A space vehicle element configured to be at least partially destroyed during re-entry of a space vehicle into the atmosphere comprises a heat generating part comprising a metallo-thermal composition for providing additional heat during re-entry of the space vehicle into the atmosphere by an exothermic reaction of the metallo-thermal composition. The destruction of the space vehicle element is expedited by the additional heat provided by the heat generating part. The heat generating part is at least partially integrated within the space vehicle element or at least partially surrounds a portion of the space vehicle element. The application further relates to a corresponding method of manufacturing a space vehicle element configured to be destroyed during re-entry of the space vehicle into the atmosphere.
Exothermic reaction aided spacecraft demise during re-entry
2022-11-15
Patent
Elektronische Ressource
Englisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
EXOTHERMIC REACTION AIDED SPACECRAFT DEMISE DURING RE-ENTRY
Europäisches Patentamt | 2020
|EXOTHERMIC REACTION AIDED SPACECRAFT DEMISE DURING RE-ENTRY
Europäisches Patentamt | 2021
|Vision-aided inertial navigation for spacecraft entry, descent, and landing
Tema Archiv | 2009
|Mid-L/D Lifting Body Entry Demise Analysis
AIAA | 2017
|Mid-L/D Lifting Body Entry Demise Analysis
NTIS | 2017
|