DEVICE FOR HOLDING AND DELIVERING AN ON-BOARD SYSTEM TO AND FROM A SPACECRAFT

Description

technical field

[0001] This disclosure falls within the domain of spacecraft equipment, including satellites or launch vehicles, and more specifically concerns a restraint and release device for an onboard system in relation to a spacecraft. Previous technique

[0002] Retention and release devices are used for deployable onboard systems of spacecraft, particularly satellites. These onboard systems can include, for example, telescopic masts, antennas, solar panels, reflectors, or observation and targeting equipment, which are typically held against the satellite during launch in a so-called launch configuration. The onboard systems are folded to minimize their volume when located within the launch vehicle's fairing, which has limited space. Once the spacecraft is launched, the onboard systems are deployed in a deployment configuration to assume an operational position, which may vary during the spacecraft's operational life.

[0003] Retention and release devices are also used to hold one or more onboard systems, such as a satellite stack on the launcher, such a stack being for example held securely to the launcher in the launch configuration.

[0004] The restraint and release devices generally include pre-tensioning systems, i.e. pre-loading, which can be released at the stacking points, i.e. compact and steep restraint points of onboard systems or spacecraft, particularly when the onboard systems or spacecraft are of large mass and / or large dimensions, typically with a mass greater than 10kg or even 15kg and / or dimensions (length and / or width) greater than 0.5m or even 1m.

[0005] Retention and release devices typically clamp embedded systems against a support due to mechanical and accommodative constraints. This generally requires preloaded tie rods with high preload levels. Tie rods are usually of reduced diameter due to mass constraints, which minimizes tie rod stiffness and thus increases the level of strain energy stored within the tie rod.

[0006] To hold the pre-loaded stay in place during launch and then release it during deployment, a locking and unlocking mechanism, commonly known as an HDRM (Hold-Down and Release Mechanism), is used. Many types of locking and unlocking mechanisms exist, using, for example, pyrotechnic systems (i.e., those employing combustion to destroy a connecting component), electromagnetic systems, or systems based on separating the components by heating. For instance, there is patent application WO 2017 / 055706, filed by AIRBUS DEFENCE AND SPACE SAS, for a controlled separation device between two components.

[0007] The preload is released typically abruptly, within a few tens of milliseconds, by the HDRM. Thus, the deformation energy stored in the stay is abruptly released and transferred to the spacecraft or a deployable appendage.

[0008] During these sudden energy transfers, the resulting shock could damage surrounding elements and might require these surrounding elements to be oversized to allow them to withstand this level of shock.

[0009] There is therefore a need to prevent damage to surrounding elements in the spacecraft when the preload is released, without oversizing, and therefore weighing down, the onboard systems.

[0010] Solutions to address this need have been proposed.

[0011] Among them, as notably described in patent EP 2 279 120 entitled "Device for assembling objects and then quickly releasing them," one solution involves designing the stacking point with a fitted conical shape and a wire or band spring system. This allows for the gradual release of the preload in the tie rod, thus dissipating the deformation energy through friction. Such a solution is limited to releasing the preload over a few millimeters and therefore does not meet the needs of very long, and thus highly flexible, tie rods. Furthermore, the costs generated by this solution are higher compared to split nut-type high-density tensioning mechanisms (HDRMs).

[0012] Another known solution involves converting the deformation energy of the tie rod into kinetic energy, thereby completely ejecting the tie rod. This solution is incompatible with an ethical and responsible use of the space environment in Earth orbit, aimed at limiting orbital debris.

[0013] Yet another known solution builds upon the previous one and consists of adding an energy absorption or dissipation system; such a system can be of the following nature: elastic, spring or suspension type, but in this case, the energy absorption or dissipation system can be very heavy, typically 200 J / Kg, or generate too many shocks on the high levels of stored elastic energy; or elastomer or other material of the same type, but such a solution generates the same problems as for the elastic system to which is added a problem of material compatibility with the space environment; or energy dissipation by mechanical plasticization, such as a crushable honeycomb or a mechanical fuse, but such a solution still poses the same problems as the two previous ones, and can be risky with regard to guaranteeing the absence of debris generation or particulate contamination; or even viscous fluidic damping, but the implementation of such a solution can be complex in the space environment and for very high reliability.

[0014] Another known solution involves using the nut housing to dissipate some of the energy through electromagnetic forces, but this remains limited in its application and operational limitations. The nut housing adds bulk and weight. Furthermore, cable tensioning and damping are particularly limited.

[0015] US 2019 / 031374 A1 discloses a restraint and release device for an onboard system in relation to a spacecraft.

[0016] US 2021 / 293225 A1 discloses a bolt retrieval device intended for use with separation nuts incorporating a magnetic damping system.

[0017] This highlights the need to improve existing restraint and release mechanisms. Summary

[0018] This disclosure improves the situation.

[0019] A device is proposed for the restraint and release of an onboard system from a spacecraft, the restraint and release device comprising: at least one support platform integral with the spacecraft, the retention and release device being configured to retain the onboard system against the support platform in launch configuration and to release the onboard system in deployment configuration, at least one tie rod, said tie rod being stretched along a longitudinal axis in launch configuration, at least one preloading system configured to preload said tie rod in launch configuration with a determined strain energy, said preloading system comprising a head disposed at a first end of said tie rod, at least one holding and releasing mechanism disposed at a second end of said tie rod, configured to retain said tie rod preloaded in launch configuration,and to release said tie rod in a deployed configuration so as to transform said deformation energy into kinetic energy with a determined initial velocity of tie rod movement.

[0020] The restraint and release system also includes: a magnetic damping system comprising: ∘ at least one electrically conductive tube having two open ends forming a through passage, said tube being disposed around the tie rod, between the head and the holding and releasing mechanism, said tube being fixed relative to the support base at least in the launch configuration and being connected to the support base or the on-board system, ∘ at least one permanent magnet fixed to the tie rod and interposed between the tie rod and said at least one tube,said at least one magnet and said at least one tube being configured such that the speed of movement of said at least one magnet in its deployed configuration creates eddy currents in said at least one tube so as to dissipate the kinetic energy as heat and thus reduce the speed of movement of the tie rod to a negligible or zero final speed after said at least one magnet has traveled a determined distance relative to said at least one tube.

[0021] The solution proposed in this disclosure offers multiple advantages. The solution proposed according to the present invention is advantageously compact and lightweight. In particular, it allows for the reuse of surrounding components.

[0022] The solution proposed in this disclosure also makes it possible to meet the needs of very long and therefore very flexible tie rods with significant longitudinal deformations, for example of 10mm or more.

[0023] The solution proposed in this disclosure also avoids generating debris. Furthermore, it creates no pollution other than very low-frequency magnetic pollution.

[0024] The solution proposed in this disclosure can be reused indefinitely, particularly for validation testing of the mechanism.

[0025] The solution proposed in this disclosure is inexpensive to implement because it imposes few assembly or operational constraints. It is a passive system, with the exception of the holding and releasing mechanism, which typically includes a separate nut that is also inexpensive.

[0026] The solution proposed in this disclosure allows for complete and adjustable control, through design or testing, of the level of energy dissipation as heat. Furthermore, this dissipation level can be easily adjusted even very late in the product development cycle.

[0027] The present disclosure allows the tie rod(s) to be ejected in a controlled manner, but with the damping system forming an energy dissipation system by eddy currents.

[0028] The presence of the damping system allows the deformation energy stored in the tie rod(s) to be dissipated in a controlled manner in order to limit the shocks exported to the on-board system or the risks of damage.

[0029] The features described in the following paragraphs may optionally be implemented independently of each other or in combination with each other.

[0030] The restraint and release device may include a clearance space in line with the head. Such a clearance space allows for head movement during deployment.

[0031] The said distance of movement determined by said at least one magnet is preferably greater than 50 mm, being preferably between 200 mm and 350 mm.

[0032] The length of said at least one tube extending towards the head, from said at least one magnet, may be greater than said determined distance of displacement of the tie rod by at least one determined gap.

[0033] The retaining and release device may further include a guide assembly configured to linearly guide the tie rod during its movement. The guide assembly may include at least one guide arranged along the longitudinal axis of the tie rod and fixed relative to the tie rod or to the support base.

[0034] Each guide can be positioned at a predetermined distance from the head of the tie rod based on at least one buckling antinode determined as a function of the initial velocity of movement of the tie rod, the length of the tie rod and the distance of the magnet from the head.

[0035] The guide(s) placed in the tube and located between the tie rod and the inner wall of the tube ensures rectilinear kinematics.

[0036] The retention and release device may further include at least one return spring disposed around the tie rod and bearing, at least temporarily, against an element integral with the tie rod, in particular against a stop present on the tie rod, and against an element integral with the support base, in particular against the head, at least in launch configuration, to return the released tie rod to a predetermined final position, said predetermined final position of the tie rod corresponding to a final distance of displacement of said at least one magnet less than said determined distance of displacement of said at least one magnet.

[0037] The presence of return spring(s) allows the residual energy to be absorbed at the end of the stroke and ensures better repeatability and stability of the tie rod in the final position.

[0038] Said at least one return spring may be located in a portion of the tie rod that is not enclosed by said at least one tube. There may be several springs, in particular at least two. The spring(s) are slightly constrained during launch and have a low level of stored energy.

[0039] Said at least one magnet may exhibit a magnetic moment chosen according to said determined displacement distance and according to the deformation energy.

[0040] Said at least one tube may have a cylindrical section with an average diameter between 10 mm and 50 mm, in particular equal to 20 mm and with a thickness between 1 mm and 5 mm, in particular equal to 2 mm.

[0041] The tie rod may have a slenderness ratio, that is, a length-to-diameter ratio, of at least 10, preferably greater than or equal to 100. The tie rod preferably has a length greater than or equal to 0.5 m, in particular a length between 0.5 m and 10 m, in particular between 1 m and 3 m. The tie rod preferably has a diameter less than or equal to 100 mm, in particular a diameter between 1 m and 20 mm.

[0042] The retention and release device can be configured so that the initial movement speed of the tie rod in deployment configuration is greater than or equal to 0.1 ms-1.

[0043] Said at least one tube may be made of a metallic material with a conductivity greater than 10⁶, preferably greater than 10*10⁶, being preferably made of aluminium.

[0044] The on-board system may be a telescopic mast comprising a hollow threaded drive rod during its deployment and constituting said at least one tube.

[0045] Alternatively, the onboard system could be a satellite stack.

[0046] The preloading system can be configured so that the preload in the tie rod created by the preloading system in launch configuration is between 1N and 1000kN, in particular greater than 500 N, or even greater than 1000 N.

[0047] The preloading system can be configured so that the determined strain energy stored in the tie rod in the launching configuration is greater than 10 Joules, for example being approximately equal to 60 Joules.

[0048] According to another aspect, a spacecraft is proposed carrying an onboard system attached to the spacecraft, in launch configuration, by at least one restraint and release device as defined above. Brief description of the drawings

[0049] Other features, details, and advantages will become apparent upon reading the detailed description below and analyzing the attached drawings, on which: [ Fig. 1 [ ] schematically shows, in partial side view, an example of a restraint and release device for an onboard system relative to a spacecraft in launch configuration. Fig. 2 ] is a view similar to the figure 1 of the restraint and release mechanism of this example during deployment. Fig. 3 ] is a view similar to the figure 1 of the restraint and release mechanism of this example at the end of deployment. Fig. 4] shows schematically, partially and in side view, an example of a spacecraft carrying an onboard system attached to the spacecraft by a restraint and release device as illustrated on the figures 1 to 3 . [ Fig. 5 [ ] shows a graph illustrating the displacement of the tie rod and the energy level as a function of time, during deployment, in the example of figures 1 to 4 . [ Fig. 6 ] is a view similar to the figure 4 another example of a spacecraft carrying an onboard system attached to the spacecraft by a retention and release device, in launch configuration. Fig. 7 ] is a view similar to the figure 1 of the restraint and release device, following the example of the figure 6 . [ Fig. 8 ] is a view similar to the figure 1 another example of a restraint and release device to restrain and release another onboard system from another spacecraft, in launch configuration. Description of the implementation methods

[0050] In the various figures, the same reference numerals designate identical or similar elements. For the sake of brevity, only the elements that are useful for understanding the described embodiment are shown in the figures and are described in detail below.

[0051] Reference is now made to the example illustrated on the figures 1 to 4 An example of a retention and release device 20 of an embedded system 2 is shown there, more clearly visible on the figure 4 , compared to a spacecraft 1 comprising a support platform 4. The retention and release device 20 is configured to retain the onboard system 2 against the support platform 4 in the launch configuration illustrated on the figure 1 and also on the figure 4 and to release or deploy the embedded system 2 in the deployment configuration, illustrated on the figures 2 And 3 .

[0052] As shown figure 1The retaining and releasing device 20 comprises at least one tie rod 3, in this example, one tie rod 3. The tie rod 3 is elongated along a longitudinal axis X. The tie rod 3 is in the form of a solid metal rod. The tie rod 3 in this example has a slenderness ratio, that is, a length-to-diameter ratio, of at least 10, preferably greater than or equal to 100. In particular, the tie rod 3 preferably has a length greater than or equal to 0.5 m, in particular a length between 0.5 m and 10 m, in particular between 1 m and 3 m, in this example equal to 2 m. Furthermore, the tie rod 3 preferably has a diameter less than or equal to 100 mm, in particular a diameter between 1 mm and 20 mm, in this example equal to 4 mm. The slenderness ratio of the tie rod 3 in this example is 500. Thus, the tie rod 3 is very long and very thin.The tie rod 3 can be made of a material chosen from the group consisting of rolled stub steel, pultruded carbon, titanium and their alloys.

[0053] The retention and release device 20 also includes at least one preloading system 5 configured to preload the tie rod 3 in its launching configuration with a predetermined strain energy Edef max. The preloading system 5 comprises a head 21 disposed at a first end 22 of the tie rod 3. In this example, the first end 22 is a distal end with respect to the support base 4.

[0054] The retaining and releasing device 20 also includes at least one holding and releasing mechanism 6, of the HDRM type, disposed at a second end 23 of the tie rod 3, which is a proximal end in this example, the holding and releasing mechanism 6 being integral with the support base 4. It should be noted that the first and second ends 22 and 23 correspond to end portions.

[0055] The holding and releasing mechanism 6 is configured to hold the pre-loaded tie rod 3 in the launching configuration, and to release the tie rod 3 in the deployment configuration so as to transform the strain energy E def max into a kinetic energy with a determined initial velocity of displacement v 0 of the tie rod 3.

[0056] The retaining and releasing device 20 further includes a magnetic damping system 10. Such a damping system 10 is suitable for large tie rod extensions, as is the case in the illustrated example given the dimensions of the tie rod 3.

[0057] By "damping system suitable for large span tie rod extensions", we mean, for example, a damping system suitable for extensions between 1 and 10 mm for tie rods with a length between 0.5 m and 10 m....

[0058] The damping system 10 comprises at least one tube 11, in this example an electrically conductive tube 11, having two open ends 25 forming a through-hole 26. The tube 11 is arranged around the tie rod 3, between the head 21 and the holding and releasing mechanism 6. The tube 11 extends along the longitudinal axis X. The tie rod 3 passes through the tube 11 lengthwise, preferably at its center. The tube 11 is fixed relative to the support base 4, at least in the launch configuration, and is connected to the support base 4 or to the onboard system 2, in this example to the support base 4.

[0059] Tube 11, in this example, has a cylindrical cross-section with an average diameter between 10 mm and 50 mm (20 mm in this example) and a thickness between 1 mm and 5 mm (2 mm in this example). Tube 11 may or may not be threaded. It can form a hollow worm gear.

[0060] In this example, tube 11 is made of a metallic material with a conductivity greater than 10⁶ Ω⁻¹·m⁻¹, preferably greater than 10 × 10⁶ Ω⁻¹·m⁻¹, and is preferably made of aluminum, chosen for its dissipation performance and density. Indeed, the conductivity of aluminum Al 6061 T6, for example, is considered to be 2.49 × 10⁷ Ω⁻¹·m⁻¹. Tube 11 may not be made of a ferromagnetic material.

[0061] The damping system 10 also includes at least one permanent magnet 12; in this example, several magnets 12 are schematically represented with a single magnet 12 for clarity of the drawing. This magnet 12 is fixed to the tie rod 3 and interposed between the tie rod 3 and the tube 11. The magnet 12 and the tube 11 are configured such that the speed of movement of the magnet 12, corresponding to the speed of movement of the tie rod 3, with the magnet 12 fixed to the tie rod 3 in its deployed configuration, creates eddy currents in the tube 11. These currents dissipate the kinetic energy as heat and thus reduce the speed of movement of the tie rod 3 to a negligible or zero final speed vf after the magnet 12, and therefore the tie rod 3, has traveled a predetermined distance dmax relative to the tube 11. This maximum deployed configuration is illustrated in the diagram. figure 2 Thus, the head 21 has a maximum linear displacement L3.

[0062] Advantageously, the damping system 10 comprises several permanent magnets, whose magnetic moment varies in size to dampen the travel of the tie rod 3 to a greater or lesser degree. It should be noted that the damping force is proportional to the ejection velocity, i.e., to the initial velocity v0. The magnetic moment can be between 1 and 20 Am2, in this example 8A.m2.

[0063] Tie rod 3 is preferably made of a non-magnetic material to avoid disturbing the magnetic field in tube 11 and to maximize the eddy currents created.

[0064] As seen on the figure 1 For example, the retaining and releasing device 20 includes a clearance space extending from the head 21. This allows the retaining and releasing device to be designed without a bolt catch for the head. As a result, the mass is reduced and the shocks caused by bolt catches are avoided.

[0065] The length L2 of the tube 11 extending from the magnet 12 towards the head 21 is greater than the determined maximum displacement distance dmax of the tie rod 3 by at least a specified distance, in order to avoid edge effects. The tube always protrudes on both sides of the magnet and generates eddy currents depending on the magnet's velocity parameter, while the geometry of the tube relative to the magnet remains unchanged. The total length L1 of the tube 11 is at least equal to the ejection length, i.e., the determined maximum displacement distance dmax of the tie rod 3, in this example 25 cm.

[0066] It should be noted that the determined displacement distance dmax is the maximum distance initially traveled by tie rod 3 once the deployment configuration is engaged. It should be noted that this distance will subsequently be reduced to a final distance df, which is less than dmax, due to the presence of return spring(s) in this example, as will be detailed later. The determined displacement distance dmax is illustrated in the figure 2 while the determined displacement distance df is illustrated on the figure 3 .

[0067] The retaining and releasing device 20 in this example includes a guide assembly 14 configured to guide the tie rod 3 linearly in its movement, in particular relative to the tube 11. The guide assembly 14 includes, again in this example, at least one guide 15, 19 arranged along the longitudinal axis X of the tie rod 3 and fixed relative to the tie rod 3 or relative to the support base 4 at least in the launching configuration.

[0068] In this example, the guide assembly 14 includes a guide 15, in particular located near, or even against, the magnet 12, and fixed relative to the tie rod 3. The guide 15 ensures the sliding guidance in translation of the tie rod 3 relative to the tube 11, since it extends between them.

[0069] There may be several guides 15, for example three guides 15, extending between the tie rod 3 and the tube 11, depending on the length of the tie rod 3, for example, and arranged at intervals, particularly regular intervals, calculated to prevent buckling of the tie rod 3. Indeed, buckling, which is an S-shaped deformation, is created by the mechanical wave propagating in the tie rod 3 and is therefore prevented by the presence of the guide(s) 15 if they are specifically positioned at the buckling antinodes. The distance between two guides 15 may be less than 500 mm. Each guide 15, fixed relative to the tie rod 3, is, for example, positioned at a determined distance from the head 21 of the tie rod 3, based on at least one buckling antinode determined according to the initial displacement velocity v0 of the tie rod 3, the length of the tie rod 3, and the distance of the magnet 12 from the head 21.It is noted that tube 11, which plays a role in damping tie rod 3, also participates in guiding tie rod 3.

[0070] Furthermore, the guide assembly 14 includes at least one guide 19 fixed relative to the onboard system 2 or the spacecraft, in this example two guides 19, forming bearings capable of sliding relative to the tie rod 3. Such guides 19 allow the tie rod 3 to be guided relative to the onboard system 2.

[0071] In the illustrated example, the retention and release device 20 also includes at least one return spring. In this example, two return springs 17 and 18 are arranged around the tie rod 3 and bear, respectively, at least temporarily, against an element fixed to the tie rod 3—in this example, against a stop 16 on the tie rod 3 or the head 21—and against an element fixed to the support base 4—in this example, one of the guides 19. A slight compressive force can be applied to the return springs 17 and 18 in the launching configuration, for example, 10 N for spring 18 and 0.1 N for spring 17. Such return springs 17 and 18 allow, at the end of the deployment configuration, after a predetermined displacement of the tie rod 3, the released tie rod 3 to be returned to a predetermined final position, different from its initial launch position. This predetermined final position of the tie rod 3 is illustrated in the figure 3, corresponds to a final displacement distance df of the magnet 12 less than the determined displacement distance d max of the magnet 12, or of the tie rod 3. Such a return movement is optional, the tie rod can be stopped by eddy currents only, but in this case possibly at a position that would be less predictable or repeatable.

[0072] The displacement of tie rod 3 and the evolution of energy over time are shown on the figure 5 .

[0073] The strain energy stored in the tie rod 3 in the launching configuration is referenced as Edef max. All of this energy is considered to be transformed into kinetic energy. The main damping force is generated by the damping system 10.

[0074] At time t0, in the launch configuration, the tie rod 3 is held in a preloaded state by the holding and releasing mechanism 6. The preloading system 5 is preferably configured such that the preload in the tie rod 3 created by the preloading system 5 in the launch configuration is between 1 N and 1000 kN, in particular greater than 500 N, or even greater than 1000 N. The preloading system 5 is configured such that the maximum predetermined strain energy Edef max stored in the tie rod 3 in the launch configuration is greater than 10 Joules, or even greater than 50 Joules.

[0075] Immediately after t0, when deployment is triggered, the holding and releasing mechanism 6 releases the pre-loaded tie rod 3 with a maximum strain energy Edef max, which is converted into kinetic energy, moving the tie rod 3 with an initial velocity v0. The strain energy is entirely converted into kinetic energy at t1. The initial velocity v0 of the tie rod 3 in the deployed configuration is, for example, greater than or equal to 0.1 m / s. However, the damping system 10, with the magnet 12 which is driven in translation with the tie rod 3 relative to the tube 11, very quickly dissipates all the kinetic energy as heat, due to eddy currents. The energy is completely dissipated and becomes zero at t2, as does the velocity of the tie rod 3. The dissipation of kinetic energy at t2 occurs after the conversion of strain energy into kinetic energy at t1.The tie rod 3 is stopped at the determined displacement distance d max. The displacement of the tie rod 3 is linear. A guide assembly 14 is provided.

[0076] Then, the presence of the return springs 17 and 18 returns the tie rod 3 at low speed in the opposite direction, until it reaches a final distance df at t3, the final position illustrated on the figure 3and in which the tie rod 3 is stabilized and immobile. The action of these springs 17 and 18 is negligible until the magnet has reached zero or negligible velocity. Thus, these springs do not contribute to the dissipation of the tie rod's kinetic energy. The final distance df corresponds at least to the elongation of the tie rod 3 after the dissipation of the strain energy generated by the preload. The distance df is controlled and therefore predetermined, due to the choice and presence of the return springs 17 and 18, as well as their preload, which is low relative to the preload of the tie rod 3 in the launching configuration, being, for example, on the order of 0.2 Joules. The return springs 17 and 18 also prevent shocks during the return movement.

[0077] The determined displacement distance dmax of the magnet 12 of the tie rod 3 is preferably greater than 50 mm, preferably between 200 mm and 350 mm, in this example equal to 250 mm. It should be noted that the magnet 12 preferably has a magnetic moment chosen as a function of this determined displacement distance dmax and as a function of the deformation energy Edefmax.

[0078] After deployment, due to the release of the preload in tie rod 3, tie rod 3 undergoes an elongation, meaning it is slightly longer than its initial length in the launch configuration. For example, if tie rod 3 has a length of 200 mm in the launch configuration, then this length will be, for example, 204 mm after stabilization in the final position. It should be noted that the goal is not for tie rod 3 to become fully reattached to the holding and releasing mechanism 6 in the final position. Thus, the final displacement distance df is preferably at least equal to the elongation of tie rod 3, which in the example given is 4 mm.

[0079] The damping created by the eddy current damping system is viscous damping, proportional to the speed, not creating friction and not creating stress at zero speed, or more precisely not creating stress at zero speed, in the absence of an external disturbing magnetic field, which in the case of the space environment has an almost negligible impact on the system.

[0080] In the example of figures 1 to 5 , and as visible on the figure 4 The onboard system 2 is a telescopic mast with a hollow threaded drive rod for deployment, forming the tube 11. In this case, the spacecraft 1 carrying such an onboard system 2, attached to the spacecraft 1 in launch configuration by means of the retention and release device 20, is a satellite. It should be noted that the tube 11 serves both as a drive rod during deployment and as part of the damping system 10.

[0081] This is also the case with the example of figures 6 And 7 However, this example differs from that of figures 1 to 5 in that the holding and releasing mechanism 6 is disposed at the second end 23 of the tie rod 3 which is a distal end with respect to the support base 4, while the head 21 of the preloading system 5 is disposed at the first end 22 of the tie rod 3 which is a proximal end with respect to the support base 4, in this example.

[0082] Thus, tie rod 3 remains attached to the satellite in the final position.

[0083] We illustrated on the figure 8Another example is in which the onboard system 2 is a stack 30 of satellites 40. In this case, the spacecraft 1 carrying such an onboard system 2, attached to the spacecraft 1 in launch configuration by means of the retention and release device 20, is a satellite launcher. The retention and release device 20 comprises a plurality of tie rods 3, two of which are shown in the figure 8 As can be seen, for each tie rod 3 there is a holding and releasing mechanism 6, a preloading system 5, a tube 11, etc.

[0084] In this example, tie rod 3 remains attached to the launcher.

[0085] Of course, this disclosure is not limited to the examples just described.

[0086] In particular, any device for retaining and releasing an onboard system from a spacecraft intended for terrestrial or aeronautical applications, geostationary orbit applications, or extraplanetary applications may be included. However, an application in low Earth orbit or on another celestial body is not suitable due to the interaction between the permanent magnet(s) of the damping system and the celestial body's magnetic field.

Claims

1. Retaining and releasing device (20) for an on-board system (2) relative to a spacecraft (1), the retaining and releasing device (20) comprising: - at least one support base (4) integral with the spacecraft (1), the retaining and releasing device being configured to retain the on-board system (2) against the support base (4) in a launch configuration and to release the on-board system (2) in a deployment configuration, - at least one tie rod (3), said tie rod (3) being stretched along a longitudinal axis (X) in the launch configuration, - at least one preloading system (5) configured to preload said tie rod (3) in the launch configuration with a determined deformation energy, said preloading system (5) comprising a head (21) disposed at a first end (22) of said tie rod (3), - at least one retaining and release mechanism (6) disposed at a second end (23) of said tie rod (3), configured to retain said preloaded tie rod (3) in the launch configuration, and to release said tie rod (3) in the deployment configuration so as to transform said deformation energy into kinetic energy with a determined initial displacement speed (v0) of the tie rod (3), characterized in that the retaining and releasing device (20) further comprises: - a magnetic damping system (10) comprising: • at least one electrically conductive tube (11) having two open ends (25) forming a through passage (26), said tube (11) being disposed around the tie rod (3), between the head (21) and the retaining and release mechanism (6), said tube (11) being fixed relative to the support base (4) at least in the launch configuration and being connected to the support base (4) or to the on-board system (2), • at least one permanent magnet (12) fixed to the tie rod (3) and interposed between the tie rod (3) and said at least one tube (11), said at least one magnet (12) and said at least one tube (11) being configured so that the displacement speed of said at least one magnet (12) in the deployment configuration creates Eddy currents in said at least one tube (11) so as to dissipate the kinetic energy into heat and thus reduce the displacement speed of the tie rod (3) to a negligible or zero final speed after said at least one magnet has traveled a determined distance (dmax) opposite said at least one tube (11).

2. Retaining and releasing device (20) according to any one of the preceding claims, comprising a clearance space in the extension of the head (21).

3. Retaining and releasing device (20) according to any one of the preceding claims, wherein said determined displacement distance (dmax) of said at least one magnet (12) is greater than 50 mm, being preferably comprised between 200 mm and 350 mm.

4. Retaining and releasing device (20) according to any one of the preceding claims, wherein the length of said at least one tube (11) extending towards the head (21), from said at least one magnet (12), is greater than said determined displacement distance of the tie rod (3) by at least a determined deviation.

5. Retaining and releasing device (20) according to any one of the preceding claims, further comprising a guiding assembly (14; 15, 19) configured to guide the tie rod (3) linearly in its displacement, the guiding assembly (14) comprising at least one guide (15, 19) disposed along the longitudinal axis (X) of the tie rod (3) and fixed relative to the tie rod (3) or relative to the support base (4).

6. Retaining and releasing device (20) according to any one of the preceding claims, further comprising at least one return spring (17, 18) disposed around the tie rod (3) and bearing, at least temporarily, against an element integral with the tie rod (3), and against an element integral with the support base (4), at least in the launch configuration, to return the released tie rod (3) to a predetermined final position, said predetermined final position of the tie rod (3) corresponding to a final displacement distance (df) of said at least one magnet (12) that is less than the determined displacement distance (dmax) of said at least one magnet (12).

7. Retaining and releasing device (20) according to any one of the preceding claims, wherein the tie rod (3) has a slenderness ratio of at least 10, preferably greater than or equal to 100, the tie rod (3) preferably having a length greater than or equal to 0.5 m, notably a length comprised between 0.5 m and 10 m, notably between 1 m and 3 m, the tie rod preferably having a diameter less than or equal to 100 mm, notably a diameter comprised between 1 m and 20 mm.

8. Retaining and releasing device (20) according to any one of the preceding claims, wherein said at least one tube (11) is made of a metallic material with a conductivity greater than 106, preferably greater than 10·106, being preferably made of aluminum.

9. Retaining and releasing device (20) according to any one of claims 1 to 8, wherein the on-board system (2) is a telescopic mast comprising a hollow threaded drive rod during its deployment and constituting said at least one tube (11).

10. Retaining and releasing device (20) according to any one of claims 1 to 8, wherein the on-board system (2) is a stack of satellites.

11. Retaining and releasing device (20) according to any one of the preceding claims, wherein the preloading system (5) is configured such that the preload in the tie rod (3) created by the preloading system (5) in the launch configuration is comprised between 1N and 1000kN, notably greater than 500 N, or even greater than 1000 N.

12. Retaining and releasing device (20) according to any one of the preceding claims, wherein the preloading system (5) is configured such that said determined deformation energy stored in the tie rod (3) in the launch configuration is greater than 10 Joules, being for example approximately equal to 60 Joules.

13. Spacecraft (1) transporting an on-board system (2) secured to the spacecraft (1), in a launch configuration, by at least one retaining and releasing device (20) according to any one of the preceding claims.