System for hold down and release of a spacecraft with respect to a launcher

A system for hold down and release of a spacecraft with respect to a launcher, configured to be able to change from a closed state to an open state, that comprises:

• an upper bracket in the form of a ring comprising an inner protruding portion,
• a lower bracket in the form of a ring comprising an inner protruding portion,
• an internal assembly fixed to the lower bracket that comprises a central beam, at least three levers, at least three clamps, at least three guiding systems for the clamps, a central rod and an actuator,
• wherein:
• the upper bracket and the lower bracket enclose an interior hollow space where the internal assembly is placed in a closed state of the system,
• the clamps of the internal assembly have a peripheral groove configured to mate with the protruding portions of the upper bracket and the lower bracket,
• each lever is rigid, is articulated to a clamp by a hinge and to the central beam by a hinge and comprises a latch system to fix the lever on the central beam in an open state of the system,
• the clamps are guided by the guiding systems that allow the radial movement of the clamps, each guiding system comprising a guide on which at least one pin protruding from the corresponding clamp is fitted, and
• the central rod is joined to the central beam, is preloaded in a closed state of the system by torquing an upper nut and is releasable by the action of the actuator.