Two-body Keplerian orbit propagation
Add ocaml-vec3: shared 3D vector type
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lib/analytic.ml
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lib/analytic.ml
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let period el = if el.a <= 0. then infinity (* hyperbolic *) else twopi /. el.n
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let eccentricity el = el.e
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let semi_major_axis el = el.a
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let inclination el = el.i
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let pp ppf el = Fmt.pf ppf "a=%.3f km e=%.6f i=%.4f rad" el.a el.e el.i
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(** {1 Public API} *)
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lib/analytic.mli
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lib/analytic.mli
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val eccentricity : elements -> float
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(** [eccentricity el] is the orbital eccentricity. *)
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val semi_major_axis : elements -> float
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(** [semi_major_axis el] is the semi-major axis in km. *)
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val inclination : elements -> float
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(** [inclination el] is the orbital inclination in radians. *)
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val pp : elements Fmt.t
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(** Pretty-print orbital elements. *)
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(** {1 Propagation} *)
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val at : pos:Vec3.t -> vel:Vec3.t -> dt:float -> Vec3.t
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lib/vec3.ml
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lib/vec3.ml
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}
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let length v = sqrt ((v.x *. v.x) +. (v.y *. v.y) +. (v.z *. v.z))
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let normalize v =
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let n = length v in
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if n < 1e-15 then v else scale (1.0 /. n) v
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let negate v = { x = -.v.x; y = -.v.y; z = -.v.z }
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let equal ?(eps = 1e-12) a b =
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Float.abs (a.x -. b.x) <= eps
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&& Float.abs (a.y -. b.y) <= eps
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&& Float.abs (a.z -. b.z) <= eps
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let pp ppf v = Fmt.pf ppf "(%g, %g, %g)" v.x v.y v.z
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lib/vec3.mli
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lib/vec3.mli
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(** 3D vector operations. *)
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(** 3D vector operations.
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Provides basic arithmetic, products, and comparison for three-component
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floating-point vectors used throughout the orbital mechanics libraries. *)
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type t = { x : float; y : float; z : float }
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val length : t -> float
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(** [length v] is the Euclidean length. *)
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val normalize : t -> t
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(** [normalize v] returns the unit vector in the direction of [v]. Returns [v]
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unchanged if its length is near zero. *)
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val negate : t -> t
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(** [negate v] is the component-wise negation of [v]. *)
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val equal : ?eps:float -> t -> t -> bool
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(** [equal ?eps a b] is [true] when each component differs by at most [eps]
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(default [1e-12]). *)
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val pp : t Fmt.t
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(** [pp] pretty-prints a vector. *)