Antenna design for Space Applications
Transcription
Antenna design for Space Applications
Antenna design for Space Applications M. Sabbadini European Space Agency, Noordwijk, The Netherlands [email protected] © distribution forbidden without written consent of the author Day 2 overview • • • • Satellite communications Communication satellite antenna design Example of reflector antenna sizing Antenna technology for communication satellites © distribution forbidden without written consent of the author Antennas for Space Applications 2 Antennas for Space Applications Satellite Communications © distribution forbidden without written consent of the author System architectures Fixed satellite communications Telephony TV distribution Data transmission C band Ka band Direct satellite broadcasting TV (analog and digital) Digital radio Ku band Mobile satellite communications Telephony Multimedia Broadband © distribution forbidden without written consent of the author L, S + Ku band* Ku-Ka band * Link to ground station Antennas for Space Applications 4 Payload function • Receive signals from ground • Amplify signals • Convert carrier frequency from uplink to downlink bands • Transmit signals to ground © distribution forbidden without written consent of the author Antennas for Space Applications 5 Fundamental parameters Capacity: amount of information that can be transmitted in unit time, strictly related to the density of the radio wave flux that the satellite can generate on ground. Availability: percentage of time in which the system operates properly, needs to be very close to 1 for communication systems (e.g. 99.95%). © distribution forbidden without written consent of the author Antennas for Space Applications 6 Payload sizing G: ~ 120dB BW: 0.2-1.5GHz H D 10W-1000W 10-100 pW Geostationary orbit case: H=35786km D=~42000km © distribution forbidden without written consent of the author Antennas for Space Applications 7 Satellite orbits Elliptic orbits LEO orbit Geostationary orbit © distribution forbidden without written consent of the author Antennas for Space Applications 8 Earth viewing angle r θ h r = 6378km h = 35860km Minimum satellite elevation angle for good visibility over the Earth horizon γ = 5°-10° © distribution forbidden without written consent of the author ⎛ r ⎞ ⎟ ≅ 8.7° ⎝r+h⎠ θ = sin −1 ⎜ ⎛ r ⎞ θ = sin ⎜ cosγ ⎟ ⎝r +h ⎠ −1 Antennas for Space Applications 9 Antennas for Space Applications Communication Satellite Antenna Design © distribution forbidden without written consent of the author Typical European coverages © distribution forbidden without written consent of the author Antennas for Space Applications 11 Flux density and beam width -80 -90 Flux density (dBm-2) -100 edge level for fixed beam width peak level for fixed beam width peak level of global beam -110 edge level of global beam -120 beam edge beam centre -130 5deg 40deg 30deg 20deg 10deg 60deg 50deg -140 250 5000 10000 © distribution forbidden without written consent of the author 20000 satellite altitude (km) 30000 35768 Antennas for Space Applications 12 Gain and spot size d a c e b Coverage a b c d e Diameter (deg) Antenna size (λ) 3 2 1.5 1 0.75 20 30 28.3 33 40 36 56.6 39 80 42 Minimum gain (dBi) © distribution forbidden without written consent of the author Antennas for Space Applications 13 Multiple beams To increase capacity with finite power beams become smaller. Several of them are needed to cover the same area. Spatial diversity © distribution forbidden without written consent of the author Antennas for Space Applications 14 How to generate multiple beams? Use several antennas (but they take a lot of space on the satellite, which is small) But thenhow is it possible to separate the beams from one another? There is need of some form of orthogonality. © distribution forbidden without written consent of the author Antennas for Space Applications 15 Multibeam antennas optical mirror © distribution forbidden without written consent of the author reflector antenna feeds Antennas for Space Applications 16 Reflector antenna parameters parabola Key quantities Aperture plane D C θ θ’ ϕ h V F Focal plane d Diameter Focal length Offset Feed spacing View angle Beam spacing Beam deviation factor D f h d φ θ κ=θ/θ’ κ<1, ≈1 f © distribution forbidden without written consent of the author Antennas for Space Applications 17 Feed layout The layout of feeds in the reflector focal plane is the mirror image of the desired coverage. © distribution forbidden without written consent of the author Antennas for Space Applications 18 Orthogonality Having identified a way to separate the input ports, there is need of a way to separate the fields radiated from of them, i.e. some form of diversity. There are 4 possibilities: Polarisation very useful, but there are only 2 distinct ones Frequency heavily used, but bandwidth is limited and filters do not have infinitely sharp edges Time of limited use since the information flow must be continuous in most communication applications Code used in some cases, it makes the receiver more complex © distribution forbidden without written consent of the author Antennas for Space Applications 19 Beam crossover The flux level across the coverage area varies since gain changes across each beam footprint. Minimum ripple is best from the system point of view. Gmax Gmin Gmin ΔG Gmax The maximum of Gmin for a given aperture is obtained with ΔG ≈ 4.3dB. ΔG ≈ 3dB is often preferred to improve the power budget. © distribution forbidden without written consent of the author Antennas for Space Applications 20 Isolation Signals falling in the frequency band allocated to one beam and coming from others are an interference. Beam orthogonality (spatial and polarisation diversity) requires some level of decoupling (isolation) among beams. Gmin Copolar Isolation © distribution forbidden without written consent of the author Crosspolar Isolation Antennas for Space Applications 21 Sidelobe level The sidelobe level is dictated by the higher spatial frequencies of source currents in the source region. Linear aperture x=[0,1] with illumination changing from uniform to sin(x). © distribution forbidden without written consent of the author Antennas for Space Applications 22 Centred reflector systems Centred reflector systems have high sidelobe levels due to the blockage effect of the feed(s) or subreflector and to the scattering of its supporting structure. A © distribution forbidden without written consent of the author Antennas for Space Applications 23 Offset reflector systems Offset reflector systems have better performances, however the feed does not illuminate equally the rim due to the difference in path attenuation if pointed along the axis of cone intersecting the rim. The feed is instead pointed at the projection on the reflector surface of the aperture centre, so that the illumination of the rim becomes approximately balanced. © distribution forbidden without written consent of the author D 2 θ θ D 2 Antennas for Space Applications 24 Surface distortions Surface distortions also affect the sidelobe level. They are due to manufacturing and to thermal loads causing deformations. Systematic (e.g. due to segmentation) and periodic (e.g. due to the supporting structure) deformations give rise to specific sidelobe patterns linked to their spatial frequencies. Random surface errors of relatively small entity can be assumed to generally reduce the peak gain and increase sidelobe. The gain reduction can be considered as a reduction in efficiency given by 2 Ruze’s formula © distribution forbidden without written consent of the author η =e ⎛ 4πσ ⎞ −⎜ ⎟ ⎝ λ ⎠ Antennas for Space Applications 25 Cross polarisation Even if the feed has very pure polarisation, e.g. a corrugated horn, the reflector curvature causes some cross polarisation to appear. In a centred system the revolution symmetry ensure a relatively low level, in an offset one the level is much higher. Currents on reflector © distribution forbidden without written consent of the author Cross-polar radiation Antennas for Space Applications 26 Beam scanning Some other departures from an ideal behaviour of reflector antennas are linked to the use of feeds out of focus . Issues: Beam deformation C Loss of gain θ Higher sidelobes Higher crosspolar Irregular beam grid d V H F © distribution forbidden without written consent of the author Antennas for Space Applications 27 Improving scan performances Scan losses, pattern distortion, sidelobe and cross polar level increase with the distance of the feed from the focus. Effects are marked when the distance is larger than a few λ. The larger the f/D ratio of the reflector the lesser the effect (the reflector surface is flatter). Part of the effect could be removed by re-pointing the feeds toward the centre of the reflector but this complicates manufacturing as feeds are not parallel any more. © distribution forbidden without written consent of the author Antennas for Space Applications 28 Contoured beams In many cases it is important to concentrate the power flux only where it is really useful and circles or ellipses do not abound in geography. © distribution forbidden without written consent of the author Elliptic coverage Contoured coverage Antennas for Space Applications 29 Two alternatives for contouring Contoured beams can be obtained by: • Using an array with suitable complex excitation • Using a reflector antenna fed by an array • Using a reflector antenna with a non-parabolic reflector Since the shape is usually fixed the use of an array with a rather complex beam forming network and a large number of elements is not justified. Using a feed array it is easy to generate multiple shaped beams, using a shaped reflector this is much more difficult, but the antenna is much simpler. © distribution forbidden without written consent of the author Antennas for Space Applications 30 Contoured-beam antennas Feeding multiple feeds with the same signal, possibly with different amplitude and phase weights, the reflector antenna generates a shaped beam by superposition. © distribution forbidden without written consent of the author Antennas for Space Applications 31 Reflector shaping Changing the shape of the reflector will alter the phase and, to a lesser extent, the amplitude of induced current (or of the equivalent aperture distribution) thus modifying the beam. Σ Σ A A Φ Φ F F Parabolic reflector © distribution forbidden without written consent of the author Shaped reflector Antennas for Space Applications 32 Shaped surface The surface profile is modified mainly looking at the phase of currents. Clearly the variations could be limited to 2π, but the reflector surface needs to be continuous. The resulting surface may differ from the initial parabolic profile by several wavelengths. © distribution forbidden without written consent of the author Antennas for Space Applications 33 Double shaped reflector The non-uniform aperture phase distribution reduces the antenna efficiency. A double reflector system can be used to minimise the phase differences while increasing amplitude variations and still produce a contoured beam. At the cost of adding a (small) reflector. © distribution forbidden without written consent of the author Σ A Φ F Antennas for Space Applications 34 Area-gain product The efficiency of countered beam antennas is rather low, i.e. their gain is much lower that what could be obtained with the same aperture, therefore a different measure of efficiency is required. The area-gain product is usually applied in these cases to have a measure of how well an antenna matches the requirements. Area is the measure in steradians of the coverage extent Gain is the minimum gain achieved over the area © distribution forbidden without written consent of the author Antennas for Space Applications 35 Double reflector antennas Double reflector antennas offer additional flexibility. The sub-reflector viewing angle may be differ from the main reflector viewing angle and the equivalent f/D ratio may differ from that of the main reflector. However they have higher losses and a higher mass. Also their scan capability is limited. © distribution forbidden without written consent of the author Sub-reflector viewing angle Main reflector viewing angle Antennas for Space Applications 36 Compensated reflector systems An interesting option offered by multiple reflector systems is that they can be arranged to behave as a centred system, e.g. have the minimum of optical aberrations, like cross polar. If constructing the image with respect to the prime focus of the main reflector, i.e. the ideal surface obtained reflecting the main reflector surface into the chain of sub-reflectors, the feed axis coincides with the axis of the main reflector image then the system is equivalent to a centred one. © distribution forbidden without written consent of the author Central ray Image of main reflector Antennas for Space Applications 37 Dragone configuration An interesting solution to reduce the level of crosspolar radiation is to use two parabolic-cylinder reflector one providing focusing in one plane and the other in the orthogonal plane. A cylindrical surface does not change the polarisation of the field upon reflection. © distribution forbidden without written consent of the author Ku-band Dragone double reflector antenna (courtesy of EADS-CASA) Antennas for Space Applications 38 Antennas for Space Applications Example of reflector antenna sizing © distribution forbidden without written consent of the author Design parameters Requirements • Geostationary satellite at 16°E • European coverage • Frequency 20/30 GHz • Minimum gain 40dBi Unknowns • Reflector diameter • Focal length • Number of beams • Feed size © distribution forbidden without written consent of the author Antennas for Space Applications 40 Design procedure All dimensions expressed in λ = 10,15 mm GdBi,peak = 3+GdBi,min → (η=0.5), Gpeak =0.5(πD)2 Gmax = η 4π A2 = η ⎛⎜ πD ⎞⎟ λ 2 ⎝ λ ⎠ D = √(4·104/π) = 113 θ −3dB = k θ-3dB= 70/D = 0.62° λ D Assume beam spacing of 0.5° (to be adjusted later) and h=D/4, f/D=1 φ =… ϕ = arctan( 4 f (h + D) 4 fh ) − arctan( 2 ) 2 2 4 f − (h + D) 4f −h Assume feed gain at reflector edge Gfeed,peak -6dB φfeed,-3dB = φ/√2 © distribution forbidden without written consent of the author ⎛θ ⎞ G (θ ) = G (0 ) + (G (θ 0 ) − G (0 ))⎜⎜ ⎟⎟ ⎝ θ0 ⎠ Antennas for Space Applications 2 41 Design procedure cont’d Derive feed diameter d = 60/φfeed,-3dB Compute scan angle θ, assuming κ =1 θ = arctan θ −3dB = k λ D d 2 ⎛ ⎞ D ⎞ ⎛ ⎜ ⎜h + ⎟ ⎟ 2 D⎞ ⎜ 2⎠ ⎟ ⎛ ⎝ + + − h f ⎜ ⎟ ⎜ ⎟ 2⎠ 4f ⎝ ⎜⎜ ⎟⎟ ⎝ ⎠ C θ Finally check consistency with assumption of 0.5° d V © distribution forbidden without written consent of the author H F Antennas for Space Applications 42 Antennas for Space Applications Antenna technology for communication satellites © distribution forbidden without written consent of the author Rigid Reflectors The reflector (shell) mainly use composite materials, i.e. a sandwich consisting of: Two surface skins in CFRP (Carbon Fibre Reinforced Plastic) (fibre + resin) An “honeycomb” supporting structure in: • Aluminum • Carbon • Kevlar • Nomex © distribution forbidden without written consent of the author Antennas for Space Applications Thick-shell Reflectors 1.4*1.8 m shaped reflector developed by Thales Alenia Space (France) in the frame of EXPRESS AM2 program (Ku-band Tx/Rx) © distribution forbidden without written consent of the author Antennas for Space Applications 45 Stiffened Thin-shell Reflectors Final product Manufacturing process Reflector Mould Reflector draping and co-curing Assembly of stiffeners © distribution forbidden without written consent of the author Antennas for Space Applications Ultra-light Reflectors 3.8m shaped reflector using triaxial skin thin sandwich of 1.5Kg/m2. Developed by Astrium and Thales Alenia Space. © distribution forbidden without written consent of the author Antennas for Space Applications 47 Ultra-light Reflectors 2.5m, 1Kg/m2 Ku-band dual-shaped Gregorian reflector using triaxial carbon fibre membrane with stiffening web. Developed by EADSCASA © distribution forbidden without written consent of the author Antennas for Space Applications 48 Ultra-light Reflectors 2.2m, 1.2Kg/m2 CFRP ultra-light shaped reflector built by Thales Alenia Space © distribution forbidden without written consent of the author Antennas for Space Applications 49 Dual-Gridded reflectors Shaped dual-gridded reflector of 2.3 m using a Kevlar front reflector and CFRP back one. EADS-CASA © distribution forbidden without writtenAntennas consent offor theSpace authorapplications Antennas Space Applications University for of Pisa,, March 8th 2005 50 Earth deck module Ka band earth deck antenna module incorporating 4 Rx and 1 Tx antennas together with LNA box and RF sensing developed by Thales Alenia Space in the frame of Hotbird VI program. © distribution forbidden without written consent of the author Antennas for Space Applications 51 Reflector antennas with large F/D Courtesy of Alcatel-Alenia Space © distribution forbidden without written consent of the author Antennas for Space Applications 52 Foldable antennas Courtesy of Alcatel-Alenia Space © distribution forbidden without written consent of the author Antennas for Space Applications 53 Dual-reflector multi-beam antenna Courtesy of Alcatel-Alenia Space © distribution forbidden without written consent of the author Antennas for Space Applications 54 Waveguide feed array Courtesy of Thales Alenia Space © distribution forbidden without written consent of the author Antennas for Space Applications 55 Thuraya satellite for mobile communications (more than 200 beams ) 12.5m mesh reflector Courtesy of RUAG Aerospace © distribution forbidden without written consent of the author Antennas for Space Applications 56 3 m reflector for L-band ARTEMIS Telecom technology satellite (ESA) ARTEMIS in the ESTEC CPTR for testing Courtesy of RUAG Aerospace © distribution forbidden without written consent of the author Antennas for Space Applications 57 Courtesy of MDA © distribution forbidden without written consent of the author Antennas for Space Applications 58 L-band feed array © distribution forbidden without written consent of the author Antennas for Space Applications 59 C-band beam forming network Courtesy of EADS-Astrium © distribution forbidden without written consent of the author Antennas for Space Applications 60 Multi-beam feed system Courtesy of Alcatel-Alenia Space © distribution forbidden without written consent of the author Antennas for Space Applications 61 Active antenna for LEO Support Structure Power unit Rx Radiating Panel Tx Radiating Panel Rx LNA / BFN Assembly Tx BFN Pointing mechanism 0.57m x 0.33m 14 kg Courtesy of Thales Alenia Space © distribution forbidden without written consent of the author Antennas for Space Applications 62 © distribution forbidden without written consent of the author Antennas for Space Applications 63 © distribution forbidden without written consent of the author Antennas for Space Applications 64