Classes
struct	FuturePosition

struct	GalacticCoordinate
	Way to position star systems on the universe. More...

struct	Impulse

struct	Kinematics
	Relative position from the parent orbiting object. More...

struct	MoveTarget

struct	Orbit

struct	OrbitDirty

struct	PolarCoordinate_tp

struct	SetTrueAnomaly

struct	SurfaceCoordinate
	Longitude and lattitude. Planet coordinates. More...

Typedefs
typedef PolarCoordinate_tp< types::astronomical_unit >	PolarCoordinate

typedef glm::dvec3	Vec3AU
	A vector3 where the units are astronomical units More...

typedef double	astronomical_unit

typedef double	light_year

typedef double	kilometer

typedef double	solar_mass

typedef double	degree

typedef double	radian

typedef double	meter_cube

typedef double	kilogram

typedef double	earth_masses

typedef double	joule

typedef double	second

Enumerations
enum	UnitType { Distance , Angle , Mass , Volume , Time }

enum	Distance { LightYear , AstronomicalUnit , Kilometer , Meter , Centimeter , Millimeter }

Functions
double	GreatCircleDistance (SurfaceCoordinate &coord1, SurfaceCoordinate &coord2)
	Calculates the angle between the two coordinates. Just multiply by the planet's diameter for fun and engagement. More...

glm::vec3	toVec3 (const SurfaceCoordinate &coord, const float &radius=1)
	Converts surface coordinate to vector3 in space so that we can get the surface coordinate to render in space More...

double	GetLaunchAzimuth (double latitude, double inclination)
	Calculates the azimuth of the orbit based on the latitude and inclination More...

double	GetLaunchInclination (double latitude, double azimuth)
	Calculates the inclination of the orbit based on the latitude and azimuth More...

SurfaceCoordinate	ToSurfaceCoordinate (const glm::vec3 &vec)

glm::vec3	toVec3 (const PolarCoordinate &coordinate)
	2D polar coordinate to opengl 3d coordinate More...

double	GetOrbitingRadius (const double &e, const double &a, const double &v)

glm::dvec3	MatrixConvertOrbParams (const double LAN, const double i, const double w, const glm::dvec3 &vec)

glm::dvec3	ConvertOrbParams (const double LAN, const double i, const double w, const glm::dvec3 &vec)
	Transforms a vector to the orbital plane vector More...

glm::dvec3	ConvertToOrbitalVector (const double LAN, const double i, const double w, const double v, const glm::dvec3 &vec)

Orbit	Vec3ToOrbit (const glm::dvec3 &position, const glm::dvec3 &velocity, const double &GM, const double &time)
	Converts position and velocity to orbit. Note: you will have to set the reference body after the orbit is returned More...

double	GetTrueAnomalyToAsymptope (const Orbit &orbit)
	Calculates v_inf, the true anomaly for the asymtope for a hyperbolic orbit The orbit is bouded within -v_inf < v < v_inf https://orbital-mechanics.space/the-orbit-equation/hyperbolic-trajectories.html#hyperbolic-trajectories-e-1. More...

glm::dvec3	OrbitToVec3 (const double &a, const double &e, const radian &i, const radian &LAN, const radian &w, const radian &v)
	Converts an orbit to a vec3. More...

double	OrbitVelocity (const double v, const double e, const double a, const double GM)

double	AvgOrbitalVelocity (const Orbit &orb)

glm::dvec3	OrbitVelocityToVec3 (const Orbit &orb, double v)

glm::dvec3	OrbitVelocityToVec3 (const Orbit &orb)

double	SolveKeplerElliptic (const double &mean_anomaly, const double &ecc, const int steps=200)
	Computes eccentric anomaly for a elliptic or circular orbit (e < 1) in radians given mean anomaly and eccentricity More...

double	SolveKeplerHyperbolic (const double &mean_anomaly, const double &ecc, const int steps=200)
	Computes eccentric anomaly for a hyperbolic or parabolic orbit (e > 1) in radians given mean anomaly and eccentricity More...

double	EccentricAnomalyToTrueAnomaly (const double &ecc, const double &E)
	Calculates true anomaly from eccentricity and eccentric anomaly More...

double	HyperbolicAnomalyToTrueAnomaly (const double &ecc, const double &H)

double	GetMtElliptic (const double &M0, const double &nu, const double &time, const double &epoch)
	Gets the Mean anomaly from the time More...

double	GetMtHyperbolic (const double &M0, const double &nu, const double &time, const double &epoch)
	Calculate mean anomaly from time for a hyperbolic object More...

radian	TrueAnomalyElliptic (const Orbit &orbit, const second &time)

radian	TrueAnomalyElliptic (const Orbit &orbit, const second &time, double &E_out)

double	GetCircularOrbitingVelocity (const double &GM, const double &radius)
	Get the circular orbiting velocity for the radius. More...

radian	TrueAnomalyHyperbolic (const Orbit &orbit, const second &time)

radian	EccentricAnomaly (double v, double e)
	Calculates Eccentric anomaly More...

radian	HyperbolicAnomaly (double v, double e)

void	UpdateOrbit (Orbit &orb, const second &time)
	Updates the orbit's true anomaly. More...

double	GetTrueAnomaly (const Orbit &orb, const second &epoch)
	Get anomaly at epoch More...

glm::dvec3	CalculateVelocity (const double &E, const double &r, const double &GM, const double &a, const double &e)

glm::dvec3	CalculateVelocityHyperbolic (const double &E, const double &r, const double &GM, const double &a, const double &e)

glm::dvec3	CalculateVelocityElliptic (const double &E, const double &r, const double &GM, const double &a, const double &e)

Orbit	ApplyImpulse (const Orbit &orbit, const glm::dvec3 &impulse, double time)
	Applies impulse based on the vector impulse For some reason y is prograde, I'm not sure what the others are. TODO(EhWhoAmI): Determine the axis of thrust for each vector I think x is radial, and z is normal. More...

double	OrbitVelocityAtR (const double GM, const double a, const double r)

glm::dvec3	OrbitTimeToVec3 (const Orbit &orb, const second &time)

double	CalculateTransferTime (const Orbit &orb1, const Orbit &orb2)

double	CalculateTransferAngle (const Orbit &start_orbit, const Orbit &end_orbit)

double	CalculatePhaseAngle (const Orbit &start_orbit, const Orbit &end_orbit, double epoch)

double	GetHyperbolicAsymptopeAnomaly (double eccentricity)

double	FlightPathAngle (double eccentricity, double v)

glm::dvec3	GetOrbitNormal (const Orbit &orbit)

double	TrueAnomalyFromVector (const Orbit &orbit, const glm::dvec3 &vec)

double	AscendingTrueAnomaly (const Orbit &start, const Orbit &dest)

Vec3AU	toVec3AU (const Orbit &orb, radian theta)
	Convert orbit to AU coordinates More...

glm::dvec3	toVec3 (const Orbit &orb, radian theta)
	Converts orbit to theta More...

glm::dvec3	toVec3 (const Orbit &orb)

Vec3AU	toVec3AU (const Orbit &orb)
	Converts orbit to AU coorrdinates. More...

void	UpdatePos (Kinematics &kin, const Orbit &orb)
	Updates the position of an orbit, in AU. More...

constexpr double	floatmod (double x, double y)

constexpr radian	normalize_radian (const radian &radian)
	Normalizes a radian to [0, PI*2) More...

constexpr double	normalize_radian_coord (const radian &radian)

constexpr degree	normalize_degree (const degree &radian)

constexpr astronomical_unit	toAU (kilometer km)

constexpr light_year	toLightYear (astronomical_unit au)

constexpr astronomical_unit	LtyrtoAU (light_year ltyr)

constexpr kilometer	toKm (astronomical_unit au)

constexpr radian	toRadian (degree theta)

constexpr degree	toDegree (radian theta)

constexpr double	operator""_deg (const long double deg)

constexpr double	operator""_au (const long double au)

Variables
constexpr double	PI = 3.14159265358979323846

constexpr double	TWOPI = PI * 2

constexpr double	HALFPI = PI / 2

constexpr double	KmInAu = 149597870.700

constexpr double	G = 6.6743015e-11

constexpr double	G_km = 6.6743015e-20

constexpr double	SunMu = 1.32712400188e11

Typedef Documentation

◆ astronomical_unit

typedef double cqsp::common::components::types::astronomical_unit

◆ degree

typedef double cqsp::common::components::types::degree

◆ earth_masses

typedef double cqsp::common::components::types::earth_masses

◆ joule

typedef double cqsp::common::components::types::joule

◆ kilogram

typedef double cqsp::common::components::types::kilogram

◆ kilometer

typedef double cqsp::common::components::types::kilometer

◆ light_year

typedef double cqsp::common::components::types::light_year

◆ meter_cube

typedef double cqsp::common::components::types::meter_cube

◆ PolarCoordinate

typedef PolarCoordinate_tp<types::astronomical_unit> cqsp::common::components::types::PolarCoordinate

◆ radian

typedef double cqsp::common::components::types::radian

◆ second

typedef double cqsp::common::components::types::second

◆ solar_mass

typedef double cqsp::common::components::types::solar_mass

◆ Vec3AU

typedef glm::dvec3 cqsp::common::components::types::Vec3AU

A vector3 where the units are astronomical units

Enumeration Type Documentation

◆ Distance

enum cqsp::common::components::types::Distance

Enumerator
LightYear
AstronomicalUnit
Kilometer
Meter
Centimeter
Millimeter

◆ UnitType

enum cqsp::common::components::types::UnitType

Enumerator
Distance
Angle
Mass
Volume
Time

Function Documentation

◆ ApplyImpulse()

Orbit cqsp::common::components::types::ApplyImpulse	(	const Orbit &	orbit,
		const glm::dvec3 &	impulse,
		double	time
	)

Applies impulse based on the vector impulse For some reason y is prograde, I'm not sure what the others are. TODO(EhWhoAmI): Determine the axis of thrust for each vector I think x is radial, and z is normal.

Parameters

orbit
impulse
time

Returns

◆ AscendingTrueAnomaly()

double cqsp::common::components::types::AscendingTrueAnomaly	(	const Orbit &	start,
		const Orbit &	dest
	)

◆ AvgOrbitalVelocity()

double cqsp::common::components::types::AvgOrbitalVelocity ( const Orbit & orb )

◆ CalculatePhaseAngle()

double cqsp::common::components::types::CalculatePhaseAngle	(	const Orbit &	start_orbit,
		const Orbit &	end_orbit,
		double	epoch
	)

◆ CalculateTransferAngle()

double cqsp::common::components::types::CalculateTransferAngle	(	const Orbit &	start_orbit,
		const Orbit &	end_orbit
	)

◆ CalculateTransferTime()

double cqsp::common::components::types::CalculateTransferTime	(	const Orbit &	orb1,
		const Orbit &	orb2
	)

◆ CalculateVelocity()

glm::dvec3 cqsp::common::components::types::CalculateVelocity	(	const double &	E,
		const kilometer &	r,
		const double &	GM,
		const kilometer &	a,
		const double &	e
	)

Calculates the vector velocity of the orbit

Parameters

[in]	E	Eccentric anomaly
[in]	r	Orbiting radius
[in]	GM	G*M of orbiting body
[in]	a	Semi major axis
[in]	e	eccentricity

◆ CalculateVelocityElliptic()

glm::dvec3 cqsp::common::components::types::CalculateVelocityElliptic	(	const double &	E,
		const double &	r,
		const double &	GM,
		const double &	a,
		const double &	e
	)

◆ CalculateVelocityHyperbolic()

glm::dvec3 cqsp::common::components::types::CalculateVelocityHyperbolic	(	const double &	E,
		const double &	r,
		const double &	GM,
		const double &	a,
		const double &	e
	)

◆ ConvertOrbParams()

glm::dvec3 cqsp::common::components::types::ConvertOrbParams	(	const double	LAN,
		const double	i,
		const double	w,
		const glm::dvec3 &	vec
	)

Transforms a vector to the orbital plane vector

All units are in radians

Parameters

LAN	Longitude of the ascending node
i	Inclination
w	Argument of periapsis
vec	Vector to convert

◆ ConvertToOrbitalVector()

glm::dvec3 cqsp::common::components::types::ConvertToOrbitalVector	(	const double	LAN,
		const double	i,
		const double	w,
		const double	v,
		const glm::dvec3 &	vec
	)

◆ EccentricAnomaly()

radian cqsp::common::components::types::EccentricAnomaly	(	double	v,
		double	e
	)

Calculates Eccentric anomaly

Parameters

v	True anomaly
e	Eccentricicy

Returns

◆ EccentricAnomalyToTrueAnomaly()

double cqsp::common::components::types::EccentricAnomalyToTrueAnomaly	(	const double &	ecc,
		const double &	E
	)

Calculates true anomaly from eccentricity and eccentric anomaly

Parameters

[in]	ecc	The eccentricity of the orbit
[in]	E	The eccentric anomaly of the orbit

◆ FlightPathAngle()

double cqsp::common::components::types::FlightPathAngle	(	double	eccentricity,
		double	v
	)

◆ floatmod()

constexpr double cqsp::common::components::types::floatmod	(	double	x,
		double	y
	)

inlineconstexpr

◆ GetCircularOrbitingVelocity()

double cqsp::common::components::types::GetCircularOrbitingVelocity	(	const double &	GM,
		const double &	radius
	)

Get the circular orbiting velocity for the radius.

◆ GetHyperbolicAsymptopeAnomaly()

double cqsp::common::components::types::GetHyperbolicAsymptopeAnomaly ( double eccentricity )

◆ GetLaunchAzimuth()

double cqsp::common::components::types::GetLaunchAzimuth	(	double	latitude,
		double	inclination
	)

Calculates the azimuth of the orbit based on the latitude and inclination

Parameters

latitude	Latitude in radians
inclination	Launch inclination in radians

Returns

◆ GetLaunchInclination()

double cqsp::common::components::types::GetLaunchInclination	(	double	latitude,
		double	azimuth
	)

Calculates the inclination of the orbit based on the latitude and azimuth

Parameters

latitude	Latitude in radians
azimuth	Launch azimuth in radians

Returns

◆ GetMtElliptic()

double cqsp::common::components::types::GetMtElliptic	(	const double &	M0,
		const double &	nu,
		const double &	time,
		const double &	epoch
	)

Gets the Mean anomaly from the time

Parameters

M0	Mean anomaly at t=0
nu	G*M of orbiting body
time	Current time

Returns

◆ GetMtHyperbolic()

double cqsp::common::components::types::GetMtHyperbolic	(	const double &	M0,
		const double &	nu,
		const double &	time,
		const double &	epoch
	)

Calculate mean anomaly from time for a hyperbolic object

Parameters

Mu	G*M of orbiting body
a	Semi-major axis
d+t	Time from periapsis

Returns

◆ GetOrbitingRadius()

double cqsp::common::components::types::GetOrbitingRadius	(	const double &	e,
		const double &	a,
		const double &	v
	)

◆ GetOrbitNormal()

glm::dvec3 cqsp::common::components::types::GetOrbitNormal ( const Orbit & orbit )

◆ GetTrueAnomaly()

double cqsp::common::components::types::GetTrueAnomaly	(	const Orbit &	orb,
		const second &	epoch
	)

Get anomaly at epoch

Parameters

orb
epoch

◆ GetTrueAnomalyToAsymptope()

double cqsp::common::components::types::GetTrueAnomalyToAsymptope ( const Orbit & orbit )

Calculates v_inf, the true anomaly for the asymtope for a hyperbolic orbit The orbit is bouded within -v_inf < v < v_inf https://orbital-mechanics.space/the-orbit-equation/hyperbolic-trajectories.html#hyperbolic-trajectories-e-1.

Parameters

orbit

Returns

◆ GreatCircleDistance()

double cqsp::common::components::types::GreatCircleDistance	(	SurfaceCoordinate &	coord1,
		SurfaceCoordinate &	coord2
	)

Calculates the angle between the two coordinates. Just multiply by the planet's diameter for fun and engagement.

Parameters

coord1
coord2

Returns

◆ HyperbolicAnomaly()

radian cqsp::common::components::types::HyperbolicAnomaly	(	double	v,
		double	e
	)

◆ HyperbolicAnomalyToTrueAnomaly()

double cqsp::common::components::types::HyperbolicAnomalyToTrueAnomaly	(	const double &	ecc,
		const double &	H
	)

◆ LtyrtoAU()

constexpr astronomical_unit cqsp::common::components::types::LtyrtoAU ( light_year ltyr )

inlineconstexpr

◆ MatrixConvertOrbParams()

glm::dvec3 cqsp::common::components::types::MatrixConvertOrbParams	(	const double	LAN,
		const double	i,
		const double	w,
		const glm::dvec3 &	vec
	)

◆ normalize_degree()

constexpr degree cqsp::common::components::types::normalize_degree ( const degree & radian )

inlineconstexpr

◆ normalize_radian()

constexpr radian cqsp::common::components::types::normalize_radian ( const radian & radian )

inlineconstexpr

Normalizes a radian to [0, PI*2)

Parameters

[in] Radian to normalizes

◆ normalize_radian_coord()

constexpr double cqsp::common::components::types::normalize_radian_coord ( const radian & radian )

inlineconstexpr

◆ operator""_au()

constexpr double cqsp::common::components::types::operator""_au ( const long double au )

inlineconstexpr

◆ operator""_deg()

constexpr double cqsp::common::components::types::operator""_deg ( const long double deg )

inlineconstexpr

◆ OrbitTimeToVec3()

glm::dvec3 cqsp::common::components::types::OrbitTimeToVec3	(	const Orbit &	orb,
		const second &	time
	)

◆ OrbitToVec3()

glm::dvec3 cqsp::common::components::types::OrbitToVec3	(	const double &	a,
		const double &	e,
		const radian &	i,
		const radian &	LAN,
		const radian &	w,
		const radian &	v
	)

Converts an orbit to a vec3.

Parameters

a	Semi major axis (unit doesn't matter)
e	Eccentricity (Dimensionless)
i	Inclinations (radians)
LAN	Longitude of ascending node (radians)
w	Argument of periapsis (radians)
v	True anomaly (radians)

Returns: The vec3, in whatever unit a was.

◆ OrbitVelocity()

double cqsp::common::components::types::OrbitVelocity	(	const double	v,
		const double	e,
		const double	a,
		const double	GM
	)

◆ OrbitVelocityAtR()

double cqsp::common::components::types::OrbitVelocityAtR	(	const double	GM,
		const double	a,
		const double	r
	)

◆ OrbitVelocityToVec3() [1/2]

glm::dvec3 cqsp::common::components::types::OrbitVelocityToVec3 ( const Orbit & orb )

◆ OrbitVelocityToVec3() [2/2]

glm::dvec3 cqsp::common::components::types::OrbitVelocityToVec3	(	const Orbit &	orb,
		double	v
	)

◆ SolveKeplerElliptic()

double cqsp::common::components::types::SolveKeplerElliptic	(	const double &	mean_anomaly,
		const double &	ecc,
		const int	steps = `200`
	)

Computes eccentric anomaly for a elliptic or circular orbit (e < 1) in radians given mean anomaly and eccentricity

Parameters

mean_anomaly
ecc
steps	Number of steps for the Newton-Raphson. More steps means more precision but less speed

Returns: Eccentric anomaly (E)goog

◆ SolveKeplerHyperbolic()

double cqsp::common::components::types::SolveKeplerHyperbolic	(	const double &	mean_anomaly,
		const double &	ecc,
		const int	steps = `200`
	)

Computes eccentric anomaly for a hyperbolic or parabolic orbit (e > 1) in radians given mean anomaly and eccentricity

Parameters

mean_anomaly
ecc
steps	Number of steps for the Newton-Raphson. More steps means more precision but less speed

Returns

◆ toAU()

constexpr astronomical_unit cqsp::common::components::types::toAU ( kilometer km )

inlineconstexpr

◆ toDegree()

constexpr degree cqsp::common::components::types::toDegree ( radian theta )

inlineconstexpr

◆ toKm()

constexpr kilometer cqsp::common::components::types::toKm ( astronomical_unit au )

inlineconstexpr

◆ toLightYear()

constexpr light_year cqsp::common::components::types::toLightYear ( astronomical_unit au )

inlineconstexpr

◆ toRadian()

constexpr radian cqsp::common::components::types::toRadian ( degree theta )

inlineconstexpr

◆ ToSurfaceCoordinate()

SurfaceCoordinate cqsp::common::components::types::ToSurfaceCoordinate ( const glm::vec3 & vec )

◆ toVec3() [1/4]

glm::dvec3 cqsp::common::components::types::toVec3 ( const Orbit & orb )

inline

◆ toVec3() [2/4]

glm::dvec3 cqsp::common::components::types::toVec3	(	const Orbit &	orb,
		radian	theta
	)

inline

Converts orbit to theta

Parameters

orb
theta	True anomaly (radians)

Returns

◆ toVec3() [3/4]

glm::vec3 cqsp::common::components::types::toVec3 ( const PolarCoordinate & coordinate )

inline

2D polar coordinate to opengl 3d coordinate

Parameters

coordinate

Returns

◆ toVec3() [4/4]

glm::vec3 cqsp::common::components::types::toVec3	(	const SurfaceCoordinate &	coord,
		const float &	radius
	)

Converts surface coordinate to vector3 in space so that we can get the surface coordinate to render in space

◆ toVec3AU() [1/2]

Vec3AU cqsp::common::components::types::toVec3AU ( const Orbit & orb )

inline

Converts orbit to AU coorrdinates.

Parameters

orb	[in] orbit of the object to convert

Returns: Vector 3 in orbit, in AU

◆ toVec3AU() [2/2]

Vec3AU cqsp::common::components::types::toVec3AU	(	const Orbit &	orb,
		radian	theta
	)

inline

Convert orbit to AU coordinates

Parameters

orb	Orbit
theta	Theta to compute

Returns: Vector 3 in orbit, in AU

◆ TrueAnomalyElliptic() [1/2]

radian cqsp::common::components::types::TrueAnomalyElliptic	(	const Orbit &	orbit,
		const second &	time
	)

Parameters

orbit	[in] Orbit to compute
time	[in] Current time (seconds)
E_put	[out] Eccentric anomaly

Returns: True anomaly in radians

◆ TrueAnomalyElliptic() [2/2]

radian cqsp::common::components::types::TrueAnomalyElliptic	(	const Orbit &	orbit,
		const second &	time,
		double &	E_out
	)

◆ TrueAnomalyFromVector()

double cqsp::common::components::types::TrueAnomalyFromVector	(	const Orbit &	orbit,
		const glm::dvec3 &	vec
	)

◆ TrueAnomalyHyperbolic()

radian cqsp::common::components::types::TrueAnomalyHyperbolic	(	const Orbit &	orbit,
		const second &	time
	)

◆ UpdateOrbit()

void cqsp::common::components::types::UpdateOrbit	(	Orbit &	orb,
		const second &	time
	)

Updates the orbit's true anomaly.

You need to call it before calculating anything to do with the orbit

Parameters

orb
time

◆ UpdatePos()

void cqsp::common::components::types::UpdatePos	(	Kinematics &	kin,
		const Orbit &	orb
	)

inline

Updates the position of an orbit, in AU.

Parameters

kin	[out] the kinematics of the orbit
orb	[in] the orbit of the orbit

◆ Vec3ToOrbit()

Orbit cqsp::common::components::types::Vec3ToOrbit	(	const glm::dvec3 &	position,
		const glm::dvec3 &	velocity,
		const double &	GM,
		const double &	time
	)

Converts position and velocity to orbit. Note: you will have to set the reference body after the orbit is returned

Parameters

position	Position of the body
velocity	Velocity of the body
GM	G*M of the orbiting body

Variable Documentation

◆ G

constexpr double cqsp::common::components::types::G = 6.6743015e-11

constexpr

◆ G_km

constexpr double cqsp::common::components::types::G_km = 6.6743015e-20

constexpr

◆ HALFPI

constexpr double cqsp::common::components::types::HALFPI = PI / 2

constexpr

◆ KmInAu

constexpr double cqsp::common::components::types::KmInAu = 149597870.700

constexpr

◆ PI

constexpr double cqsp::common::components::types::PI = 3.14159265358979323846

constexpr

◆ SunMu

constexpr double cqsp::common::components::types::SunMu = 1.32712400188e11

constexpr

◆ TWOPI

constexpr double cqsp::common::components::types::TWOPI = PI * 2

constexpr

Classes

Typedefs

Enumerations

Functions

Variables

Typedef Documentation

◆ astronomical_unit

◆ degree

◆ earth_masses

◆ joule

◆ kilogram

◆ kilometer

◆ light_year

◆ meter_cube

◆ PolarCoordinate

◆ radian

◆ second

◆ solar_mass

◆ Vec3AU

Enumeration Type Documentation

◆ Distance

◆ UnitType

Function Documentation

◆ ApplyImpulse()

◆ AscendingTrueAnomaly()

◆ AvgOrbitalVelocity()

◆ CalculatePhaseAngle()

◆ CalculateTransferAngle()

◆ CalculateTransferTime()

◆ CalculateVelocity()

◆ CalculateVelocityElliptic()

◆ CalculateVelocityHyperbolic()

◆ ConvertOrbParams()

◆ ConvertToOrbitalVector()

◆ EccentricAnomaly()

◆ EccentricAnomalyToTrueAnomaly()

◆ FlightPathAngle()

◆ floatmod()

◆ GetCircularOrbitingVelocity()

◆ GetHyperbolicAsymptopeAnomaly()

◆ GetLaunchAzimuth()

◆ GetLaunchInclination()

◆ GetMtElliptic()

◆ GetMtHyperbolic()

◆ GetOrbitingRadius()

◆ GetOrbitNormal()

◆ GetTrueAnomaly()

◆ GetTrueAnomalyToAsymptope()

◆ GreatCircleDistance()

◆ HyperbolicAnomaly()

◆ HyperbolicAnomalyToTrueAnomaly()

◆ LtyrtoAU()

◆ MatrixConvertOrbParams()

◆ normalize_degree()

◆ normalize_radian()

◆ normalize_radian_coord()

◆ operator""_au()

◆ operator""_deg()

◆ OrbitTimeToVec3()

◆ OrbitToVec3()

◆ OrbitVelocity()

◆ OrbitVelocityAtR()

◆ OrbitVelocityToVec3() [1/2]

◆ OrbitVelocityToVec3() [2/2]

◆ SolveKeplerElliptic()

◆ SolveKeplerHyperbolic()

◆ toAU()

◆ toDegree()

◆ toKm()

◆ toLightYear()

◆ toRadian()

◆ ToSurfaceCoordinate()

◆ toVec3() [1/4]

◆ toVec3() [2/4]

◆ toVec3() [3/4]

◆ toVec3() [4/4]

◆ toVec3AU() [1/2]

◆ toVec3AU() [2/2]

◆ TrueAnomalyElliptic() [1/2]

◆ TrueAnomalyElliptic() [2/2]