Struct OrbitDual

pub struct OrbitDual {
    pub x: OHyperdual<f64, U7>,
    pub y: OHyperdual<f64, U7>,
    pub z: OHyperdual<f64, U7>,
    pub vx: OHyperdual<f64, U7>,
    pub vy: OHyperdual<f64, U7>,
    pub vz: OHyperdual<f64, U7>,
    pub dt: Epoch,
    pub frame: Frame,
}

Orbit defines an orbital state

Unless noted otherwise, algorithms are from GMAT 2016a StateConversionUtil.cpp. Regardless of the constructor used, this struct stores all the state information in Cartesian coordinates as these are always non singular. Note: although not yet supported, this struct may change once True of Date or other nutation frames are added to the toolkit.

Fields

x: OHyperdual<f64, U7>

in km

y: OHyperdual<f64, U7>

in km

z: OHyperdual<f64, U7>

in km

vx: OHyperdual<f64, U7>

in km/s

vy: OHyperdual<f64, U7>

in km/s

vz: OHyperdual<f64, U7>

in km/s

dt: Epoch

frame: Frame

Frame contains everything we need to compute state information

Implementations

impl OrbitDual

pub fn partial_for( &self, param: StateParameter, ) -> Result<OrbitPartial, AstroError>

pub fn rmag_km(&self) -> OrbitPartial

Returns the magnitude of the radius vector in km

pub fn vmag_km_s(&self) -> OrbitPartial

Returns the magnitude of the velocity vector in km/s

pub fn hx(&self) -> OrbitPartial

Returns the orbital momentum value on the X axis

pub fn hy(&self) -> OrbitPartial

Returns the orbital momentum value on the Y axis

pub fn hz(&self) -> OrbitPartial

Returns the orbital momentum value on the Z axis

pub fn hmag(&self) -> OrbitPartial

Returns the norm of the orbital momentum

pub fn energy_km2_s2(&self) -> PhysicsResult<OrbitPartial>

Returns the specific mechanical energy

pub fn sma_km(&self) -> PhysicsResult<OrbitPartial>

Returns the semi-major axis in km

pub fn ecc(&self) -> PhysicsResult<OrbitPartial>

Returns the eccentricity (no unit)

pub fn inc_deg(&self) -> OrbitPartial

Returns the inclination in degrees

pub fn aop_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the argument of periapsis in degrees

pub fn raan_deg(&self) -> OrbitPartial

Returns the right ascension of ther ascending node in degrees

pub fn ta_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the true anomaly in degrees between 0 and 360.0

pub fn tlong_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the true longitude in degrees

pub fn aol_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the argument of latitude in degrees

NOTE: If the orbit is near circular, the AoL will be computed from the true longitude instead of relying on the ill-defined true anomaly.

pub fn periapsis_km(&self) -> PhysicsResult<OrbitPartial>

Returns the radius of periapsis (or perigee around Earth), in kilometers.

pub fn apoapsis_km(&self) -> PhysicsResult<OrbitPartial>

Returns the radius of apoapsis (or apogee around Earth), in kilometers.

pub fn ea_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the eccentric anomaly in degrees

This is a conversion from GMAT’s StateConversionUtil::TrueToEccentricAnomaly

pub fn fpa_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the flight path angle in degrees

pub fn ma_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the mean anomaly in degrees

pub fn semi_parameter_km(&self) -> PhysicsResult<OrbitPartial>

Returns the semi parameter (or semilatus rectum)

pub fn longitude_deg(&self) -> OrbitPartial

Returns the geodetic longitude (λ) in degrees. Value is between 0 and 360 degrees.

Although the reference is not Vallado, the math from Vallado proves to be equivalent. Reference: G. Xu and Y. Xu, “GPS”, DOI 10.1007/978-3-662-50367-6_2, 2016

pub fn latitude_deg(&self) -> PhysicsResult<OrbitPartial>

Returns the geodetic latitude (φ) in degrees. Value is between -180 and +180 degrees.

Reference: Vallado, 4th Ed., Algorithm 12 page 172.

pub fn height_km(&self) -> PhysicsResult<OrbitPartial>

Returns the geodetic height in km.

Reference: Vallado, 4th Ed., Algorithm 12 page 172.

pub fn right_ascension_deg(&self) -> OrbitPartial

Returns the right ascension of this orbit in degrees

pub fn declination_deg(&self) -> OrbitPartial

Returns the declination of this orbit in degrees

pub fn semi_minor_axis_km(&self) -> PhysicsResult<OrbitPartial>

Returns the semi minor axis in km, includes code for a hyperbolic orbit

pub fn velocity_declination(&self) -> OrbitPartial

Returns the velocity declination of this orbit in degrees

pub fn c3(&self) -> PhysicsResult<OrbitPartial>

Returns the $C_3$ of this orbit

pub fn hyperbolic_anomaly_deg(&self) -> Result<OrbitPartial, AstroError>

Returns the hyperbolic anomaly in degrees between 0 and 360.0

Trait Implementations

impl Clone for OrbitDual

fn clone(&self) -> OrbitDual

Returns a copy of the value.

fn clone_from(&mut self, source: &Self)

Performs copy-assignment from source.

impl Debug for OrbitDual

fn fmt(&self, f: &mut Formatter<'_>) -> Result

Formats the value using the given formatter.

impl From<CartesianState> for OrbitDual

fn from(orbit: Orbit) -> Self

Initialize a new OrbitDual from an orbit, no other initializers

impl TimeTagged for OrbitDual

fn epoch(&self) -> Epoch

Retrieve the Epoch

fn set_epoch(&mut self, epoch: Epoch)

Set the Epoch

impl Copy for OrbitDual