Keplerian Elements

vec2orbElem(rs, vs, mus) converts the position vector (rs) and velocity vector (vs) of an object into Keplerian orbital elements using the gravitational parameter (mus). Input:- rs: 3n x 1 stacked initial position vector:[r1(1); r1(2); r1(3); r2(1); r2(2); r2(3); ...; rn(1); rn(2); rn(3)]or 3 x n position matrix.- vs: 3n x 1 stacked initial velocity vector or 3 x n matrix.- mus: gravitational parameter (G*m_i) where G is the gravitational constant and m_i is the mass of the i-th object. If all vectors represent the same object, mus can be a scalar. Output:- a: semi-major axis- e: eccentricity- E: eccentric anomaly- i: inclination- omega: argument of periapsis- Omega: longitude of ascending node- P: orbital period- tau: time of periapsis passage- A, B: direction matrices (see Vinti, 1998) All units must be consistent; for example, if position is in AU, time should be in days.

使用非NaN元素在二维数组中插入NaN元素。也可以外推，因为它不使用数据的三角剖分。Inpaint_nans提供了几种不同的插值方法，可以在准确性与速度和所需内存之间进行权衡。目前在inpaint_nans中发现的所有方法都基于稀疏线性代数和PDE离散化。本质上，PDE被求解为与提供的信息一致。