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

Total Landed Mass

Gaussian Fit	Beta Fit
Mean: 51 (+/- 0.16 / 0.16) Standard deviation: 3.6 (+/- 0.12 / 0.11)	Location: 43 Scale: 15 Beta A: 0.72 Beta B: 0.71

PDF/CDF data (download)
Centile data (download)

Total Impact Energy

Gaussian Fit	Beta Fit
Mean: 5.8e+04 (+/- 8.2e+02 / 8.2e+02) Standard deviation: 1.9e+04 (+/- 6e+02 / 5.6e+02)	Location: 2.4e+04 Scale: 9.7e+04 Beta A: 0.89 Beta B: 1.4

PDF/CDF data (download)
Centile data (download)

ESA PADRE 2021