Launching vehicle and satellite connection-separation apparatus

1. In a launcher and satellite connection-separation apparatus for launching satellite vehicles, the launcher and satellite connection-separation apparatus comprising a band-clamp assembly having a band ( 11 ) with an inner channel in which a plurality of clamps ( 13 ) are located in a sliding manner for application to rings ( 15 , 17 ) interfacing between the vehicles, and a union-separation device ( 41 , 61 , 71 ) on ends ( 7 , 9 ) of the band including a locking element ( 47 ) and means ( 48 ) for unlocking the locking element, the improvements comprising:

a) means ( 19 ) for radially tightening the band; and

b) a mechanism in the union-separation device ( 41 , 61 , 71 ) for a controlled opening of the band ( 11 ) in first and second phases, the ends ( 7 , 9 ) of the band ( 11 ) shifting contact with the rings ( 15 , 17 ) in the first of the phases for dissipating by friction elastic energy corresponding to the tightening of the band ( 11 ) and, in the second of the phases, the band ( 11 ) separating from the rings ( 15 , 17 ) until reaching a parking position,

wherein the union-separation device ( 41 ) also comprises a support ( 43 ) of mass M and two connecting rods ( 45 ) respectively connecting the mass to the ends ( 7 , 8 ) of the band ( 11 ) in an articulating manner such that, once the locking element ( 47 ) is unlocked, the ends ( 7 , 8 ) of the band ( 11 ) shift in the first of the phases tangentially to the rings ( 15 , 17 ) for the dissipating of the elastic energy corresponding to the tightening of the band ( 11 ), the support ( 43 ) moving substantially radially away from the band ( 11 ) in the first phase, and, in the second of the phases, shift in a radial direction to the rings ( 15 , 17 ) until reaching the parking position.

2. A launcher and satellite connection-separation apparatus according to claim 1 , wherein said means for radially tightening the band-clamp assembly consist of a plurality of pushing elements ( 19 ) for the clamps ( 13 ) arranged along their perimeter.

3. A launcher and satellite connection-separation apparatus according to claim 2 , wherein said pushing elements ( 19 ) consist of screws ( 19 ) which cooperate with nuts ( 21 ) located in through drill holes ( 23 ) arranged on the band ( 11 ).

4. A launcher and satellite connection-separation apparatus according to claim 3 , wherein the number of screws ( 19 ) per clamp ( 13 ) is from 1 to 3.

5. In a launcher and satellite connection-separation apparatus for launching satellite vehicles, the launcher and satellite connection-separation apparatus comprising a band-clamp assembly having a band ( 11 ) with an inner channel in which a plurality of clamps ( 13 ) are located in a sliding manner for application to rings ( 15 , 17 ) interfacing between the vehicles, and a union-separation device ( 41 , 61 , 71 ) on ends ( 7 , 9 ) of the band including a locking element ( 47 ) and means ( 48 ) for unlocking the locking element, the improvements comprising:

a) means ( 19 ) for radially tightening the band; and

b) a mechanism in the union-separation device ( 41 , 61 , 71 ) for a controlled opening of the band ( 11 ) in first and second phases, the ends ( 7 , 9 ) of the band ( 11 ) shifting contact with the rings ( 15 , 17 ) in the first of the phases for dissipating by friction elastic energy corresponding to the tightening of the band ( 11 ) and, in the second of the phases, the band ( 11 ) separating from the rings ( 15 , 17 ) until reaching a parking position,

wherein the union-separation device ( 61 ) also comprises a support ( 63 ) of mass M with two guide grooves ( 65 ) respectively for shafts ( 67 ) joined to the ends ( 7 , 8 ) of the band ( 11 ) so that, once the locking element ( 47 ) is unlocked, the shafts ( 67 ) shift in the first of the phases along first parts ( 68 ) of the guide grooves ( 65 ) for the dissipating of the elastic energy corresponding to the tightening of the band ( 11 ) and, in the second of the phases, shift along second parts ( 69 ) of the guide grooves ( 65 ) for guiding the band ( 11 ) to the parking position.

6. A launcher and satellite connection-separation apparatus according to claim 5 , wherein said means for radially tightening the band-clamp assembly consist of a plurality of pushing elements ( 19 ) for the clamps ( 13 ) arranged along their perimeter.

7. A launcher and satellite connection-separation apparatus according to claim 6 , wherein said pushing elements ( 19 ) consist of screws ( 19 ) which cooperate with nuts ( 21 ) located in through drill holes ( 23 ) arranged on the band ( 11 ).

8. A launcher and satellite connection-separation apparatus according to claim 7 , wherein the number of screws ( 19 ) per clamp ( 13 ) is from 1 to 3.

9. In a launcher and satellite connection-separation apparatus for launching satellite vehicles, the launcher and satellite connection-separation apparatus comprising a band-clamp assembly having a band ( 11 ) with an inner channel in which a plurality of clamps ( 13 ) are located in a sliding manner for application to rings ( 15 , 17 ) interfacing between the vehicles, and a union-separation device ( 41 , 61 , 71 ) on ends ( 7 , 9 ) of the band including a locking element ( 47 ) and means ( 48 ) for unlocking the locking element, the improvements comprising:

a) means ( 19 ) for radially tightening the band; and

b) a mechanism in the union-separation device ( 41 , 61 , 71 ) for a controlled opening of the band ( 11 ) in first and second phases, the ends ( 7 , 9 ) of the band ( 11 ) shifting contact with the rings ( 15 , 17 ) in the first of the phases for dissipating by friction elastic energy corresponding to the tightening of the band ( 11 ) and, in the second of the phases, the band ( 11 ) separating from the rings ( 15 , 17 ) until reaching a parking position,

wherein the union-separation device ( 71 ) also comprises a support ( 73 ) of mass M with grooves ( 75 ) configured so that shafts ( 77 ) joined to the ends ( 7 , 8 ) of the band ( 11 ) may be located in first and second positions ( 78 , 79 ), a nub disposed between the shafts ( 77 ), such that once the retaining element ( 47 ) is unlocked, the shafts ( 77 ) shift away from each other in the first of the phases from the first of the positions ( 78 ) to the second of the positions ( 79 ) overcoming resistance presented by respective separators ( 76 ) for the dissipating of the elastic energy corresponding to the tightening of the band ( 11 ), the nub moving radially with respect to the support ( 73 ) to assist the shafts ( 77 ) in moving tangentially and in overcoming the resistance presented by the respective separators ( 76 ) to allow the separation, and, in the second of the phases, shift along the second of the positions ( 79 ) to the parking position.

10. A launcher and satellite connection-separation apparatus according to claim 9 , wherein said means for radially tightening the band-clamp assembly consist of a plurality of pushing elements ( 19 ) for the clamps ( 13 ) arranged along their perimeter.

11. A launcher and satellite connection-separation apparatus according to claim 10 , wherein said pushing elements ( 19 ) consist of screws ( 19 ) which cooperate with nuts ( 21 ) located in through drill holes ( 23 ) arranged on the band ( 11 ).

12. A launcher and satellite connection-separation apparatus according to claim 11 , wherein the number of screws ( 19 ) per clamp ( 13 ) is from 1 to 3.