Class astrea::astro::LambertSolver¶

ClassList > astrea > astro > LambertSolver

Class for solving Lambert's problem. More...

#include <LambertSolver.hpp>

Public Types¶

Type	Name
enum EnumType	OrbitDirection Enum class for orbit direction.

Public Functions¶

Type	Name
	LambertSolver () = delete Deleted constructor for LambertSolver .
	~LambertSolver () = delete Deleted destructor for LambertSolver .

Public Static Functions¶

Type	Name
Cartesian	solve (const Cartesian & state0, const Time & dt, const GravParam & mu) Solve Lambert's problem for a given initial and final state. Returns the minimum energy solution.
std::pair< VelocityVector< frames::earth::icrf >, VelocityVector< frames::earth::icrf > >	solve (const RadiusVector< frames::earth::icrf > & r0, const RadiusVector< frames::earth::icrf > & rf, const Time & dt, const GravParam & mu, const OrbitDirection & direction) Solve Lambert's problem for a given initial and final state. Returns the minimum energy solution.

Detailed Description¶

This class provides methods for solving Lambert's problem, which involves finding the orbital trajectory between two points in space given certain initial conditions.

Public Types Documentation¶

enum OrbitDirection¶

Enum class for orbit direction.

enum astrea::astro::LambertSolver::OrbitDirection {
    PROGRADE,
    RETROGRADE
};

Public Functions Documentation¶

function LambertSolver¶

Deleted constructor for LambertSolver .

astrea::astro::LambertSolver::LambertSolver () = delete

This constructor is deleted to prevent instantiation of the LambertSolver class.

function ~LambertSolver¶

Deleted destructor for LambertSolver .

astrea::astro::LambertSolver::~LambertSolver () = delete

This destructor is deleted to prevent destruction of the LambertSolver class.

Public Static Functions Documentation¶

function solve [1/2]¶

Solve Lambert's problem for a given initial and final state. Returns the minimum energy solution.

static Cartesian astrea::astro::LambertSolver::solve (
    const Cartesian & state0,
    const Time & dt,
    const GravParam & mu
)

Parameters:

state0 The initial state (position and velocity) of the spacecraft.
dt The time of flight.
mu The gravitational parameter of the central body.

Returns:

The final state (position and velocity) of the spacecraft.

function solve [2/2]¶

Solve Lambert's problem for a given initial and final state. Returns the minimum energy solution.

static std::pair< VelocityVector < frames::earth::icrf >, VelocityVector < frames::earth::icrf > > astrea::astro::LambertSolver::solve (
    const RadiusVector < frames::earth::icrf > & r0,
    const RadiusVector < frames::earth::icrf > & rf,
    const Time & dt,
    const GravParam & mu,
    const OrbitDirection & direction
)

Parameters:

r0 The initial position of the spacecraft.
rf The final position of the spacecraft.
dt The time of flight.
mu The gravitational parameter of the central body.
direction The direction of the orbit (prograde or retrograde).

Returns:

A pair of velocity vectors (initial and final) for the spacecraft.

The documentation for this class was generated from the following file astrea/astro/astro/propagation/analytic/LambertSolver.hpp