Class MoonMeanDynamics

• Defined in File numerical_orbit_dynamics.h

Inheritance Relationships

Base Type

• public lupnt::NumericalDynamics (Class NumericalDynamics)

Class Documentation

class MoonMeanDynamics : public lupnt::NumericalDynamics

Public Functions

MoonMeanDynamics()

virtual VecX ComputeRates(Real t, const State &x) const override

inline virtual StateType GetStateType() const override

Return the StateType tag of the state vector this dynamics model operates on (e.g. Cart6::TYPE, Attitude::TYPE, ClockState3::TYPE).

Used by state-converters and asset wiring code to verify that a dynamics object is paired with a compatible state representation.

virtual State Propagate(const State &x0, Real t0, Real tf, const State *u = nullptr) override

Propagate the state from t0 to tf without computing a state transition matrix.

This is the core propagation entry point implemented by every concrete dynamics class (e.g. NumericalDynamics::Propagate, AnalyticalDynamics::Propagate, ClockDynamics::Propagate). It is called once per integration/measurement step by simulation drivers in applications/ and by agents/ to advance an object’s true or estimated state.

Parameters:

• x0 – Initial state at time t0 (layout/units defined by the subclass).

• t0 – Initial epoch [s, TDB since J2000 for orbit/attitude dynamics].

• tf – Final epoch [s, TDB since J2000 for orbit/attitude dynamics].

• u – Optional control/forcing input (e.g. thrust, RTN reference state); nullptr if unused.

Returns:

Propagated state at time tf.

virtual State Propagate(const State &x0, Real t0, Real tf, const State *u, MatXd *stm)

Propagate the state and compute the state transition matrix (STM) d(xf)/d(x0) via automatic differentiation.

Default implementation: if stm == nullptr, forwards to the no-STM Propagate overload; otherwise wraps Propagate(x0, t0, tf, u) in an autodiff Jacobian (jacobian(...)) with respect to x0. Used by filters (filters/) that need the linearized state transition for covariance propagation (e.g. EKF/UKF time updates).

Parameters:

• x0 – Initial state at time t0.

• t0 – Initial epoch [s, TDB since J2000].

• tf – Final epoch [s, TDB since J2000].

• u – Optional control/forcing input; nullptr if unused.

• stm – Output: state transition matrix d(xf)/d(x0); left unmodified if nullptr.

Returns:

Propagated state at time tf.

virtual MatX Propagate(const State &x0, const VecX &tfs, const State *u = nullptr)

Propagate the state to a sequence of output epochs.

Repeatedly calls Propagate(x0, t0, tf, u) between consecutive entries of tfs, accumulating each result as a row of the returned matrix. Used by applications/ and analysis scripts to generate a full trajectory time history in one call, with optional progress-bar output (see SetPrintProgress).

Parameters:

• x0 – Initial state at tfs(0).

• tfs – Vector of output epochs [s, TDB since J2000], including the initial epoch as tfs(0).

• u – Optional control/forcing input applied at every step; nullptr if unused.

Returns:

Matrix whose i-th row is the propagated state at tfs(i).