constants updated and enriched

doc/constants.rst

@@ -15,22 +15,26 @@ the various `pykep` objects and functionalities.
      - Symbol in pykep
      - Units
      - Value
-   * - Astronomical Unit
+   * - Astronomical Unit 
      - pykep.AU
      - :math:`m` 
-     - 149597870700.0
+     - 1.495978707e+11
    * - Cavendish constant
      - pykep.CAVENDISH
-     - :math:`\frac{N m^2}{kg^2}` 
-     - 7.36687e-10
+     - :math:`\frac{m^3}{sec^2 kg}` 
+     - 6.67430e-11
    * - Sun's gravitational parameter
      - pykep.MU_SUN
      - :math:`\frac{m^3}{sec^2}` 
-     - 1.32712440018e+20
-   * - Earth's gravitational parameter
+     - 1.32712440041279419e20
+   * - Earth's gravitational parameter (JPL DE440)
      - pykep.MU_EARTH
      - :math:`\frac{m^3}{sec^2}` 
-     - 398600441800000.0
+     - 3.98600435507e+14
+   * - Moon's gravitational parameter (JPL DE440)
+     - pykep.MU_MOON
+     - :math:`\frac{m^3}{sec^2}` 
+     - 4.902800118e+12
    * - Earth's velocity
      - pykep.EARTH_VELOCITY
      - :math:`\frac{m}{sec}` 
@@ -43,6 +47,10 @@ the various `pykep` objects and functionalities.
      - pykep.EARTH_J2
      - --
      - 0.00108262668
+   * - CR3BP: Moon-Earth parameter
+     - pykep.CR3BP_EARTH_MOON
+     - --
+     - 0.01215058439470971
    * - Seconds in one day
      - pykep.DAY2SEC
      - --
@@ -51,3 +59,7 @@ the various `pykep` objects and functionalities.
      - pykep.RAD2DEG
      - --
      - 57.29577951308232
+   * - Radians in one degree
+     - pykep.DEG2RAD
+     - --
+     - 0.017453292519943295

doc/propagation.rst

@@ -12,7 +12,7 @@ seamlessly via variational equations.
 
 The main routines are listed here:
 
-Keplerian dynamics 
+Keplerian 
 ******************
 
 .. currentmodule:: pykep
@@ -23,7 +23,7 @@ Keplerian dynamics
 
 ---------------------------------------------------------
 
-Non-Keplerian dynamics
+Non-Keplerian 
 ************************
 
 .. currentmodule:: pykep

include/kep3/core_astro/constants.hpp

@@ -22,14 +22,13 @@ enum elements_type {
     MEQ_R,  // Modified Equinoctial Elements (retrogade)
     POSVEL, // position and Velocity
 };
-
 inline constexpr double pi = boost::math::constants::pi<double>();
 inline constexpr double half_pi = boost::math::constants::half_pi<double>();
-
-inline constexpr double AU = 149597870700.0;                 // Astronomical Unit (m)
-inline constexpr double CAVENDISH = 73.6687e-11;             // Cavendish constant (N M^2 / kg^2)
-inline constexpr double MU_SUN = 1.32712440018e20;           // Sun's gravitational parameter (m^3/s^2 kg)
-inline constexpr double MU_EARTH = 398600441800000.0;        // Earth's gravitational parameter (m^3/s^2 kg)
+inline constexpr double AU = 149597870700.0;                 // Astronomical Unit (m) - IAU 2012 Resolution B1
+inline constexpr double CAVENDISH = 6.67430e-11;             // Cavendish constant (m^3/s^2/kg)
+inline constexpr double MU_SUN = 1.32712440041279419e20;     // Sun's gravitational parameter (m^3/s^2 kg) - DE440
+inline constexpr double MU_EARTH = 398600435507000.0;        // Earth's gravitational parameter (m^3/s^2 kg) - DE440
+inline constexpr double MU_MOON =  4902800118000.0;          // Moon's gravitational parameter (m^3/s^2 kg) - DE440
 inline constexpr double EARTH_VELOCITY = 29784.691831696804; // Earth's velocity. (m/s)
 inline constexpr double EARTH_J2 = 1.08262668E-03;
 inline constexpr double EARTH_RADIUS = 6378137; // Earth's radius (m)
@@ -39,6 +38,8 @@ inline constexpr double DAY2SEC = 86400.0;
 inline constexpr double SEC2DAY = (1. / DAY2SEC);
 inline constexpr double DAY2YEAR = (1. / 365.25);
 inline constexpr double G0 = 9.80665; // Acceleration at Earth's surface (m/s^2)
+inline constexpr double CR3BP_EARTH_MOON = 0.01215058439470971; // (M_moon + M_Earth) / M_Earth
+
 
 } // namespace kep3
 

pykep/core.cpp

@@ -57,10 +57,12 @@ PYBIND11_MODULE(core, m)
     m.attr("EARTH_J2") = py::float_(kep3::EARTH_J2);
     m.attr("EARTH_RADIUS") = py::float_(kep3::EARTH_RADIUS);
     m.attr("RAD2DEG") = py::float_(kep3::RAD2DEG);
+    m.attr("DEG2RAD") = py::float_(kep3::RAD2DEG);
     m.attr("DAY2SEC") = py::float_(kep3::DAY2SEC);
     m.attr("SEC2DAY") = py::float_(kep3::SEC2DAY);
     m.attr("DAY2YEAR") = py::float_(kep3::DAY2YEAR);
     m.attr("G0") = py::float_(kep3::G0);
+    m.attr("CR3BP_EARTH_MOON") = py::float_(kep3::CR3BP_EARTH_MOON);
 
     // We expose here global enums:
     py::enum_<kep3::elements_type>(m, "el_type", "")

pykep/docstrings.cpp

@@ -1286,7 +1286,7 @@ std::string get_stark_docstring()
 {
     return R"(get_stark(tol)
 
-Gets the Taylor adaptive propagator (Heyoka) for the Stark problem from the global cache and returns a copy.
+Returns a Taylor adaptive propagator (Heyoka) for the Stark problem retreiving one from a global cache and making a copy. 
 
 In `pykep`, abusing a term well established in electrodynamics, 
 this is the initial value problem of a fixed inertial thrust mass-varying spacecraft orbiting a main body.
@@ -1320,7 +1320,7 @@ std::string get_stark_var_docstring()
 {
     return R"(get_stark_var(tol)
 
-Gets the variational (order 1) Taylor adaptive propagator (Heyoka) for the Stark problem from the global cache and returns a copy.
+Returns a (order 1) variational Taylor adaptive propagator (Heyoka) for the Stark problem retreiving one from a global cache and making a copy. 
 
 .. note:
    Variations are only considered with repsect to initial conditions and the fixed inertial thurst.

test/ta_cr3bp_test.cpp

@@ -65,6 +65,7 @@ TEST_CASE("dynamics")
         std::vector<double> ic{1.01238082345234, -0.0423523523454,  0.22634376321,
                                -0.1232623614,    0.123462698209365, 0.123667064622};
         std::copy(ic.begin(), ic.end(), ta.get_state_data());
+        // Assign value for cis-lunar case. (note: not the official pykep on in this case)
         *ta.get_pars_data() = 0.01215058560962404;
         auto out = ta.propagate_until(5.7856656782589234);
         std::vector<double> const ground_truth = {0.43038358727124, -1.64650668902846, 0.10271923139472,
@@ -90,6 +91,7 @@ TEST_CASE("variational_dynamics")
         std::vector<double> ic{1.01238082345234, -0.0423523523454,  0.22634376321,
                                -0.1232623614,    0.123462698209365, 0.123667064622};
         std::copy(ic.begin(), ic.end(), ta.get_state_data());
+        // Assign value for cis-lunar case. (note: not the official pykep on in this case)
         *ta.get_pars_data() = 0.01215058560962404;
         auto out = ta.propagate_until(5.7856656782589234);
         std::vector<double> const ground_truth = {0.43038358727124, -1.64650668902846, 0.10271923139472,