EP0379434A1 - Ultra-high frequency and high-temperature antenna, especially for a spacecraft - Google Patents

Ultra-high frequency and high-temperature antenna, especially for a spacecraft Download PDF

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Publication number
EP0379434A1
EP0379434A1 EP90400140A EP90400140A EP0379434A1 EP 0379434 A1 EP0379434 A1 EP 0379434A1 EP 90400140 A EP90400140 A EP 90400140A EP 90400140 A EP90400140 A EP 90400140A EP 0379434 A1 EP0379434 A1 EP 0379434A1
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EP
European Patent Office
Prior art keywords
panel
waveguide
antenna according
composite material
carbon
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP90400140A
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German (de)
French (fr)
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EP0379434B1 (en
Inventor
Jean-Pierre Astier
Christian Bertone
Alain Dujardin
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Societe Europeenne de Propulsion SEP SA
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Societe Europeenne de Propulsion SEP SA
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q21/00—Antenna arrays or systems
    • H01Q21/06—Arrays of individually energised antenna units similarly polarised and spaced apart
    • H01Q21/061—Two dimensional planar arrays
    • H01Q21/064—Two dimensional planar arrays using horn or slot aerials
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/27—Adaptation for use in or on movable bodies
    • H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
    • H01Q1/286—Adaptation for use in or on aircraft, missiles, satellites, or balloons substantially flush mounted with the skin of the craft
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/40—Radiating elements coated with or embedded in protective material
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q13/00—Waveguide horns or mouths; Slot antennas; Leaky-waveguide antennas; Equivalent structures causing radiation along the transmission path of a guided wave
    • H01Q13/06—Waveguide mouths
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q13/00—Waveguide horns or mouths; Slot antennas; Leaky-waveguide antennas; Equivalent structures causing radiation along the transmission path of a guided wave
    • H01Q13/10—Resonant slot antennas
    • H01Q13/18—Resonant slot antennas the slot being backed by, or formed in boundary wall of, a resonant cavity ; Open cavity antennas

Definitions

  • the present invention relates to a microwave antenna capable of operating at high temperature.
  • a particular field of application of the invention is that of antennas intended to equip apparatuses, machines or vehicles, in particular space planes, in parts undergoing a significant heating during use.
  • antennas are arranged in areas exposed to overheating due to friction on the layers of the atmosphere, in particular around the nose of the aircraft.
  • the external structures are formed for example by juxtaposed panels of refractory material, and it is known to protect the antennas against overheating by masking them behind a thermal protection.
  • the thermal protection material must then have low permittivity and very low attenuation losses and retain these dielectric properties up to very high temperatures. Different materials have been proposed for this purpose, for example in documents FR 2 483 689, FR 2 553 403 and US 4 358 772.
  • the object of the invention is to provide a microwave antenna capable of operating at very high temperature without it being necessary to completely mask it by thermal protection.
  • the antenna comprises at least one waveguide which opens to the outside through an opening in a panel and which comprises a tubular part formed by one piece with the panel, projecting therefrom on the inside and connecting to the rest of the panel around the opening, the panel with the integrated waveguide being made of a refractory composite material capable of ensuring propagation of microwave waves and constituting an element of a structure which can be brought to high temperature.
  • the antenna may include an array of several waveguides formed in the same panel or in neighboring panels.
  • the material constituting the waveguide panel assembly provides both a thermal protection function and a mechanical function. It is further necessary that this material retains its ability to propagate microwave waves at very high temperatures, at least equal to 1000 ° C and, preferably, at least equal to 1500 ° C.
  • This material is chosen from composite materials with reinforcement in refractory fibers (carbon or ceramic fibers) and with refractory matrix (carbon matrix, ceramic matrix or mixed carbon / ceramic matrix).
  • a C / C-SiC composite material carbon fiber reinforcement and mixed carbon-silicon carbide matrix
  • the composite material may be provided, in a manner known per se, with anti-oxidation protection.
  • the waveguide opening to the outside is advantageously filled with a refractory material ensuring surface continuity of the panel.
  • the filling material must have good resistance to thermal shock and good resistance to erosion. It must also be insensitive to moisture and have a coefficient of expansion substantially equal to that of the composite material constituting the panel-waveguide assembly.
  • the packing material must have dielectric properties: low permittivity and low losses, and keep these properties at high temperatures.
  • the lining material is advantageously a refractory composite material of the ceramic-ceramic or oxide-oxide type, for example an alumina-alumide composite.
  • the waveguide can be extended by a ring made of a refractory material forming a thermal barrier, for example a pyrographite ring, connected to the antenna body.
  • FIG. 1 schematically illustrates part of a structure formed by the juxtaposition of panels or tiles 10 of refractory material and intended, for example, for a hypersonic machine or a space vehicle.
  • the panels 10 have a structural function, as a constituent of the cell of the spacecraft or of the spacecraft, and a thermal protection function of the latter against overheating due to friction on the gaseous layers of the Earth atmosphere.
  • each waveguide is formed in one piece with a covering panel 10.
  • the same panel can comprise one or more waveguides associated with the same antenna, possibly in combination with one or more waveguides. waves integrated in a neighboring panel.
  • FIG. 1 shows panels 10 of substantially square shape each comprising three waveguides 20 aligned along a diagonal of the panel.
  • the panels provided with waveguides and those not provided with waveguides have the same external dimensions, so that the integration of one or more several antennas in the structure does not raise any particular difficulty for the assembly of the panels.
  • each waveguide 20 comprises a tubular part 22 formed integrally with the panel 10 in which the waveguide is integrated.
  • the tubular part 22 is of circular section. Any other shape could be given to this section, for example square, rectangular or ellipsoidal.
  • the tubular part 22 projects from the inside of the panel 10 and is connected to the rest of the latter around an opening 12 of the panel 10 through which the waveguide opens to the outside.
  • the waveguide 20 is extended by a ring 24 of insulating material forming a thermal barrier which connects the waveguide to the antenna body 30 from which protrudes a probe 32 for excitation of the electromagnetic field at bottom of the waveguide. Because it opens to the outside, the waveguide 20 is, for aerodynamic reasons, filled with a refractory dielectric material 26 which ensures the surface continuity of the panel.
  • the constituent material of the panel 10 and of the part 22 of the waveguide is a thermostructural refractory composite material obtained by producing a fibrous reinforcement, constituting a preform of the part to be produced, then by densifying the preform by infiltration or impregnation with the material. of the matrix within the porosity of the reinforcement.
  • the fibrous reinforcement is made of refractory fibers, for example carbon fibers or ceramic fibers, such as silicon carbide fibers.
  • the fibers are, for example, in the form of stacked layers of fabric bonded to each other by needling.
  • the realization of fibrous reinforcements plane or cylindrical by stacking two-dimensional layers and needling is described in the French patent applications No. 2,584,106, 2,584,107 and 88 13 132.
  • the densification is performed for example by chemical vapor infiltration.
  • Techniques for vapor infiltration of carbon or ceramic, such as silicon carbide, are well known. Reference may be made to French patent application No. 2189807 and 2401 888.
  • the fiber-matrix connection is improved by forming on the fibers an intermediate layer, or interphase, of a material with a lamellar structure, such as a pyrolytic carbon, as described in the French patent application. No. 2,567,874.
  • a fiber preform of the plate-shaped panel and cylindrical fiber preforms of the tubular parts 22 are produced separately by stacking and needling layers of carbon fiber fabric, as described above. Openings 12 are then cut in the preform of the panel at the desired locations for the waveguides, then the preforms of the panel and the tubular parts are assembled and maintained, for example by a tool. The material constituting the matrix is then simultaneously infiltrated within the assembled preforms. This co-densification secures the tubular parts with the rest of the panel due to the continuity of the matrix material at the interfaces between the assembled preforms.
  • the matrix is obtained by vapor vapor infiltration of carbon followed by a final densification phase by vapor vapor infiltration of silicon carbide.
  • Electromagnetic characterization tests of the composite material thus obtained have shown that the reflection coefficient of this material remains greater than 0.99 in module and equal to 180 ⁇ 1 ° in phase up to a temperature of 1,800 ° C.
  • the attenuation due to the waveguide is less than 0.5 dB per wavelength at room temperature.
  • Electrical conductivity increases with temperature, increasing from approximately 5.103 / cm at room temperature at around 5.104 / cm at 1800 ° C, thus minimizing ohmic losses under operating conditions.
  • the ring 24 acting as a thermal barrier at the bottom of the waveguide is made, for example, of pyrographite which has thermal conductivity properties in one of its planes and thermal insulation in the perpendicular direction.
  • the ring 24 is produced so as to obtain thermal insulation in the axial direction and thermal conductivity in the radial direction.
  • the filling material 26 is a ceramic-ceramic composite such as an alumina-alumina type composite formed by a fibrous texture (a mat) of silico-aluminous fibers densified by alumina by a liquid impregnation process or of vapor infiltration, as described for example in European patent No. 0 085 601.
  • a ceramic-ceramic composite such as an alumina-alumina type composite formed by a fibrous texture (a mat) of silico-aluminous fibers densified by alumina by a liquid impregnation process or of vapor infiltration, as described for example in European patent No. 0 085 601.
  • such a material is resistant to thermal shock and erosion, is not sensitive to moisture and has a coefficient of expansion close that of the C / C-SiC composite material used for the panel 10-tubular part 22 assembly of the waveguide.
  • the lining 26 does not contribute to the mechanical strength of the panel. It is therefore not necessary to use a material having particular mechanical properties. Ceramic fillers, for example in the form of boron nitride powder, can be incorporated into the filling material 26, in particular by dispersion within a matrix formed by liquid impregnation, which reduces the permittivity and the dielectric losses in the material. . The permittivity and the dielectric losses can also be adjusted by acting on the density of the filling material, which density is regulated by the conditions of densification of the material by the matrix.
  • the fibrous texture in alumina mat forming the preform of the filling material is prepreg of aluminum oxychloride.
  • the preform thus obtained is machined to the dimensions of the waveguide and introduced into it.
  • the connection between the parts is then obtained by heat treatment in a neutral atmosphere at a temperature of around 900 ° C.
  • a finishing treatment comprising in particular a deposit of a protective layer, for example in an alkaline silicate as described in patent application FR 88 16 862, can be applied to the panel-waveguide-filling material assembly to provide protection against oxidation and humidity.
  • a protective layer for example in an alkaline silicate as described in patent application FR 88 16 862

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Physics & Mathematics (AREA)
  • Remote Sensing (AREA)
  • Details Of Aerials (AREA)
  • Waveguide Aerials (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)

Abstract

The antenna comprises at least one waveguide (20) which opens to the outside through an aperture (12) in a panel (10) of the covering and which includes a tubular portion (22) formed in one piece with the panel, projecting relative to the latter on the inside and connecting with the remainder of the panel around the aperture, the panel with the integrated waveguide being made of a thermostructural refractory composite material, such as carbon/carbon or carbon/ceramic, capable of ensuring propagation of the ultra high frequency waves and constituting an element of a structure which can be taken to high temperature. The waveguide (20) is filled with a refractory dielectric material (26) such as an alumina/alumina type composite material. <IMAGE>

Description

La présente invention concerne une antenne hyperfréquence pouvant fonctionner à température élevée.The present invention relates to a microwave antenna capable of operating at high temperature.

Un domaine particulier d'application de l'invention est celui des antennes destinées à équiper des appareils, engins ou véhicules, notamment des avions spatiaux, dans des parties subissant un échauffement important en cours d'utilisation.A particular field of application of the invention is that of antennas intended to equip apparatuses, machines or vehicles, in particular space planes, in parts undergoing a significant heating during use.

Dans le cas d'un avion spatial, des antennes sont disposées dans des zones exposées à des échauffements dus au frottement sur les couches de l'atmosphère, en particulier autour du nez de l'appareil. Dans ces zones, les structures extérieures sont formées par exemple par des panneaux juxtaposés en matériau réfractaire, et il est connu de protéger les antennes contre l'échauffement en les masquant derrière une protection thermique. Le matériau de protection thermique doit alors présenter une faible permittivité et des pertes par atténuation très basses et conserver ces propriétés diélectriques jusqu'à de très hautes températures. Différents matériaux ont été proposés à cet effet, par exemple dans les documents FR 2 483 689, FR 2 553 403 et US 4 358 772.In the case of a space plane, antennas are arranged in areas exposed to overheating due to friction on the layers of the atmosphere, in particular around the nose of the aircraft. In these areas, the external structures are formed for example by juxtaposed panels of refractory material, and it is known to protect the antennas against overheating by masking them behind a thermal protection. The thermal protection material must then have low permittivity and very low attenuation losses and retain these dielectric properties up to very high temperatures. Different materials have been proposed for this purpose, for example in documents FR 2 483 689, FR 2 553 403 and US 4 358 772.

L'invention a pour but de fournir une antenne hyper­fréquence capable de fonctionner à très haute température sans qu'il soit nécessaire de la masquer totalement par une protection thermique.The object of the invention is to provide a microwave antenna capable of operating at very high temperature without it being necessary to completely mask it by thermal protection.

Ce but est atteint du fait que, conformément à l'inven­tion, l'antenne comporte au moins un guide d'ondes qui s'ouvre à l'extérieur à travers une ouverture d'un panneau et qui comprend une partie tubulaire formée d'une seule pièce avec le panneau, en saillie par rapport à celui-ci du côté intérieur et se raccordant au reste du panneau autour de l'ouverture, le panneau avec le guide d'ondes intégré étant en un matériau composite réfractaire capable d'assurer la propagation des ondes hyperfréquences et constituant un élément d'une structure pouvant être portée à température élevée.This object is achieved by the fact that, in accordance with the invention, the antenna comprises at least one waveguide which opens to the outside through an opening in a panel and which comprises a tubular part formed by one piece with the panel, projecting therefrom on the inside and connecting to the rest of the panel around the opening, the panel with the integrated waveguide being made of a refractory composite material capable of ensuring propagation of microwave waves and constituting an element of a structure which can be brought to high temperature.

La réalisation en une seule pièce d'un guide d'ondes avec un panneau permet une véritable intégration de l'antenne dans un ensemble structural ayant en outre une fonction de protection thermique avec continuité radioélectrique entre le guide d'ondes et la structure. Les problèmes de liaison qui pouvaient se poser, notamment en raison de dilatation différentielle, en cas de réali­sation séparée des éléments de l'antenne et de structure de la protection thermique sont ainsi évités.The realization in one piece of a waveguide with a panel allows a real integration of the antenna in a structural assembly also having a thermal protection function with radioelectric continuity between the waveguide and the structure. The problems of connection which could arise, in particular because of differential expansion, in the event of separate production of the elements of the antenna and of structure of the thermal protection are thus avoided.

L'antenne peut comporter un réseau de plusieurs guides d'ondes formés dans un même panneau ou dans des panneaux voisins.The antenna may include an array of several waveguides formed in the same panel or in neighboring panels.

Le matériau constitutif de l'ensemble panneau-guide d'ondes assure à la fois une fonction de protection thermique et une fonction mécanique. Il est nécessaire en outre que ce matériau conserve sa capacité de propagation des ondes hyperfréquences à des températures très élevées, au moins égales à 1 000°C et, de préfé­rence, au moins égales à 1 500°C.The material constituting the waveguide panel assembly provides both a thermal protection function and a mechanical function. It is further necessary that this material retains its ability to propagate microwave waves at very high temperatures, at least equal to 1000 ° C and, preferably, at least equal to 1500 ° C.

Ce matériau est choisi parmi les matériaux composites à renfort en fibres réfractaires (fibres en carbone ou en céramique) et à matrice réfractaire (matrice carbone, matrice céramique ou matrice mixte carbone/céramique). Un matériau composite de type C/C-SiC (renfort en fibres de carbone et matrice mixte carbone-­carbure de silicium) s'est avéré répondre aux conditions exigées. Le matériau composite pourra être muni, de façon connue en soi, d'une protection anti-oxydation.This material is chosen from composite materials with reinforcement in refractory fibers (carbon or ceramic fibers) and with refractory matrix (carbon matrix, ceramic matrix or mixed carbon / ceramic matrix). A C / C-SiC composite material (carbon fiber reinforcement and mixed carbon-silicon carbide matrix) has been found to meet the required conditions. The composite material may be provided, in a manner known per se, with anti-oxidation protection.

Le guide d'ondes débouchant à l'extérieur, il est avan­tageusement rempli par un matériau réfractaire assurant une conti­nuité de surface du panneau. Le matériau de remplissage doit présenter une bonne tenue aux chocs thermiques et une bonne résis­tance à l'érosion. Il doit être en outre insensible à l'humidité et présenter un coefficient de dilatation sensiblement égal à celui du matériau composite constitutif de l'ensemble panneau-guide d'ondes. Bien entendu, le matériau de garnissage doit présenter des propriétés diélectriques : faible permittivité et faibles pertes, et conserver ces propriétés aux températures élevées. Le matériau de garnissage est avantageusement un matériau composite réfractaire de type céramique-céramique ou oxyde-oxyde, par exemple un composite alumine-alumide.The waveguide opening to the outside, it is advantageously filled with a refractory material ensuring surface continuity of the panel. The filling material must have good resistance to thermal shock and good resistance to erosion. It must also be insensitive to moisture and have a coefficient of expansion substantially equal to that of the composite material constituting the panel-waveguide assembly. Of course, the packing material must have dielectric properties: low permittivity and low losses, and keep these properties at high temperatures. The lining material is advantageously a refractory composite material of the ceramic-ceramic or oxide-oxide type, for example an alumina-alumide composite.

A son extrémité opposée à celle raccordée au reste du panneau, le guide d'ondes peut être prolongé par une bague en un matériau réfractaire formant barrière thermique, par exemple une bague en pyrographite, reliée au corps d'antenne.At its end opposite to that connected to the rest of the panel, the waveguide can be extended by a ring made of a refractory material forming a thermal barrier, for example a pyrographite ring, connected to the antenna body.

D'autres particularités de l'antenne conforme à l'inven­tion ressortiront à la lecture de la description faite ci-après, à titre indicatif, mais non limitatif, en référence aux dessins annexés, dans lesquels :

  • - la figure 1 est une vue schématique d'une partie d'une structure externe de protection thermique formée de panneaux juxta­posés et dans lequel est intégrée une antenne, et
  • - la figure 2 est une vue en coupe d'un panneau du revê­tement de la figure 1 montrant, à échelle agrandie, un guide d'ondes contitutif de l'antenne.
Other features of the antenna according to the invention will emerge on reading the description given below, by way of indication, but not limitation, with reference to the appended drawings, in which:
  • FIG. 1 is a schematic view of part of an external thermal protection structure formed from juxtaposed panels and in which an antenna is integrated, and
  • - Figure 2 is a sectional view of a panel of the coating of Figure 1 showing, on an enlarged scale, a contiguous waveguide of the antenna.

La figure 1 illustre schématiquement une partie d'une structure formée par la juxtaposition de panneaux ou tuiles 10 en matériau réfractaire et destinée, par exemple, à un engin hyper­sonique ou un véhicule spatial. Les panneaux 10 ont une fonction structurale, en tant que constituant de la cellule de l'engin ou de l'avion spatial, et une fonction de protection thermique de celui-ci contre l'échauffement du au frottement sur les couches gazeuses de l'atmosphère terrestre.FIG. 1 schematically illustrates part of a structure formed by the juxtaposition of panels or tiles 10 of refractory material and intended, for example, for a hypersonic machine or a space vehicle. The panels 10 have a structural function, as a constituent of the cell of the spacecraft or of the spacecraft, and a thermal protection function of the latter against overheating due to friction on the gaseous layers of the Earth atmosphere.

Les communications avec l'engin ou véhicule spatial sont assurées au moyen d'antennes comportant chacune un guide d'ondes 20 ou un réseau de guides d'ondes 20 qui sont, conformément à l'inven­tion, intégrés à la structure formant protection thermique. A cet effet, chaque guide d'ondes est formé en une seule pièce avec un panneau de revêtement 10. Un même panneau peut comprendre un ou plusieurs guides d'ondes associés à une même antenne, éventuelle­ment en combinaison avec un ou plusieurs guides d'ondes intégrés dans un panneau voisin. La figure 1 montre des panneaux 10 de forme sensiblement carrée comprenant chacun trois guides d'ondes 20 alignés suivant une diagonale du panneau. Les panneaux munis de guides d'ondes et ceux non munis de guides d'ondes ont les mêmes dimensions extérieures, de sorte que l'intégration d'une ou plusieurs antennes dans la structure ne soulève aucune difficulté particulière pour l'assemblage des panneaux.The communications with the spacecraft or vehicle are ensured by means of antennas each comprising a waveguide 20 or a network of waveguides 20 which are, according to the invention, integrated into the structure forming thermal protection. To this end, each waveguide is formed in one piece with a covering panel 10. The same panel can comprise one or more waveguides associated with the same antenna, possibly in combination with one or more waveguides. waves integrated in a neighboring panel. FIG. 1 shows panels 10 of substantially square shape each comprising three waveguides 20 aligned along a diagonal of the panel. The panels provided with waveguides and those not provided with waveguides have the same external dimensions, so that the integration of one or more several antennas in the structure does not raise any particular difficulty for the assembly of the panels.

Comme le montre la figure 2, chaque guide d'ondes 20 comprend une partie tubulaire 22 formée d'une seule pièce avec le panneau 10 auquel le guide d'ondes est intégré. Dans l'exemple illustré, la partie tubulaire 22 est à section circulaire. Toute autre forme pourrait être donnée à cette section, par exemple carrée, rectangulaire ou ellipsoïdale.As shown in Figure 2, each waveguide 20 comprises a tubular part 22 formed integrally with the panel 10 in which the waveguide is integrated. In the example illustrated, the tubular part 22 is of circular section. Any other shape could be given to this section, for example square, rectangular or ellipsoidal.

La partie tubulaire 22 fait saillie du côté intérieur du panneau 10 et se raccorde au reste de celui-ci autour d'une ouver­ture 12 du panneau 10 à travers laquelle le guide d'ondes s'ouvre à l'extérieur. A son extrémité, le guide d'ondes 20 est prolongé par une bague 24 en matériau isolant formant barrière thermique qui relie le guide d'ondes au corps d'antenne 30 d'où fait saillie une sonde 32 d'excitation du champ électromagnétique au fond du guide d'ondes. Du fait qu'il s'ouvre à l'extérieur, le guide d'ondes 20 est, pour des raisons aérodynamiques, rempli par un matériau diélectrique réfractaire 26 qui assure la continuité de surface du panneau.The tubular part 22 projects from the inside of the panel 10 and is connected to the rest of the latter around an opening 12 of the panel 10 through which the waveguide opens to the outside. At its end, the waveguide 20 is extended by a ring 24 of insulating material forming a thermal barrier which connects the waveguide to the antenna body 30 from which protrudes a probe 32 for excitation of the electromagnetic field at bottom of the waveguide. Because it opens to the outside, the waveguide 20 is, for aerodynamic reasons, filled with a refractory dielectric material 26 which ensures the surface continuity of the panel.

Le matériau constitutif du panneau 10 et de la partie 22 du guide d'ondes est un matériau composite réfractaire thermostruc­tural obtenu en réalisant un renfort fibreux, constituant une préforme de la pièce à réaliser, puis en densifiant la préforme par infiltration ou imprégnation par le matériau de la matrice au sein de la porosité du renfort. Le renfort fibreux est en fibres réfrac­taires, par exemple en fibres de carbone ou en fibres de céramique, telles que des fibres en carbure de silicium. Les fibres sont par exemple sous forme de couches de tissu empilées liées les unes aux autres par aiguilletage. La réalisation de renforts fibreux plans ou cylindriques par empilement de couches bidimensionnelles et aiguilletage est décrite dans les demandes de brevets français no 2 584 106, 2 584 107 et 88 13 132. La densification est réalisée par exemple par infiltration en phase vapeur. Les techniques d'infiltration en phase vapeur du carbone ou de céramique, telle que le carbure de silicium, sont bien connues. On pourra se référer aux demandes de brevets français no 2 189 807 et 2 401 888. Dans le cas d'un matériau à matrice céramique, la liaison fibres-matrice est améliorée en formant sur les fibres une couche intermédiaire, ou interphase, en une matière à structure lamellaire, telle qu'un carbone pyrolytique, comme décrit dans la demande de brevet français no2 567 874.The constituent material of the panel 10 and of the part 22 of the waveguide is a thermostructural refractory composite material obtained by producing a fibrous reinforcement, constituting a preform of the part to be produced, then by densifying the preform by infiltration or impregnation with the material. of the matrix within the porosity of the reinforcement. The fibrous reinforcement is made of refractory fibers, for example carbon fibers or ceramic fibers, such as silicon carbide fibers. The fibers are, for example, in the form of stacked layers of fabric bonded to each other by needling. The realization of fibrous reinforcements plane or cylindrical by stacking two-dimensional layers and needling is described in the French patent applications No. 2,584,106, 2,584,107 and 88 13 132. The densification is performed for example by chemical vapor infiltration. Techniques for vapor infiltration of carbon or ceramic, such as silicon carbide, are well known. Reference may be made to French patent application No. 2189807 and 2401 888. In the In the case of a material with a ceramic matrix, the fiber-matrix connection is improved by forming on the fibers an intermediate layer, or interphase, of a material with a lamellar structure, such as a pyrolytic carbon, as described in the French patent application. No. 2,567,874.

Pour former en une seule pièce un panneau 10 avec plusieurs parties tubulaires 22 en matériau composite de type C/C-SiC, il est, par exemple, procédé de la façon suivante.To form a single piece of a panel 10 with several tubular parts 22 of composite material of the C / C-SiC type, it is, for example, as follows.

Une préforme fibreuse du panneau en forme de plaque et des préformes fibreuses cylindriques des parties tubulaires 22 sont réalisées séparément par empilement et aiguilletage de couches de tissu en fibres de carbone, comme décrit plus haut. Des ouvertures 12 sont découpées ensuite dans la préforme du panneau aux emplace­ments voulus pour les guides d'ondes, puis les préformes du panneau et des parties tubulaires sont assemblées et maintenues, par exemple par un outillage. Le matériau constitutif de la matrice est ensuite infiltré simultanément au sein des préformes assem­blées. Cette co-densification assure la solidarisation des parties tubulaires avec le reste du panneau en raison de la continuité du matériau de la matrice aux interfaces entre les préformes assem­blées. La matrice est obtenue par infiltration en phase vapeur de carbone suivie d'une phase de densification finale par infiltration en phase vapeur de carbure de silicium.A fiber preform of the plate-shaped panel and cylindrical fiber preforms of the tubular parts 22 are produced separately by stacking and needling layers of carbon fiber fabric, as described above. Openings 12 are then cut in the preform of the panel at the desired locations for the waveguides, then the preforms of the panel and the tubular parts are assembled and maintained, for example by a tool. The material constituting the matrix is then simultaneously infiltrated within the assembled preforms. This co-densification secures the tubular parts with the rest of the panel due to the continuity of the matrix material at the interfaces between the assembled preforms. The matrix is obtained by vapor vapor infiltration of carbon followed by a final densification phase by vapor vapor infiltration of silicon carbide.

Des essais de caractérisation électromagnétique du maté­riau composite ainsi obtenu ont montré que le coefficient de réflexion de ce matériau reste supérieur à 0,99 en module et égal à 180 ± 1° en phase jusqu'à une température de 1 800°C. L'atténuation due au guide d'ondes est inférieure à 0,5 dB par longueur d'onde à température ambiante. La conductivité électrique croît avec la température, en passant d'environ 5.10³

Figure imgb0001
/cm à la température ambiante à environ 5.10⁴
Figure imgb0002
/cm à 1 800°C, minimisant ainsi les pertes ohmiques en condition de fonctionnement.Electromagnetic characterization tests of the composite material thus obtained have shown that the reflection coefficient of this material remains greater than 0.99 in module and equal to 180 ± 1 ° in phase up to a temperature of 1,800 ° C. The attenuation due to the waveguide is less than 0.5 dB per wavelength at room temperature. Electrical conductivity increases with temperature, increasing from approximately 5.10³
Figure imgb0001
/ cm at room temperature at around 5.10⁴
Figure imgb0002
/ cm at 1800 ° C, thus minimizing ohmic losses under operating conditions.

La bague 24 faisant fonction de barrière thermique au fond du guide d'ondes est réalisée, par exemple, en pyrographite qui a des propriétés de conductivité thermique dans l'un de ses plans et d'isolation thermique en direction perpendiculaire. La bague 24 est réalisée de manière à obtenir l'isolation thermique en direction axiale et la conductivité thermique en direction radiale.The ring 24 acting as a thermal barrier at the bottom of the waveguide is made, for example, of pyrographite which has thermal conductivity properties in one of its planes and thermal insulation in the perpendicular direction. The ring 24 is produced so as to obtain thermal insulation in the axial direction and thermal conductivity in the radial direction.

Le matériau de remplissage 26 est en un composite céramique-céramique tel qu'un composite de type alumine-alumine formé par une texture fibreuse (un mat) en fibres silico-­alumineuses densifiée par de l'alumine par un procédé d'imprégna­tion liquide ou d'infiltration en phase vapeur, comme décrit par exemple dans le brevet européen no 0 085 601. Un tel matériau résiste aux chocs thermiques et à l'érosion, n'est pas sensible à l'humidité et a un coefficient de dilatation voisin de celui du matériau composite C/C-SiC utilisé pour l'ensemble panneau 10-partie tubulaire 22 du guide d'ondes. D'un point de vue hyper­fréquence, la permittivité ε′ de ce matériau de remplissage est de 3,2 et les pertes s'expriment par tgδ = 2,4.10⁻³. Il est à noter que le garnissage 26 ne contribue pas à la tenue mécanique du panneau. Il n'est donc pas nécessaire d'utiliser un matériau ayant des propriétés mécaniques particulières. Des charges céramiques, par exemple sous forme de poudre de nitrure de bore, peuvent être incorporées au matériau de remplissage 26, notamment par dispersion au sein d'une matrice formée par imprégnation liquide, ce qui réduit la permittivité et les pertes diélectriques dans le matériau. La permittivité et les pertes diélectriques peuvent en outre être ajustées en agissant sur la densité du matériau de remplissage, laquelle densité est réglée par les conditions de densification du matériau par la matrice.The filling material 26 is a ceramic-ceramic composite such as an alumina-alumina type composite formed by a fibrous texture (a mat) of silico-aluminous fibers densified by alumina by a liquid impregnation process or of vapor infiltration, as described for example in European patent No. 0 085 601. such a material is resistant to thermal shock and erosion, is not sensitive to moisture and has a coefficient of expansion close that of the C / C-SiC composite material used for the panel 10-tubular part 22 assembly of the waveguide. From a microwave point of view, the permittivity ε ′ of this filling material is 3.2 and the losses are expressed by tgδ = 2,4.10⁻³. It should be noted that the lining 26 does not contribute to the mechanical strength of the panel. It is therefore not necessary to use a material having particular mechanical properties. Ceramic fillers, for example in the form of boron nitride powder, can be incorporated into the filling material 26, in particular by dispersion within a matrix formed by liquid impregnation, which reduces the permittivity and the dielectric losses in the material. . The permittivity and the dielectric losses can also be adjusted by acting on the density of the filling material, which density is regulated by the conditions of densification of the material by the matrix.

Afin de réaliser l'assemblage du matériau de remplissage 26 et du guide d'ondes 20, il peut être procédé de la façon suivante. La texture fibreuse en mat d'alumine formant la préforme du matériau de remplissage est préimprégnée d'oxychlorure d'alumi­nium.In order to assemble the filling material 26 and the waveguide 20, it can be carried out as follows. The fibrous texture in alumina mat forming the preform of the filling material is prepreg of aluminum oxychloride.

La préforme ainsi obtenue est usinée aux dimensions du guide d'ondes et introduite dans celui-ci. La liaison entre les pièces est obtenue ensuite par traitement thermique en atmosphère neutre à une température d'environ 900°C.The preform thus obtained is machined to the dimensions of the waveguide and introduced into it. The connection between the parts is then obtained by heat treatment in a neutral atmosphere at a temperature of around 900 ° C.

Un traitement de finition comprenant notamment un dépôt d'une couche de protection, par exemple en un silicate alcalin comme décrit dans la demande de brevet FR 88 16 862, peut être appliqué à l'ensemble panneau-guide d'ondes-matériau de remplissage pour apporter une protection contre l'oxydation et l'humidité.A finishing treatment comprising in particular a deposit of a protective layer, for example in an alkaline silicate as described in patent application FR 88 16 862, can be applied to the panel-waveguide-filling material assembly to provide protection against oxidation and humidity.

Claims (10)

1. Antenne hyperfréquence pouvant fonctionner à tempéra­ture élevée, caractérisée en ce qu'elle comporte au moins un guide d'ondes (20) qui s'ouvre à l'extérieur à travers une ouverture (12) d'un panneau (10) et qui comprend une partie tubulaire (22) formée d'une seule pièce avec le panneau, en saillie par rapport à celui-­ci du côté intérieur et se raccordant au reste du panneau autour de l'ouverture, le panneau avec le guide d'ondes intégré étant en un matériau composite réfractaire capable d'assurer la propagation des ondes hyperfréquences et constituant un élément d'une structure pouvant être portée à température élevée.1. Microwave antenna capable of operating at high temperature, characterized in that it comprises at least one waveguide (20) which opens to the outside through an opening (12) of a panel (10) and which comprises a tubular part (22) formed in one piece with the panel, projecting therefrom on the inner side and connecting to the rest of the panel around the opening, the panel with the waveguide integrated being made of a refractory composite material capable of ensuring the propagation of microwave waves and constituting an element of a structure which can be brought to high temperature. 2. Antenne selon la revendication 1, caractérisée en ce que le guide d'ondes (20) est rempli d'un matériau diélectrique réfractaire (26).2. Antenna according to claim 1, characterized in that the waveguide (20) is filled with a refractory dielectric material (26). 3. Antenne selon la revendication 2, caractérisée en ce que le matériau de remplissage (26) est essentiellement un matériau composite de type alumine-alumine.3. Antenna according to claim 2, characterized in that the filling material (26) is essentially a composite material of the alumina-alumina type. 4. Antenne selon l'une quelconque des revendications 1 à 3, caractérisée en ce que le matériau constitutif du panneau est un matériau composite thermostructural choisi parmi les matériaux com­posites carbone-carbone et les matéraux composites à matrice au moins en partie en céramique.4. An antenna according to any one of claims 1 to 3, characterized in that the material constituting the panel is a thermostructural composite material chosen from carbon-carbon composite materials and composite materials with matrix at least partly ceramic. 5. Antenne selon la revendication 4, caractérisée en ce que le matériau composite constitutif du panneau est un matériau composite à renfort en fibres de carbone et matrice mixte carbone-­céramique.5. Antenna according to claim 4, characterized in that the composite material constituting the panel is a composite material with carbon fiber reinforcement and mixed carbon-ceramic matrix. 6. Antenne selon l'une quelconque des revendications 1 à 5, caractérisée en ce que le guide d'ondes (20) est prolongé, à son extrémité opposée à celle raccordée au reste du panneau, par une bague en matériau réfractaire (24) formant barrière thermique.6. Antenna according to any one of claims 1 to 5, characterized in that the waveguide (20) is extended, at its end opposite to that connected to the rest of the panel, by a ring of refractory material (24) forming thermal barrier. 7. Antenne selon la revendication 6, caractérisée en ce que la bague (24) est en pyrographite.7. Antenna according to claim 6, characterized in that the ring (24) is made of pyrographite. 8. Antenne selon l'une quelconque des revendications 1 à 7, caractérisée en ce qu'ele comporte plusieurs guides d'ondes (20) comprenant des parties tubulaires (22) formées d'une seule pièce avec un même panneau (10).8. An antenna according to any one of claims 1 to 7, characterized in that it comprises several waveguides (20) comprising tubular parts (22) formed in one piece with the same panel (10). 9. Antenne selon l'une quelconque des revendications 1 à 7, caractérisée en ce qu'elle comporte plusieurs guides d'ondes (20) comprenant des parties tubulaires (22) formées d'une seule pièce avec des panneaux (10) respectifs voisins.9. Antenna according to any one of claims 1 to 7, characterized in that it comprises several waveguides (20) comprising tubular parts (22) formed in one piece with neighboring neighboring panels (10) . 10. Antenne selon l'une quelconque des revendications 1 à 9, caractérisée en ce que le panneau avec le guide d'ondes intégré constitue un élément d'une structure de cellule d'engin hyper­sonique ou d'avion spatial formant également protection thermique.10. An antenna according to any one of claims 1 to 9, characterized in that the panel with the integrated waveguide constitutes an element of a cell structure of hypersonic machine or space plane also forming thermal protection.
EP90400140A 1989-01-19 1990-01-18 Ultra-high frequency and high-temperature antenna, especially for a spacecraft Expired - Lifetime EP0379434B1 (en)

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FR8900627A FR2641903B1 (en) 1989-01-19 1989-01-19 HIGH-TEMPERATURE MICROWAVE ANTENNA, ESPECIALLY FOR SPATIAL AIRCRAFT
FR8900627 1989-01-19

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Owner name: SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MO

Effective date: 20050131