A separation mechanism (100) for passive separation of a first spacecraft component (200) from a second spacecraft component (300) comprises a first structural element (10), a second structural element (20) and joining means (30) for mechanically joining the first and second structural elements (10, 20). The first structural element (10) has a receiving hole with an inner first connecting surface (11) and is adapted to be mounted to the first spacecraft component (200). The second structural element (20) is adapted to be at least in part received within the receiving hole of the first structural element (10) and has an outer second connecting surface (21) facing the inner first connecting surface (11) when the second structural element (20) is at least in part received within the receiving hole of the first structural element (10). The second structural element (20) is adapted to be mounted to the second spacecraft component. The joining means (30) is adapted to mechanically join the first and second structural elements (10, 20) together via their first and second connecting surfaces (11, 21). The joining means (30), in a joint state of the passive separation mechanism (100), is sandwiched between and connects the inner first connecting surface (11) and the outer second connecting surface (21) together when the second structural element (20) is at least in part received within the receiving hole of the first structural element (10). The joining means (30) is solder meltable at a temperature in the range of 100°C to 300°C so as to separate the first and second structural elements (10, 20) when a melting temperature, i.e., a temperature in the range of 100°C to 300°C, is experienced by the separation mechanism (100).
TWO-PART PASSIVE SEPARATION MECHANISM FOR SEPARATION OF TWO SPACECRAFT COMPONENTS DURING THE ATMOSPHERIC RE-ENTRY OF THE SPACECRAFT
ZWEITEILIGER PASSIVER TRENNMECHANISMUS ZUR TRENNUNG VON ZWEI RAUMFAHRZEUGKOMPONENTEN WÄHREND DES ATMOSPHÄRISCHEN WIEDEREINTRITTS DES RAUMFAHRZEUGS
MÉCANISME DE SÉPARATION PASSIF EN DEUX PARTIES POUR SÉPARER DEUX COMPOSANTS D'ENGINS SPATIAUX PENDANT LA RENTRÉE ATMOSPHÉRIQUE DE L'ENGIN SPATIAL
2024-12-04
Patent
Electronic Resource
English
A Simplified Passive Spacecraft Separation System
NTIS | 1966
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