Satellite separation system

Abstract

To provide a separation system that enables smooth and linear deployment of a satellite without an impact from a launcher.SOLUTION: The present invention relates to a separation system of launching a satellite from a launcher along a discharge axis, the separation system including a first ring mounted in the launcher, a second ring mounted in the satellite, and deployment means that applies a separation force to the first and second rings.SELECTED DRAWING: Figure 1

Description

Technical Field

[0001] The present invention relates to a separation system for ejecting a satellite along an ejection axis from a launch vehicle, comprising a first ring for mounting on the launch vehicle, a second ring for mounting on the satellite, and deployment means for applying a separating force to the first and second rings.

Background Art

[0002] Satellites, especially microsatellites of up to about 150 kg, are usually orbited by a rocket equipped with a launch vehicle and separated from the launch vehicle by a separation system. Known separation systems use a structure such as a belt to fix and transport the satellite to the launch vehicle. In orbit, the belt is released, whereby a preloaded spring relaxes and ejects the satellite. The spring typically features a stroke of only about 2 cm. Thus, the stored energy, i.e., the spring force, is completely released over a very short travel path, impacting the satellite. This poses a risk of damage to sensitive satellites, optical payloads, and electronic components. It is a further risk of such systems that an undesirable tilting moment may occur during satellite deployment if the holding force is released non-uniformly along the circumference of the separation system.

Summary of the Invention

Problems to be Solved by the Invention

[0003] An object of the present invention is to provide a separation system that enables smooth and linear deployment of a satellite without impact from the launch vehicle.

Means for Solving the Problems

[0004] This object is achieved by the separation system according to claim 1, in particular by deployment means for applying a separating force to the first and second rings, the separating force applied by said deployment means increasing as soon as it is released, and is achieved by the separation system. This object is also achieved by the separation system according to claim 17, in particular by deployment means for separating the first ring from the second ring by means of at least one spring, said spring being connected to a lever mechanism for releasably supporting the second ring, and is achieved by the separation system.

[0005] According to an embodiment of the invention, a separation system for ejecting a satellite along an ejection axis from a launcher comprises a first ring for attachment to the launcher, a second ring for attachment to the satellite, retaining means for interconnecting the first and second rings in a retaining position, deployment means for applying a separating force to the first and second rings, and release means for releasing the interconnection of the first and second rings, the separating force applied by the deployment means increasing as soon as it is released.

[0006] The general idea of the invention is that in order to ensure a smooth acceleration of the satellite, the deployment of the satellite is initiated with only a minimum separating force. A further increase in the separating force during the deployment process ensures an effective ejection of the satellite into orbit. In this way, a separation of the satellite from the launcher without impact can be achieved, protecting the structural and functional integrity of its components and payload.

[0007] In general, in the separation system, shapes other than a ring shape are also possible. However, highly reliable and lightweight components are of utmost importance for space applications. Therefore, a symmetric ring shape may be preferred because it requires a minimum number of parts and mechanical components. To minimize the load on the launcher, the separation system, or the selection of its components, in particular the first and second rings, and other rings attached thereto, can be manufactured from very lightweight materials such as carbon fiber.

[0008] The first ring and the second ring are adapted to be attached to the launcher and the satellite respectively along their entire circumferences, such that the radiation surfaces of the rings are directed at least approximately parallel to the attachment surfaces of the launcher and the satellite respectively. In the holding position, i.e., while the satellite is being transported into orbit, the first ring and the second ring can be interconnected by their radiation surfaces which are oriented parallel to each other by holding means. The release axis can be directed at least approximately perpendicular to the radiation surfaces of the rings.

[0009] The separation system further comprises deployment means for applying a separation force to the satellite and release means for releasing the interconnection of the first and second rings. In general, the deployment and release means can be arranged on either the first ring or the second ring. Since the second ring remains on the satellite after deployment, it is advantageous if both of those means are arranged on the first ring.

[0010] The release means is equipped to release the holding position by unlocking the lock of the holding means so as to be able to separate the first ring and the second ring. The release means can include at least one spring or a group of springs. The springs are, for example, preloaded in the holding position and relax at the start of satellite deployment, thereby being able to release the interconnection of the first and second rings by their spring force.

[0011] In one embodiment, the deployment means comprises a first group of springs and a second group of springs, the first group of springs having a different spring force compared to the spring force of the second group of springs. These two groups of springs function independently of each other and apply spring forces at different times. The first group of springs may constitute the main actuator of the deployment means for pushing out the satellite, while the second group of springs may function as a support actuator, in particular with a reduced spring force, in particular for initiating the deployment process. Thus, the two groups of springs ensure a particularly reliable deployment.

[0012] In a further embodiment, at least one actuating ring is slidably attached to the first ring. Such an actuating ring can be rotatably attached around a common center with the first ring and is thus movable relative to the first ring, which can be regarded as a static base (with respect to the launcher). With respect to the ejection axis, the actuating ring can be fixed against axial and lateral translational displacements. By providing a slidable rigid actuating ring, an actuating movement initiated at a point of the actuating ring is directly transmitted to all other points of the actuating ring by mechanical restricted guidance without time delay or attenuation. Thereby, an operation over the entire circumference of the actuating ring, and thus an immediate response to the operation of the separation system, is ensured.

[0013] In further development, at least two actuating rings are slidably attached to the first ring, and the release means means driving the two actuating rings in opposite directions (circumferentially) relative to each other. The two actuating rings can be arranged on both sides of the first ring, for example, radially outside and inside the first ring. At least two of them can be connected such that the movement started at a point on one of the actuating rings is transmitted to all other points on both actuating rings by mechanical limit guidance, and at the same time, the movement of one ring is achieved by synchronous movement in the opposite direction to the other actuating ring. The release means can be connected to the actuating rings that actuate their synchronous movement in opposite directions relative to each other, for example, by applying a spring force.

[0014] According to a further embodiment of the present invention, the holding means comprises a plurality of holding devices distributed along the circumferences of the first and second rings. This makes the interconnection of the first and second rings a multi-point connection, providing a stable connection between the first ring and the second ring, and at the same time having the advantage of ensuring the distribution and support of the satellite load while being connected to the launcher. For example, the holding device comprises a plurality of connecting devices arranged on the first ring and a plurality of corresponding connecting pins arranged on the second ring, and the pins are designed to be captured and held by the connecting devices to establish the interconnection of the two rings.

[0015] In further development, each holding device comprises two connecting brackets that are movable relative to each other in opposite directions. These connecting brackets are part of the connecting device on the first ring and can be connected to the first ring itself or an additional part thereof, in particular to the actuating ring. The connecting brackets can be arranged movably relative to the first ring. In particular, the brackets are in the open configuration where they are at the maximum distance from each other and are open to release the connecting pin of the second ring, and in the closed configuration where they are at the minimum distance from each other and surround and hold the connecting pin of the second ring, and are movable relative to each other in opposite directions between these configurations. For example, in its closed configuration, the connecting bracket can be arranged to surround the connecting pin from two opposite sides, thereby fixing the connecting pins in a predetermined position.

[0016] The connecting brackets can be moved, in particular, in synchronization by two actuating rings. To release the grip on the connecting pin, both connecting brackets can be separated by rotating the two actuating rings in opposite directions relative to each other. By removing both connecting brackets synchronously, the holding force around the entire connecting pin is evenly released, thereby preventing the generation of tilting moments. Since all connecting devices can be connected via the actuating ring, the opening operation reaches simultaneously the connecting brackets of all connecting devices distributed along the circumference of the first ring. Thereby, the second ring can be uniformly released without generating tilting moments.

[0017] According to another embodiment, each connecting device comprises a receptacle fixed between the said connecting brackets. The connecting brackets and the fixed receptacle together form a connecting device for holding the connecting pins of the second ring in a holding position. When establishing the connection between the first ring and the second ring, the fixed receptacle serves to guide the connecting pins into the correct position. In a second step, by using the connecting brackets, a stable connection is ensured and the connecting pins are fixed against translational movements along the release axis as well as translational movements perpendicular to the release axis by surrounding the pins with an appropriate connecting surface.

[0018] In a further embodiment, a plurality of operating levers are pivotally attached to the first ring, and the operating levers drive two actuating rings slidably attached to the first ring in opposite directions relative to each other. The operating levers can be rotatably attached to the pivot axis of the first ring, while the arms on both sides of the operating levers are each connected to an actuating ring, thereby driving the two actuating rings simultaneously in opposite directions relative to each other. For example, one operating lever can be associated with each connecting device of the separation system, thereby ensuring smooth operation of the two actuating rings around the entire circumference of the first ring. The movement of the operating levers can be generated, for example, by one spring or a group of springs of the release means, for example, one spring per operating lever.

[0019] In another embodiment, the separation system comprises a starter mechanism coupled to one of the operating levers, and the said starter mechanism actuates the said operating lever. The starter mechanism is designed to initiate the separation process of the satellite from the launch vehicle. The starter mechanism can, in particular, release the operating lever and relax a spring preloaded with the release means associated with that operating lever. Also, the other springs of the release means are simultaneously freely relaxed, and the energy stored in the springs is converted by the operating lever into a sliding movement of the actuating ring, in particular in circumferential directions opposite to each other. The immediate non-damped transmission of this movement throughout the separation system can be protected by the limited mechanical connection by the actuating ring, thereby further enhancing the reliability of the separation mechanism.

[0020] In a further development, the deployment means comprises a plurality of lever mechanisms each including a first lever and a second lever pivotally connected to each other. Thus, the first and second levers can form a lever mechanism like a pair of pliers. The first and / or second levers may exhibit a twisted or straight shape in order to optimize the transmission of the force of the lever mechanism. Due to spatial requirements, it is beneficial to arrange the lever mechanism outside the first ring, but generally it is also possible to arrange the lever mechanism inside the first ring.

[0021] The lever mechanism can be designed such that the first end of the first lever and the first end of the second lever are fixed to the first ring or a component attached to the first ring. Each lever mechanism can be characterized by at least one point for establishing contact with the second ring in order to apply a separating force to the second ring. The contact point with the second ring can be arranged, for example, at the second end of the first lever and / or the second end of the second lever. The second ends of the first and second levers can each be arranged on respective lever arms beyond the pivot point of the lever mechanism as seen from the first ends of the first and second levers.

[0022] Since the deployment of the satellite is carried out along the release axis, the effective movement of the contact point between the lever mechanism and the second ring can also be directed along the release axis. Thus, in the deployed position, the second ends of the first and second levers are at the maximum distance from the plane of the first ring, and the entire lever mechanism resembles an X-shape or an inverted Y-shape.

[0023] In the holding position, the lever arms of the first lever and the second lever can be at least approximately aligned with each other, and the entire lever mechanism resembles a closed pliers shape. In this position, the lever mechanism is at least approximately in an equilibrium position. The pivot point and the first ends of the first and second levers are arranged substantially in a straight line.

[0024] When the lever mechanism is actuated between the positions such as the closed pliers and the X, the distance between the first ends of the first and second levers, which are at least approximately located in the plane of the first ring, changes. One of the first ends of the first or second lever can be fixed to the first ring, and the other can be movably attached to the first ring. The movement can be restricted so that the connecting line between the first ends of the first lever and the second lever always maintains a tangent to the first ring.

[0025] In order to make the separation force evenly distributed over the entire circumference of the separation system, several lever mechanisms can be arranged around the circumference of the first ring. For example, several lever mechanisms can be evenly arranged around the first ring.

[0026] In another embodiment, the first group of springs connects the first ring and an actuating ring slidably attached to the first ring. Movement induced at any point of the actuating ring is transmitted to all other points of the actuating ring without time delay or attenuation. The first group of springs is part of the deployment means and can drive the deployment means, so that the movement of the deployment means, for example, the movement of a lever mechanism, can be advanced across the entire actuating ring. This ensures that all deployment means operate simultaneously and helps to avoid tilting moments during deployment.

[0027] In a further embodiment, in the holding position, a starter spring arranged on one of the first and second levers exerts a spring force on the other of the first and second levers. This second group of springs functions independently of the other components of the deployment means and assists in the initiation of deployment. Since the lever mechanism is close to equilibrium in the holding position, the additional spring force applied by the second group of springs ensures a reliable trigger for the deployment means.

[0028] In the holding position, the lever arms of the first and second levers can be closely aligned. The starter spring can be arranged on the lever arm of the first and / or second lever and is thereby pushed together, i.e., preloaded, by the adjacent lever arm of the other lever. When pushed back, the starter spring exerts the resulting spring force on the adjacent lever arm.

[0029] The starter spring of another embodiment is arranged in the tangential plane of the first ring. The longitudinal spring axis of the starter spring or a group of starter springs changes direction during the deployment of the separation system, but the reorientation of the spring axis can be limited to the tangential plane of the first ring or a plane parallel to the tangential plane of the first ring. Thus, the spring force is directed towards the lever mechanism with maximum efficiency.

[0030] In another embodiment, the first end of the first lever and the first end of the second lever are each attached to pivot about two perpendicular axes. One of those axes can be parallel to the release axis and the other can be parallel to the plane of the first ring. In this way, a scissor-like lever mechanism functions without limit, allowing for changes in the distance between the first end of the first lever and the first end of the second lever in the plane of the first ring, as well as changes in the angle between the first lever and the second lever and the plane of the first ring. The low-loss operation of the lever mechanism without distortion enables a highly efficient deployment of the satellite.

[0031] In a further development, the longitudinal axis of each spring is arranged tangentially with respect to the first ring. The longitudinal axes of the springs of the first group or the second group, or both, can be arranged in the tangent plane of the first ring, but a group of springs of the deployment means, for example, the springs of the first group of the deployment means, can also have their longitudinal axes parallel to the plane of the first ring and arranged to contact the first ring.

[0032] Since the release axis is at least approximately perpendicular to the latter direction, in order to deploy the satellite, the spring force has to be redirected by a specific means, for example, a lever mechanism. The redirection of the spring force advantageously occurs such that the separation force exerted by the deployment means increases upon release of the satellite.

[0033] Alternatively or additionally, the spring elements of the release means of the separation system can also be directed in a direction where the longitudinal axis of each spring is arranged tangentially with respect to the first ring. Alternatively, the axis of the spring of the release means can also be arranged parallel to the tangent direction, for example, inside the first ring.

[0034] In a further embodiment, the maximum movement range or stroke of the second ring relative to the first ring along the release axis between the holding position and the release position is, upon deployment, at least 4 cm, preferably at least 6 cm, and in particular at most 8 cm. Such a stroke is large compared to the most advanced ones and enables the transmission of the separating force to the satellite over a longer movement range, resulting in a gentle acceleration of the satellite. In particular, the movement range of the deployment means along the release axis may be larger than the spring movement range of the spring that operates the deployment means. Combined with the separating force exerted by the deployment means, which increases upon release of the satellite, smooth acceleration and thus an impact-free deployment of the satellite can be achieved.

[0035] However, another aspect of the invention that can be combined with the above subject matter is a separation system for ejecting a satellite along the release axis from a launcher, comprising a first ring for attachment to the launcher, a second ring for attachment to the satellite, holding means for interconnecting the first ring and the second ring in a holding position, deployment means for separating the first ring from the second ring by means of at least one spring, and release means for releasing the interconnection of the first ring and the second ring, wherein the spring is connected to a lever mechanism that releasably supports the second ring.

[0036] The general idea of this aspect of the invention is that the separating force exerted by the spring does not act directly between the first ring and the second ring, but is applied to the satellite via a lever mechanism. Thereby, the development of the spring force is influenced by the design of the lever mechanism, and in particular, a gently induced acceleration of the satellite with a minimum initial force over a long movement range can be achieved. The lever mechanism may include a plurality of levers or a group of levers.

[0037] All the advantages according to the first aspect of the invention can also be achieved in this aspect of the invention.

[0038] In one embodiment, all levers of the lever mechanism are connected via mechanically limited guidance. Thus, the movement of one lever of the lever mechanism is transmitted to all levers of the lever mechanism without time delay and without attenuation, ensuring the simultaneous and synchronous action of the separating force on the second ring by the deployment means.

[0039] In a further development, the movement range of the levers of the lever mechanism along the release axis is greater than the movement range of the spring. Thus, while expanding the movement range in which the spring force acts, the spring force is transmitted by the lever mechanism to the second ring, thereby providing a gentle application of the spring force to the deployment means and thus to the satellite.

[0040] In another embodiment, the separating force exerted by the deployment means increases upon release. The lever mechanism can be designed to transmit a low force to the deployment means at the start of satellite deployment, but the force transmitted to the deployment means increases over the deployment process. This ensures a smooth acceleration of the satellite, which is beneficial in order not to impair the structural and functional integrity of sensitive equipment.

[0041] Further embodiments of the present invention can be seen from the claims, the description, and the drawings. The present invention is described only by way of example below with reference to the schematic drawings.

Brief Description of the Drawings

[0042]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

DETAILED DESCRIPTION OF THE INVENTION

[0043] The drawings show a separation system 20 comprising a first ring 22 attached to a launch machine and configured thereby to form a stationary base for the launch machine, and a second ring 24 attached to a satellite, movable relative to the first ring 22 and configured to be releasable therefrom. The central axes of the first ring 22 and the second ring 24 define an ejection axis D along which the satellite is ejected into orbit.

[0044] FIG. 1 shows the separation system 20 in the released state. This is also the state on Earth before putting the separation system 20 into the transport state, in which the first ring 22 and the second ring 24 are firmly compressed (FIG. 4) and arranged coaxially. In the released state, the second ring 24 is supported only by the deployment means 26 of the first ring 22 at the contact site 28.

[0045] To hold the first ring 22 and the second ring 24 in a firmly compressed transport state, the separation system 20 comprises holding means. The holding means includes a plurality of holding devices 30 distributed along the periphery of the separation system 20, each holding device 30 including complementary counterparts arranged on the first ring 22 and the second ring 24 respectively. Each holding device 30 comprises a connecting pin 38 arranged on the second ring and a complementary connecting device arranged on the first ring 22. Each connecting device includes two connecting brackets 32a, 32b movable in opposite directions along the first ring 22 and a fixed receptacle 34 arranged between those connecting brackets 32a, 32b. In the released state, as shown in FIG. 1, the connecting brackets 32a, 32b are at the maximum distance from each other (FIG. 6).

[0046] The fixed receptacle 34 is disposed on the first ring 22. The connecting brackets 32a, 32b are rotatably attached respectively on separate operating rings, i.e., on the outer operating ring 36a and the inner operating ring 36b which are coaxially disposed and rotatably attached on the first ring 22. By rotating the operating rings 36a and 36b in circumferential directions opposite to each other, the connecting brackets 32a, 32b can move synchronously between the open configuration shown in FIGS. 1 and 6 and the closed configuration shown in FIGS. 2 and 5.

[0047] In their open configuration, for transporting the separation system 20, the connecting device can receive the corresponding connecting pins 38 of the second ring 24 which are disposed along the periphery of the second ring 24 and aligned with the position of the connecting device on the first ring 22. While the satellite is being deployed into orbit, the connecting pins 38 of the second ring 24 can be released from the connecting device in their open configuration.

[0048] The connecting pins 38 can have various shapes. As shown in FIG. 1, those connecting pins may show a shape like a knob designed to be closed by the corresponding connecting surfaces of the connecting brackets 32a, 32b and held in a predetermined position in the closed configuration.

[0049] The operation of the outer and inner operating rings 36a and 36b, and thus the connecting brackets 32a, 32b, is performed by the releasing means 40. The releasing means 40 comprises a plurality of two - arm operating levers 42 pivotally attached to the first ring 22 at respective pivots 44. The inner arm of each operating lever 42 is connected to the inner operating ring 36b, and the outer arm of each operating lever 42 is connected to the outer operating ring 36a, such that pivoting about the pivot 44 drives the operating rings 36a and 36b in circumferential directions opposite to each other. This can be best understood by comparing FIGS. 5 and 6.

[0050] The release means 40 further comprises a plurality of release springs 46, each of which is connected to and designed to actuate each operating lever 42. As shown in FIGS. 1 and 6, the release springs 46 are in a relaxed position, which establishes the lever position of the operating lever 42 corresponding to the open arrangement of the connecting brackets 32a, 32b.

[0051] To launch the satellite into orbit, the separation system 20 comprises deployment means 26 for applying a separating force to the first ring 22 and the second ring 24.

[0052] The deployment means 26 comprises a plurality of lever mechanisms, each of which comprises a first lever 48 and a second lever 50 which are pivotally connected to each other at a central pivot 49 so as to have a pair of pliers-like shapes.

[0053] FIG. 1 shows the lever mechanism in the released state, which takes the shape of an inverted Y. In the region of each first end, both the first and second levers 48, 50 are attached directly to the first ring 22 or indirectly to a component attached to that ring. In particular, the first end of the second lever 50 is connected to the first ring 22, while the first end of the first lever 48 is rotatably attached to and coaxial with the first ring and is connected to a third actuating ring 52. The third actuating ring 52 rotates back and forth when the pliers-like lever mechanism moves between the open state (FIG. 1) and the closed state (FIG. 4).

[0054] As shown in FIGS. 1 to 3, the separation system 20 comprises four lever mechanisms evenly distributed around the circumference of the first ring 22. Simultaneous operation of the four lever mechanisms ensures a linear deployment of the satellite along the release axis D, i.e., perpendicular to the plane of the first ring 22, without inducing a tilting moment by the separation system 20. The second end of each first lever 48 forms a contact point 28 with the second ring 24, thereby applying the separating force of the deployment means 26 to the second ring 24 during launch of the satellite into orbit.

[0055] The deployment means 26 further includes a first group of springs 54 and a second group of springs 56. The first group of springs 54 has a spring force different from the spring force of the second group of springs 56. Each of the springs 54 and 56 defines a longitudinal axis along which compression of the spring occurs during preloading. The longitudinal axes of each spring 54 of the first group and each spring 56 of the second group are arranged tangentially with respect to the first ring 22. In particular, the longitudinal axis of the first group of springs 54 is directed parallel to the plane of the first ring 22, while the longitudinal axis of the second group of springs 56 is in contact with the first ring 22 and is directed to a plane parallel to the release axis D.

[0056] FIG. 1 shows the first group of springs 54 in a relaxed state corresponding to the released state of the separation system. In this position, the second ring 24 is removable from the first ring 22. The first group of springs 54 connects the first ring 22 to the third actuating ring 52, which is best seen in FIG. 3. In this embodiment, the first group of springs 54 is connected to the first ring 22 in the region of the connection point between the second lever 50 and the first ring 22 and to the third actuating ring 52 in the region of the connection point between the first lever 48 and the third actuating ring 52. However, it is also possible to arrange the first group of springs 54 at other positions around the circumferences of the first ring 22 and the actuating ring 52.

[0057] The first group of springs 54 functions as an actuator for rotating the third actuating ring 52 with respect to the first ring 22. Ultimately, all of the first and second levers 48, 50 of the lever mechanism of the deployment means 26 are connected to each other via mechanical restricted guidance by the first ring 22 and the third actuating ring 52, i.e., a movement of one of the levers 48, 50 is immediately transmitted to all of the other levers 48, 50 via the rings 22, 52.

[0058] The springs 56 of the second group can be seen, for example, in FIG. 4, which shows a detailed side view of the lever mechanism of the deployment means 26 in the retained state. The springs 56 of the second group act as starter springs and assist in the initial operation of the lever mechanism when the satellite is deployed. The starter springs 56 are arranged on one arm of each of the second levers 50 and, in the retained state, they are compressed against the restoring force by the associated first lever 48. Next, the starter springs 56 exert a spring force on the associated first lever 48. Alternatively, the starter springs 56 may be arranged on the first lever 48, or on both the first and second levers 48, 50.

[0059] The first end of the first lever 48 and the first end of the second lever 50 are each rotatably mounted about two axes S1 and S2 that are perpendicular to each other. Thus, when the springs 54 of the first group go from the relaxed state to the preloaded state, or vice versa, and their longitudinal elongation changes during that process (FIGS. 5 and 6), the longitudinal axis of the springs 54 of the first group remains tangentially oriented with respect to the first ring 22.

[0060] FIG. 2 shows the separation system 20 in the transport or retained state. The transition from the released state of FIG. 1 to the transport state of FIG. 2 includes the following steps.

[0061] The deployment means 26 is brought into the transport state by folding the lever mechanism in the closed state, for example, by aligning the second ring 24 with the contact point 28 of the deployment means 26 and pushing the second ring 24 downward onto the first ring 22. Thus, the connecting pin 38 of the second ring 24 is brought between the connecting brackets 32a, 32b of the connecting device within the fixed receptacle 34 of the first ring 22.

[0062] As a result, the springs 54 of the first group are lengthened and thus a preload is applied by the rotation of the third actuating ring 52 relative to the first ring 22 (FIG. 3). The arms of the first and second levers 48, 50 are positioned closely to each other, and the springs 56 of the second group are compressed and thus a preload is applied by the first lever 48. An appropriately designed tool may be used to move the deployment means 26 to its holding position, thereby assisting in applying a preload to the springs 54 of the first group and the springs 56 of the second group (FIG. 4). In this held state, the first end of the first lever 48, the central pivot 49, and the first end of the second lever 50 are substantially aligned with each other. Thus, in this held state, the lever mechanism is at least approximately in an equilibrium state.

[0063] To fix the deployment means 26 in its holding position, a fixing bolt 58 is inserted into the openings 60 of the first lever 48 and the second lever 50, as well as the first ring 22 and the third actuating ring 52. The fixing bolt 58 prevents the movement of the third actuating ring 52 relative to the first ring 22 and the actuation of the deployment means 26 by the springs 54, 56 of the first and second groups. The fixing bolt 58 is removed before transporting the separation system 20 into orbit.

[0064] The movement of the connecting brackets 32a, 32b to their closed positions is effected by rotating the operating lever 42, which rotates the outer and inner actuating rings 36a, 36b in opposite directions relative to each other. For this purpose, a lever extension (not shown) can be attached to an appendage 72 of the operating lever 42 located on the opposite side of the first ring 22. By operating the lever extension, the preloading of all the release springs 46 and the closing of all the connecting brackets 32a, 32b are achieved simultaneously.

[0065] Even though spring force is applied to the operating lever 42 by the preloaded release spring 46, the separation system 20 includes a starter mechanism 62 connected to one of the operating levers 42 to fix the operating lever 42 in the holding position. The operation of the starter mechanism 62 can be obtained from FIGS. 5 and 6. The starter mechanism 62 includes a blocking bolt 64 that fixes the associated operating lever 42 in its holding position (FIG. 5). By the direct connection of all the operating levers 42 by the outer and inner operating rings 36a, 36b, all the operating levers 42, and thus the release means 40, are fixed in the holding position. The blocking bolt 64 is held in place by a first magnet 66a that cooperates with a first magnetic plate 70a provided on the first arm of the rocker lever 68, and a second magnet 66b that cooperates with a second magnetic plate 70b provided on the second arm of the rocker lever 68. The rocker lever 68 is connected to the blocking bolt 64 by a rod 69, and the rod 69 holds the blocking bolt 64 in a position that blocks the movement of the operating lever 42 when the first and second magnets 66a, 66b hold the first and second magnetic plates 70a, 70b. The first and second magnets 66a, 66b may be permanent magnets that generate a holding force without an energy input.

[0066] Starting from the transport state of the separation system 20, the deployment of the second ring 24 is carried out as follows. The start of the deployment is induced by the starter mechanism 62 as shown in FIG. 6. The magnetic field of the first magnet 66a is reduced, for example, by an electrically induced opposing field, reducing or canceling the holding force exerted by the first magnet 66a on the first magnetic plate 70a, rotating the rocker lever 68, for example, by a spring 71, and releasing the blocking bolt 64. Redundancy is incorporated into the starter mechanism 62 by the second arm of the rocker lever 68. During the deployment of the satellite, the separation system 20 can be programmed to continuously release both arms of the rocker lever 68 independently of each other. If the first arm of the rocker lever 68 cannot release the blocking bolt 64, the other arm can be actuated.

[0067] The operating lever 42 previously held by the blocking bolt 64 is released, and a plurality of preloaded release springs 46 relax simultaneously across the circumference of the separation system 20. As a result, since the plurality of operating levers 42 rotate simultaneously, the outer and inner actuating rings 36a, 36b rotate circumferentially in opposite directions relative to each other, thereby moving the plurality of connecting brackets 32a, 32b simultaneously to their open positions across the circumference of the separation system 20.

[0068] Accordingly, the holding force of the connecting brackets 32a, 32b on the connecting pins 38 is canceled, and the preloaded springs 54, 56 of the deployment means 26 can relax. A group of status springs 56 immediately apply their full spring force to the first lever 48 of the deployment means 26. Thereby, the lever mechanism smoothly moves from its equilibrium state, and the first group of springs 54 actuates the deployment means 26 to shift to the release position as shown in FIG. 1. In this release position, the second ring 24 is not connected to the first ring 22 and is lifted by the spring force, thereby ejecting the second ring 24 together with the satellite.

[0069] The movement of the levers 48, particularly the movement of the contact point 28 between their holding and release positions along the release axis D, is preferably greater than the stroke of the first group of springs 54. Accordingly, as a result of the lever mechanism, the spring force applied by the first group of springs 54 is applied to the second ring 24 over a longer movement range and thus more smoothly compared to the arrangement of the springs acting directly between the first ring 22 and the second ring 24.

[0070] The maximum movement range of the second ring 24 between its holding position and its release position with respect to the first ring 22 along the release axis D is at least 4 cm, preferably at least 6 cm, and in particular at most 8 cm. Due to the shape of the lever mechanism of the deployment means 26, the separating force exerted by the deployment means 26 increases upon release. Starting from at least approximately the equilibrium position of the lever mechanism, the separating force directed along the release axis D is small at the start of deployment, increases during the deployment process, thereby ensuring a smooth and normal ejection of the satellite into orbit.

Explanation of Signs

[0071] 20…Separation system 22…First ring 24…Second ring 26…Deployment means 28…Contact point 30…Holding device 32a…Outer connection bracket 32b…Inner connection bracket 34…Fixed receptacle 36a…Outer actuating ring 36b…Inner actuating ring 38…Connecting pin 40…Release means 42…Operating lever 44…Pivot of the operating lever 46…Release spring 48…First lever 49…Central pivot of the lever mechanism 50…Second lever 52…Third actuating ring 54…First group of springs 56…Starter spring 58…Fixed bolt 60…Opening 62…Starter mechanism 64…Blocking bolt 66a…First magnet 66b…Second magnet 68…Rocker lever 69…Rod 70a…First magnetic plate 70b…Second magnetic plate 71…Spring of the starter mechanism D…Dispensing axis S1…First pivot axis S2…Second pivot axis

Claims

1. A separation system (20) for launching a satellite from a launch vehicle along a release axis (D), comprising: a first ring (22) for attachment to said launch vehicle; a second ring (24) for attachment to said satellite; - retention means interconnecting said first ring (22) and said second ring (24) in a retention position; - deployment means (26) for separating the first ring (22) from the second ring (24) by means of a plurality of springs (54), the deployment means (26) comprising a plurality of lever mechanisms, each of the lever mechanisms comprising a spring (54), a first lever (48) having a first end and a second end, and a second lever (50) pivotally connected to the first lever (48) at a pivot (49) located between the first end and the second end of the first lever (48); - releasing means (40) for releasing the interconnection between said first ring (22) and said second ring (24); Equipped with - said springs (54) are attached to each of said lever mechanisms operable to separate said first ring (22) from said second ring (24); - said lever mechanism releasably supports said second ring (24) against said first ring (22) at a contact point (28) located at said second end of said first lever (48); A separation system (20), wherein all levers of said lever mechanism are linked via mechanical limited guiding means, whereby the movement of one lever of said lever mechanism is transmitted to all levers of said lever mechanism without time delay and damping, thereby ensuring that the separation forces by said deployment means (26) act simultaneously and synchronously on said second ring (24).

2. 2. The separation system (20) of claim 1, wherein the range of movement of the levers (48, 50) of the lever mechanism along the ejection axis (D) is greater than the range of movement of the spring (54).

3. The separation system (20) of claim 1, wherein the separation force exerted by the deployment means (26) increases upon release.

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