acceleration.hpp File Reference

Data Structures
struct	Legendre

Functions
Vector3d	accelSourcePoint (const Vector3d observer, const Vector3d origin, const double GM, Matrix3d *dAdPos_ptr=nullptr)
	Source point acceleration from a planet acting on a satellite.
Vector3d	accelCentralForce (const Vector3d observer, const double GM, Matrix3d *dAdPos_ptr=nullptr)
	Central force acceleration.
Vector3d	accelSPH (const Vector3d r, const MatrixXd C, const MatrixXd S, const int n, const double GM)
	Compute the acceleration of due to a spherical harmonic field acting on the satellite.
Vector3d	accelJ2 (const double C20, const Matrix3d eci2ecf, Vector3d bodyPos, double GM)
	"The indirect J2 effect".

Function Documentation

accelCentralForce()

Vector3d accelCentralForce	(	const Vector3d	observer,
		const double	GM,
		Matrix3d *	dAdPos_ptr = nullptr )

Central force acceleration.

Parameters

observer	position of the oberserver
GM	value of GM of the acting force
dAdPos_ptr	Optional pointer to differential matrix

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accelJ2()

Vector3d accelJ2	(	const double	C20,
		const Matrix3d	eci2ecf,
		Vector3d	bodyPos,
		double	GM )

"The indirect J2 effect".

ref: GOCE standards GO-TN-HPF-GS-0111

Parameters

C20	Value of the C20
eci2ecf	Rotation inertial to terestrila
bodyPos	Position of the planets
GM	Value of GM constant of the body in question

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accelSourcePoint()

Vector3d accelSourcePoint	(	const Vector3d	observer,
		const Vector3d	origin,
		const double	GM,
		Matrix3d *	dAdPos_ptr = nullptr )

Source point acceleration from a planet acting on a satellite.

Parameters

observer	Vector posiiong of the satellite w.r.t to the orbiting body
origin	Vector position of the planet w.r.t to the orbiting body
GM	Constant GM of the acting body
dAdPos_ptr	Optional pointer to differential matrix

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accelSPH()

Vector3d accelSPH	(	const Vector3d	r,
		const MatrixXd	C,
		const MatrixXd	S,
		const int	maxDeg,
		const double	GM )

Compute the acceleration of due to a spherical harmonic field acting on the satellite.

Note

This function does not contain the degree 0 acceleration need to be done via "accelCentralForce"

(Re/R)**n : we start from deg 2 this formulation works.

Parameters

r	Vector of the position of the satelite (ECEF)
C	Matrix of the "C" spherical harmonic coefficient
S	Matrix of the "S" spherical harmonic coefficient
maxDeg	Maximum degree use for the summation of the harmonics //todo aaron, limit this to max found in file/struct
GM	Value of GM constant of the body in question.

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