Separation system for spacecraft

Abstract

Separation system for a spacecraft, capable of providing the separation of the spacecraft from a launcher and / or the separation of launcher interstages, comprising an upper ring (1), a lower ring (2) and a rotating ring (3), wherein: - the upper ring (1) is suitable for attachment to the spacecraft and comprises several protruding teeth (4), the teeth (4) being circumferentially arranged on its inner face, with a gap (5) between each two adjacent teeth (4), - the lower ring (2) is suitable for attachment to the launcher and comprises several through holes (6) arranged circumferentially and elongated in a circumferential direction, and - the rotating ring (3) comprises several pins (7), at least one actuating means (8) suitable for rotating the rotating ring (3), the at least one actuating means (8) comprising a portion connected to the lower ring (2), and a connection element (9) between the rotating ring (3) and the lower ring (2), releasable by the action of an actuator (10).

Description

[0001] SEPARATION SYSTEM FOR SPACECRAFT

[0002] Field of invention

[0003] The present invention relates to a separation system for spacecraft, which is particularly applicable to the separation of a satellite from a launch vehicle or to the separation of intermediate stages from a launch vehicle.

[0004] Previous technique

[0005] Document IN213933 (patent application number IN2000MA00036), relating to “a low-shock ball-lock separation mechanism for separating upper stages and satellites from a space launch vehicle,” presents a mechanism comprising locking the interface rings by means of balls and maintaining them in a locked condition by means of a rotating retaining ring provided with radial holes for the release of the balls during separation. The retaining ring is actuated by a pair of thrusters, preferably pyrotechnic thrusters, and the entire separation technique depends solely on the actuation of either thruster, thus improving reliability.

[0006] Although the shock during separation is reduced, the actuation of the pyrotechnic propellants still involves high levels of shock that are transmitted to the interface rings.

[0007] In this state-of-the-art system, the balls are supported at two points, one on the upper ring and one on the lower ring, thus increasing the loads at these two points and creating a probable local plastic deformation.

[0008] The rings, the swivel ring, and the manufacturing tolerances of the balls may not provide uniform pressure distribution, compromising the system's homogeneous load-bearing capacity. The contact pressure between the balls and rings may exceed the elastic limit under heavy loads.

[0009] Therefore, it would be desirable to have a spacecraft separation system that reduces the loads on the rings, thereby increasing the system's capacity and allowing more spacecraft mass to be launched into space. Summary of the invention

[0010] Thus, it is an object of the invention to provide a separation system for spacecraft that is capable of overcoming the aforementioned drawbacks.

[0011] The invention provides a separation system for a spacecraft, capable of providing the separation of the spacecraft from a shuttle and / or the separation of the shuttle's intermediate stages, comprising an upper ring, a lower ring, and a rotating ring, wherein:

[0012] - the upper ring is suitable for attaching to the spacecraft and comprises several projecting teeth, the teeth being arranged circumferentially on its inner face, with a gap between each pair of adjacent teeth,

[0013] - the lower ring is suitable for attachment to the shuttle and comprises several circumferentially arranged through holes elongated in a circumferential direction,

[0014] - the rotating ring comprises radially preloaded pins with a cross-section smaller than that of the through holes of the lower ring, at least one actuator means suitable for rotating the rotating ring, the at least one actuator means comprising a part attached to the lower ring, and a connecting element between the rotating ring and the lower ring, suitable for being released by the action of an actuator, such that in an assembled state:

[0015] - the inner face of the upper ring is oriented towards the outer face of the lower ring, forming a circumferential groove between the inner face of the upper ring and the outer face of the lower ring where the protruding teeth of the upper ring and the gaps between each pair of adjacent teeth are located, and

[0016] - the rotating ring is oriented towards the inner face of the lower ring, and the pins of the rotating ring are inserted into the through holes of the lower ring, in which

[0017] - The rotating ring has a locked position and a disengaged position, the disengaged position being caused by the action of the actuator which releases the connecting element between the rotating ring and the lower ring and allows the actuator to act on the rotating ring, thus allowing the rotating ring to rotate.

[0018] - In the locked position, each pin is positioned overlapping one tooth of the upper ring, holding the upper and lower rings together, and

[0019] - In the separation position, each pin is located in a gap between two adjacent teeth, after the rotating ring has turned, so that the upper ring can be released from the lower ring.

[0020] The separation system configuration for a spacecraft of the invention allows the transmission of the load pressure in the upper ring over a larger contact area, which implies less stress and its applicability to larger loads, such as spacecraft and heavy shuttle intermediate stages.

[0021] The radial preload of the rotating ring pins ensures uniform contact of the pins with the upper ring and the preload between the rotating ring and the upper ring, increasing the system's capacity and allowing the launch of spacecraft with greater mass into space.

[0022] Other features and advantages of the present invention will become clear from the following detailed description of an illustrative embodiment and without limiting its scope in relation to the accompanying figures.

[0023] Description of the figures

[0024] Figure 1 shows a perspective view of the spacecraft separation system of the invention in the locked position.

[0025] Figure 2 shows a detail of some elements of the spacecraft separation system of the invention in the locked position.

[0026] Figure 3 shows a perspective view of the spacecraft separation system of the invention, showing only the upper ring and the lower ring.

[0027] Figure 4 shows a detail of the connection between the upper ring and the lower ring of Figure 3. Figure 5 shows a detail of pins inserted into the holes of the lower ring.

[0028] Figure 6 shows a detail of a drive means and a connecting element in the rotating ring.

[0029] Figure 7 shows the top ring and the rotating ring in the locked position, when the rotating ring is about to turn.

[0030] Figure 8 shows the top ring and the rotating ring in the separation position, once the rotating ring has rotated.

[0031] Figure 9 shows the upper ring separated from the rotating ring.

[0032] Detailed description of the invention

[0033] Figures 1 and 2 show the spacecraft separation system of the invention in the locked position. The system basically comprises an upper ring

[0034] 1, a lower ring 2 and a rotating ring 3. For the purposes of this document, the upper ring 1, or first ring, shall be understood to mean the ring located in a higher position in Figures 1 to 4 and suitable for attachment to a spacecraft, and the lower ring

[0035] 2, or second ring, the ring located in a lower position in figures 1 to 4 and suitable for attachment to a shuttle.

[0036] As can be seen in Figures 2, 3, and 4, the upper ring 1 comprises several projecting teeth 4 arranged circumferentially on its inner face. Figures 3 and 4 show that there is a gap 5 between each pair of adjacent teeth 4.

[0037] As can be seen in figures 3, 4 and 5, the lower ring 2 comprises elongated, circumferentially arranged through-holes 6.

[0038] The rotating ring 3 can be seen in Figures 1, 2 and 6, and comprises several radially preloaded pins 7, at least one actuating means 8 suitable for rotating the rotating ring 3 (see Figure 6), the at least one actuating means 8 comprising a part attached to the lower ring 3 and a connecting element 9 (see Figure 6) between the rotating ring 3 and the lower ring 2, suitable for being released by the action of an actuator 10. In Figure 5 it can be seen that the pins 7 of the rotating ring 3 have a smaller cross-section than the through holes 6 of the lower ring 2.

[0039] Figures 1 and 2 show the assembled state of the spacecraft separation system of the invention, in which:

[0040] The inner face of the upper ring 1 is oriented towards the outer face of the lower ring 2 (see Figures 2 and 4). In this way, a circumferential groove 11 is formed between the inner face of the upper ring 1 and the outer face of the lower ring 2 (see Figure 4). The projecting teeth 4 of the upper ring 1 and the gaps 5 between each pair of adjacent teeth 4 are located in this groove 11.

[0041] - The rotating ring 3 is oriented towards the inner face of the lower ring 2 (see figures 1 and 2), and the pins 7 of the rotating ring 3 are inserted into the through holes 6 of the lower ring 2 (see figures 2 and 5).

[0042] The rotating ring 3 has a locked position and a disengaged position. The disengaged position is caused by the action of actuator 10, which releases the connecting element 9 between the rotating ring 3 and the lower ring 2. Once the connecting element 9 is released and no longer connects the rotating ring 3 and the lower ring 2, the actuator 8 acts on the rotating ring 3, allowing it to rotate (see Figures 6 and 7). The actuator 8 that causes the rotating ring 3 to rotate may comprise elastic means, such as springs.

[0043] A fire nut can be used as an actuator 10. A release screw 14 can be used to release the connecting element 9.

[0044] Another possibility is to use a non-explosive actuator as actuator 10.

[0045] The locking position of the rotating ring is shown in Figure 7. In this figure, each pin 7 is positioned overlapping a tooth 4 of the upper ring 1, holding the upper ring 1 and lower ring 2 together, for example, during the rocket launch stages.

[0046] The separation position is shown in Figure 8. In this figure, each pin 7 is positioned in a gap 5 between two adjacent teeth 4, after the rotation of the rotating ring 3. In this way, the pins 7 do not overlap the teeth 4 of the upper ring 1, and the upper ring 1 can be released from the lower ring 2. This position corresponds to the spacecraft's ejection point (or the separation point between stages).

[0047] As shown in Figures 2 and 5, the pins 7 can have a cylindrical body 12 and a tapered tip 13. The tapered tip 13 is suitable for mating a corresponding inclined surface of groove 11 and a corresponding inclined surface of the corresponding tooth 4 (see Figure 2). In this way, the load pressure is exerted on two interconnecting lines.

[0048] During installation, the radial pressure of the pins 7 can be adjusted by screwing each pin until the tapered tip 13 makes contact with the corresponding tooth 4 of the upper ring 4 with a given torque.

[0049] Figures 7, 8 and 9 show the sequence of steps for the separation of the upper ring 1 (with a spacecraft, for example) from the lower ring 2 (for example, attached to a shuttle).

[0050] In Figure 7, the upper ring 1 and the rotating ring 3 are in the locked position, with each pin 7 of the rotating ring 3 overlapping a corresponding tooth 4 of the upper ring 1, which holds the upper ring 1 and the lower ring 2 together. In this position, the rotating ring 3 is about to rotate (its rotation is indicated by arrows).

[0051] In Figure 8, the upper ring 1 and the rotating ring 3 are in the separation position, once the rotating ring 3 has rotated and each pin 7 of the rotating ring 3 is positioned in a gap 5 between two adjacent teeth 4, allowing the upper ring 1 to be released from the lower ring 2.

[0052] Figure 9 shows the upper ring 1 separated from the rotating ring 3 (and, consequently, also separated from the lower ring 2, not shown in this figure).

[0053] Although the present invention has been fully described in relation to the preferred embodiments, it is evident that modifications can be made within the scope, without considering this as limited by these embodiments, but by the content of the following claims.

Claims

CLAIMS 1 Separation system for a spacecraft, capable of providing separation of the spacecraft from a shuttle and / or separation of intermediate stages from a shuttle, comprising an upper ring (1), a lower ring (2) and a rotating ring (3), wherein: - the upper ring (1) is suitable for attachment to the spacecraft and comprises several projecting teeth (4), the teeth (4) being arranged circumferentially on its inner face, with a gap (5) between each pair of adjacent teeth (4), - the lower ring (2) is suitable for attachment to the shuttle and comprises several circumferentially arranged through holes (6) elongated in a circumferential direction, - the rotating ring (3) comprises radially preloaded pins (7) with a cross-section smaller than that of the through holes (6) of the lower ring (2), at least one actuator means (8) suitable for rotating the rotating ring (3), the at least one actuator means (8) comprising a part attached to the lower ring (3), and a connecting element (9) between the rotating ring (3) and the lower ring (2), suitable for being released by the action of an actuator (10), such that in an assembled state: - the inner face of the upper ring (1 ) is oriented towards the outer face of the lower ring (2), forming a circumferential groove (11 ) between the inner face of the upper ring (1 ) and the outer face of the lower ring (2) where the projecting teeth (4) of the upper ring (1 ) and the gaps (5) between each pair of adjacent teeth (4) are located, and - the rotating ring (3) is oriented towards the inner face of the lower ring (2), and the pins (7) of the rotating ring (3) are inserted into the through holes (6) of the lower ring (2), in which - the rotating ring (3) has a locked position and a disengaged position, the disengaged position being caused by the action of the actuator (10) which releases the connecting element (9) between the rotating ring (3) and the lower ring (2) and allows the half actuator (8) acts on the rotating ring (3), allowing the rotating ring (3) turn, - in the locked position each pin (7) is positioned overlapping one tooth (4) of the upper ring (1 ), holding the upper ring (1 ) and the lower ring (2) together, and - In the separation position, each pin (7) is located in a gap (5) between two adjacent teeth (4), after the rotation of the rotating ring (3), so that the upper ring (1) can be released from the lower ring (2).

2. Separation system for a spacecraft, according to claim 1, wherein the actuating means (8) that causes the rotation of the rotating ring (3) comprises springs. 3.- Separation system for a spacecraft, according to any of the preceding claims, wherein the pins (7) have a cylindrical body (12) and a conical tip (13), the conical tip (13) being suitable for coupling to a corresponding inclined surface of the groove (1 1 ) and to a corresponding inclined surface of the corresponding tooth (4). 4.- Separation system for a spacecraft, according to any of the preceding claims, wherein a pyronut is used as an actuator (10).

5. Separation system for a spacecraft, according to any of claims 1 to 3, wherein the actuator (10) is a non-explosive actuator.

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