GB2277200A - A cover for a spacecraft antenna - Google Patents

A cover for a spacecraft antenna Download PDF

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Publication number
GB2277200A
GB2277200A GB9307912A GB9307912A GB2277200A GB 2277200 A GB2277200 A GB 2277200A GB 9307912 A GB9307912 A GB 9307912A GB 9307912 A GB9307912 A GB 9307912A GB 2277200 A GB2277200 A GB 2277200A
Authority
GB
United Kingdom
Prior art keywords
layer
cover
cover according
antenna
radio frequency
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
GB9307912A
Other versions
GB9307912D0 (en
GB2277200B (en
Inventor
Ian Honstvet
Neil Dunbar
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
MMS Space Systems Ltd
Original Assignee
British Aerospace PLC
British Aerospace Space Systems Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by British Aerospace PLC, British Aerospace Space Systems Ltd filed Critical British Aerospace PLC
Priority to GB9307912A priority Critical patent/GB2277200B/en
Publication of GB9307912D0 publication Critical patent/GB9307912D0/en
Publication of GB2277200A publication Critical patent/GB2277200A/en
Application granted granted Critical
Publication of GB2277200B publication Critical patent/GB2277200B/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/002—Protection against seismic waves, thermal radiation or other disturbances, e.g. nuclear explosion; Arrangements for improving the power handling capability of an antenna
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/18—Layered products comprising a layer of synthetic resin characterised by the use of special additives
    • B32B27/20—Layered products comprising a layer of synthetic resin characterised by the use of special additives using fillers, pigments, thixotroping agents
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/28—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42
    • B32B27/281—Layered products comprising a layer of synthetic resin comprising synthetic resins not wholly covered by any one of the sub-groups B32B27/30 - B32B27/42 comprising polyimides
    • 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
    • H01Q1/288—Satellite antennas
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q1/00—Details of, or arrangements associated with, antennas
    • H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/306—Resistant to heat
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/40—Properties of the layers or laminate having particular optical properties
    • B32B2307/41—Opaque
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2379/00—Other polymers having nitrogen, with or without oxygen or carbon only, in the main chain
    • B32B2379/08—Polyimides
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Abstract

A multilayer, thermally resistant, at least partially flexible, substantially radio frequency transparent, cover (1) for a spacecraft antenna is made up of an insulating layer (4) of glass fibre which is sandwiched between a first layer (5) of polymer film which is directed towards the antenna (3) and a second layer (6) of non-conductive polymer film on the outermost surface of the insulating layer (4). The second layer (6) is, or is rendered, opaque to visible and infrared radiation and carries an electrically conductive coating layer (8) on its outermost surface and means (9) for electrically grounding the coating layer (8). The polymer film layers (5, 6) may be made of polyimide or glass fibre and quartz material, conductive coating (8) may be Germanium or Indium-Tin Oxide and the second layer (6) may be made opaque by a layer of paint or the polyimide layer being loaded with a pigment. <IMAGE>

Description

A COVER FOR A SPACECRAFT ANTENNA This invention relates to a cover for a spacecraft antenna and particularly, but not exclusively, to a multilayer, thermally resistant, at least partially flexible, substantially radio frequency transparent cover for at least an active surface of a spacecraft antenna.
Spacecraft antennas in use undergo a wide variation in temperature which can lead to undesirable thermal distortions. There is thus a need for a thermal cover or shield designed to control the temperature of a spacecraft antenna and thereby reduce the thermal distortion.
Three conventional types of thermal cover have been proposed. A first of these involves insulating the non-active surfaces of the antenna only and employing thermally resistant paint on the active surface of the antenna. This approach results in relatively poor thermal control. For example a spacecraft antenna reflector treated in this way would still experience a variation of temperature as wide as Z50 C. This results in high thermal distortion which is even more noticeable if the antenna has a complex construction such as is the case with multi shell reflectors.
A further known technique is to suspend a metallised polymer film over the active face of the spacecraft antenna with the metal layer etched into a frequency selective pattern operative to allow radio frequency signals to pass through. Whilst this system has better thermal performance it has the disadvantages that the thermal performance is degraded by the metal removed from the etching set, the shield or cover requires a relatively heavy support to avoid imposing thermal distortion loads on the antenna, the shield is expensive and the large metal content in the antenna field of view gives rise to a significant risk of signal distortion or attenuation due to passive intermodulation.
A third known system involves suspending a non-metallised opaque film over the active surface of the antenna. Whilst this latter technique avoids the problems associated with the etched metallised polymer technique it does so at the expense of a greatly reduced thermal performance and therefore higher antenna temperature ranges and thermal distortion.
There is thus a need for generally improved cover for a spacecraft antenna which is effectively transparent to radio frequency signals but which at least minimises the foregoing disadvantages inherent in the conventional techniques.
According to one embodiment of the present invention there is provided a multilayer, thermally resistant, at least partially flexible, substantially radio frequency transparent, cover for at least an active surface of a spacecraft antenna, which cover includes an insulating layer of fibrous, non-metallic radio frequency transparent, insulating material, a first layer of non-conductive radio frequency transparent polymer film on one surface of the insulating layer, which first layer is directed, in use, towards at least the active surface of a spacecraft antenna, a second layer of non-conductive, radio frequency transparent, polymer film on the surface of the insulating layer opposite to said one surface, which second layer is, or is rendered, opaque to visible and infrared radiation and is directed, in use, away from the at least active surface of the spacecraft antenna, an electrically conductive, radio frequency transparent, coating layer on the outermost surface of the second layer, and means for electrically grounding the electrically conductive coating layer.
Preferably the insulating layer is a mat of glass fibres Conveniently the first layer is made of a polyimide or glass fibre and quartz material.
Advantageously the polyimide material is KAPTON (Registered Trade Mark) and the glass fibre and quartz material is BETACLOTH (Registered Trade Mark).
Preferably the second layer ismade of a polyimide or glass fibre and quartz material rendered opaque to visible or infrared radiation by a non-conductive optically opaque paint coating layer on at least one surface thereof.
Conveniently the polyimide material is KAPTON (Registered Trade Mark) and the glass fibre and quartz material is BETACLOTH (Registered Trade Mark).
Alternatively the second layer is made of polyimide material loaded with a pigment to render is opaque to visible and infrared radiation.
Advantageously the polyimide material is KAPTON (Registered Trade Mark).
Conveniently the coating layer is made of Germanium or Indium-Tin Oxide.
Advantageously the means for electrically grounding the electrically conductive layer include a plurality of strips connected to said electrically conductive layer.
Conveniently the cover includes means for attachment to an antenna.
Advantageously the attachment means are polymer studs or hook and eye tape.
According to a further aspect of the present invention there is provided a cover assembly including two multilayer, thermally resistant, at least partially flexible covers as hereinbefore disclosed for covering both the active and inactive surfaces of a spacecraft antenna.
For a better understanding of the present invention, and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which; Figure 1 is diagrammatic perspective view of a spacecraft antenna provided with a multilayer, thermally resistant, at least partially flexible cover, according to a first embodiment of the present invention, and Figure 2 is a cross-sectional view, to an enlarged scale, of a detail of the cover of Figure 1.
A multilayer, thermally resistant, at least partially flexible, coversubstantially radio frequency transparent, 1 according to a first embodiment of the present invention, as shown in Figures 1 and 2 of the accompanying drawings, is intended for use to cover at least an active surface 2 of a spacecraft antenna 3. The cover 1 includes an insulating layer 4 of fibrous, non-metallic, radio frequcny transparent, insulating material such as a mat of glass fibres. Prferably the layer 4 is in the form of a slab which is flexible and provides the thermal insulating properties for the cover. The thickness of the layer 4 is chosen to meet the thermal performance required. A suitable thickness is 25 mm. The insulting layer 4 contains no metallic materials as these would otherwise distort or attenuate the radio frequency signal.
A first layer 5 of non-conductive, radio frequency transparent, polymer film is provided on one surface of the insulating layer 5 and is directed, in use, towards at least the active surface 2 of the antenna 3. This first layer 5 is made of a polyimide material such as KAPTON (Registered Trade Mark) or glass fibre and quartz material such as BETACLOTH (Registered Trade Mark). The polymer is selected to withstand the electromagnetic and particulate radiation environment in space and to withstand the expected temperature cycle range to which the cover will be subjected in use.
Also forming part of the cover 1 is a second layer 6 of non-conductive, radio frequency transparent, polymer film which is provided on the surface of the insulating layer 4 opposite to said one surface. Thus the second layer 6, in use of the cover 1, is directed outwardly of the cover and is most remote from the antenna surface 2.
The second layer 6 is, or is rendered, opaque to visible and infrared radiation and is directed, in use of the cover, away from the surface 2 of the antenna 3.
This second layer 6 can be made in two different ways. According to a first way forming part of the present invention, the layer 6 is made of polyimide such as KAPTON (Registered Trade Mark) or glass fibre and quartz such as BETACLOTH (Registered Trade Mark) rendered opaque to visible and infrared radiation by a non-conductive optically opaque paint coating layer 7 on at least one surface thereof. Preferably the surface 7 is that directed towards the insulating layer 4. This paint can be any suitable commercially available non-conductive optically opaque paint.
According to a second way, which also forms part of the present invention, the layer 6 is made of polyimide material, preferably KAPTON (Registered Trade Mark) loaded with a pigment to render is opaque to visible and infrared radiation. However the second layer 6 is formed the paint coating layer 7 or loading in the layer 6 prevents sunlight and infrared radiation penetrating the cover 1 and degrading the thermal performance thereof.
An electrically conductive, radio frequency transparent, coating layer 8 is provided on the outermost surface of the second layer 6. This coating layer 8 may be made of Germanium deposited thereon in any convenient manner or of any commercially available high resistance material such as Indium'- Tin Oxide. This coating layer 8 provides just sufficient lateral electrical conduction path to leak the build up of electrical charge to the means for antenna 3 or spacecraft structure via means for electrically grounding the electrically conductive coating layer 8. This means may include a plurality of straps 9 connected to the layer 8.- The electrical conductivity of the layer 8 is insufficient significantly to affect the antenna radio frequency performance. The cover 1 is attachable to the antenna surface 2 in any convenient manner such as by polymer studs or hook and eye tape (not shown).
A cover of the present invention is intended to be substantially radio frequency transparent at frequencies below 300 GHz. Preferably the required radio frequency transparent range is from 0.1 to 50 GHz and more preferably from 0.1 to 20 GHz.
The flexible nature of the cover 1 means that its outermost surface can be made undulating, as shown in Figure 1 to break up specular reflections of sunlight.
This may be done by securing the cover to the antenna surface by means of rivets or the like having different lengths. Thus at one point the rivet may be short enough to secure the cover in face to face contact with the antenna surface whilst at a different point the rivet may be elongated sufficiently to support the cover at a spacing away from the antenna surface. The undulating surface produced in this way prevents the sun's rays being focussed by the cover on a feed horn for the antenna, which focussing would undesirably heat up the feed horn.
Although in the aforegoing description and in the embodiments illustrated in Figures 1 and 2, the cover has been shown as applied only to the active surface 2 of a spacecraft antenna 3, it is to be understood that a further cover 1 could be provided over the inactive surface of the antenna 3 so that the two covers 1 together make up a cover assembly for the antenna 3.
A cover 1 and cover assembly of the present invention have better thermal performance than conventional covers or shields and thereby reduces the thermal distortion of the antenna in operation. No elaborate support structure is required which avoids- undue loading on the antenna and hence resulting distortion. The metallic components of the cover are kept to a minimum thereby reducing risk of radio frequency signal interference. The cover of the invention is of relatively light weight and flexible so that it may be draped over an antenna surface without requiring to be stretched or carried on heavy expensive support structures as is conventional. This and the other constructional features of the cover of the present invention make it less expensive to manufacture than the conventional systems.

Claims (14)

1. A multilayer, thermally resistant, at least partially flexible, substantially radio frequency transparent cover for at least an active surface of a spacecraft antenna, which cover includes an insulating layer of fibrous, non-metallic, radio frequency transparent, insulating material, a first layer of non-conductive polymer, radio frequency transparent film on one surface of the insulating layer, which first layer is directed, in use, towards at least the active surface of a spacecraft antenna, a second layer of non-conductive, radio frequency transparent, polymer film on the surface of the insulating layer opposite to said one surface, which second layer is, or is rendered, opaque to visible and infrared radiation and is directed, in use, away from the at least the active surface of the spacecraft antenna, an electrically conductive, radio frequency transparent, coating layer on the outermost surface of the second layer, and means for electrically grounding the electrically conductive coating layer.-
2. A cover according to claim 1, wherein the insulating layer is a mat of glass fibres.
3. A cover according to claim 1 or claim 2, wherein the first layer is made of a polyimide or glass fibre and quartz material.
4. A cover according to claim 3, wherein the polyimide material is KAPTON (Registered Trade Mark) and the glass fibre and quartz material is BETACLOTH (Registered Trade Mark).
5. A cover according to claim 3 or claim 4, wherein the second layer is made of a polyimide or glass fibre and quartz material rendered opaque to visible and infrared radiation by a non-conductive optically opaque paint coating layer on at least one surface thereof.
6. A cover according to claim 5, wherein the polyimide material is KAPTON (Registered Trade Mark) and the glass fibre and quartz material is BETACLOTH (Registered Trade Mark).
7. A cover according to any one of claims 1 to 4, wherein the second layer is made of polyimide material loaded with a pigment to render it opaque to visible and infrared radiation.
8. A cover according to claim 7, wherein the polyimide material is KAPTON (Registered Trade Mark).
9. A cover according to any one of claims 1 to 8, wherein the coating layer is made of Germanium or Indium-Tin Oxide.
10. A cover according to any one of claims 1 to 9, wherein the means for electrically grounding the electrically conductive layer include a plurality of strips connected to said electrically conductive layer.
11. A cover according to any one of claims 1 to 10, including means for attachment to an antenna.
12. A cover according to claim 11, wherein the attachment means are polymer studs or hook and eye tape.
13. A multilayer, thermally resistant, at least partially flexible cover for at least an active surface of a spacecraft antenna, substantially as hereinbefore described and as illustrated in Figures 1 and 2 of the accompanying drawings.
14. A cover assembly including two multi-layer thermally resistant, at least partially flexible, covers according to any one of claims 1 to 13 for covering both the active and inactive surfaces of a spacecraft antenna.
GB9307912A 1993-04-16 1993-04-16 A cover for a spacecraft antenna Expired - Fee Related GB2277200B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB9307912A GB2277200B (en) 1993-04-16 1993-04-16 A cover for a spacecraft antenna

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB9307912A GB2277200B (en) 1993-04-16 1993-04-16 A cover for a spacecraft antenna

Publications (3)

Publication Number Publication Date
GB9307912D0 GB9307912D0 (en) 1993-06-02
GB2277200A true GB2277200A (en) 1994-10-19
GB2277200B GB2277200B (en) 1997-03-12

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0780921A3 (en) * 1995-12-22 1997-08-13 HE HOLDINGS, INC. dba HUGHES ELECTRONICS Sunshield film transparent to radio frequency energy and shielded articles
WO1998040927A1 (en) * 1997-03-07 1998-09-17 Robert Bosch Gmbh System comprising an electrical apparatus with an antenna and a motor vehicle
FR2784235A1 (en) * 1998-09-25 2000-04-07 Daimler Chrysler Ag Plastics vehicle fairing component with metallized zones on exterior, e.g. center part of radiator grille, has multilayer structure with deposited thin metal films allowing passage of radar signals
WO2006123188A1 (en) * 2005-05-20 2006-11-23 Eads Astrium Limited Thermal control film for spacecraft
WO2007000795A2 (en) * 2005-06-28 2007-01-04 Finmeccanica S.P.A. Antistatic coating for surfaces made of metal materials and dielectric materials or of dielectric materials only and method of application
DE102010043086A1 (en) * 2010-10-28 2012-05-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Casing for protecting equipment against high-energy radiation in space, has heat insulation layer, gas diffusion-proof layer and radiation protection layers that are positioned between mechanical protection layers
FR2966984A1 (en) * 2010-10-29 2012-05-04 Thales Sa DEVICE FOR TRANSMITTING RADIO WAVES, ANTENNA AND SPACE ENGINE.
CN110342913A (en) * 2019-06-28 2019-10-18 湖北三江航天江北机械工程有限公司 The preparation method of ceramic base A type interlayer wave transparent antenna house
GB2603954A (en) * 2021-02-22 2022-08-24 Thales Holdings Uk Plc Multifunction composite antenna enclosure

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4479131A (en) * 1980-09-25 1984-10-23 Hughes Aircraft Company Thermal protective shield for antenna reflectors
GB2228142A (en) * 1988-12-07 1990-08-15 Telefunken Systemtechnik Radome
EP0489531A1 (en) * 1990-12-05 1992-06-10 General Electric Company Antenna sunshield membrane
EP0529776A1 (en) * 1991-08-27 1993-03-03 Space Systems / Loral, Inc. Thermal control and electrostatic discharge laminate

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4479131A (en) * 1980-09-25 1984-10-23 Hughes Aircraft Company Thermal protective shield for antenna reflectors
GB2228142A (en) * 1988-12-07 1990-08-15 Telefunken Systemtechnik Radome
EP0489531A1 (en) * 1990-12-05 1992-06-10 General Electric Company Antenna sunshield membrane
EP0529776A1 (en) * 1991-08-27 1993-03-03 Space Systems / Loral, Inc. Thermal control and electrostatic discharge laminate

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5916668A (en) * 1995-12-22 1999-06-29 Hughes Electronics Corporation Sunshield film transparent to radio frequency energy and shielded articles
EP0780921A3 (en) * 1995-12-22 1997-08-13 HE HOLDINGS, INC. dba HUGHES ELECTRONICS Sunshield film transparent to radio frequency energy and shielded articles
WO1998040927A1 (en) * 1997-03-07 1998-09-17 Robert Bosch Gmbh System comprising an electrical apparatus with an antenna and a motor vehicle
FR2784235A1 (en) * 1998-09-25 2000-04-07 Daimler Chrysler Ag Plastics vehicle fairing component with metallized zones on exterior, e.g. center part of radiator grille, has multilayer structure with deposited thin metal films allowing passage of radar signals
US8665175B2 (en) 2005-05-20 2014-03-04 Astrium Limited Thermal control film for spacecraft
WO2006123188A1 (en) * 2005-05-20 2006-11-23 Eads Astrium Limited Thermal control film for spacecraft
WO2007000795A2 (en) * 2005-06-28 2007-01-04 Finmeccanica S.P.A. Antistatic coating for surfaces made of metal materials and dielectric materials or of dielectric materials only and method of application
WO2007000795A3 (en) * 2005-06-28 2007-03-29 Finmeccanica Spa Antistatic coating for surfaces made of metal materials and dielectric materials or of dielectric materials only and method of application
DE102010043086A1 (en) * 2010-10-28 2012-05-03 Deutsches Zentrum für Luft- und Raumfahrt e.V. Casing for protecting equipment against high-energy radiation in space, has heat insulation layer, gas diffusion-proof layer and radiation protection layers that are positioned between mechanical protection layers
FR2966984A1 (en) * 2010-10-29 2012-05-04 Thales Sa DEVICE FOR TRANSMITTING RADIO WAVES, ANTENNA AND SPACE ENGINE.
CN102593607A (en) * 2010-10-29 2012-07-18 泰勒斯公司 Device for emitting radio waves, antenna and spacecraft
EP2451007A1 (en) * 2010-10-29 2012-05-09 Thales Device for emitting radio waves, antenna and spacecraft
US8760358B2 (en) 2010-10-29 2014-06-24 Thales Radio wave transmitting device, antenna and spacecraft
CN102593607B (en) * 2010-10-29 2016-03-30 泰勒斯公司 Wireless transmitter part, antenna and spacecraft
CN110342913A (en) * 2019-06-28 2019-10-18 湖北三江航天江北机械工程有限公司 The preparation method of ceramic base A type interlayer wave transparent antenna house
CN110342913B (en) * 2019-06-28 2021-11-09 湖北三江航天江北机械工程有限公司 Preparation method of ceramic-based A-type interlayer wave-transparent radome
GB2603954A (en) * 2021-02-22 2022-08-24 Thales Holdings Uk Plc Multifunction composite antenna enclosure
GB2603954B (en) * 2021-02-22 2023-06-28 Thales Holdings Uk Plc Multifunction composite antenna enclosure

Also Published As

Publication number Publication date
GB9307912D0 (en) 1993-06-02
GB2277200B (en) 1997-03-12

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Legal Events

Date Code Title Description
732E Amendments to the register in respect of changes of name or changes affecting rights (sect. 32/1977)
PCNP Patent ceased through non-payment of renewal fee

Effective date: 19980416