System for separating separable spacecraft and shuttle elements

Abstract

A separation system for separable elements of spacecraft and launchers includes an upper ring, a lower ring and a band with an inner channel which houses slidable clamps, which are applied against the upper ring and the lower ring that form the connection interface between the two separable elements. A device joins/separates the ends of the band, both the upper ring and the lower ring including an outer protruding element with a wedged section to be lodged in the clamps. The upper ring also has an inner protruding element with a wedged section that matches a channel shaped section in the lower ring, the lower ring also has an outer portion including the outer protruding element with a wedged section and the channel shaped section, the outer portion protruding from a main part of the lower ring and being spaced from it creating a groove.

Claims

1. Separation system for separable elements of spacecrafts and launchers; the system comprising: an upper ring, a lower ring and a band with an inner channel which houses a plurality of slidable clamps, which are applied against the upper ring and the lower ring that form a connection interface between the two separable elements, and a device for joining/separating ends of the band, both the upper ring and the lower ring comprise an outer protruding element with a wedged section to be lodged in the clamps, the upper ring further comprises an inner protruding element with a wedged section that matches a channel shaped section in the lower ring, the lower ring also comprising an outer portion including the outer protruding element with a wedged section and the inner channel shaped section, the outer portion protruding from a main body of the lower ring and being spaced from the lower ring creating a groove.

2. Separation system for separable elements of spacecrafts and launchers according to claim 1, wherein the outer portion of the lower ring is an integral part of the lower ring.

3. Separation system for separable elements of spacecrafts and launchers according to claim 1, wherein the outer portion of the lower ring is a separate part attached to the main body of the lower ring by a fastener.

4. Separation system for separable elements of spacecrafts and launchers according to claim 3, wherein the outer portion of the lower ring is at least one separate plate attached to the main body of the lower ring by screws or fasteners.

5. Separation system for separable elements of spacecrafts and launchers according to claim 3, wherein the separate part comprises at least one through hole facing a corresponding through hole on the main body of the lower ring.

6. Installation procedure for a separation system for separable elements of spacecrafts and launchers of claim 4, which comprises the following steps: placing the upper ring on top of the lower ring; introducing a screw through the hole of the plate and through the hole of the main part of the lower ring; rotating the screw to bring the plate nearer the rest of the lower ring, allowing the inner protruding element with a wedged section to be lodged in the channel shaped section of the plate; placing the assembly clamps-band in a working position, with the outer protruding elements with a wedged section of the upper and lower rings lodged in the gap of the clamps; removing the screw used to bring the plate nearer the rest of the lower ring.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) For a more complete understanding of the present invention, it will be described below in greater detail, making reference to the attached drawings, in which:

(2) FIG. 1 is a sectional view of the separation system of the invention.

(3) FIG. 2 is a perspective view of the clamp band assembly and the device 19 for joining/separating the ends of the band.

(4) FIG. 3 is a view of a first embodiment of the invention.

(5) FIG. 4 is a detail of the lower ring, of the second embodiment of the invention.

(6) FIG. 5 is a chart load-tension for a prior existing separation systems and for the system of the invention.

(7) FIG. 6 is a schematic representation of the release process of the two separable elements with a separation system of the invention.

(8) FIGS. 7a to 7f are a representation of the assembling process of the device of the invention.

DETAILED DESCRIPTION OF THE INVENTION

(9) FIG. 1 represents a sectional view of the separation system 1 of the invention including the related upper ring 5 and lower ring 6. It can be seen that the system 1 also comprises a band 2 with an inner channel 3 which houses a plurality of slidable clamps 4 (the assembly clamps-band is represented in FIG. 2) which are applied against the upper ring 5 and the lower ring 6 that form the connection interface between the two separable elements of a spacecraft or a launcher, and that is provided with a device 19 (represented in FIG. 2) for joining/separating the ends of the band 2.

(10) It can also be seen that both the upper ring 5 and the lower ring 6 comprise each one an outer protruding element 7 and 8 with a wedged section to be lodged in the gap 20 of the clamps 4.

(11) The upper ring 5 additionally comprises an inner protruding element 9 with a wedged section that matches a channel shaped section 10 (FIG. 4) in the lower ring 6. The lower ring 6 also comprises an outer portion 11 (fastened in FIG. 4) including the outer protruding element 8 with a wedged section and the channel shaped section 10. The outer portion 11 of the lower ring 6 is spaced from the main body 12 of the lower ring 6, creating a groove 13 between the outer portion 11 and the main body 12 of the lower ring 6. In the system 1 represented in FIG. 1 the outer portion 11 is represented fastened to the base 14 of the main body 12 of the lower ring 6. This outer portion can be fastened or machined integral to the lower ring 6.

(12) FIG. 2 shows a view of the assembly clamps-band with a device 19 for joining/separating the ends of the band 2.

(13) FIG. 3 corresponds to a representation of a first embodiment of the invention, in which the outer portion 11 of the lower ring 6 is an integral part of the lower ring 6, the intermediate groove 13 being formed, in this representation, through machining.

(14) FIG. 4 corresponds to a representation of the lower ring 6 of an alternative embodiment of the invention, in which the outer portion 11 of the lower ring 6 is a separate part attached to the main part 12 of the lower ring 6 by fastening means 15.

(15) As represented in FIG. 4, the outer portion 11 of the lower ring 6 may be constituted by several plates 21 working as spring plates, attached to the main part 12 of the lower ring 6 by means of screws or fasteners 15.

(16) FIG. 4 also shows that the plates 21 may comprise at least one through hole 16 facing a corresponding through hole 17 on the main part 12 of the lower ring 6. The function of these through holes 16, 17 will be described in detail when describing FIG. 7.

(17) FIG. 5 represents a typical chart load-tension for a band in prior existing separation systems and for the separation system 1 of the invention, in this case for a particular diameter of 4.8 m.

(18) It can be seen that in the prior separation systems the failure happens for less than 100 N/mm when the band is tensioned at 72 kN. The chart shows sliding (gap point) at about 80 N/mm.

(19) The system 1 of the invention shows initial instability not before 180 N/mm, and no failure even for more than 250 N/mm. Accordingly, the system 1 of the invention bears higher loads, that do not lead to a significant increase in the band tension, and the failure would be due to deformation.

(20) FIG. 6 schematically shows the release process of the two separable elements with a separation system 1 of the invention. In phase 1, the assembly clamps-band loosens (the device 19 acts separating the ends of the band 2), liberating the outer protruding elements 7, 8 with a wedged section of the upper ring 5 and of the lower ring 6 previously lodged in the gap 20 of the clamp 4.

(21) In phase 2 the outer portion 11 of the lower ring 6 is released and opens with respect to the main body 12 of the lower ring 6 due to the effect of the spring energy, causing the inner protruding element 9 with a wedged section of the upper ring 5 to be liberated from the channel shaped section 10 in the outer portion 11 of the lower ring 6 that previously lodged it.

(22) Finally, in phase 3 once the upper ring 5 and the lower ring 6 are completely released, it is possible the separation of both rings (for instance, one belonging to the launcher and the other one to the satellite).

(23) FIG. 7 shows the installation procedure for the system 1 of the invention, for an embodiment comprising plates 21 with at least one through hole 16, facing another through hole 17 on the main part 12 of the lower ring 6. In step 1 (FIG. 7a) there is represented the lower ring 6 alone. In step 2 (FIG. 7b) the upper ring 5 is placed on top of the lower ring 6. In step 3 (FIG. 7c) a screw 18 is introduced through the holes 16, 17 of the plate 21 and the main body 12 of the lower ring 6. In step 4 (FIG. 7d) the screw 18 is screwed to bring the plate 21 nearer the main body 12 of the lower ring 6 and allowing the inner protruding element 9 with a wedged section to be lodged in the channel shaped section 10 of the plate 21 of the lower ring 6. In step 5 (FIG. 7e) the assembly clamps-band is placed in its working position, with the outer protruding elements 7, 8 with a wedged section of the upper ring 5 and lower ring 6 lodged in the gap 20 of the clamps 4. In step 6 (FIG. 7f) the screw 18 used to bring the plate 21 nearer the main body 12 of the lower ring 6 in step 4 is removed.

(24) Although the present invention has been fully described in connection with preferred embodiments, it is evident that modifications may be introduced within the scope thereof, not considering this as limited by these embodiments, but by the contents of the following claims.