Electrical cable arrangement comprising at least one cable clamping device

Abstract

The invention relates to an arrangement (300) of at least one electrical cable (100), suitable for a space environment, comprising an outer sheath (110) and at least a plurality of longitudinal conductors (120) arranged within the sheath, the sheath having an outer diameter corresponding to the diameter of the cable. The cable arrangement includes a cable clamping element (200) configured to exert at least one clamping force (F) on the sheath to transversely clamp the conductors and the sheath. The clamping force is determined to create a deformation of the cable cross-section, creating thermal conduction bridges directly connecting the longitudinal conductors and an external surface of the sheath, thereby dissipating heat generated by the flow of electric current in said cable. The invention also relates to a spacecraft (10) comprising such an arrangement. (See Figure 5 for abbreviations.)

Description

Title of the invention: Electrical cable arrangement comprising at least one cable clamping element. TECHNICAL FIELD OF THE INVENTION

[0001] The field of the invention is that of electrical cables and arrangements of electrical cables in space applications.

[0002] More specifically, the invention relates to an electrical cable arrangement comprising at least one cable pinching element. STATE OF THE ART

[0003] Prior art exists for a ground-based electrical cable of the type comprising a sheath forming an outer covering and comprising a plurality of longitudinal conductors arranged within the outer sheath, inside the cable. The longitudinal conductors include, for example, metallic cores electrically insulated by means of surrounding sheaths. The outer sheath of the cable may be electrically conductive, for example, to form a shield for the cable, or it may be electrically insulating. Other elements, in particular electrically insulating elements such as other electrically insulating inner sheaths, may also be arranged within the outer sheath.

[0004] Electrical cables generally require little heat dissipation.

[0005] However, new uses, such as for example for plasma thrusters, involving high amperages at high frequencies, around 1MHz for example, reveal the need to modify the power supply arrangement in order to be able to manage new requirements of high evacuation of the heat energy generated in the cable. Description of the invention

[0006] The present invention aims to provide a cable arrangement that is particularly simple to implement, and that allows for efficient heat dissipation.

[0007] To this end, the invention relates to an arrangement of at least one electrical cable, adapted to a spatial environment, said cable being of the type comprising a sheath forming an outer covering of said cable and comprising at least a plurality of longitudinal conductors arranged in the sheath, the sheath having an outer diameter corresponding to the diameter of the cable, the cable arrangement being characterized in that it comprises at least one cable clamping element, configured to exert at least one clamping force on the sheath in at least two clamping zones of the sheath to transversely clamp the longitudinal conductors and the sheath, the force of pinching being determined to create, at each pinching element, a deformation of the cable cross-section creating thermal conduction bridges directly linking the longitudinal conductors and an external surface of the sheath, thus evacuating heat produced by an electric current flow in said cable.

[0008] In the cable arrangement according to the invention, the pinching element(s) permanently perform a pinching and deformation function on the cable, that is, at all times during the use of the cable arrangement. For example, when the cable arrangement is used in a spacecraft, each pinching element pinches the cable at all times during the spacecraft's lifetime, and in particular when the spacecraft is in outer space.

[0009] The term "pinching" refers to the fact that the pinching element exerts a force on the cable in such a way as to modify the internal arrangement of the cable, in which its components are locally pressed against one another. The pinching is exerted, for example, by the pinching element in two distinct pinching zones on the cable. The pinching zones are arranged, for example, so that the pinching force exerted by the pinching element causes local deformation, creating thermal bridges by conduction along radial lines from the conductors to the outer sheath. The outer surface of the electrically insulating sheath around each conductor thus comes locally closer to the inner surface of the outer sheath to facilitate thermal bridging at each pinching zone. The core of each conductor can also be mobile within its electrically insulating sheath and pressed against it.

[0010] Thus, thermal conduction bridges are formed locally and radially at each pinching point. These bridges are directed substantially radially from the inside of the cable, i.e., for example, from the conductor cores to each of the pinching points on the outer surface of the cable sheath. The heat transmitted by conduction to the outer surface of the sheath can then be dissipated, for example, by convection and radiation. The thermal bridge forms, for example, a direct thermal conduction path from the center of the conductor to a pinching point, thanks to the pinching force. Such a direct thermal conduction path makes it possible to efficiently dissipate heat from the inside of the cable.

[0011] Heat is also transmitted by conduction between the outer surface of the sheath and the support areas with the pinching elements which in turn diffuse heat by convection and radiation from their outer surface.

[0012] The heat produced inside the cable, under the effect of an electric current passing through the cable, can thus be efficiently dissipated from inside the cable up to the outer surface of the sheath, or even towards the pinching element, to dissipate heat into the cable environment. In particular, when an electrical current of several amperes or several tens of amperes flows through the cable at a high frequency, for example above 106 Hz, electrical losses are high, which necessitates significant heat dissipation to prevent damage to the cable.

[0013] Advantageously the need for heat dissipation can be regulated by multiplying the number of pinching elements.

[0014] Advantageously, any type of cable can be used and adapted without modifying the cable itself; the clamping elements are simply positioned, as an additional feature, on the external surface of the sheath. Thus, the function of dissipating heat generated by the cable, as required by a specific task, is no longer necessarily dependent solely on the cable used.

[0015] The pinching element can advantageously play the role of a radiator, by providing an additional surface for radiating heat from the cable which can prove critical in the airless space environment.

[0016] The clamping element performs a function distinct from the holding element, although one could consider an element combining both functions. The holding element is, for example, achieved by a hose clamp or a retaining loop. The retaining element exerts, for example, zero or minimal pressure on the cable. In the case of a retaining element, the aim is not to deform a section of the cable to modify its internal arrangement. A uniform pressure on the external surface is, for example, applied by the retaining element. A holding action can therefore be distinguished from a clamping action. Thus, clamping elements can be arranged in sufficient number and in suitable positions to achieve efficient heat dissipation, while retaining elements can be arranged in sufficient number and in suitable positions to achieve mechanical holding.Furthermore, for a plasma motor, for example, a power cable must have a certain degree of mobility to allow for motor orientation.

[0017] Moreover, this separation of the pinching and holding functions facilitates the design and thus makes it possible to design the pinching element in such a way as to promote the evacuation of heat, i.e. the cooling of the cable, according to the needs of the mission, while the holding element can be designed in such a way as to promote holding according to the needs of the mission.

[0018] However, it is also possible that the pinching organ and the holding organ are formed by the same pinching and holding organ.

[0019] The pinch zones are, for example, substantially transversely opposed on the cable. When the cable has a substantially circular cross-section, the zones of pinch points can, for example, be diametrically opposed on the cable.

[0020] When the spacecraft reaches outer space, the cable, not being in a pressurized environment, is evacuated from the air particles initially present inside the cable and replaced, for example after a few minutes, by a vacuum. The clamping elements are therefore all the more important because the dissipation of the energy generated inside the cable requires thermal conduction.

[0021] According to a particular feature of the invention, each long conductor comprises an electrically conductive core and is electrically insulated by an electrically insulating sheath specific to each conductor.

[0022] According to another feature, the cable arrangement according to the invention further comprises at least one cable retaining member configured to retain the cable relative to a structural element of a spacecraft, at least temporarily at the time of a launch of the spacecraft, each pinching member being separate from said retaining member, the retaining member being configured to exert, on the cable, outside the launch phase, a compressive force of zero or less than a determined negligible compressive force not causing deformation of the cable cross-section.

[0023] According to another feature of the invention, each pinching member is fixed, by a mechanical link, to said cable exclusively.

[0024] According to another feature of the invention, each pinching member is connected to a flexible thermal braid for heat dissipation.

[0025] According to another feature of the invention, each pinching member exerts said pinching force in two transversely opposed pinching zones on said cable.

[0026] According to another feature of the invention, each pinching member comprises at least two arms bearing on the sheath at the level of said pinching areas, and an elastic return element exerting a return force on the arms so that they exert said pinching force.

[0027] According to another feature of the invention, at least one pinching member comprises a surface forming a thermal radiator.

[0028] According to another feature of the invention, the surface forming a thermal radiator includes a solar optical reflector.

[0029] According to another feature of the invention, at least one pinching member is coated with a coating having a determined emissivity.

[0030] According to another feature of the invention, the emissivity of the coating of the pinching element is greater than the emissivity of the external surface of the sheath.

[0031] According to another feature of the invention, the emissivity of the coating of the pinching element is greater than or equal to 0.5, and preferably greater than or equal to 0.8.

[0032] According to another feature of the invention, the coating is made from a paint and / or a surface treatment.

[0033] According to another feature of the invention, each pinching member bearing on the cable sheath extends, along the longitudinal direction of the cable, over a length between 1 and 3 times the diameter of the cable.

[0034] According to another feature of the invention, the arrangement comprises a plurality of pinching members mounted on the cable.

[0035] According to another feature of the invention, the pinching members are separated from each other by a distance, taken along said cable, of between 6 and 10 times the diameter of the cable.

[0036] The invention also relates to a spacecraft comprising at least one cable arrangement according to the invention.

[0037] The cable is held in position relative to a structural element of the spacecraft at least during launch. The cable is clamped at least when the spacecraft is in outer space. BRIEF DESCRIPTION OF THE FIGURES

[0038] The invention will be well understood and its advantages will become more apparent upon reading the following detailed description, given by way of example and not limiting in any way, with reference to the attached drawings illustrating examples of embodiment.

[0039] Fig. 1 represents an example of a spacecraft comprising a cable arrangement according to the invention.

[0040] Figure [Fig. 2] represents an example of cable used in a cable arrangement according to the invention.

[0041] Fig. 3 is a cross-sectional view of the cable of Fig. 2 showing the internal contact points without the pinching according to the invention.

[0042] Fig. 4 is a cross-sectional view of the cable of Fig. 2 on which a pinching member is placed according to an exemplary embodiment, and showing internal contact points forming radial thermal bridges.

[0043] [Fig.5] is a view similar to that of [Fig.4], which shows in particular pinching areas on the cable.

[0044] Fig. 6 shows an example of a cable arrangement with three pinching members placed on a cable.

[0045] Fig. 7 is a cross-sectional view of the cable of Fig. 2 on which a pinching member is placed according to an exemplary embodiment, and showing internal contact points forming radial thermal bridges.

[0046] Figure 8 shows an example of a cable arrangement with three components pinching according to an example of implementation.

[0047] Fig. 9 shows a schematic cross-sectional view of an example of a pinching and holding device according to an example embodiment.

[0048] Fig. 10 shows, in cross-section, another example of cable that can be used in a cable arrangement according to the invention. DETAILED DESCRIPTION OF THE INVENTION

[0049] Figure 1 represents a spacecraft 10, which may, for example, be in the form of an artificial satellite. Such a satellite may, for example, be a telecommunications satellite. The spacecraft may also be in the form of an interplanetary space probe. The spacecraft includes, for example, a plasma thruster powered by electrical energy via cables according to the invention. The plasma thruster will, for example, be oriented relative to the frame of the spacecraft during its operation, requiring the electrical power cables to be mobile relative to the frame of the spacecraft. The spacecraft 10 thus includes electrical or electronic equipment, which is connected to each other by electrical cables. Here, for example, the spacecraft 10 includes solar cell panels 11 intended to supply electrical energy to the spacecraft.In the illustrated example, the spacecraft 10 includes, in particular, a cable 100 connecting the electrical energy storage battery to a group of solar panels 11 or to equipment of the spacecraft 10.

[0050] The cable 100 according to the invention can be placed under a protective sheet of the MLI (Multi-Layer Insulation) or SLI (Single-Layer Insulation) type. The cable according to the invention can also be placed outside the spacecraft. For example, protective screens for the cable against solar radiation or against thermal radiation from a plasma engine may be provided.

[0051] The cable is for example held on the spacecraft 10 by means of retaining elements 310, which at least temporarily hold the cable 100 in relation to a structural element of the spacecraft 10 during the launch phases. The retaining elements can also play the role of holding a cable within a determined volume, for example for the supply of a plasma engine.

[0052] The retaining elements 310 are, for example, configured to hold the cable 100 relative to a structural element of the spacecraft 10 during the transition from a first state, in which the spacecraft 10 is stationary on the Earth's surface, for example before takeoff, to a second state, in which the spacecraft 10 is moving in space, for example in orbit around the Earth. In other words, the retaining elements 310 exert, for example, at least temporarily, a holding force cable 100 on or in the structural element of spacecraft 10.

[0053] Furthermore, the spacecraft 10 includes one or more pinching elements 200 for at least one cable 100. When the cable 100 carries an electric current of several amperes or several tens of amperes, for example, for a plasma engine, at a frequency of 1 MHz, the heat generated by the electrical resistance of the cable increases. Each pinching element 200 is configured to efficiently dissipate heat from the interior of the cable 100 to the external surface of the cable's outer sheath. The pinching efficiency has been tested, in particular, under vacuum in the laboratory. The heat dissipation efficiency is, for example, locally improved by a factor of 10 or even a factor of 100, depending on the cable type and the pinching forces applied.

[0054] For this purpose, the pinching elements 200 are for example configured to exert, permanently, a pinching force on the cable 100 and cause a local deformation of the cable cross-section.

[0055] The clamping elements 200 are, for example, configured to clamp the cable 100 in at least two clamping zones in the first state, in which the spacecraft 10 is stationed on the Earth's surface, during the transition from the first state to the second state, and in the second state, in which the spacecraft 10 is operating in outer space. Thus, the clamping elements 200, for example, clamp the cable 100 permanently, that is, for the entire lifetime of the spacecraft 10.

[0056] The pinching elements 200 can also themselves carry out a heat dissipation from the cable and transmitted to the pinching elements to be subsequently evacuated by convection or by radiation or even by conduction to a structural part of the spacecraft.

[0057] As shown in [Fig.1], the retaining members 310 and the pinching members 200 can, for example, be distinct.

[0058] As also shown in [Fig. 1], a holding member and a pinching member can, for example, be achieved by the same pinching and holding member 200b. The pinching and holding member 200b exerts at least temporarily a holding force on the cable 100, and permanently a pinching force on the cable 100. An example of a holding and pinching member is illustrated, for example, in [Fig. 9].

[0059] The cable 100 and the pinching element(s) 200 together form a cable arrangement 300. The configuration and positioning of the cable arrangement 300 on the spacecraft 10 can vary according to mission requirements.

[0060] Figure [Fig.2] illustrates the electrical cable 100 according to an example of an embodiment.

[0061] The electrical cable 100 includes, for example, an outer sheath 110 forming the outer casing of the cable 100.

[0062] The electrical cable 100 comprises, for example, one or more long, straight electrical conductors 120. The long, straight conductors 120 may, for example, be in the form of metallic cables coated with electrically insulating material 121. The conductors 120 are arranged inside the outer sheath 110 that surrounds them, that is to say, inside the cable 100.

[0063] The cable may for example include additional internal sheaths, in particular electrically insulating sheaths, for example made of fiberglass, which may be arranged between the outer sheath 110 and the conductors 120. The outer sheath 110 is for example made of a dielectric material such as PTFE.

[0064] The cable 100 may, for example, comprise an outer shielding sheath 110, arranged around a sheath 130, for example, made of polytetrafluoroethylene (PTFE), which itself surrounds the conductors 120. The shielding may, for example, have an electromagnetic shielding function and / or a mechanical shielding function. The outer shielding sheath is, for example, made of a metallic material, but nevertheless retains a flexible character.

[0065] The cable 100 is subject to thermal heating when an electric current passes through it, due to the cable's electrical resistance. This heating increases with the intensity and frequency of the electrical signal passing through it. For example, the currents can be a few amperes or even a few tens of amperes. Heating due to the cable's electrical resistance is therefore particularly problematic for frequencies exceeding 100 kHz. The invention could also be applied to currents on the order of a few milliamperes for small-diameter cables, enabling, for example, mass reduction.

[0066] In order to dissipate the heat produced inside the cable 100, the cable arrangement 300 further includes at least one cable 100 pinching element 200.

[0067] The pinching element 200 thus makes it possible to efficiently dissipate heat from the inside of the cable 100 to its external surface, or even via the pinching element 200. The dissipation of heat from the inside of the cable 100 to its environment is thus greatly improved compared with a cable 100 without a pinching element 200.

[0068] Fig. 3 shows a cross-sectional view of the cable 100, without a pinching element 200, and Fig. 4 shows a cross-sectional view of the cable 100 equipped with a pinching element 200.

[0069] Here, the cable 100 shown in figures 3 and 4 comprises two inner sheaths 130 and 131, arranged between the outer sheath 110 and the conductors 120.

[0070] As shown in [Fig. 3], in the cable 100 without a pinching element 200, one can see the outer sheath 110 surrounding the first inner sheath 130, itself surrounding the second inner sheath 131, the latter being arranged around the conductors 120. The conductors each comprise a conductive core surrounded by an electrically insulating sheath 121. As illustrated, the internal contact points 140 are randomly distributed at the internal and external surfaces of the sheaths.

[0071] Thus, heat produced at the conductors 120 can only be evacuated by conduction to the outside of the cable by following the thermal path, passing through these internal contact points 140, which follows significant portions inside the different inner sheaths to join two successive contact points.

[0072] As shown in [Fig. 4], in the portion of cable 100 equipped with a member of At the pinch point 200, the outer sheath 110, the inner sheaths 130 and 131, and the conductors 120 are in contact with each other at internal contact points 141 located opposite one another. Thus, each thermal bridge, using thermal conduction, simply passes through the thickness of each sheath. Alternatively, the conductive core of each conductor 120 can be placed against its dielectric sheath 121.

[0073] Thus, the thermal path where the cable is pinched, shown in [Fig. 4] as a dashed arrow path, is considerably shorter and more direct compared to the thermal path in [Fig. 3], where the cable is not pinched. In other words, the thermal path passing through the internal contact points 141 is much shorter when the cable 100 is equipped with the pinching element 200.

[0074] In certain configurations, the thermal path can, for example, be oriented along a radial direction of the cable 100.

[0075] It is specified here that, particularly in a cable arrangement 300 used in a spacecraft, the heat generated by the electrical resistance of the cable, in the core of the conductors, is dissipated by conduction. Indeed, in the absence of air in the cable, when the spacecraft leaves the atmosphere, heat dissipation by convection is then substantially zero, and heat dissipation by radiation is then low inside the cable 100.

[0076] The pinching member 200 is for example configured to exert, permanently, a pinching force F on the cable 100, in at least two pinching zones 150 of the cable 100.

[0077] Figure 5 illustrates, for example, the position of two pinching zones 150 on the cable 100, which are located at transversely opposite positions. In the case of a cable having a circular cross-section, the two pinching zones are, for example, radially opposite.

[0078] In this way, the pinching member 200 clamps and deforms, for example, transversely the conductors 120, the outer sheath 110 and the inner sheaths 130 and 131.

[0079] The pinching force F is, for example, exerted permanently on the cable 100, that is to say that during the use of the cable arrangement 300, the pinching element 200 exerts the pinching force F without discontinuing.

[0080] For example, in the context of use in a spacecraft, the pinching member 200 is configured so that it exerts the pinching force F during the takeoff of the spacecraft launcher, during the journey through the atmosphere and then in space, until its end of life.

[0081] Moreover, the pinching force F is such that it is, for example, constant to within 20% over time, that is to say, it does not disappear over time, as a holding force used specifically for the launch phase might.

[0082] For this purpose, the clamping element 200 can, for example, be formed by an elastic clip, as shown in Figures 4 to 6. The elastic clip includes, for example, a leaf spring. The material of the leaf spring will be chosen to be resistant to buckling, i.e., capable of maintaining a controlled pressure for an extended period of time, such as 15 years for a telecommunications satellite.

[0083] As shown in [Fig. 5], the clamping member 200 comprises, for example, two arms 210 and a base 220 connecting the arms 210. The base 220 is, for example, a return element that tends to bring the arms 210 closer together. The return effect is achieved, for example, by the elasticity of the material from which the clamping member 200 is made. This could be, for example, a metallic material such as steel.

[0084] Thus, the base 220 acting as a return element exerts, for example, indirectly the pinching force F on the cable 100, via the arms 210 which come to rest against the cable 100 at the pinching zones 150.

[0085] The pinching member 200 can, for example, be formed from a sheet of material, in particular metallic, folded so as to present a clip-shaped section, as illustrated in Figures 4 and 5.

[0086] Alternatively, the pinching elements can, for example, be made, at least in part, of a dielectric material.

[0087] Figure 6 illustrates an example of a cable arrangement 300 with three clamping elements 200. As can be seen in Figure 6, a clamping element 200 has a width, i.e., a dimension in the longitudinal direction of the cable 100, corresponding, for example, to twice the diameter of the cable 100. Alternatively, the width of the clamping element 200 can, for example, be between one and three times the diameter of the cable 100. The clamping element comes, for example, into linear contact with the outer surface of the outer sheath of the cable. The bearing area is, for example, essentially a line with a width of approximately a few hundred micrometers, or even 1 mm or a few millimeters.

[0088] Cable diameter 100 means an average diameter of the cable 100 over its length, in a state not clamped by a pinching element 200.

[0089] The clamping element may, for example, be mechanically attached to the cable only. The clamping element, attached to the cable, may include a flexible, thermally conductive heat-dissipating braid 25. Such a flexible braid 25 does not impede the clamping element's movements. The braid is, for example, connected at one end to the frame of the spacecraft or to a radiator for improved heat dissipation. The flexible braid is, for example, made of copper.

[0090] As shown in [Fig.7], the pinching member comprises, for example, two arms 210, and a joint 230 connecting the arms 210. The pinching member 200 is here in the form of a clamp.

[0091] The arms 210 each include, for example, a first arm extending on one side relative to the joint 230, designed to bear against the cable 100 to clamp it. Furthermore, the arms 210 each include a second arm extending, on the opposite side, on a second side relative to the joint 230. The clamping member 200 further includes a return element 220, which is, for example, a helical spring under compression. The spring is, for example, made of steel. The return element 220 is arranged between the second arms of the arms 210, so as to move the second arms away from each other. In this way, the first branches of the arms 210 are brought closer together, so that the cable 100 located between the first branches of the arms 210 can be tightened. The arms include, for example, steel.The arms can also include aluminum or copper, allowing for good thermal conductivity. Alternatively, the arms can also be made of a dielectric material.

[0092] Regardless of the embodiment, the return element is configured, for example, so that the pinching force exerted on the cable 100 remains constant over time and varies little in intensity. The intensity is, for example, constant within + / - 20% of a nominal value.

[0093] This can be achieved, in particular, by a spring made of steel. Another metal with a low yield strength and low stress relaxation could also be used. For the arms, metals with high thermal conductivity are preferred, for example.

[0094] In addition, the return element is configured, for example, so that the pinching force exerted on the cable 100 remains substantially constant regardless of the stroke of the arms 210. This ensures that the pinching force varies little in intensity even if the cable moves or works over time, for example if the cable 100 is moved, expands, contracts or retracts.

[0095] The return element 220 can, for example, be formed in a different material from the arms 210. For example, the return element 220 is made of steel, to exert a continuous return force over time, while the arms 210 are made of copper or aluminum, which are metals with high thermal conductivity, and which thus participate in efficient heat dissipation.

[0096] Fig. 8 illustrates a cable arrangement 300 showing pinching members according to an embodiment in which the pinching members 200 each have a surface 240 at their base 220.

[0097] This surface 240 forms a thermal radiator. The surface 240 can, for example, be flat, and can, for example, extend along a rectangular radiating surface.

[0098] The radiative surface 240 allows the heat dissipation of the pinching element 200 to increase, and thus increase the heat evacuated from the cable 100.

[0099] Regardless of the embodiment variant, each pinching member 200 can for example include a surface 240 forming a thermal radiator.

[0100] The radiative surface 240 can, for example, be equipped with a solar optical reflector. Such a reflector is particularly suitable for use of the cable arrangement outside a spacecraft, so as to avoid the absorption of solar radiation and prevent heating by solar rays.

[0101] Regardless of the embodiment, the pinching element 200 can, for example, be coated with a coating having a specific emissivity. This emissivity is, for example, greater than the emissivity of the outer sheath 110.

[0102] This coating comprises, for example, aluminum oxide. This type of coating can be applied, for example, by anodic oxidation when the pinching element 200 is made of aluminum.

[0103] Alternatively, the coating is for example a paint with high emissivity.

[0104] When the 300 cable arrangement is intended for use outside a spacecraft, the paint is, for example, chosen so as to also have low solar absorption. For example, a white paint may be chosen.

[0105] The emissivity of the cable is for example 0.2. The emissivity of the coating is for example greater than or equal to 0.2, preferably greater than or equal to 0.5, or even more preferably greater than or equal to 0.8.

[0106] Generally, the number of 200 pinching elements used in the 300 cable arrangement is chosen according to the needs of the mission.

[0107] A spacing between two consecutive pinching members 200 on the cable 100 corresponds, for example, to 6 to 10 times the diameter of the cable 100.

[0108] As illustrated in [Fig. 9], the pinching member can also perform the holding function. The pinching member comprises, for example, two arms 20a and 20b. The two arms are connected at one end to the spacecraft structure 21 and held together at their other ends by a clamping element 23 to perform the pinching function. The arms may, for example, be elastic. The two arms may, for example, be fixed at one end to the spacecraft structure. In one embodiment, one of the arms may, for example, be rotationally movable relative to the spacecraft structure 21, while the other arm is fixed to this structure.

[0109] The clamping element is, for example, constrained by a clamping spring 22 and obstructs the space between the two arms receiving the cable, in order to perform the holding function. The clamping element 23 is, for example, in the form of a metal rod connected on one side to one of the arms 20b and on the other side to the spring 22, while the spring 22 bears against the other arm 20a.

[0110] As illustrated in [Fig.10], the cable used in a cable arrangement may also comprise, for example, several long, thin conductors 26 not electrically insulated from each other and gathered together in a single electrically insulating sheath 27. Here again, one or more pinches will improve the dissipation of heat generated by electrical resistance in the cable.

[0111] It should be noted that the invention is not limited to the examples described and represented.

Claims

Demands

1. An arrangement (300) of at least one electrical cable (100), suitable for a space environment, said cable being of the type comprising a sheath (110) forming an outer covering of said cable and comprising at least a plurality of longitudinal conductors (120) arranged in the sheath, the sheath having an outer diameter corresponding to the diameter of the cable, the cable arrangement being characterized in that it comprises at least one cable clamping element (200), configured to exert at least one clamping force (F) on the sheath in at least two clamping zones (150) of the sheath to transversely clamp the longitudinal conductors and the sheath, the clamping force being determined to create, at each clamping element, a deformation of the cable cross-section creating thermal conduction bridges directly connecting the longitudinal conductors and an external surface of the sheath,thus dissipating heat produced by the flow of electric current in said cable, at least one pinching element (200) being coated with a coating having a determined emissivity.

2. Cable arrangement (300) of cable (100) according to claim 1, wherein each long conductor comprises an electrically conductive core and is electrically insulated by an electrically insulating sheath (121) specific to each conductor.

3. Cable (100) arrangement (300) according to claim 1, further comprising at least one cable retainer (310) configured to retain the cable relative to a structural element of a spacecraft (10), at least temporarily at the time of a launch of the spacecraft, each pinching member being separate from said retainer, the retainer (310) being configured to exert, on the cable, outside the launch phase, a compressive force of zero or less than a determined negligible compressive force not causing deformation of the cable cross-section.

4. Cable (300) arrangement (100) according to any one of the preceding claims, wherein each pinching member is fixed, by a mechanical link, to said cable exclusively.

5. Cable (300) arrangement (100) according to claim 4, wherein each pinching member is connected to a flexible thermal heat-dissipating braid (25).

6. Cable (300) arrangement (100) according to any one of the preceding claims, wherein each pinching member (200) exerts said pinching force (F) in two transversely opposed pinching zones on said cable.

7. Cable arrangement (300) of cable (100) according to any one of the preceding claims, wherein each pinching member (200) comprises at least two arms (210) bearing against the sheath at said pinching areas (150), and an elastic return element (220) exerting a return force on the arms so that they exert said pinching force (F).

8. Cable arrangement (300) according to any one of the preceding claims, wherein at least one pinching member (200) comprises a surface (240) forming a heat radiator.

9. Cable (300) arrangement (100) according to the preceding claim, wherein the surface (240) forming a heat radiator comprises a solar optical reflector.

10. An arrangement (300) of electrical cable (100) according to any one of the preceding claims, wherein the emissivity of the coating of the pinching element is greater than the emissivity of the external surface of the sheath (110).

11. Cable arrangement (300) of cable (100) according to any one of the preceding claims, wherein the emissivity of the coating of the pinching member is greater than or equal to 0.5, and preferably greater than or equal to 0.

8.

12. Cable arrangement (300) (100) according to any one of the preceding claims, wherein the coating is made from a paint and / or surface treatment.

13. Cable (100) arrangement (300) according to any one of the preceding claims, wherein each pinching member (200) bearing on the cable sheath extends, along the longitudinal direction of the cable, over a length between 1 and 3 times the diameter of the cable.

14. Cable (100) arrangement (300) according to any one of the preceding claims, wherein the arrangement comprises a plurality of pinching members (200) mounted on the cable.

15. Cable (300) arrangement (100) according to the preceding claim, wherein the pinching members are separated from each other by a distance, taken along said cable, of between 6 and 10 times the diameter of the cable.

16. Spacecraft (10) comprising at least one arrangement (300) of cable (100) according to any one of the preceding claims.

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