My dev (typos only)

source/base/angle.h

@@ -19,7 +19,7 @@
 
 /** @brief Angle in radians.
 * @ingroup vector3dGroup
-* Its only used to distinguish between doubles and angles in input/output.
+* It's only used to distinguish between doubles and angles in input/output.
 * Angle is converted from/to degrees in input/output. */
 class Angle
 {

source/base/ellipsoid.h

@@ -40,7 +40,7 @@ class Ellipsoid
 
   /** @brief Transformation ellipsoidal coordinates in @a Vector3d.
   * @param L longitude (-PI,PI]
-  * @param B latitude [-PI,PI]
+  * @param B latitude [-PI/2,PI/2]
   * @param h height [m]
   */
   const Vector3d operator()(Angle L, Angle B, Double h) const;

source/base/portable.h

@@ -5,7 +5,7 @@
 * @brief Define standard types.
 *
 * This is important to account for different systems.
-* e.g. 'int' have some times 16 Bit or 32 Bit size.
+* e.g. 'int' have sometimes 16 Bit or 32 Bit size.
 *
 * @author Torsten Mayer-Guerr
 * @date 2004-10-25
@@ -36,7 +36,7 @@
 
 /** @brief Standard types.
 * This is important to account for different systems.
-* e.g. 'int' have some times 16 Bit or 32 Bit size.
+* e.g. 'int' have sometimes 16 Bit or 32 Bit size.
 */
 //@{
 typedef float             Float;

source/config/config.cpp

@@ -710,7 +710,7 @@ void ProgramConfig::run(VariableList &variableList, Parallel::CommunicatorPtr co
         {
           std::string comment;
           StackNode top = config.stack.top();
-          config.stack.pop(); // coment is given in <program> not in <choiceElement>
+          config.stack.pop(); // comment is given in <program> not in <choiceElement>
           XmlAttrPtr attr = config.stack.top().xmlNode->getAttribute("comment");
           if(attr)
             comment = attr->getText();

source/files/fileGriddedData.cpp

@@ -230,10 +230,10 @@ template<> void load(InArchive &ar, GriddedData &x)
   for(UInt i=0; i<pointCount; i++)
   {
     ar>>beginGroup("points");
-    ar>>nameValue("longitude", lat);
-    ar>>nameValue("latitude",  lon);
+    ar>>nameValue("longitude", lon);
+    ar>>nameValue("latitude",  lat);
     ar>>nameValue("height",    h);
-    x.points.at(i) = x.ellipsoid(lat, lon, h);
+    x.points.at(i) = x.ellipsoid(lon, lat, h);
     if(hasArea)
       ar>>nameValue("areas",  x.areas.at(i));
     for(UInt k=0; k<x.values.size(); k++)

source/plot/plotMapLayer.cpp

@@ -30,14 +30,14 @@
 // Latex documentation
 static const char *docstringPlotMapLayerGrid = R"(
 \subsection{GriddedData}
-Creates a regular grid of yxz values. The standard \reference{dataVariables}{general.parser:dataVariables}
+Creates a regular grid of xyz values. The standard \reference{dataVariables}{general.parser:dataVariables}
 are available to select the data column of \configFile{inputfileGriddedData}{griddedData}.
 Empty grid cells are not plotted. Cells with more than one value will be set to the mean value.
 The grid spacing can be determined automatically for regular rectangular grids otherwise
 it must be set with \config{increment}. To get a better display together with some projections
 the grid should be internally \config{resample}d to higher resolution.
 It is assumed that the points of \configFile{inputfileGriddedData}{griddedData} represents centers of grid cells.
-This assumption can be changed with \config{gridlineRegistered} (e.g if the data starts at the north pole).
+This assumption can be changed with \config{gridlineRegistered} (e.g. if the data starts at the north pole).
 )";
 
 class PlotMapLayerGrid : public PlotMapLayer

source/programs/preprocessing/preprocessingVariationalEquation.cpp

@@ -13,23 +13,23 @@
 // Latex documentation
 #define DOCSTRING docstring
 static const char *docstring = R"(
-This program integrates an orbit dynamically using the given forces and setup the state transition matrix
-for each time step. These are the prerequisite for a least squares adjustement (e.g. gravity field determination) using
-the variational equation approach. The variational equations are computed arc wise as defined by \configFile{inputfileOrbit}{instrument}.
-This means for each arc new initial state parameters are setup.
+This program integrates an orbit dynamically using the given forces and set up the state transition matrix
+for each time step. These are the prerequisites for a least squares adjustment (e.g. gravity field determination) using
+the variational equation approach. The variational equations are computed arc-wise as defined by \configFile{inputfileOrbit}{instrument}.
+This means for each arc new initial state parameters are set up.
 
 In a first step the \configClass{forces}{forcesType} acting on the satellite are evaluated at the apriori positions given
-by \configFile{inputfileOrbit}{instrument}. Non-conservative forces like solar radiation pressure needs the orientation of the
-satellite (\configFile{inputfileStarCamera}{instrument}) and additional a satellite macro model (\config{satelliteModel})
+by \configFile{inputfileOrbit}{instrument}. Non-conservative forces like solar radiation pressure need the orientation of the
+satellite (\configFile{inputfileStarCamera}{instrument}) and additionally, a satellite macro model (\config{satelliteModel})
 with the surface properties. Furthermore \configFile{inputfileAccelerometer}{instrument} observations are also considered.
 
-In a second step the accelerations are integrated twice to an dynamic orbit using a moving polynomial with the degree
+In a second step the accelerations are integrated twice to a dynamic orbit using a moving polynomial with the degree
 \config{integrationDegree}. The orbit is corrected to be self-consistent. This means the forces should be evaluated
 at the new integrated positions instead of the apriori ones. This correction is computed in a linear approximation
 using the gradient of the forces with respect to the positions (\config{gradientfield}). As this term is small generally
-only the largest force components has to be considered. A low degree spherical harmonic expansion of the static gravity
+only the largest force components have to be considered. A low degree spherical harmonic expansion of the static gravity
 field (about up to degree 5) is sufficient in almost all cases. In this step also the state transition matrix (the partial
-derivatices of the current state, position and velocity) with respect to the initial state is computed.
+derivatives of the current state, position and velocity) with respect to the initial state is computed.
 The integrated orbit together with the state transitions are stored in \configFile{outputfileVariational}{variationalEquation},
 the integrated orbit only in \configFile{outputfileOrbit}{instrument}.
 

source/programs/preprocessing/preprocessingVariationalEquationOrbitFit.cpp

@@ -20,18 +20,18 @@ and stochastic pulses (velocity jumps) at given times, \configClass{stochasticPu
 \configFile{outputfileSolution}{matrix} and an extra file with the parameter names is created. The fitted orbit is written
 as new reference in \configFile{outputfileVariational}{variationalEquation} and additionally in \configFile{outputfileOrbit}{instrument}.
 
-The observed orbit positions (\configFile{inputfileOrbit}{instrument}) together with the epoch wise covariance matrix
-(\configFile{inputfileCovariancePodEpoch}{instrument}) must be splitted in the same arcs as the variational equations but not
-necessarily uniform distributed (use irregularData in \program{InstrumentSynchronize}). An iterative downweighting of
+The observed orbit positions (\configFile{inputfileOrbit}{instrument}) together with the epoch-wise covariance matrix
+(\configFile{inputfileCovariancePodEpoch}{instrument}) must be split in the same arcs as the variational equations but not
+necessarily uniformly distributed (use irregularData in \program{InstrumentSynchronize}). An iterative downweighting of
 outliers is performed by M-Huber method.
 
-The observation equations (parameter sensitity matrix) are computed by integration of the variational equations
+The observation equations (parameter sensitivity matrix) are computed by integration of the variational equations
 (\configFile{inputfileVariational}{variationalEquation}) using a polynomial with \config{integrationDegree} and interpolated to the
 observation epochs using a polynomial with \config{interpolationDegree}.
 
 All parameters used here must be reestimated in the full least squares adjustment
 for the gravity field determination to get a solution which is not biased towards the reference field.
-The solution of additional estimations are relative (deltas) as the parameters are already used as Taylor point
+The solutions of additional estimations are relative (deltas) as the parameters are already used as Taylor point
 in the reference orbit.
 
 See also \program{PreprocessingVariationalEquation}.