ESA PADRE Analysis Results

Summary - Overall Vehicle Landed Mass and Energy

Test case: Example SAMj Controlled 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 SAMj. Uncertainties in the initial state vector, atmosphere density, material properties, drag and heating coefficients are considered. A standard Monte-Carlo of between 1000 simulations has been executed.

Status

Analysis started: 2025-08-05 12:18:50
Last updated: 2025-08-05 16:29:41
Elapsed time: 15050 secs
Simulation count: 1000
Batch count: 4
Analysis complete: True

Configuration

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

Total Landed Mass

Gaussian Fit	Beta Fit
Mean: 1.1e+02 (+/- 0.37 / 0.37) Standard deviation: 6 (+/- 0.28 / 0.25)	Location: -6.2e+06 Scale: 6.2e+06 Beta A: 2.3e+06 Beta B: 5.1

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

Total Impact Energy

Gaussian Fit	Beta Fit
Mean: 1.1e+05 (+/- 1.3e+03 / 1.3e+03) Standard deviation: 2.1e+04 (+/- 9.8e+02 / 9e+02)	Location: 4.5e+04 Scale: 1.5e+05 Beta A: 4.7 Beta B: 6.1

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

ESA PADRE 2025