US 2023/0141538 A1Published application

System for the Release of Satellites from a Launch Vehicle

AssigneeThales Alenia Space Italia S.p.A. Con Unico Socio

InventorsAniceto Panetti, Andrea Marchetti, Alberto Ritorto, Andrea Adriani, Luigi Scialanga

Life of this patent

Estimating the term…

Loading patent…

Abstract

A release system for the release of satellites from a launch vehicle is provided that includes: (i) a torsion bar, having a first end which is fixed by means of support means to a launch vehicle and is locked in rotation around a longitudinal axis of the torsion bar, and a second end which is connected by means of hinge means to the launch vehicle and is free to rotate around the longitudinal axis; (ii) at least one launch arm extending perpendicularly from the torsion bar and comprising (a) a torsion lever having a first end which is fixed to the torsion bar in an integral manner, and (b) a guide having a first end connected to a second end of the torsion lever, and a second free end; (iii) at least one slider which is fixed in an integral manner to a satellite to be launched and arranged to engage the guide in a sliding manner; and (iv) and a limit stop element designed to act upon the torsion lever to stop the rotation of the launch arm around the longitudinal axis.

Claims6

Dependent claims

A release system (1) for release of satellites from a launch vehicle;

said release system (1) comprising:
(i) a torsion bar (2) having a first end (2a), which is fixed to a launch vehicle (3) by means of support means (4) and is locked in the rotation around a longitudinal axis (X) of the torsion bar (2), and a second end (2b), which is connected to said launch vehicle (3) by means of hinge means (5) and is free to rotate around said longitudinal axis (X);
(ii) at least one launch arm (6) extending perpendicularly from said torsion bar (2) and comprising (a) a torsion lever (7) having a first end (7a) which is fixed to said torsion bar (2) in an integral manner, and (b) a guide (8) having a first end (8a) connected to a second end (7b) of said torsion lever (7), and a second free end (8b);
(iii) at least one slider (10), which is fixed to a satellite (18) to be launched in an integral manner and is arranged so as to engage, in a sliding manner, said guide (8);
and
(iv) a limit stop element (12), which is designed to act on said torsion lever (7) to interrupt the rotation of the launch arm (6) around the longitudinal axis (X).

3 more elements

Dependencies are inferred from the claim text.