Struct inertialsim::geodesy::GeodeticDatum¶

ClassList > inertialsim > geodesy > GeodeticDatum

Geodetic datum. More...

#include <datums.h>

Public Attributes¶

Type	Name
double	angular_velocity
double	first_eccentricity
double	first_eccentricity_squared
double	flattening
double	flattening_factor
double	gravitational_constant
double	linear_eccentricity
double	normal_gravity_equator
double	normal_gravity_k
double	normal_gravity_m
double	normal_gravity_pole
Vector3D	origin = `Vector3D::Zero(3, 1)`
double	prime_meridian = `0.0`
double	second_eccentricity
double	second_eccentricity_squared
double	semimajor_axis
double	semiminor_axis

Detailed Description¶

Defines a datum for Earth. Two shape parameters are required for coordinate conversions/transforms and two mass and rotation parameters are required for gravity calculations.

Note:

Derived parameters: Four parameters are the theoretical minimum required to define a geodetic datum, however InertialSim requires additional derived parameters. Theoretically these derived parameters can be calculated from the four fundamental parameters but often they are specified explicitly to avoid losing numeric precision.

Warning:

InertialSim does not support geodetic datums with origin other than the center of mass of the Earth (0.0, 0.0, 0.0).

Warning:

InertialSim does not support geodetic datums with prime meridians other than the IERS reference meridian.

Public Attributes Documentation¶

variable angular_velocity¶

double inertialsim::geodesy::GeodeticDatum::angular_velocity;

variable first_eccentricity¶

double inertialsim::geodesy::GeodeticDatum::first_eccentricity;

variable first_eccentricity_squared¶

double inertialsim::geodesy::GeodeticDatum::first_eccentricity_squared;

variable flattening¶

double inertialsim::geodesy::GeodeticDatum::flattening;

variable flattening_factor¶

double inertialsim::geodesy::GeodeticDatum::flattening_factor;

variable gravitational_constant¶

double inertialsim::geodesy::GeodeticDatum::gravitational_constant;

variable linear_eccentricity¶

double inertialsim::geodesy::GeodeticDatum::linear_eccentricity;

variable normal_gravity_equator¶

double inertialsim::geodesy::GeodeticDatum::normal_gravity_equator;

variable normal_gravity_k¶

double inertialsim::geodesy::GeodeticDatum::normal_gravity_k;

variable normal_gravity_m¶

double inertialsim::geodesy::GeodeticDatum::normal_gravity_m;

variable normal_gravity_pole¶

double inertialsim::geodesy::GeodeticDatum::normal_gravity_pole;

variable origin¶

Vector3D inertialsim::geodesy::GeodeticDatum::origin;

variable prime_meridian¶

double inertialsim::geodesy::GeodeticDatum::prime_meridian;

variable second_eccentricity¶

double inertialsim::geodesy::GeodeticDatum::second_eccentricity;

variable second_eccentricity_squared¶

double inertialsim::geodesy::GeodeticDatum::second_eccentricity_squared;

variable semimajor_axis¶

double inertialsim::geodesy::GeodeticDatum::semimajor_axis;

variable semiminor_axis¶

double inertialsim::geodesy::GeodeticDatum::semiminor_axis;

The documentation for this class was generated from the following file cpp/include/inertialsim/geodesy/datums.h