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CelestLab >> Trajectory and maneuvers > CL_dsp_covCoord

CL_dsp_covCoord

Conversion of type of orbital elements in a covariance matrix

Calling Sequence

[param2,cov2]=CL_dsp_covCoord(param1,cov1,conv1to2 [,mu])

Description

Parameters

param1:

State vector (with components of type 1). (6xN)

cov1:

Covariance matrix associated with param1. (6x6xN)

conv1to2:

(string) Type of conversion (from 1 to 2). It is the name of the CelestLab function that performs the same conversion without the prefix 'CL_oe_'.

mu :

(optional) Gravitational constant [m^3/s^2]. (default value is %CL_mu)

param2:

State vector (with components of type 2). (6xN)

cov2:

Covariance matrix associated with param2. (6x6xN)

Authors

See also

Examples

// Change correlation matrix: cartesian to circular-adapted
bul = [-1877901 -3909428 -5026025 7428.157 -1541.857 -1576.532]';
cor = [1 -0.467016 -0.447601 0.960396 0.987145 0.995826;...
0 1 -0.088751 -0.359696 -0.412472 -0.540655;...
0 0 1 -0.248472 -0.582834 -0.431908;...
0 0 0 1 0.915197 0.943178;...
0 0 0 0 1 0.980679;...
0 0 0 0 0 1]; //upper triangle of correlation matrix
cor = cor+cor'-eye(cor); // correlation matrix (symmetric)
// standard  deviation :
sd = [15939.681;2912.099;3079.494;6.819104;9.500176;12.146244];
// Covariance matrix in cartesian parameters
cov_car = CL_cor2cov(cor,sd);
[bul_cir,cov_cir] = CL_dsp_covCoord(bul,cov_car,'car2cir');
[cor_cir,sd_cir] = CL_cov2cor(cov_cir);
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