Configuration
- Analysis configuration: View / Download
- Uncertainties configuration: View / Download
- Vehicle model: View / Download
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.
Probability of compliance with 1e-4 risk: 0.40 (95% confidence interval of compliance: 0.37 - 0.43)
| Gaussian Fit | Beta Fit |
|---|---|
| Mean: 2 (+/- 0.12 / 0.12) Standard deviation: 2 (+/- 0.09 / 0.083) | Location: -1.2e-31 Scale: 21 Beta A: 0.81 Beta B: 13 |
| Gaussian Fit | Beta Fit |
|---|---|
| Mean: 21 (+/- 0.094 / 0.094) Standard deviation: 1.5 (+/- 0.07 / 0.064) | Location: 18 Scale: 7.3 Beta A: 0.58 Beta B: 1.1 |
| Gaussian Fit | Beta Fit |
|---|---|
| Mean: 27 (+/- 0.12 / 0.12) Standard deviation: 1.9 (+/- 0.087 / 0.08) | Location: 25 Scale: 8.1 Beta A: 0.38 Beta B: 1 |
| 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 |
ESA PADRE 2025