Support device for supporting a fluid circulation duct and an assembly comprising said device and said duct - Patents.com

Abstract

1. A support device 20 for supporting a fluid circulation duct C, said support device comprising: a link 22 for supporting the duct by means of two end portions 22a of the link separated from one another in the longitudinal direction, which in cross section adopt a curved shape to support a portion Ca of the duct, the two end portions 22a being connected together by two intermediate portions of the link, each intermediate portion connecting one end 22a1, 22a2 of the two end portions 22a; two links 24, 26 for fastening the support device to an outer structure; and connection elements 28a-28d between the support link 22 and the fastening links 24, 26, each connection element having a fastening link and an intermediate portion of the support link passing through the fastening link and allowing sliding of the fastening link and the support link through the connection element.

Description

[Technical field]

[0001] The present invention relates to a support device for supporting a fluid circulation duct. [Background technology]

[0002] In aeronautics and space, various fluids are used (oxygen, hydrogen, helium, etc.) which must be transported from one point to another, for example between the engine and the launcher or between the launcher and the launch point, by ducts for circulating the fluids.

[0003] Due to the severe operating conditions to which they are subjected, the fluid circulation ducts described above meet particularly demanding specifications. In particular, this type of duct: The requirement that the duct be relatively long (e.g., about 0.3 to 2 meters) and The requirement that the ducts be capable of conveying fluids whether or not the fluids are pressurized, depending on the phase of operation; The duct must be capable of transporting liquids and gases. The requirement that the ducts may have large diameters and high mass flow rates (e.g., of the order of 250 kg / s or more); The requirement that the ducts be subjected to high dynamic stresses; The requirement that the duct may have to accommodate small displacements of thermomechanical origin, in particular at the two ends of the duct attached to / suspended from different components with more or less statically indeterminate connections, all of which have different temperatures and different coefficients of thermal expansion, and The requirement that the duct may need to accommodate engine movement / displacement; The ducts must be capable of satisfying the requirements (cumulative or not) that may be required to connect parts of different engines to each other or to connect parts of the engine to parts of the launcher.

[0004] In general, taking these conditions into account, standard (conventional) commercial products such as hoses consisting of (corrugated) metal convolutions covered at both ends with metal braid are not suitable for the intended application. Indeed, when a hose has to connect together different engine parts or parts of one engine to a part of the launching device, the length of the hose (for example of the order of 1 m for a diameter of 15 cm) is such that its first natural (vibration) frequency proves too low to prevent unacceptably large dynamic displacements in operation.

[0005] The use of standard (conventional) commercially available hoses is possible if the length of the hose is short enough or if the hose is stiff enough not to cause dynamic displacements that are too high to be operationally acceptable.

[0006] Where such conventional hoses cannot be used, it is possible to resort to gimbals (lines with metal convolutions to contain the pressure and provide sealing) or composite assemblies of several short lengths of hose connected by rigid line sections.

[0007] However, these solutions are not satisfactory and in this respect there is a clear need to enable the use of existing long (conventional) hoses for conveying fluids by reducing the above-mentioned disadvantages, particularly during dynamic displacement or offset of the hose under operating conditions. Summary of the Invention

[0008] An embodiment provides a support device for supporting at least one fluid circulation duct, comprising: The support device is a link, called a support link, intended to provide support for said at least one fluid circulation duct by means of two end parts of the link separated from one another in a longitudinal direction X, each end part being capable of adopting, in a cross section relative to the longitudinal direction X, a substantially curved shape intended to receive and support a portion of said at least one fluid circulation duct, said two end parts of the link being connected together by two intermediate parts of the link, each intermediate part connecting one of the two ends of an end part to one of the two ends of the other end part; two links, called fastening links, intended to provide fastening of the support device by two ends of each fastening link, each fastening link intended to be fastened to an outer structure of the support device; The device comprises at least two elements, called connecting elements, separated from each other in a longitudinal direction X and providing a connection between a support link and a fastening link, each connecting element having, on the one hand, at least one fastening link and at least one intermediate portion of the support link passing therethrough, and, on the other hand, at least two elements capable of allowing sliding of the fastening link and the support link through the connecting element.

[0009] This support device allows the at least one fluid circulation duct to be supported in two separate regions along its length by two separate end portions of the support link, whereby a first natural frequency of the support device of the at least one fluid circulation duct (1 / 2π(k / m), where k is the stiffness of the duct and m is its mass) is obtained. 1 / 2) and thus limit the amplitude of the dynamic response of the at least one duct when it is exposed at its ends to strong dynamic excitations. In general, the dynamic response of the at least one fluid circulation duct is reduced to an acceptable level, which makes it possible to avoid degradation, possibly even damage, of the fluid circulation duct. More specifically, said support device makes it possible to reduce the amplitude of the transverse / lateral displacements of said at least one duct relative to said longitudinal direction to an acceptable level, while allowing the duct to move, in particular during relative movements between the structures to which the fastening links are attached (for example between an engine and its launcher, in particular in the case of flexures in parts of the engine or the engine and the launcher). It is noted that said at least one fluid circulation duct can be flexible or rigid. The support device can have different shapes when it is not functionally connected to said at least one fluid circulation duct, in particular its two separate end parts do not necessarily have to take a substantially curved (concave) shape in the absence of the duct. The support device can be used to support one or more ducts, either isolated or physically joined by a shroud or fastening system.

[0010] According to another possible feature, the support device comprises two pairs of connection elements, each formed from two connection elements separated in the longitudinal direction, the two pairs of connection elements being separated in the transverse direction and parallel to each other and in the longitudinal direction, each of the two connection elements of each pair of connection elements having, on the one hand, one of the two fastening links and, on the other hand, one of the two parallel intermediate parts of the support link passing through it. Each connection element is a band or a ring, the shape of each connection element can be circular or elliptical or, more generally, a shape suitable for ensuring the sliding of the fastening link in the longitudinal direction and the sliding of the support link in the transverse and longitudinal directions. The support device comprises a spacing element arranged between said at least two connection elements in the longitudinal direction. The spacing element is selected from the following elements: a rigid rod connecting said at least two connection elements to each other in the longitudinal direction, and a rigid tube having, on the one hand, one of the two fastening links and, on the other hand, one of the two parallel intermediate parts of the support link passing through it, the rigid tube having an inner diameter smaller than the diameter of the connection element. (Some fastening links are subjected to longitudinal tension / traction during assembly / installation of the duct and equipment assemblies before each is attached to the outer structure.) A traction preload (or "pre-drawn tight") is applied to both fastening links (prior to use). The support links and fastening links are made from materials such as Kevlar®, stainless steel, Inconel®, etc.

[0011] Another embodiment relates to an assembly, as briefly disclosed above, comprising at least one fluid circulation duct and at least one device for supporting said at least one fluid circulation duct. By way of example, several support devices can be used to support different parts of one or more ducts.

[0012] According to another possible feature, the assembly comprises protection means for protecting the at least one fluid circulation duct against deformation, which protection means are positioned, on the one hand, between each of the two separate end portions of the support link having a generally curved shape in cross section, and, on the other hand, between each part of the at least one fluid circulation duct received and supported by the respective end portion. The protective means are selected from a protective strip arranged between each of the two separate end portions of the support link having a substantially curved shape and the respective portion of the at least one fluid circulation duct, a positioning guide having a U-shaped cross section arranged between each of the two separate end portions of the support link having a substantially curved shape and the respective portion of the at least one fluid circulation duct to receive the end portion of the respective support link, preventing the duct from being displaced laterally by each of the two sides or branches of the U and allowing it to extend from the portion forming the bottom of the U, providing local protection for the duct, and a sleeve having a circular cross section arranged around each of the two separate end portions, the sleeve having a substantially curved shape of the support link.

[0013] Another embodiment relates to a spacecraft, such as a launcher, comprising several internal components and at least one duct support assembly as briefly disclosed above, wherein at least one fluid circulation duct of said at least one assembly fluidly connects two internal components of said spacecraft with each other.

[0014] Another embodiment relates to a fluid supply system for an aircraft or spacecraft, comprising at least one duct support apparatus assembly as briefly disclosed above.

[0015] The objects and advantages of the present disclosure will be better understood by reading the detailed description given below of different embodiments, given as non-limiting examples, which description makes reference to the attached drawings, in which: [Brief description of the drawings]

[0016] [Figure 1A] FIG. 1A shows in side view a possible application of a fluid duct support device connecting a launcher to its engine. [Figure 1B] FIG. 1B shows a front view of the device of FIG. [Figure 1C] FIG. 1C shows the apparatus of FIG. 1A during engine angle adjustment. [Figure 1D] FIG. 1D shows the apparatus of FIG. 1B during engine angle adjustment. [Figure 2A] FIG. 2A shows a possible embodiment of the support device of FIGS. 1A-1D in a front view. [Figure 2B] FIG. 2B shows a side view of the support device of FIG. 2A. [Figure 2C] FIG. 2C shows a cross-sectional view of the support device of FIGS. 2A-2B. [Figure 2D] FIG. 2D is a partial enlarged view of one of the connection elements of FIGS. 2A-2C that connects the links of the support device. [Figure 3A] FIG. 3A shows a front view of a modified embodiment of the support device of FIGS. 2A to 2D. [Figure 3B] FIG. 3B shows a side view of the support device of FIG. 3A. [Figure 3C] FIG. 3C illustrates a side view of another modified embodiment of the support device of FIGS. 2A-2D. [Figure 3D] FIG. 3D illustrates a side view of yet another alternative embodiment of the support device of FIGS. 2A-2D. [Figure 4A] FIG. 4A illustrates in cross-section another possible embodiment of the support device of FIGS. 1A-1D. [Figure 4B] FIG. 4B shows a top view of the support device of FIG. 4A. [Diagram 5] FIG. 5 illustrates a possible configuration for inserting a damping cushion between the support structures. [Figure 6A] FIG. 6A shows a first possible configuration of multiple ducts supported by a support device such as that of FIGS. 2A-2D. [Figure 6B]FIG. 6B shows a second possible configuration of multiple ducts supported by a support apparatus such as that of FIGS. 2A-2D. [Figure 6C] FIG. 6C shows a third possible configuration of multiple ducts supported by a support apparatus such as that of FIGS. 2A-2D. [Figure 6D] FIG. 6D shows a fourth possible configuration of multiple ducts supported by a support apparatus such as that of FIGS. 2A-2D. [Figure 7A] FIG. 7A shows another possible example of the application of a fluid duct support device within a launch vehicle propulsion system. [Figure 7B] FIG. 7B shows another possible example of a fluid duct support arrangement that connects the launcher to the ground facility and connects two internal components of the launcher to each other. [Figure 7C] FIG. 7C shows another possible example of a fluid duct support device connecting ground equipment to an aircraft. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0017] 1A and 1B show, in side and front views, respectively, an exemplary embodiment in which a fluid duct support device 20 is used to maintain or support a fluid duct C carrying a fluid such as hydrogen, methane, oxygen, nitrogen, helium, between a launcher 10 and an engine 12 attached thereto, by means of a gimbal 14 type articulation mechanism capable of transmitting torsional movements. Here, the fluid duct C is a conventional hose with a relatively high length (e.g. 1 meter) that allows connecting a part 10a of the launcher 10 to a part 12a of the engine 12. Schematic figures 1C and 1D show the angular movements that the engine can adopt and therefore that the duct C must follow without degradation, while maintaining its functionality, under the operating conditions of the launcher engine assembly. The dotted lines in 1C and 1D show the rest position of the duct C (without engine angle adjustment).

[0018] 2A et seq., is able to follow these engine angle adjustment movements, especially in the case of large dynamic stresses, so that it is also able to limit lateral displacements in the dynamic response of the duct C (note that if the duct is arranged horizontally, the device can also limit vertical displacements). The device 20 is relatively flexible in following the movements of the flexible duct C relative to the surrounding support structures 10 and 12.

[0019] 2A-2C show a possible embodiment of the support device 20 for a duct C in a front view (duct C in the background), a side view and a transverse view, respectively. The duct C here extends in a curved manner in the rest state (it should be noted that in other configurations the duct may extend substantially in a straight manner in the rest state when the duct C is installed and attached to the parts 10a and 12). As illustrated in Figs. 1A-1B, locally the duct can be considered to extend substantially in the longitudinal direction indicated by the reference X in Figs. 2A-2C (straight duct).

[0020] The support device 20 mainly comprises a link 22 that maintains or supports a fluid circulation duct C, two fastening links 24, 26 that allow the device 20 to be attached or fastened to the surrounding structures (here the launcher 10 and the engine 12), and at least two bands 28a-28d or connecting elements (alternatively these elements can have other shapes such as rings) that are separated from each other in the longitudinal direction X and connect the support link 22 and the fastening links 24, 26 together. The support link 22 passes through all the bands, regardless of their number, whereas if there are only two bands, the fastening links pass through the entirety of the bands. If there are four bands, each fastening link passes through only two of the four bands, as will be seen below. The support device 20 and the duct C jointly form a functional assembly when the device is attached to the surrounding support structure and is connected to the duct by a connecting structure briefly described above. The connecting elements are closed to prevent the links or cables passing through them from escaping from the connecting elements. Links 24 and 26 are simply slid into connecting elements 28a-28d.

[0021] In the embodiment described, the support device 20 comprises two pairs of bands, each formed of two bands 28a, 28b and bands 28c, 28d separated from each other (in each pair) in the longitudinal direction X. The two pairs of bands 28a, 28b and bands 28c, 28d are separated from each other in the transverse direction (in the plane of FIG. 2C) and are arranged along the duct C, parallel to each other (or generally parallel to each other, i.e. they can accept an angle of the order of a few degrees between their general alignment directions) and parallel to the longitudinal direction X. A connection structure with four bands makes it possible to form a structure supporting a duct with the general shape of a cradle with two support areas, as shown in the cross-sectional view of FIG. 2C with the support area 22a.

[0022] The support link 22 is generally rigid, but may have a certain elasticity without excessive stretching when the links 24 and 26 are preloaded or prestressed. It may be, for example, a link made of Kevlar®, stainless steel or Inconel®. The support link 22 (e.g. a cable) is inserted through the four bands 28a-d so as to close on itself and form: two separate end portions 22a, 22b (FIGS. 2A-2B) separated from each other and arranged opposite to each other in the longitudinal direction X, each of which may adopt, in a cross-sectional view (FIG. 2C), a generally curved shape (generally a U-shape with an open top) whose recess allows it to receive and support a portion Ca, Cb of the fluid circulation duct C (in a direction perpendicular to the longitudinal direction of the duct, in particular in a displacement direction F1 in FIG. 2C), while no support is applied to the duct C in a displacement direction F2 opposite to F1. Two intermediate portions 22c, 22d (FIGS. 2A-2B), generally parallel to each other and to the duct C and the longitudinal direction X (a gap of several degrees can be considered between the two intermediate portions in the duct and / or longitudinal direction), each of which connects one of the two generally curved ends 22a1, 22a2 of one end portion 22a of the two end portions 22a, 22b to one of the two generally curved ends 22b1, 22b2 of the other end portion 22b, respectively, at bands 28a, 28b for end portion 22c and at bands 28c, 28d for end portion 22d (see, for example, a partial enlargement of band 28a in FIG. 2D).

[0023] It should be noted that systems can be envisaged that allow joining (by crimping or welding) the two ends / tips of the support link 22. Alternatively, hooks can be equipped on the two ends / tips of the support link 22, which can be hooked together once the link 22 is slid into the band. Alternatively, a knot can be tied in the link 22.

[0024] By supporting the duct in two separate areas, i.e. by supporting the two conduit parts Ca, Cb by two separate end parts 22a, 22b respectively, the supporting forces can be distributed and thus local concentrations of stresses on the duct can be avoided. In general, the two end parts 22a and 22b are axially separated from each other by a minimum distance between 2 and 5 times the diameter of the duct C. The two end parts 22a, 22b are arranged separately from the two ends of the duct that the device supports, and the maximum separation between these two end parts depends on the stiffness of the duct to be supported. The greater the stiffness, the closer the two end parts can be to each other. These general remarks apply regardless of the embodiment of the invention or its variants.

[0025] Each end portion, such as end portion 22a in Fig. 2C, extends from one band 28b of the bands here to another band 28d of the other pair, facing here in the transverse direction, forming a curvature or concave surface (here a U-shape) at its base, at which a part of the duct (here Ca) is accommodated. The two bands 28b, 28d (here in Fig. 2C) are thus arranged vertically at a position (or dimension) greater than the position (or dimension) of the bottom of the end portion, here labeled with reference number 22a (Fig. 2C) and the position (or dimension) of the duct C. The two bands 28b, 28d are separated in the transverse direction so as not to be arranged directly (vertically) above the duct C (Fig. 2C), and at the two ends adopt a whole U-shape, the two branches of which are arranged at the two ends of the end portion 22a so as to extend along an angular sector of up to about 60°. The transverse spacing between the two bands 28b and 28d is equal to the diameter k* of the duct C (where k is between 2 and 4 for an angle of 60°), as for the other separate end portion 22b with bands 28a, 28c. Furthermore, the minimum spacing between the median plane passing through the two bands 28b, 28d and the median plane passing through the duct C may be between 2 and 4 times the diameter of the duct in this exemplary embodiment.

[0026] Each of the two fastening links 24, 26 has two ends 24a-24b, 26a-26b, for example shown in Fig. 1B, each of which is intended to be attached (for example by a band) to a structure such as the launcher 10 and the engine 12. Each fastening link 24, 26 extends from one end to the opposite end through two successive bands 28a, 28b of the device 20, through an intermediate portion 24c of the link 24, through two successive rings 28c, 28d, through an intermediate portion 26c of the link 26. The intermediate portions 24c, 26c of each link 24, 26 passing through the two bands of the same pair extend parallel to the intermediate portions 22c, 22d (support links 22) passing through the same two bands. The links are cables with a small amount of elasticity, too much elasticity would not contribute enough stiffness to the "flexible links + fastening links" assembly, and too little elasticity would reduce the "fluidity" of the support of the device according to the embodiment of the invention in the event of engine flexures. Examples of materials for the fastening means include steel, Inconel, Kevlar.

[0027] In the embodiment described, the fastening links 24, 26 can be pretensioned while being placed in relation to the duct C on the support structure (this pretension can be applied and adjusted in a known manner to the links or cables, for example as a function of preliminary testing). Thus, the fastening links can pretension the duct C during assembly. When the duct is pressurized, it naturally tends to deform outward (and not towards the support structure), i.e. in the direction indicated by the arrow F1 in FIG. 2C, thereby increasing the tension in the links 24 and 26. The fastening links are made of a material such as, for example, Kevlar®, stainless steel, Inconel®, etc.

[0028] The fastening links 24, 26 and the support links 22 passing through the band can slide / slide inside them (in other words, a relative sliding movement can occur between the band and the different links), which allows the support device 20 to adapt to the movements of the duct C and the surrounding movable support structures 10 and 12 as much as possible (in other words, it allows it to "gently" follow the movements / displacements of the duct C (in particular in the presence of engine deflections)), especially in the case of engine angle adjustments. This device 20 actually allows to follow certain movements of the duct C and to limit the amplitude of certain movements (for example lateral displacements perpendicular to the displacement directions F1 and F2 in FIG. 2C), which would risk deteriorating the duct.

[0029] The support device 20 makes it possible to achieve a minimum factor of two between the excitation frequency of the assembly of the launcher 10 and the engine 12 and the first natural frequency of the duct C (once the duct is supported by the device that is the object of the invention), thus making it possible to avoid too strong vibration phenomena (unacceptable amplitudes of the transverse dynamic displacements of the duct that would be able to damage it). In other words, the device makes it possible to modify (increase) the first frequency of the range of frequencies in which the level of dynamic excitation coming from the launcher is maximum. The dynamic amplification factor of the response of the duct C is then reduced.

[0030] 3A and 3B show a front view and a side view of the support device of FIGS. 2A-2D in a modified embodiment, which in the longitudinal direction X (or in the longitudinal direction which can therefore accommodate a relative transverse angular gap) provides for both band pairs a spacing element (an element which provides a minimum spacing) between two separate bands of the same band pair 28a-28b and band pair 28c-28d. The support device 20' has more particularly two spacing elements 30a and 30b parallel to each other and to the duct C, thus maintaining a minimum spacing between the two bands 28a, 28b and bands 28c, 28d, respectively, and preventing the two bands of the same pair from approaching each other in the axial direction. By maintaining a minimum spacing between these bands, the forces for supporting the duct are better distributed and therefore more effective than if they were allowed to approach each other in the longitudinal direction.

[0031] As an example (FIGS. 3A-3B), each spacing element can be a rigid rod 30a, 30b that connects two bands of the same pair to each other at their two ends, for example attached (by welding) to these bands, or possibly not attached to the bands, each rod being arranged, for example, between two parallel intermediate portions 22c, 24c and intermediate portions 22d, 26c of the links that pass through the respective band.

[0032] Alternatively (FIG. 3C), each spacing element of the support device 20″ can be a rigid tube such as tube 32 in the side view of FIG. 3C, which on the one hand has the intermediate portion of each of the two fastening links, here intermediate portion 24c of link 24, and on the other hand has the two parallel intermediate portions of support link 22, here passing through intermediate portion 22c. Tube 32 has an inner diameter smaller than the diameter of bands 28a-28b, so that the bands cannot penetrate into tube 32. Between bands 28c and 28d, an identical tube, not shown, is provided, surrounding intermediate portions 26c and 22d.

[0033] In each variant embodiment of the support device of FIGS. 2A-2D and 3A-3C, the support device 20″ may have means for protecting the fluid circulation duct C against deformation. This type of means has the function of distributing the contact pressure between, on the one hand, each end portion 22a, 22b having a general shape of a U partially surrounding the duct portion Ca, Cb (FIG. 2C) and, on the other hand, each corresponding duct portion Ca, Cb in contact with it, in order to avoid pinching or punching of the duct C (here a hose) by the support link 22, in particular under the operating conditions of the duct C. The protection means are more particularly positioned between each end portion 22a, 22b of the support link and each portion Ca, Cb of the duct that is received and maintained in the substantially U-shaped recess of said end portion.

[0034] As shown in Fig. 3D, the protection means comprises two positioning guides 34, each of which has a U-shaped cross section and is arranged between each of the two separate end portions 22a, 22b of the support link 22 and a respective portion Ca, Cb of the fluid circulation duct C, for receiving the respective end portion 22a, 22b inside the guide. A lateral edge of each guide prevents the respective portion of the duct from moving laterally out of the protected area.

[0035] According to an alternative embodiment (not shown), the protective means can take the form of a protective (or reinforcing) strip arranged between each of the two separate end portions 22a, 22b of the support link 22 and the respective portion Ca, Cb of the duct C, instead of a U-shaped positioning guide, in the case where a spacing element is arranged between the two bands of each pair (Figures 3A to 3C), i.e. a sleeve of circular cross section around each of the two separate end portions 22a, 22b of the support link, each sleeve therefore being in contact with a respective portion Ca, Cb of the duct C - it should be noted that the width of the strip must be sufficient so that the strip is satisfactory and that the link remains on it under the operating conditions of the duct, in particular when the duct is subject to longitudinal or axial displacements.

[0036] It should be noted that each of the above-mentioned elements may be integrated into the support link 22 or into the duct C, perhaps independent of each of them, or simply interposed between them upon their functional connection.

[0037] As an alternative embodiment (not shown), additional links or cables can be associated along the fastening links 24 and 26 in order to limit lateral displacements during the flight phase when the duct C is not pressurized and therefore not stiffened or rigidified. These additional links or cables can be attached to the engine or to the launcher, possibly to both. It is also possible to connect together the two parts of the link 24, as well as the parts of the link 26, i.e. those located above or below the "cradle" formed by the support link 22. It is also possible to connect the links 24 and 26 directly together.

[0038] According to yet another variant embodiment, one or more intermediate damping cushions can be placed between the duct C and one or more rigid components of the engine. Figure 5 illustrates an example of a possible configuration, in which a cushion 50 of this type is positioned between two structures or components 52 and 54, between which is placed a support device 56 similar to any one of the devices described above.

[0039] Each of the above-mentioned support devices is particularly easy to deploy for maintaining / supporting the fluid duct, and also easy to remove (eg in the case of maintenance).

[0040] It should be noted that on the same fluid duct (channel) carrying fluid between two points, several support devices conforming to the previous one can be used. Alternatively, it is also possible to place several devices conforming to the invention on the same duct C at different locations along the duct, for example to simply make the dynamic offset of the duct sufficiently "calm" in all directions if it is long.

[0041] Under operating conditions, each of the support devices described above can operate as described below.

[0042] During the cooling phase and under thermo-mechanical stress, the length of the duct C may decrease, which has the effect of slightly releasing the tension in the fastening links 24 and 26 while the duct C remains supported by these links.

[0043] Under pressure loading, the length of the duct C increases, which has the effect of increasing the tension in the fastening links 24, 26. The duct C is slightly displaced. The bands 28a, 28b slide slightly along the link 24 and the bands 28c, 28d slide slightly along the link 26. The approximate U-shape of each end portion 22a, 22b becomes slightly more pronounced (the opening of the U closes). The distance between the bands 28a-d changes. The dynamic response of the duct C is limited due to the stiffening provided by the device according to the invention.

[0044] During the angular adjustment of the engine, the duct C is displaced. The bands 28a, 28b slide significantly along the link 24 and the bands 28c, 28d slide along the link 26 (the amplitude of the sliding movement depends on the side on which the engine rotates, and here it is considered that the engine rotates towards the side which causes the greatest sliding in the bands 28a-28b). The approximate U-shape of each end portion 22a, 22b changes. The distance between the bands 28a-28d changes. The dynamic response of the duct C is limited due to the stiffening provided by the device according to the invention.

[0045] According to another embodiment shown in Figures 4A and 4B, the support device 40 comprises only two separate bands 42a, 42b (connecting elements) spaced apart from each other in the longitudinal direction X and arranged in a fluid circulation duct C'. Unlike the other support devices, here the support link 44 has two end portions 44a, 44b, each of which assumes a substantially curved shape that is more completely encircling than in the previous figures (U-shaped with an angle of about 60°), the duct C' forming a loop or collar around it (Figure 4A), the two end portions joining one of the two bands (here band 42b for end portion 44b). With respect to the previous figures, the support link 44 also comprises two parallel or generally parallel intermediate portions 44c, 44d, each of which extends from one band to the other band and passes through it to join one of the two end portions of the corresponding end portion 44a, 44b. As with the previous figures, the support device 40 comprises two fastening links 24' and 26', which here extend through two identical bands through their respective intermediate portions 24'c and 26'c. Thus, each of the two bands 42a and 42b has two intermediate portions 24'c and 26'c of the two fastening links and two parallel intermediate portions 44c, 44d of the support link 44 passing therethrough.

[0046] This configuration has the same stiffening effect as the four-band configuration during displacement of the duct in the direction indicated by arrow F' in Figure 4A (see arrow F1 in Figure 2C). During lateral (horizontal) displacement of duct C', this configuration makes it possible to limit the lateral dynamic displacement, however less effective than the four-band configuration.

[0047] Figures 6A to 6D show different possible configurations of an assembly or system in which a support device provides support to several fluid ducts (here shown, for example, by three ducts C1, C2, C3, but the number can be different).

[0048] In Fig. 6A, the ducts C1-C3, freely placed in a cradle formed by two end portions with end portion 22a, are physically separated or free with respect to each other, i.e. can be freely displaced with respect to each other. In Fig. 6B, the ducts C1-C3 are physically joined / grouped by links or connecting elements 60 (e.g. Serflex® type links). In Fig. 6C, the ducts C1-C3 are connected together by a comb-type device 62 that provides a defined lateral separation between the ducts. In Fig. 6D, the ducts C1-C3 are joined inside the outer shroud, here inside a tube that may extend over a virtual total of the length of the ducts or only a part of their length supported by a support device.

[0049] All of the above, in particular the different features, functions and advantages of the above-mentioned embodiment and its variants, also apply to the embodiment of Figures 4A-4B, insofar as there are no technical incompatibilities between the embodiments, e.g. the number of bands.

[0050] The above-mentioned support device for supporting fluid circulation ducts is applicable to any ducts subjected to strong dynamic stresses and thermomechanical stresses of the type inducing bending moments, tension or compression forces, shear forces and even torsion moments in the ducts. Stresses of this kind arise from temperature fluctuations from the temperature of cold fluids (20° K) to that of hot gases (over 800° K), from thermal excitation by the engine to the stage (launcher) or wind (wind) on the supply pipeline connecting this stage to the ground installation of the launch point, causing depth effects from several kilometers to several tons. More precisely, the value of the thermomechanical stresses depends on the material, the temperature and the type of failure in question; for the behavior of ducts under (non-repeated) direct stress, it is preferable to avoid plasticization of the ducts. With regard to the risk of crack initiation due to fatigue or propagation of cracks under dynamic loading (low or high number of cycles), the permissible level of alternating stresses at each cycle depends on the mean stress, the material and the temperature. The severity of the loads in the duct supported by the device according to the invention is transformed into torsor forces (tension and shear forces, bending and twisting moments), the strength of which depends on the material of the duct, on the support means (including the support device according to the invention), on the constraints of the duct, on the length of the duct, on the type of duct (type of hose, number of braids), on the material supporting the duct, on the temperature of the duct and on the displacements of its environment, i.e. the components to which it is attached (e.g. engine deflections). They also depend on the amplitude of the dynamic response of the hose in response to the stresses resulting from the flow of the fluid it carries on the one hand and the stresses resulting from the excitation of the components to which it is connected on the other hand. In general, the hose must not suffer unacceptable or irreversible damage under the influence of thermomechanical stresses, such as the initiation or propagation of fatigue and plasticization of the hose.

[0051] The ducts to be maintained / supported can be flexible or rigid, as already mentioned above.

[0052] The elongated hose and associated support device can replace the costly fluid (drain) ducts with one or more gimbals. In such a case, the elongated flexible element is attached to the exhaust line by means of several fastening elements of the Serflex® type (fastened to the support structure, in particular the engine, by inserting one or more cushions, as shown in FIG. 5). Under operating conditions, the exhaust line is hot, so that the clamping force exerted by the fastening elements of the Serflex® type increases.

[0053] In liquid propellant propulsion systems, small diameter rigid lines / ducts (which may have wire diameters of, for example, 6mm, 8mm, 12mm, 24mm...60mm, 90mm and 110mm) connect different parts of the engine and may sometimes not be supported sufficiently, which may lead to dynamic frequencies that are too low and thus to lateral dynamic displacements that are too high during the test phase or during flight. By using support devices such as the one described above, the amplitude of the lateral displacements of said rigid lines can be limited to an acceptable level.

[0054] FIG. 7A shows a possible application of the fluid duct support device according to the invention in an engine 70 of a space launcher, for example in a cryogenic propulsion system. Ducts 72, 74, in which one or various fluids circulate, connect two internal components of the engine together. Here, two ducts are shown, but it is understood that a different number of ducts is conceivable (e.g. one duct or more than two). The ducts can fluidly link / connect the internal components or elements constituting the launcher with each other, in particular, but without being limited to, elements of its propulsion system, i.e., elements of the fuel regulation system and / or elements of the fluid pressurization system and / or elements constituting the combustion chamber of the propulsion system, as for example the injection system. In the shown example, the fluid duct 72 connects the fluid pressurization system 78 to the injection system 76, and the fluid duct 74 connects two internal components 80 and 82 of the fuel regulation system with each other. Each of these fluid ducts can be supported / maintained by one or more fluid duct support devices 84, 86 according to the invention described above. The fluid ducts and the support devices collectively form one or more ductwork assemblies.

[0055] 7B shows a possible example of application of the fluid duct support device according to the present invention between a space launcher 90 and a ground facility 92 (launch point). More specifically, one or more fluid ducts 94 (filling supply pipelines for fluid supply) fluidly couple / connect the lower part 92a of the ground facility 92 to the first stage 90a of the launcher 90, and one or more fluid ducts 96 (supply pipelines for fluid supply) fluidly couple / connect the upper part 92b of the ground facility 92 to the second stage 90b of the launcher 90. Similarly, two inner components of the first stage 90a of the launcher, such as the engine 90a1 and the fuel or oxidizer reservoir 90a2, may be fluidly coupled / connected to each other by one or more fluid ducts 98. Each of these fluid ducts 94, 96, 98 may be maintained / supported by one or more fluid duct support devices 100, 102, 104 according to the present invention, as described above. The fluid ducts and the support devices jointly form one or more duct device assemblies. It should be noted that said at least one fluid circulation duct support device 94, 100 assembly is part of the fluid supply system of the spacecraft 90, and the same applies to said at least one fluid circulation duct and support device 96, 102 assembly. Device 100 is fastened, for example, to the lower part 92a of the ground facility 92, device 102 is fastened, for example, to the upper part 92b of the ground facility 92, and device 104 is fastened, for example, to the first stage 90a of the launcher.

[0056] 7C shows a possible example of application of the fluid duct support device according to the invention in the aviation field. More specifically, one or more fluid ducts 110 connect a ground equipment 112 to an aircraft such as an aircraft 114, in particular fluidly coupled / connected to a fuel reservoir of the aircraft for supplying fuel to the aircraft. The fluid ducts 110 can be maintained / supported by one or more fluid duct support devices 116 according to the invention, as described above. The fluid ducts and the support devices jointly form one or more duct device assemblies. It is noted that the assembly of at least one fluid circulation duct support device 110, 116 is part of the fluid supply system of the aircraft 114. The devices 116 are for example fixed to the ground equipment 112.

[0057] Although the present invention has been described by reference to specific embodiments, it is clear that modifications and changes can be made to these embodiments without departing from the general scope of the invention as defined by the scope of the claims. In particular, individual features of the different embodiments shown / mentioned can be combined into additional embodiments. Thus, the description and drawings should be considered in an illustrative sense, and not in a restrictive sense.

[0058] It will also be apparent that all features described with reference to a method, either alone or in any combination, can be transformed into an apparatus, and conversely, all features described with reference to an apparatus, either alone or in any combination, can be transformed into a method.

Claims

1. A support device (20; 40) for supporting at least one fluid circulation duct (C), The support device is a link (22), called a support link, intended to provide support for said at least one fluid circulation duct by means of two end portions (22a, 22b) of the link separated from one another in a longitudinal direction (X), each end portion being capable of adopting, in a cross section relative to the longitudinal direction (X), a substantially curved shape intended to receive and support a portion (Ca, Cb) of said at least one fluid circulation duct, said two end portions (22a, 22b) being connected together by two intermediate portions (22c, 22d) of said link, each intermediate portion connecting one end (22a1, 22a2, 22b1, 22b2) of the two end portions (22a, 22b) to one end of said two end portions (22a, 22b) of the other end portion (22a, 22b); two links (24, 26), called fastening links, intended to provide fastening of the support device (20; 40) by means of the two ends (24a, 24b, 26a, 26b) of each fastening link, each fastening link intended to be attached to an outer structure of the support device; A supporting device (20; 40) comprising at least two elements, called connecting elements (28a-28d), separated from each other in the longitudinal direction (X) and providing a connection between said supporting link (22) and said fastening links (24, 26), each connecting element having, on the one hand, at least one fastening link and at least one intermediate portion of said supporting link passing through said at least one fastening link, and, on the other hand, at least two elements capable of allowing sliding of said at least one fastening link and said supporting link through said connecting element.

2. 2. The support device according to claim 1, characterized in that the support device (20) comprises two pairs of connection elements (28a-28d) each formed from two connection elements separated in the longitudinal direction (X), the two pairs of connection elements being transversely separated and parallel to each other and parallel in the longitudinal direction, each of the two connection elements of each pair having, on the one hand, one of the two fastening links (24, 26) and, on the other hand, one of the two parallel intermediate portions (22c, 22d) of the support link passing therethrough.

3. 3. A support device according to claim 1 or 2, characterized in that each connecting element is a band or a ring.

4. The supporting device according to any one of claims 1 to 3, characterized in that the supporting device has a spacing element (30a-30b; 32) between the at least two connecting elements (28a-28d) in the longitudinal direction (X).

5. The spacing elements are the following elements: a rigid rod (30a-30b) longitudinally connecting said at least two connection elements (28a-28d) to each other; 5. The supporting device according to claim 1, characterized in that the supporting device is selected from: a rigid tube (32) having, on the one hand, one of the two fastening links (24, 26) and, on the other hand, one of the two parallel intermediate portions (22c, 22d) of the supporting link (22) passing through it, the rigid tube (32) having an inner diameter smaller than the diameter of the connecting element.

6. A supporting device according to any one of the preceding claims, characterized in that a traction preload is applied to each of the two fastening links (24, 26).

7. The support device according to any one of claims 1 to 6, characterized in that the support links (22) and the fastening links (24, 26) are made from materials such as Kevlar®, stainless steel, Inconel®, or the like.

8. 8. An assembly, characterized in that it comprises at least one fluid circulation duct (C) and at least one support device (20; 40) according to any one of claims 1 to 7 for supporting said at least one fluid circulation duct (C).

9. 9. An assembly according to claim 8, characterized in that the assembly comprises protection means (34) for protecting the at least one fluid circulation duct (C) against deformation, said protection means being positioned, on the one hand, between each of the two separate end portions (22a, 22b) of the supporting link and, on the other hand, the respective portions (Ca, Cb) of the at least one fluid circulation duct received and supported by said end portions.

10. The protection means is a protective band disposed between each of the two separate end portions of the support link and a respective portion of the at least one fluid circulation duct; a positioning guide (34) having a U-shaped cross section, said positioning guide (34) being arranged between each of the two separate end portions of said support link and a respective portion of said at least one fluid circulation duct, said positioning guide receiving and supporting said end portion of said respective support link in a predetermined position; 10. The assembly according to claim 9, characterized in that the support link is selected from a sleeve having a circular cross section disposed around each of the two end portions separate from the support link.

11. A spacecraft, such as a launcher, comprising several internal components and at least one assembly according to any one of claims 8 to 10, A spacecraft, such as a launcher, wherein at least one fluid circulation duct (C) of at least one said assembly fluidly connects two internal components of the spacecraft.

12. A fluid supply system for an aircraft or spacecraft, comprising at least one assembly according to any one of claims 8 to 10.

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