Table 2
Comparison of the representative re-entry analysis tools

Parameter	SCARAB	ORSAT	DAS	DRAMA	STELA
Category of the code	Spacecraft-Oriented	Object-Oriented	Object-Oriented	Object-Oriented	Object-Oriented
Satellite Modeling Complexity	High complexity, entire detailed satellite modeling using internally stored program	Simple modeling by individual decomposed elements	Simple modeling by individual decomposed elements	Simple modeling by individual decomposed elements using CROC module	Simple modeling by individual decomposed elements using internally stored tool
Simulation Method	6 DOF dynamics equation and 3D thermal equations	3 DOF dynamics equation and 1 D thermal equations	3 DOF dynamics equation and 1 D thermal equations	3 DOF dynamics equation and 1 D thermal equations	Statistical analysis through the use of Monte Carlo simulation
Break-up Altitude	Calculation of breakup altitude by analyzing the actually acting mechanical and thermal loads dynamically	Constant fixed break-up altitude of 75 km	Constant fixed break-up altitude of 75 km	Constant fixed break-up altitude of 75 km	Calculation of lifetime analysis by using the orbital trajectory element
Fragmentation Process	Thermal ablation and mechanical fracture based on force, torque and heat loads during trajectory	Decomposition of the parent object into predefined child objects at break-up altitude	Decomposition of the parent object into predefined child objects at break-up altitude	Decomposition of the parent object into predefined child objects at break-up altitude	-
Casualty Risk Analysis	Casualty risk low resolution	Casualty risk low resolution	Casualty risk high resolution: Risk analysis by individual part	Casualty risk high resolution: Risk analysis by latitude through internally store population function	-
Input	Detailed satellite’s shape, mass, thermodynamic modeling	Satellite’s shape, mass, orbital element, etc.	Satellite’s shape, mass, orbital element, etc.	Satellite’s shape, mass, orbital element, etc.	Satellite’s shape, mass, orbital element, etc.
Output	Orbital element and reentry trajectory after break-up	Orbital element and extinction altitude and re-entry trajectory	Extinction altitude by each part, casualty area and casualties producing probability	Survivability of parts, casualties producing probability and re-entry trajectory	Orbital lifetime analysis and satisfaction of disuse condition status
Advantage	Detailed satellite modeling and break-up analysis by mechanical and thermal loads	Analysis of individual reentry survivability with regards to each part of a satellite	Simple modeling and analysis of first cut footprints	Efficient re-entry analysis using the catalogued space debris data through the use of space environment modeling	Accurate lifetime prediction using long term propagator