Main differences between V4.17 and V4.16

PATRIUS V4.17 is a major release adding some new features and correcting some bugs.

New functionalities

• When reading SP3 files, if the accuracy was not present, the parsing failed. This behavior has been modified to allow the parsing of files without accuracy. In that case, the accuracy is set to “0”. This is an impossible value of accuracy since in the SP3 file it is expressed as 2^n, so it is easy for the user to identify the values that have not been read.
• To construct a SurfaceDistanceDetector, the CelestialBody attribute has been replaced by a BodyShape. Moreover, the getBody() method from DistanceDetector has been renamed getTarget().
• The LaguerreSolver has been modifier to accept as input the maximum number of iterations allowed as well as multiple initial guesses (and their respective maximum iterations)
• A new solver PolynomialRootsFinder that computes the roots for a polynomial using the eigenvalues of the companion matrix A of the input polynomial has been added to Patrius
• It is now possible to define an extrapolation function builder in TimeStampedInterpolableEphemeris to complete the interpolation with an extrapolation feature on the left and right side of the samples. A new TimeStampedExtrapolationFunctionBuilder interface is created with no standard implementation.
• New feature in ApparentRadiusProvider allowing to compute the apparent radius of the occulting body from the spacecraft (observer) position given a specific direction to describe the computation plane. In comparison, the existing method predefine this plane with the direction of the occulted object. The rest of the method / behavior stays identical.
• BodyShape implements ApparentRadiusProvider and VariableRadiusProvider is deleted.
• New feature RealMatrix#getDeterminant() to compute the determinant value directly from the matrix instead of having to use the appropriate decomposition solver on the matrix. Also, new feature in ArithmeticUtilsTest to compute all the permutations from a double vector (equivalent to “perms” function in MatLab).
• New class AnomalyUtils to centralize every conversion methods between mean, eccentric and true anomalies.
• It is now possible to accept the non-optimal range interpolation in AbstractBoundedPVProvider (i.e. : EphemerisPvLagrange and EphemerisPvHermite)
• New constructors to build a LofOffset directly from a Rotation object
• New constructor in SensorVisibilityDetector to describe the SatToSatLinkType/LinkType (before it was forced to be in SECONDARY_TO_MAIN mode)
• Users can now read special TDB segments contained in BSP files in order to build a TDB model with TT-TDB offsets.
• New body point solar incidence detector based on the angle between the interest point-satellite vector and the interest point-sun vector.
• Possibility to provide an AbstractHarmonicGravityModel to a ThirdBodyAttraction in order to take into account the gravitational effects of the central body on this third body. The implemented modifications model the attraction of the third body γ as follows: γ = γ(third body → spacecraft) - γ(third body → central body).
• CELESTLAB inspired mission analysis functionalities added: InterplanetaryUtils (SOI computation, DV needed to join / leave an hyperbolic orbit from / to an elliptical one), ProgDetectorUtils (EventDetector wrapper used to compute intervals), EventUtils (Computation of shadow zones, visibility windows and geometry between a satellite and its target), KeplerianParamUtils (computation and conversion of several kerplerian orbit characteristics) and KeplerianParamComputer (Computation of all keplerian characteristics pertaining to an orbit defined with a semi-major axis, eccentricity and true anomaly)

Bugs fixes

• The class StrictAttitudeLegsSequence can now be serialized (also, the interfaces MultiEventDetector, TimeSequence & TimeStamped extend Serializable).
• SP3 format expresses the accuracy in mm but Patrius interprets it as m. The conversion was missing.
• The interface MultiOrbitalCovarianceProvider (since 4.16) define a default implementation for its getOrbitalCovarianceProvider method.
• Fix the local time’s signal propagation computation in BodyPointLocalTimeAngleDetector.
• Fix the ConvergenceException exist only when the threshold value is reached in CartesianOrbit#meanToEccentric, CartesianOrbit#meanToHyperbolicEccentric, FacetBodyShape#getApparentRadius, CircularParameters#hyperbolicMeanToEccentric and KeplerianParameters#meanToHyperbolicEccentric
• Generalize the behavior to throw a ConvergenceException when the convergence algorithm failed in AlternateEquinoctialParameters#getLE, CircularParameters#ellipticMeanToEccentric and EquinoctialParameters#meanToEccentric
• Fix the use of the deprecated PatriusMessages.DIMENSIONS_MISMATCH error message using an explicit message instead.
• In AbstractEllipsoidBodyShape#getApparentRadius the ellipsoid’s B radius was defined uncorrectly which may result in incorrect radius computation.
• In the LineMaskingDetector detector, the case when mainElement isn’t null is now well managed.
• In AbstractBodyAttraction, the acceleration derivatives with respect to the parameter K is now computed in the input frame instead of being computed in the body frame.
• In SolarTimeAngleDetector and in AlignmentDetector the sun (respectively the body) is now expressed in the working frame, corresponding to the first pseudo-inertial frame ancestor, when the spacecraft state’s frame isn’t pseudo-inertial.
• Fix the body masking distance and the spacecraft masking distance computation in in SensorVisibilityDetector#g (uses LinkType.DOWNLINK instead of LinkType.UPLINK)
• Fix the UserIAUPole#getAngularCoordinates#ICRF_TO_INERTIAL computation by using Euler angles