DEPLOYABLE SCREEN FOR SPACE TELESCOPE

Abstract

Deployable solar protection screen for space equipment (1) configured to move from a stored configuration to a deployed configuration and comprising: -- first rods (21), -- second rods (22) for deploying the screen (2) in a radial direction (r, θ), -- third rods (23) for deploying the screen (2) in an axial direction (z) and -- rotary links (24, 25) joining rods (21, 22, 23) together, the rotary links being active (25) storing a quantity of energy or passive (24), the second rods (22) and third rods (23) being folded when the screen (2) is in the stored configuration, the active rotary links (25) being configured to unfold said second and third rods (22, 23) and trigger the move from the stored configuration to the deployed configuration, by causing the passive rotary links (24) to rotate and deploy in an axial direction and in a radial direction.Abstract figure: Figure 1.

Description

Title of the invention: DEPLOYABLE SCREEN FOR SPACE TELESCOPE Technical field

[0001] The present disclosure relates to the field of protection of optical instruments and more particularly to the protection of optical space observation equipment, typically in a space telescope or in an Earth observation satellite. Prior art

[0002] Spacecraft, for example an exploration probe or an Earth observation satellite, may generally include space equipment (such as space telescopes), which may include components (e.g., mirrors) - vulnerable to illumination, coming directly from the Sun and / or from light reflections (e.g., reflections of light on the Moon or the Earth). It is therefore known, in the space field, to use protective screen type devices on board spacecraft in order to protect the onboard space equipment during observation phases, for example, when the spacecraft is in orbit.

[0003] The use of such protective screens is subject to numerous structural and functional constraints imposed by the space context. First of all, the launch phase of the spacecraft, for its placing in orbit by a launcher, imposes a limited volume and mass at launch, in particular within the limit of the dimensions of the launcher fairing of the space equipment. Such protective screens must therefore have compact structures and masses adapted to be embarked during launch. A gain in mass and a gain in volume are particularly sought for reasons of costs (in particular energy) of placing in orbit and choice of launcher. In addition, a gain in mass in orbit can also be sought because this limits the inertia of the satellite and consequently increases its agility.

[0004] Document US2015 / 0146288 filed in the name of UTAH STATE UNIVERSITY RESEARCH FOUNDATION teaches a petal-deployed telescope that includes space equipment including a half-cylinder screen in which the petals are partially deployed and extending beyond a deployed secondary mirror. Such space equipment, once in orbit, requires that the protective screen be constantly placed between the stray light source and the space equipment, in particular when the orientation of the spacecraft changes, for example when it passes the equator, in particular in the case of a sun-synchronous Earth orbit. Thus, The spacecraft generally performs orientation maneuvers, called "flips", in order to orient the protective screen towards the light source. These maneuvers, however, constitute losses of operational time for the spacecraft and in particular for the space equipment (eg, a space telescope does not acquire images during such orientation maneuvers). Such an orientation maneuver of a protective screen of a spacecraft is thus an operational constraint of the spacecraft. In addition, such orientation maneuvers are planned as quickly as possible, so that the space equipment can be quickly operational again. It is then expected that the solar protection screen has sufficient rigidity and damping during such orientation phases.

[0005] Patent EP2520494 filed in the name of THALES teaches a device for protecting multi-beam optical equipment. The protection device extending beyond a secondary mirror is deployed laterally to cover the main mirrors.

[0006] There appears to be a need to improve existing space equipment protection devices and in particular to improve their compactness while maintaining good performance when used in the space context. Summary

[0007] The present invention aims to overcome the drawbacks of the prior art by proposing a deployable protective screen for space equipment, in particular for deployable space equipment.

[0008] For this purpose, a deployable solar protection screen for space equipment is proposed, having at least one attachment zone to a platform of a spacecraft including said space equipment, said screen being configured to move from a stored configuration to a configuration deployed in orbit and characterized in that it comprises: - rods, - rotary connections joining rods together, the rotary connections being of the active rotary connection type storing a quantity of energy or of the passive rotary connection type, the rods being covered by a thermally insulating film folded when the screen is in the stored configuration and stretched between the rods when the screen is in the deployed configuration, in which the rods are constituted by at least: - first structural rods, forming a peripheral structural base in the stored configuration as well as in the deployed configuration, - second radial extension rods, connected together at least in pairs to form sets of second rods, each set of second rods connecting two consecutive first rods and being configured to deploy the screen in a radial direction, - third axial extension rods, connected together at least in pairs to form sets of third rods, each set of third rods connecting two consecutive first rods and being configured to deploy the screen in an axial direction and - each set of second rods or third rods comprising at least one active rotary connection, said second and third rod assemblies being folded when the screen is in the stored configuration, the active rotary joints being configured to unfold said second and third rod assemblies and trigger the transition from the stored configuration to the deployed configuration, by causing the rotation of the passive rotary joints and a deployment in an axial direction and in a radial direction.

[0009] Advantageously, the proposed protective screen has a particularly compact stored configuration and allows a particularly advantageous gain in volume and mass during the launch phase of the space vehicle. Notably, a deployment of the screen both in the axial direction and in the radial direction makes it possible to further optimize the compactness of the screen.

[0010] In addition, the proposed protective screen allows, while maintaining a reduced mass and compactness, in particular at launch, 360-degree protection around the space equipment, by both radial and axial deployment, which allows the spacecraft to avoid so-called "flip" orientation maneuvers: such a protective screen then ensures operational continuity for the space equipment. In particular, in the case of space telescopes having a petal-deployable main mirror and a secondary mirror that is also deployable, the proposed protective screen allows the telescope to be completely surrounded, regardless of the orientation of the spacecraft in space.

[0011] Furthermore, the proposed protective screen advantageously makes it possible to obtain a simple structure, which can be deployed by mechanical means, without requiring motorized means, via the energy stored in the active rotary connections, the deployment of the screen being induced by mechanical rotary movements of the rods via the rotary connections connecting the rods. In addition, the structure of such a protective screen allows stiffness of the screen once deployed, in particular once the pairs of second and third rods are unfolded.

[0012] The features set out in the following paragraphs may, optionally, be implemented, independently of one another or in combination with one another:

[0013] In an exemplary embodiment, the first rods are distributed in stages according to the axial direction, each stage comprising the same number of first rods, greater than or equal to three.

[0014] Consequently, the distribution of the first rods in layers makes it possible to ensure a peripheral structure in height of the screen. Moreover, such a structure is easily adjustable, for example by varying the number of layers provided for the screen, depending for example on the dimensions of the space equipment to be protected.

[0015] In an embodiment, the screen having at least three distinct layers, wherein said layers are spaced apart from one another by the third rods during the deployment of the screen along the axial direction.

[0016] In an embodiment, at each layer, two consecutive first rods are connected by said sets of second rods, while two first rods of two consecutive layers are connected by said sets of third rods.

[0017] In an exemplary embodiment, in the deployed configuration, the first rods and the second rods of the same stage form a planar polygonal structure, this planar polygonal structure being present at several of the stages.

[0018] Consequently, each stage of the screen advantageously has a regular structure, which facilitates its deployment both in the axial direction and in the radial direction. Each stage being formed by first and second rods and third rods connecting two successive stages, the deployment of the screen and its structure in superimposed stages results directly from the deployment of the second and third rods.

[0019] Advantageously, the volume and structure of the screen can be easily anticipated or predicted from the dimensions, arrangement and / or number of rods. For example, when the third rods have the same length, the same stage can have a planar polygonal structure. Conversely, if some third rods are higher than others, a stage and in particular the last stage, can have a non-planar structure, which can be adapted to certain specific needs.

[0020] In an exemplary embodiment, in the deployed configuration, the stages extend parallel to the same plane.

[0021] In an exemplary embodiment, the area for attachment to the platform of the spacecraft comprises rotary links connected to sets of third rods, said sets of third rods connecting first rods to first attachment rods in contact with said platform.

[0022] In an exemplary embodiment, the rotary connections are arranged exclusively at the ends of the rods.

[0023] Therefore, the deployment of the rods relative to each other is driven by the rotation of the rotary links at their ends.

[0024] In an exemplary embodiment, in the stored configuration and in the confi When deployed, the rods are arranged to form a closed structure in the radial direction capable of surrounding the space equipment.

[0025] In an exemplary embodiment, a volume formed by said closed structure increases both when the screen is deployed in the radial direction and when the screen is deployed in the axial direction.

[0026] For example, the screen may include a prism shape, the volume of which increases laterally upon radial deployment of the screen (e.g., the side faces of the prism move apart) and longitudinally upon axial deployment of the screen (e.g., the bases of the prism formed by the two end stages of the screen move apart).

[0027] In an exemplary embodiment, the second rods and the third rods are connected respectively in pairs, and: - in the stored configuration, the two third rods of each of the pairs of third rods form the same first angle and the two second rods of each of the pairs of second rods form the same second angle, said first and second angles being between 0 and 180 degrees, and - in the deployed configuration, the two third rods of each of the pairs of third rods extend parallel to the axial direction and the two second rods of each of the pairs of second rods extend parallel to the same plane.

[0028] Therefore, the protective screen has, for example, a regular structure. In particular in the deployed configuration, all of the third rods can be straight and aligned, parallel to the axial direction.

[0029] In an exemplary embodiment, at least one passive rotary link comprises at least two distinct pivot links connecting at least three rods among the first rods, the second rods and the third rods.

[0030] In an exemplary embodiment, the active rotary connection connecting said pairs of second rods and third rods comprises at least one element among at least: - metal strips, of the metal tape measure type, forming a rail on either side of the rods of each of said pairs of second rods and third rods, - a torsion spring, or - an engine.

[0031] Advantageously, when the active connections are made by metal strips of the tape measure type, the rigidity of the tape measures once unfolded directly confers the rigidity of the active rotary connections and therefore of the screen, thus ensuring the screen is held against mechanical buckling.

[0032] In one exemplary embodiment, the stored energy is related to twisting or bending of the active rotary links in the stored configuration and said active rotary links reach an equilibrium position when the screen is in the deployed configuration.

[0033] Therefore, the stored configuration of the screen can be adopted by bending or twisting the elements forming the active rotary link. In particular, the amount of energy stored in the active rotary links can depend on elastic constraints of the metal strips or stiffness of the torsion spring.

[0034] Furthermore, once the deployed configuration of the screen is reached, an equilibrium position of the torsional and / or flexural elements forming the active rotary connections is reached. In particular, such an equilibrium position is stable. The screen thus deployed advantageously has a rigidity linked to mechanical properties of the active rotary connections, which makes it possible to lock the structure of the screen once in the deployed configuration.

[0035] In an exemplary embodiment, the active rotary links of the third rods storing a first amount of energy and the active rotary links of the second rods storing a second amount of energy, and wherein the transition from the stored configuration to the deployed configuration is triggered by a release of the first amount of energy and the second amount of energy resulting in one of the deployment sequences among: - the deployment of the screen in the axial direction followed by the deployment of the screen in the radial direction, - the deployment of the screen in the radial direction followed by the deployment of the screen in the axial direction, and - the deployment of the screen in the radial direction and in the axial direction concurrently, depending on at least: - a difference between the first quantity of energy and the second quantity of energy, and / or - a time lag between the release of the first quantity of energy and the second quantity of energy.

[0036] Consequently, the deployment of the screen can be controlled by modulating the quantities of energy stored by the different active rotary links and / or by delaying the release of these quantities of energy. In other words, the proposed screen can advantageously be configured to be deployed in the axial and radial directions simultaneously, synchronized, successively or delayed. The proposed screen can then advantageously adapt to the deployment process of each piece of space equipment.

[0037] According to another aspect, there is provided a system comprising at least one piece of equipment space and a deployable protective screen according to any one of the preceding claims.

[0038] In an exemplary embodiment, the space equipment of the system is a deployable telescope comprising deployable petals forming at least one deployable primary mirror and one deployable secondary mirror.

[0039] In an exemplary embodiment, the system further comprises a launch hold device connected to rods of the screen and configured to be able to separate from the rods to allow the screen to adopt a deployed configuration by a release of stored energy.

[0040] In an exemplary embodiment, the launch support device is connected to several first rods superimposed in an axial direction. Brief description of the drawings Fig.l

[0041] [Fig.l] represents a schematic view of a system comprising a protective screen in deployed configuration according to an exemplary embodiment. Fig. 2

[0042] [Fig.2] represents a schematic view of a system comprising a protective screen in stored configuration according to an exemplary embodiment. Fig. 3

[0043] [Fig.3] represents a schematic view of a protective screen in deployed configuration according to an exemplary embodiment. Fig. 4

[0044] [Fig.4] represents a protective screen in stored configuration according to an exemplary embodiment. Fig. 5

[0045] [Fig.5] represents a protective screen in deployment according to an exemplary embodiment. Fig. 6

[0046] [Fig.6] represents a protective screen in deployed configuration according to an exemplary embodiment. Fig. 7

[0047] [Fig.7] represents an aerial view of a protective screen in stored configuration according to an exemplary embodiment. Fig. 8

[0048] [Fig.8] represents an aerial view of a protective screen in deployed configuration according to an exemplary embodiment. Fig. 9

[0049] [Fig.9] shows a location of rotary links in a protective screen according to an example of realization. Fig. 10

[0050] [Fig. 10] represents an active rotary connection of a protective screen in stored configuration according to an exemplary embodiment. Fig. 11

[0051] [Fig. 11] represents an active rotary connection of a protective screen in stored configuration according to another exemplary embodiment. Fig. 12

[0052] [Fig. 12] represents an active rotary connection of a protective screen in deployed configuration according to an exemplary embodiment. Fig. 13

[0053] [Fig. 13] represents an active rotary connection of a protective screen in deployed configuration according to another exemplary embodiment. Fig. 14

[0054] [Fig. 14] represents a passive rotary connection of a protective screen according to an exemplary embodiment. Fig. 15

[0055] [Fig. 15] shows rods and rotatable links forming a panel of a protective screen in a stored configuration and configured to deploy axially according to an exemplary embodiment. Fig. 16

[0056] [Fig. 16] shows rods and rotating links forming a panel of a protective screen in a stored configuration and configured to deploy axially and radially according to an exemplary embodiment. Fig. 17

[0057] [Fig. 17] represents a passive rotary connection in stored configuration at a first rotation point according to an exemplary embodiment. Fig. 18

[0058] [Fig. 18] represents a passive rotary connection in deployed configuration at a first rotation point according to an exemplary embodiment. Fig. 19

[0059] [Fig. 19] represents a passive rotary connection in stored configuration at a second rotation point according to an exemplary embodiment. Fig. 20

[0060] [Fig.20] represents a passive rotary link in a deployed configuration in a second point of rotation according to an example of realization. Fig. 21

[0061] [Fig.21] represents a passive rotary link in stored configuration at a third rotation point according to an exemplary embodiment. Fig. 22

[0062] [Fig.22] represents a passive rotary link in deployed configuration at a third rotation point according to an exemplary embodiment. Description of the embodiments

[0063] Reference is now made to [Fig.l]. [Fig.l] schematically illustrates a system comprising a protective screen 2 and space equipment 1 connected to a spacecraft 3 via a platform 31 of the spacecraft 3.

[0064] In the remainder of the description, the system is considered in a predefined reference frame and the kinematics of any part of the system can be considered according to a predefined coordinate system associated with the reference frame. For example, the reference frame can be defined by the orthogonal coordinate system (x,y,z) and / or by polar coordinates (r, 0) and / or spherical coordinates. The notions of displacement, speed or deployment in given directions are therefore defined according to the coordinate system. In particular, a reference axis of the system can be defined, which can for example correspond to an axis along which the system moves in a rectilinear movement in the reference frame. In the context of the present description, the reference axis of the system can correspond to the z axis.

[0065] The spacecraft 3 may be a space vehicle with or without a human crew, configured to be launched from Earth into space using a launcher, so as to be placed in orbit. The spacecraft 3 may be configured to fulfill one or more space missions, for example observation, reconnaissance, mapping, telecommunications missions, etc. Such a spacecraft 3 may, for example, correspond to a space probe or even an artificial satellite. In order to allow the figures to be readable, such a spacecraft 3 is shown diagrammatically in the figures as having a cylindrical shape. However, the spacecraft may adopt any known shape or structure. The spacecraft 3 comprises at least one payload and a platform 31.The platform 31, which may also be designated by bus or service module, may group together a set of devices providing one or more service and / or support functionalities for the spacecraft 3 such as the piloting of the spacecraft, its communication with other systems, its propulsion or even the structural maintenance and storage of the payload. Such a platform 31 may also comprise a payload reception area, by which the elements composing the payload may be secured to the spacecraft 3. The payload of the spacecraft 3 may group together one or more pieces of space equipment making it possible to. carry out the space mission. Space equipment may for example correspond to a space telescope, an observation instrument, telecommunications equipment or even a radar for example. In the remainder of the description, space equipment (designated by space equipment 1) included in the payload of the spacecraft 3 is considered. Such space equipment 1 is shown schematically in the figures by a cylindrical shape. In other exemplary embodiments, the spacecraft 3 may include numerous other space equipment and such space equipment may adopt any known shape or structure.

[0066] The space equipment 1 may be configured to carry out the space mission, for example once the spacecraft 3 has been put into orbit. For this purpose, the space equipment 1 may comprise one or more components enabling the mission to be implemented. For example, the space equipment may comprise optical instruments such as primary and secondary mirrors. In the context of the present description, the space equipment 1 may for example be a space telescope comprising mirrors. In an exemplary embodiment, the space equipment 1 may be deployable, for example in the case of a deployable space telescope. An example of a deployable telescope is illustrated in document US2015 / 0146288. The deployment of the space equipment 1 may be controlled. The deployment of the space equipment 1 may be reversible or not.In the case of a space equipment 1 that can be deployed, the volume occupied by the space equipment 1 may vary, sometimes considerably, depending on whether the space equipment 1 is in a deployed state or not. The volume occupied by the folded and then deployed equipment may for example vary by a factor of 10. The deployment of the space equipment 1 may be understood as the deployment of one or more of its components, as in the case of deployable mirrors for example. In particular, the volume occupied by the deployed space equipment 1 may be greater than the volume occupied by the non-deployed space equipment 1. The deployment of the space equipment 1 may be implemented in one or more directions. For example, the space equipment 1 may be deployed in a so-called axial direction, or in height, corresponding to the reference direction z and / or in a so-called radial direction, or in width, corresponding to a deployment in the (x,y) plane for example.In another exemplary embodiment, the space equipment 1 may be non-deployable. In the case of non-deployable space equipment 1, the volume occupied by the space equipment 1 is substantially constant, subject to possible volume variations due to expansion and / or contraction phenomena of the space equipment (or some of its components) in space.

[0067] The protective screen 2, which can also be designated as a solar protection screen, solar protection shield or even more simply screen 2, corresponds to a structure attached to the spacecraft 3, for example via an attachment zone to the platform 31 of the spacecraft 3. The screen 2 has a structure adapted to protect the space equipment 1 from illuminations in space, in particular coming (directly or indirectly, via reflections) from the Sun. For this, the screen 2 can be positioned in the frame of reference so as to be interposed between the space equipment 1 and a source of illuminations (eg, the Sun). In particular, the screen 2 can be arranged so as to surround the space equipment 1 around the reference axis z of the system, as shown in Figures 1 and 2. In other words, the screen 2 can form a closed structure around the space equipment 1, extending in particular around the reference axis z of the system, in the plane (x,y), called the radial plane (x,y). Such a closed structure can also be designated as a 360 degree (°) closed structure, in that it completely surrounds a circumference of the space equipment 1.Such a circumference of the space equipment 1 can be understood as being the perimeter of a relatively circular shape approximately delimiting the surface of the space equipment 1, corresponding for example to the cylindrical shape representing the space equipment 1 in Figures 1 and 2. Thus, the closed structure of the screen 2 can surround the space equipment 1 at 360 degrees in a so-called radial direction (r, 0), corresponding to the direction in which the radial plane (x, y) extends, as shown in Figures 1 to 9..

[0068] In particular, the screen 2 is configured to be deployable, so as to pass from a stored configuration to a deployed configuration. In particular, the stored configuration of the screen 2 can be adopted during the launch phase of the spacecraft 3 and the deployed configuration of the screen 2 can be adopted when the spacecraft 3 (and more particularly the space equipment 1) is in orbit. The passage of the screen 2 from the stored configuration to the deployed configuration can be triggered mechanically, electromechanically, electrically, electronically or even motorized for example. Such a passage of the screen 2 between the stored configuration and the deployed configuration can be irreversible (typically, in the case of a mechanical trigger) or reversible (typically, in the case of a motorized trigger). The triggering of the passage of the screen 2 from the stored configuration to the deployed configuration will be detailed later in the description.

[0069] The deployable nature of the screen 2 causes a change in the shape and volume occupied by the screen 2 between the stored configuration and the deployed configuration. In particular, the volume surrounded by the screen 2 that can be occupied by the space equipment 1 increases when the screen 2 passes from the stored configuration to the deployed configuration. Such a deployable nature of the screen 2 is advantageously adapted in the particular case of space equipment 1 that is also deployable. Indeed, the change in volume linked to the deployment of a deployable space telescope 1 may be accompanied by a change in volume linked to the deployment of the screen 2 protecting such a telescope 1, which makes it possible to optimize the volume occupied by the assembly formed by the space equipment 1 and its protective screen 2 both during the launch phase of the spacecraft 3 and when the spacecraft 3 is in orbit and operational for carrying out the space mission. As an example, Figures 7 and 8 diagrammatically show examples in aerial view (or in the radial plane (x,y)) of a screen 2 in the stored configuration and deployed configuration respectively. Figures 7 and 8 diagrammatically show a possible change in volume delimited by the structure of the screen 2 between the stored configuration and the deployed configuration.In other embodiments, the difference in volume between the stored configuration and the deployed configuration of the screen 2 may differ from those shown in FIGS. 7 and 8, depending on the dimensions of the space equipment 1 to be protected (in particular its dimensions at launch and once in orbit) and / or the shape of the screen 2 for example.

[0070] By way of example, Figures 1 to 8 illustrate examples of a screen 2 for protecting a space equipment 1 in stored or deployed configurations. Examples of deployed configuration of the screen 2 are illustrated in Figures 1, 3, 6 and 8. Examples of stored configuration of the screen 2 are illustrated in Figures 2, 4 and 7. [Fig. 5] illustrates an example of intermediate configuration of the screen 2 during deployment to move from the stored configuration of [Fig. 4] to the deployed configuration of [Fig. 6].

[0071] The structure of the protective screen 2 is now detailed.

[0072] The screen 2 comprises at least a plurality of rods 21, 22, 23 joined together by rotary connections 24, 25, as detailed in [Fig.l] for example. The plurality of rods 21, 22, 23 can be distinguished at least into first rods 21, second rods 22 and third rods 23.

[0073] The first rods 21 are so-called structural rods, which form a peripheral structural base of the screen 2 in the stored configuration as well as in the deployed configuration. In particular, the first rods 21 do not contribute directly to the deployment of the screen 2. In other words, the first rods do not unfold in any direction in the frame of reference of the screen 2. As illustrated in FIGS. 7 and 8 for example, the first rods 21 do not unfold between the stored configuration and the deployed configuration.

[0074] The second rods 22 are so-called radial extension rods, which are configured to deploy the screen 2 in a radial direction (r, 0) in the frame of reference of the screen 2. Thus, if the space equipment 1 can be schematized by a cylindrical volume, as in Figures 1 and 2, the second rods 22 make it possible to deploy the screen 2 according to the diameter of the cylinder. As illustrated in Figures 7 and 8 for example, the second rods 22 unfold tangentially between the stored configuration and the deployed configuration, so as to separate the first rods 21. For this, the second rods 22 may be connected together at least in pairs to form sets of second rods 22. Each set of second rods 22 may for example comprise two second rods 22, as illustrated in Figures 1 to 6, 9, 11 and 13. Alternatively, each set of second rods 22 may comprise more than two second rods 22, as illustrated in [Fig. 16], in which each set of second rods 22 comprises four second rods 22. In particular, each set of second rods 22 may connect two consecutive first rods 21. For example, with reference to Figures 7 and 8, sets of second rods 22 are interposed between two first rods 21, so that an aerial view of the peripheral structure of the screen corresponds to a closed structure alternating first rods 21 and sets of second rods 22. In the stored configuration, the sets of second rods 22 are folded, as illustrated in [Fig.2].In the deployed configuration, the sets of second rods 22 are unfolded, so that the sets of second rods 22 on the one hand, and the first rods 21 on the other hand, are coplanar to the radial plane (x,y). The deployment of the sets of second rods 22 will be detailed in the remainder of the description.

[0075] The third rods 23 are so-called axial extension rods, which are configured to deploy the screen 2 in an axial direction z in the frame of reference of the screen 2. Such an axial direction z may correspond to the reference direction z of the space equipment 1. Thus, the third rods 23 are configured to implement a longitudinal deployment of the screen 2 along the reference axis of the space equipment 1. Thus, if the space equipment 1 can be represented diagrammatically by a cylindrical volume, as in FIGS. 1 and 2, the third rods 23 make it possible to deploy the screen 2 along the length or height of the cylinder. For this, the third rods 23 can be connected to each other at least in pairs to form sets of third rods 23. Each set of third rods 23 can for example comprise two third rods 23, as illustrated in FIGS. 1 to 6, 9, 10 and 12.Alternatively, each set of third rods 23 may comprise more than two third rods 23, as illustrated in [Fig. 15], wherein each set of third rods 23 comprises four third rods 23.

[0076] The plurality of rods 21, 22, 23 may also comprise first attachment rods 21' to the spacecraft 3, as illustrated in FIGS. 1 and 9 for example. Like the first rods 21, the first attachment rods 21' do not unfold in any direction in the frame of reference of the screen 2 and in particular, the first attachment rods 21' do not unfold between the stored configuration and the deployed configuration.

[0077] The first rods 21, the sets of second rods 22 and the sets of third rods 23 can be arranged between them so as to form a structure closed protective screen 2 capable of surrounding the space equipment 1, both in the stored configuration, in [Fig.2], and in the deployed configuration, in [Fig.l].

[0078] In particular, the plurality of rods 21, 22, 23 may be arranged to form one or more stages, also referred to as levels, of the screen 2. For example, with reference to FIGS. 4, 5 and 6, the reference points A, B, C belong to distinct stages. In particular, each stage of the screen 2 in the deployed configuration may correspond to a set of coplanar rods, parallel to the radial plane (x,y). Each stage of the screen 2 can be formed on the one hand by first rods 21 and, on the other hand, by sets of second rods 22. In particular, the first rods 21 and the sets of second rods 22 of each stage of the screen 2 are arranged end to end at their ends so as to form a closed structure, as illustrated in FIGS. 7 and 8. In particular, a stage can be composed of an alternation of first rods 21 and sets of second rods 22.For example, with reference to Figures 1 to 6, the screen 2 shown comprises three distinct stages. The deployment of the screen 2 from the stored configuration to the deployed configuration includes an extension of the sets of second rods 22 at each stage. Thus, the deployment of the screen 2 in a radial direction (r, 0) is implemented by a radial extension of the sets of second rods 22 at each stage. For this, in the stored configuration, the first rods 21 may remain coplanar with the radial plane (x,y) while the sets of second rods 22 may belong to intersecting or oblique planes relative to the radial plane (x,y). In particular, in the stored configuration, the second rods 22 of each set of second rods 22 may, two by two, form a second non-flat angle 02, as detailed in Figures 11 and 16. Thus, with reference to [Fig.7], the second rods 22 shown in dotted lines indicate that the second rods 22 are not in the same plane (x,y) as the first rods 21 in the stored configuration. Upon deployment to the deployed configuration, the second rods 22 gradually unfold, as illustrated in [Fig. 5], such that such a second angle 02 increases to a flat angle (of 180 degrees) when the second rods 22 are substantially aligned and coplanar with the first rods 21, as illustrated in Figures 6 and 13. Thus, with reference to [Fig. 8], the second rods 22 shown in solid lines indicate that the second rods 22 are in the same plane (x,y) as the first rods 21 in the deployed configuration.

[0079] Referring to Figures 1 to 8, the plurality of rods 21, 22, 23 is arranged such that a planar regular polygonal structure is formed by each stage of the deployed screen 2, by way of example. In such examples, each stage is similar and is composed of three first rods 21 and three sets of second rods 22. Each set of second rods 22 comprises two second rods 22. In confi deployed structure, each stage therefore has a hexagonal shape, similar to a cell shape, as shown in [Fig.8]. In particular, each stage here has a flat shape, parallel to the axial plane (x,y).

[0080] The different stages of the screen 2 can be superimposed and connected to each other by the sets of third rods 23. For this, the sets of third rods 23 can connect two first rods 21 of two successive stages, as illustrated in [Fig. 15] for example, each of the first rods 21 of [Fig. 15] belonging to a stage. In the stored configuration, the third rods 23 of the sets of third rods 23 are folded so that the distance separating two successive stages of the screen 2 is minimal. For example, with reference to [Fig.4], the distances respectively separating the points A, B, C are minimal. A height of the screen 2 formed by the superposition of its stages is therefore minimal in the stored configuration. During axial deployment of the screen 2 (in the z direction), the sets of third rods 23 unfold so as to separate the stages from each other.Figures 5 and 6 illustrate the screen 2 and the arrangement of the stages once the axial deployment has been carried out: the points A, B, C have been moved away from each other. In order to implement the deployment in the axial direction z of the screen 2, the third rods 23 of the sets of third rods 23 have a folded position in the stored configuration and an unfolded position in the deployed configuration. In particular, in the stored configuration, the third rods 23 of each set of third rods 23 can, two by two, form a first non-flat angle 0i (i.e., different from 0 degrees or 180 degrees), as detailed in Figures 10 and 15. During deployment to the deployed configuration, the third rods 23 unfold progressively, to pass from the (stored) configuration of [Fig. 4] to the (intermediate) configuration of [Fig.5], such that such a first angle Oi increases to become a flat angle (of 180 degrees) when the third rods 23 of each set of third rods 23 are substantially aligned, as illustrated in Figures 5, 6 and 12. Notably, in the deployed configuration, the third rods 23 of all sets of third rods 23 may be substantially parallel, for example to the reference axis z.

[0081] With reference to Figures 1, 3 and 6, by way of example, the plurality of rods 21, 22, 23 is arranged so that the deployed screen 2 forms a prism. In such examples, two successive stages of the screen are connected to each other by six sets of third rods 23, so that each first rod 21 of each stage is connected to a consecutive first rod 21 of a successive stage at its two ends by two sets of third rods 23 respectively. The three stages of the screen 2 as shown in Figures 1 to 6 are therefore spaced apart from each other by the deployment of twelve sets of third rods 23. Furthermore, sets of third rods 23 can also make it possible to deploy the area for attaching the screen 2 to the platform. 31 of the spacecraft 3. For this, three additional sets of third rods 23 are included in the screen 2 illustrated in Figures 1 to 6. The screen 2 shown in [Fig.l] thus has eighteen sets of third rods 23 connecting the three stages of the screen 2 as well as the attachment zone of the screen 2.

[0082] In the examples of screen 2 illustrated in the figures, the plurality of rods 21, 22, 23 is arranged so that the screen 2, once in the deployed configuration, includes a prism shape, highlighted in figures 1, 3 and 6 in particular. The prism formed by the screen 2 in the deployed configuration has in particular two bases and several faces. In the exemplary embodiments of the figures, the bases of the prism formed by the screen 2 in the deployed configuration are hexagonal, as illustrated in [Fig.8]. Such bases are delimited by first rods 21 and sets of second rods 22. In particular, in the examples illustrated in the figures, the first rods 21 and the second rods 22 of the sets of second rods 22, once the screen 2 is in the deployed configuration, have the same length from one stage to the next.In one embodiment, the first rods 21 and the second rods 22 of the sets of second rods 22, once the screen 2 is in the deployed configuration, have the same length within the same floor, such that the polygon formed by the deployed screen 2 is regular. Similarly, the third rods 23 of the sets of third rods 23 have, once the screen 2 is in the deployed configuration, the same length (which may or may not correspond to the length of the first and second rods 21, 22) between two floors, and in one embodiment, for all consecutive floors, and / or within the same floor. The example of prism formed by the screen 2 in the deployed configuration in Figures 1, 3 and 6 also has twelve so-called lateral faces, which are substantially identical rectangles.In particular, certain lateral faces of the prism may be formed on the one hand by first rods 21 and on the other hand by two sets of third rods 23, for example in the case of the face illustrated in [Fig. 15]. Other lateral faces of the prism may be formed on the one hand by two sets of second rods 22 and on the other hand by two sets of third rods 23, for example in the case of the face illustrated in [Fig. 16].

[0083] The screen 2 also comprises other faces forming the attachment zone of the screen 2 to the platform 31 of the spacecraft 3. With reference to [Fig.6], the attachment zone of the screen 2 is formed by three faces, called attachment faces. Each attachment face of the screen 2 is formed by a first rod 21, two sets of third rods 23 and a first attachment rod 21'.

[0084] The lateral and attachment faces of the screen 2 may be covered by a thermally insulating film 20, for example of the multi-layer insulation (MLI) type or of the single-layer insulation (MLI) type. "single-layer insulation" or SLI). Such a thermally insulating film 20 may for example be attached at the level of the rods 21, 22, 23 forming the faces of the screen 2, so that the faces of the screen are able to surround and protect the space equipment 1 from illuminations thanks to the thermally insulating film 20, as illustrated in [Fig. 3]. In particular, when the screen is in the stored configuration, the thermally insulating film 20 is folded and when the screen is in the deployed configuration, the thermally insulating film 20 is stretched between the rods 21, 22, 23.

[0085] The rods 21, 22, 23 forming the structure of the protective screen 2 are joined together by rotary connections 24, 25. The rotary connections 24, 25 may include passive rotary connections 24 and active rotary connections 25. An example of distribution of the rotary connections 24, 25 on a screen 2 is shown in [Fig.9]: the passive rotary connections 24 are represented by a circle while the active rotary connections 25 are represented by a square. The rotary links 24, 25 may also include rotary attachment links at the attachment area of ​​the screen 2 to the platform 31 of the spacecraft 3, so as to allow relative movement between the screen 2 and the platform 3: such rotary attachment links are also represented by a triangle in [Fig.9], by way of example.In one exemplary embodiment, the rotary connections 24, 25 are arranged exclusively at the ends of each of the plurality of rods 21, 22, 23, such that the rods 21, 22, 23 are connected to each other at their ends by the rotary connections 24, 25.

[0086] The active rotary links 25 are configured to implement the deployment of the screen 2 from the stored configuration to the deployed configuration. For this, the active rotary links 25 can store a quantity of energy, also referred to as precharge, the release of such a quantity of energy making it possible to activate the deployment of the screen 2 from the stored configuration to the deployed configuration. The deployment of such a quantity of energy stored by the active rotary links 25 will be detailed later in the description. In an exemplary embodiment, the energy stored by the active rotary links 25 may be mechanical energy. Alternatively, the energy stored by the active rotary links 25 may be electrical energy for example.

[0087] In particular, each of the sets of second rods 22 and the sets of third rods 23 comprises at least one active rotary connection 25 connecting at least two second rods 22 or two third rods 23 respectively. In other words, each of the sets of second rods 22 and the sets of third rods 23 is configured to release energy stored at its active rotary connection(s) 25, such that the deployment of each set of second or third rods 22, 23 causes deployment in the directions respectively radial (r, 0) and axial z of the screen 2. For example, with reference to figures 9 to 13, each of the sets of second rods 22 (respectively third rods 23) comprises two second rods 22 (respectively third rods 23) connected to each other by an active rotary connection 25. In another example, with reference to [Fig. 15] (respectively [Fig. 16]), two sets of third rods 23 (respectively, second rods 22) are shown and each set of third rods 23 (respectively, second rods 22) comprises four third rods 23 (respectively, second rods 22) connected to each other by active rotary links 25: each set of third rods 23 (respectively, second rods 22) thus comprises three active rotary links 25.

[0088] In an exemplary embodiment, each active rotary connection 25 may comprise metal strips 25a, of the metal tape measure type, connecting together the ends of two second or third rods 22, 23. In particular, an active rotary connection 25 between two rods may be formed by assembling two metal strips 25a, of the metal tape measure type, on the one hand on two opposite faces of the end of one rod, and on the other hand on two opposite faces of the end of the other rod, thus forming rails on either side of the ends of the rods which are thus connected together by the connection. Such metal strips 25a are for example illustrated in FIGS. 10, 12, 15 and 16, on which the metal strips 25a form rails for pairs of third rods 23. [Fig. 16] also illustrates metal strips 25a forming a pair of rails for pairs of second rods 22.When the screen 2 is in the stored configuration, such metal strips 25a may be flexed, so that the first and second rods 22, 23 are folded, as illustrated in FIGS. 10, 15 and 16, by storing an amount of energy tending to return the metal strips to a straight configuration, and thus to unfold the pair of rods connected together by this pair of strips. When the screen 2 is in the deployed configuration, the metal strips 25a may be straight, so that the first and second rods 22, 23 are unfolded and aligned between the metal strips 25a, as illustrated in [Fig. 12].

[0089] Alternatively, the active rotary connection 25 may comprise a torsion spring 25b, configured to connect pairs of second and / or third rods 22, 23. In particular, when the screen 2 is in a stored configuration, the torsion spring 25b exerts a non-zero torsional force on the rods 22, 23 so that the rods 22, 23 are folded, as illustrated in [Fig. 1 1]. When the screen 2 is in the deployed configuration, the torsion spring 25b may be in an equilibrium (resting) position, so that the rods 22, 23 are unfolded and aligned, as illustrated in [Fig. 13]. In other alternatives, the active rotary connection 25 could comprise a motorized element or a combination of the elements cited.

[0090] The passive rotary links 24 are configured to accompany the deployment movement of the screen 2 initiated by the active rotary links 25 by ensuring the consistency of deployment of the structure of the screen 2 by all of its rods 21, 22, 23. The passive rotary links 24 are therefore pivot links that do not store energy, and do not as such allow initiating a deployment of the screen 2. The passive rotary links 24 rather allow introducing a degree of freedom in the movement of the rods 21, 22, 23 forming the screen 2 during its deployment. For this, each passive rotary link 24 can be formed by at least one shaft (such as a screw) and bore type system, allowing rotational guidance (also designated by a pivot link) of two rods 21, 22, 23 connected by such a passive rotary link 24.The passive rotary connections 24 make it possible in particular to accommodate the variation of the angle formed between a first rod 21 on the one hand, and a second rod 22 or a third rod 23 to which the first rod 21 is connected on the other hand, in the deployment of the screen 2 from the stored configuration to the deployed configuration. For this, in an exemplary embodiment as illustrated in [Fig. 9], the passive rotary connections 24 are arranged at least at the ends of the first rods 21. In particular, in such an embodiment, each passive rotary connection 24 connects at least three rods among the first rods 21, the second rods 22 and the third rods 23. For example, with reference to [Fig. 9], each of the points A, B and C corresponds to a passive rotary connection 24, which will be detailed below for each of the points A, B, C.The side faces Fl, F2, F3, F4 and the attachment face FA detailed below are shown in figures 3 and 5 respectively.

[0091] The passive rotary connection 24 at point A comprises two pivot connections connecting three rods: a first rod 21, a second rod 22 and a third rod 23. The rotational guidance of the passive rotary connection 24 at point A is shown in FIGS. 17 and 18, corresponding respectively to a positioning of the rods 21, 22, 23 at point A in the stored configuration and in the deployed configuration. In particular, the first rod 21 and the third rod 23 belong to a first lateral face F1 intersecting a second adjacent lateral face F2 including the second rod 22 and the same third rod 23 (the third rod 23 being an edge at the intersection of the first and second lateral faces F1, F2). The passive rotary connection 24 at point A therefore makes it possible to guide the rods 21, 22, 23 in rotation so as to obtain two adjacent lateral faces Fl, F2 of the prism formed by the screen 2.

[0092] The passive rotary connection 24 at point B comprises three pivot connections connecting four rods: a first rod 21, a second rod 22 and two third rods 23, designated third rods 23a and 23b. In particular, the first rod 21 and the third rod 23a belong to the first lateral face F1 intersecting the second neighboring lateral face F2 including the second rod 22 and the same third rod 23a (the third rod 23a being an edge at the intersection of the first and second lateral faces). In the same way, the first rod 21 and the third rod 23b belong to a third lateral face F3 parallel to the first lateral face F1 and intersecting a fourth neighboring lateral face F4, parallel to the second lateral face F2, and including the second rod 22 and the same third rod 23b (the third rod 23b being an edge at the intersection of the third F3 and fourth lateral faces F4). The rotational guidance of the passive rotary connection 24 at point B is shown in FIGS. 19 and 20, corresponding respectively to a positioning of the rods 21, 22, 23a, 23b at point B in the stored configuration and in the deployed configuration.The passive rotary connection 24 at point B is therefore located at the intersection of four lateral faces Fl, F2, F3, F4 and therefore makes it possible to guide the rods 21, 22, 23a and 23b in rotation so as to obtain four adjacent lateral faces Fl, F2, F3, F4 of the prism formed by the screen 2.

[0093] The passive rotary connection 24 at point C comprises three pivot connections connecting four rods: a first rod 21, a second rod 22 and two third rods 23, designated third rods 23c and 23d. In particular, the first rod 21 and the third rod 23c belong to the third lateral face F3 (described in the previous paragraph) intersecting the neighboring fourth lateral face F4 including the second rod 22 and the same third rod 23c (the third rod 23c being an edge at the intersection of the third F3 and fourth lateral faces F4). Furthermore, the third rods 23b and 23c form, in the example of [Fig.9], a set of third rods 23. Furthermore, the first rod 21 and the third rod 23d belong to an attachment face FA intersecting the third lateral face F3 (the first rod 21 being an edge at the intersection of the third lateral face F3 and the attachment face F4).The rotational guidance of the passive rotary connection 24 at point C is shown in Figures 21 and 22, corresponding respectively to a positioning of the rods 21, 22, 23c, 23d at point C in the stored configuration and in the deployed configuration. In particular, at point C, the passive rotary connection 24 is configured to allow rotational guidance specific to the attachment face FA, shown at point Ch so that, unlike the first F1 and third parallel lateral faces F3, the third lateral face F3 and the attachment face FA are intersecting. Point C therefore allows rotational guidance of the rods 21, 22, 23c for the positioning of the lateral faces F3, F4 while point Ci allows rotational guidance of the rod 23d for the positioning of the attachment face FA.

[0094] The rotary attachment links at the ends of the first attachment rods 21' allow rotational guidance between the screen 2 (more particularly the area attachment of the screen 2) and the platform 31 of the spacecraft 3. Such a rotary attachment link is notably represented at point D. In an exemplary embodiment, such a rotary attachment link may be of the passive rotary link 24 type.

[0095] A phase of deployment of the protective screen 2 from a stored configuration, as illustrated in [Fig.2] and 4, to a deployed configuration, as illustrated in Figures 1 and 6 can now be described.

[0096] In an initial phase, the screen 2 is in a stored configuration. Such an initial phase corresponds for example to a launch phase of the spacecraft 3. In the stored configuration, the sets of second rods 22 as well as the sets of third rods 23 are in a folded position. In other words, each of the active rotary links 25 included in each of the sets of second rods 22 and the sets of third rods 23 stores at this stage a predefined quantity of energy. In an exemplary embodiment, all of the third rods 23 of the same set of third rods 23 form, two by two, the same first angle 0b as illustrated in [Fig. 15]. In particular, such a first angle 0i can be identical for all the sets of third rods 23 of the screen 2. In the same way, all the second rods 22 of the same set of second rods 22 form, two by two, the same second angle 02, as illustrated in [Fig.16]. In particular, such a second angle 02 may be identical for all the sets of second rods 22 of the screen 2. In particular, the quantity of energy stored by each of the active rotary connections 25 may depend on the elastic and / or torsional properties of the elements forming the active rotary connection 25, typically as a function of an elasticity rate of the metal strips 25a or a stiffness of the torsion spring 25b. Furthermore, the choice of metal strips 25a and / or torsion springs 25b to form the active rotary connections 25 may depend on the quantity of stored energy targeted for the different sets of second and third rods 22, 23. The quantity of stored energy makes it possible In particular to control the deployment (in particular its speed, its unwinding) of the screen 2. Such an aspect will be detailed in the description of the deployment phase of the screen 2.

[0097] During the initial phase, the energy is stored at the active rotary links 25 by twisting or bending the elements forming the active rotary links 25. For example, in the case of metal strips 25a, the energy is stored at the active rotary links 25 by bending the metal strips 25a, making it possible to keep the sets of rods 22, 23 folded. In the case of a torsion spring 25b, the twisting of the spring 25b makes it possible to keep the sets of rods 22, 23 folded and to store a quantity of energy in the form of elastic energy stored at the spring 25b. In particular, the presence of stored energy is made possible in that the elements 25a, 25b forming the active rotary links 25 are not at rest, in other words, are not in an equilibrium position. In an exemplary embodiment, maintaining the active rotary links 25 in an out-of-equilibrium position may be made possible by the use of a launch-holding device, for example of the “Hold Down & Release Mechanisms” or HDRM type, at the rods 21, 22, 23. For example, with reference to [Fig. 15], maintaining the folded position of the third rods 23 may be made possible by a launch-holding device (not shown in [Fig. 15]) attached between the first two rods 21 and making it possible to maintain a minimum distance between these first two rods 21.

[0098] In a deployment phase of the screen 2, the quantity of energy stored by the active rotary links 25 of each of the sets of second rods 22 and third rods 23 is released. Such a deployment phase may for example correspond to placing the spacecraft 3 into orbit or to starting an operational phase of the space equipment 1 for example. In an exemplary embodiment, such a release of the energy stored by the active rotary links 25 may be made possible by a release or relaxation command of the launch support device, so that the elements 25a, 25b forming the active rotary links 25 are no longer constrained. The active rotary links 25 can then release the stored energy, causing the sets of second and third rods 22, 23 to deploy.In other words, the first and second angles 0b 02 change and approach a flat angle during the deployment phase as the second and third rods 22, 23 unfold. In addition, the deployment of the second and third rods 22, 23 causes a deployment of the peripheral structural base of the screen 2 by rotating the passive rotary links 24.

[0099] In particular, the release of the stored energy can be implemented by an ordered trigger, so as to control the deployment of the screen 2. For example, in an exemplary embodiment, the triggering of the deployment phase can be unique for the entire screen 2, via a single command to release the stored energy by all the active rotary links 25 of the screen 2.In another exemplary embodiment, the triggering of the deployment phase can be implemented according to a sequence of several triggers, for example by controlling a first release in a first time of a first quantity of energy Q1 stored by certain active rotary links 25 (typically, the active rotary links 25 included in the sets of third rods 23) followed, in a second time, by a second release in a second time of a second quantity of energy Q2 stored by the other active rotary links 25 (typically, the active rotary links 25 included in the sets of second rods 23). The delayed triggering can then make it possible to decompose the deployment phase of . the screen 2 into a first axial deployment phase along the axial direction z and into a second radial deployment phase along the radial direction (r, 0). Similarly, a delayed trigger can make it possible to decompose the deployment phase of the screen 2 into a first radial deployment phase followed by a second axial deployment phase. Alternatively, the first and second quantities of energy stored in the sets of second rods 22 and third rods 23 respectively can differ, so that the deployment of the screen 2 can be decomposed into different deployment directions due to the differences in quantities of stored energy, which impact the speed and duration of deployment of the sets of second and third rods 22, 23. For example, [Fig.5] illustrates an intermediate deployment phase, during which a deployment in the axial direction z has taken place (the quantity of energy stored by the sets of third rods 23 has been released) and a deployment in the radial direction (r, 0) is in progress or to come (the quantity of energy stored by the sets of second rods 22 has not been completely or yet released).

[0100] In a deployed phase, the screen 2 is in a deployed configuration. Such a deployed phase corresponds for example to an operational phase of the space equipment 1, the screen 2 ensuring the solar protection of the space equipment 1 during its space mission. In the deployed configuration of the screen, the first angles Oi and the second angles O2 formed respectively by the pairs of third rods 23 and second rods 22 are flat, as illustrated in FIGS. 12 and 13. In an exemplary embodiment, all of the active rotary links 25 reach an equilibrium position when the deployed configuration is reached. In particular, such an equilibrium position makes it possible to lock the structure of the screen 2 in the deployed configuration, so that the deployment is irreversible.Alternatively, the active rotary links 25 may include motorized elements, and the power supplied to the active rotary links 25 is zero once the deployed configuration is reached. In the case of motorized active rotary links 25, the deployment of the screen 2 could be reversible.

[0101] In the context of the present description and of Figures 1 to 12, the structure of the protective screen and its deployment are described by considering a regular closed structure. In particular, the screen 2 is considered to have a polyhedron structure, and more particularly a prism structure having rectangular lateral faces and polygonal bases, here hexagonal, planar. Nevertheless, in other exemplary embodiments, the screen 2 may have a structure different from a prism. In other exemplary embodiments, the number of stages, the number and / or the arrangement of first and second rods 21, 22 per stage may differ. The number of rods 21, 22 may differ between different stages. The number of rods 21, 22, 23 per set of second and / or third rods 22, 23 may differ and / or vary from one set to another. Each stage may be a non-planar polygonal structure: for example, certain sets of third rods 23 separating two successive stages may have third rods 23 longer than the third rods 23 of the remaining sets of third rods 23, so that the screen has portions at different heights along the reference axis z. The dimensions and directions of deployment may also vary depending on the number, dimensions and arrangement of the plurality of rods 23 and / or the rotary connections 24, 25. The structure of the screen 2 may thus be modified, in particular to adapt to non-regular shapes of space equipment 1 to be protected. List of reference signs

[0102] - 1: space equipment

[0103] - 3: spacecraft

[0104] - 31: spacecraft platform

[0105] - 2: protective screen

[0106] - 20: thermally insulating film

[0107] - 21: first stem

[0108] - 21': first attachment rod to the spacecraft

[0109] - 22: second rod (radial extension)

[0110] - 23, 23a, 23b, 23c, 23d: third rods (axial extension)

[0111] - 24: passive rotary link

[0112] - 25: active rotary link

[0113] - 25a: active rotary connection via metal strips

[0114] - 25b: active rotary connection via a torsion spring

[0115] - Q1: first quantity of energy

[0116] - Q2: second quantity of energy

[0117] - 0i: first angle (formed by two third rods)

[0118] - 02: second angle (formed by two second rods)

[0119] - A, B, C, D, Ci: rotation points

[0120] - Fl, F2, F3: lateral faces

[0121] - FA: attachment face

Claims

Claims

1. Deployable solar protection screen (2) for space equipment (1), having at least one attachment zone to a platform (31) of a spacecraft (3) including said space equipment (1), said screen (2) being configured to pass from a stored configuration to a configuration deployed in orbit and characterized in that it comprises: — rods, — rotary links (24, 25) joining rods (21, 22, 23) together, the rotary links being of the active rotary link type (25) storing a quantity of energy or of the passive rotary link type (24), the rods (21, 22, 23) being covered by a thermally insulating film (20) folded when the screen (2) is in the stored configuration and stretched between the rods (21, 22, 23) when the screen (2) is in the deployed configuration, in which the rods are constituted by at least less : — first structural rods (21), forming a peripheral structural base in the stored configuration as well as in the deployed configuration, — second radial extension rods (22), connected together at least in pairs to form sets of second rods, each set of second rods (22) connecting two consecutive first rods (21) and being configured to deploy the screen (2) in a radial direction (r,0), — third axial extension rods (23), connected together at least in pairs to form sets of third rods, each set of third rods (23) connecting two consecutive first rods (21) and being configured to deploy the screen (2) in an axial direction (z) and — each set of second rods (22) or third rods (23) comprising at least one active rotary link (25), said sets of second rods (22) and third rods (23) being folded when the screen (2) is in the stored configuration, the active rotary links (25) being configured to unfold said set of second rods (22) and third rods (23) and trigger the transition from the stored configuration to the deployed configuration, by causing the rotation of the passive rotary links (24) and deployment in an axial direction and in a radial direction.

2. Screen (2) according to claim 1, in which the first rods (21) are distributed in stages in the axial direction (z), each stage comprising the same number of first rods (21), greater than or equal to three.

3. Screen (2) according to claim 2, having at least three distinct stages, in which said stages are spaced from each other by the third rods (23) when the screen (2) is deployed in the axial direction (z).

4. Screen (2) according to one of claims 2 and 3, in which, at each stage, two consecutive first rods (21) are connected by said sets of second rods (22), while two first rods (21) of two successive stages are connected by said sets of third rods (23).

5. Screen (2) according to claim 4, in which, in the deployed configuration, the first rods (21) and the second rods (22) of the same stage form a planar polygonal structure, this planar polygonal structure being present at several of the stages.

6. Screen (2) according to one of claims 2 to 5, in which, in the deployed configuration, the stages extend parallel to the same plane (x,y).

7. Screen (2) according to one of claims 2 to 4, in which the area of ​​attachment to the platform (31) of the spacecraft (3) comprises rotary links connected to sets of third rods (23), said sets of third rods (23) connecting first rods (21) to first attachment rods (21') in contact with said platform (31).

8. Screen (2) according to one of the preceding claims, in which the rotary connections (24, 25) are arranged exclusively at the ends of the rods (21, 22, 23).

9. Screen (2) according to one of the preceding claims in which, in the stored configuration and in the deployed configuration, the rods (21, 22, 23) are arranged to form a closed structure in the radial direction (r, 0) capable of surrounding the space equipment (1).

10. A screen (2) according to claim 9, wherein a volume formed by said closed structure increases both when the screen (2) is deployed in the radial direction (r, 0) and when the screen (2) is deployed in the axial direction (z).

11. Screen (2) according to one of the preceding claims, in which the second rods (22) and the third rods (23) are connected respec- tively in pairs, and: - in the stored configuration, the two third rods (23) of each of the pairs of third rods (23) form the same first angle (0J and the two second rods (22) of each of the pairs of second rods (22) form the same second angle (02), said first angle (0J and second angle (02) being between 0 and 180 degrees, and - in the deployed configuration, the two third rods (23) of each of the pairs of third rods (23) extend parallel to the axial direction (z) and the two second rods (22) of each of the pairs of second rods (22) extend parallel to the same plane (x,y).

12. Screen (2) according to one of the preceding claims, in which at least one passive rotary connection (24) comprises at least two separate pivot connections connecting at least three rods among the first rods (21), the second rods (22) and the third rods (23).

13. Screen (2) according to one of the preceding claims, in which the active rotary connection (25) connecting said pairs of second rods (22) and third rods (23) comprises at least one element among at least: - metal strips (25a), of the metal tape measure type, forming a rail on either side of the rods (22, 23) of each of said pairs of second rods (22) and third rods (23), - a torsion spring (25b), or - a motor.

14. A screen (2) according to any preceding claim, wherein the stored energy is related to twisting or bending of the active rotary links (25) in the stored configuration and said active rotary links (25) reach an equilibrium position when the screen (2) is in the deployed configuration.

15. A screen (2) according to any one of the preceding claims, the active rotary connections of the third rods (23) storing a first quantity of energy (Ql) and the active rotary connections of the second rods (22) storing a second quantity of energy (Q2), and in which the transition from the stored configuration to the deployed configuration is triggered by a release of the first quantity of energy (Ql). and the second quantity of energy (Q2) causing one of the deployment sequences among: - the deployment of the screen (2) in the axial direction (z) followed by the deployment of the screen (2) in the radial direction (r, 0), - the deployment of the screen (2) in the radial direction (r, 0) followed by the deployment of the screen (2) in the axial direction (z), and - the deployment of the screen (2) in the radial direction (r, 0) and in the axial direction (z) concurrently, depending at least on: - a difference between the first quantity of energy (Ql) and the second quantity of energy (Q2), and / or - a time lag between the release of the first quantity of energy (Ql) and the second quantity of energy (Q2).

16. System comprising at least one piece of space equipment (1) and a deployable protective screen (2) according to any one of the preceding claims.

17. System according to claim 16, wherein the space equipment (1) is a deployable telescope comprising deployable petals forming at least one deployable primary mirror and one deployable secondary mirror.

18. A system according to one of claims 16 and 17 further comprising a launch holding device connected to rods (21, 22, 23) of the screen (2) and configured to be able to separate from the rods (21, 22, 23) to allow the screen (2) to adopt a deployed configuration by a release of stored energy.

19. System according to claim 18, wherein the launch holding device is connected to several first rods (21) superimposed in an axial direction (z).

Images