in R2024b

    See Also

    Objects

    Functions

    Topics