ESA PADRE Analysis Results

Summary - Overall Vehicle Landed Mass and Energy

Test case: Example DRAMA Uncontrolled Component-Centric Vehicle Re-entry

Demonstration of the PADRE spacecraft assessment mode. This analysis simulated the destructive re-entry of a 1000kg component-centric vehicle, modelled as a relatively simple structore comprising approximately 40 components. Re-entry is predicted from a circular sun-synchronous orbit of 130km altitude using the DRAMA v3.0.4 version of SESAM. Uncertainties in the initial true anomaly, atmosphere density, material properties, drag and heating coefficients are considered. A standard Monte-Carlo of between 2000 and 5000 simulations has been executed.

Status

Analysis started: 2022-02-03 20:49:59
Last updated: 2022-02-04 00:28:53
Elapsed time: 13134 secs
Simulation count: 2000
Batch count: 8
Results converged: True
Analysis complete: True

Configuration

Analysis configuration: View / Download
Uncertainties configuration: View / Download

Fragment Count Sensitivity

Sensitivity of 'fragmentCount' to 'heatFluxMult'

Sensitivity parameters
Correlation coefficient: -0.2523012022795629 Slope: -0.011236345667194387 N: 2000

Sensitivity of 'fragmentCount' to 'dragMult'

Sensitivity parameters
Correlation coefficient: 0.044472254523806765 Slope: 0.00593930871716165 N: 2000

Sensitivity of 'fragmentCount' to 'densityMultiplier'

Sensitivity parameters
Correlation coefficient: 0.0035299645357404407 Slope: 0.0002755701627471307 N: 2000

Landed Mass Sensitivity

Sensitivity of 'mass' to 'heatFluxMult'

Sensitivity parameters
Correlation coefficient: -0.3785837352392934 Slope: -0.07980723374249421 N: 2000

Sensitivity of 'mass' to 'dragMult'

Sensitivity parameters
Correlation coefficient: 0.04223631987385087 Slope: 0.026699760053696574 N: 2000

Sensitivity of 'mass' to 'densityMultiplier'

Sensitivity parameters
Correlation coefficient: 0.007221390781830842 Slope: 0.0026684387125402473 N: 2000

ESA PADRE 2021