NUMERICAL OPTIMIZATION OF A SATELLITE SHF NULLING MULTIPLE BEAM ANTENNA

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1 NUMERICAL OPTIMIZATION OF A SATELLITE SHF NULLING MULTIPLE BEAM ANTENNA D. Maiarelli (1), R. Guidi (2), G. Galgani (2), V. Lubrano (1), M. Bandinelli (2) (1) Alcatel Alenia Space Italia, via Saccomuro, 24, Roma, Italy, davide.maiarelli@aleniaspazio.it (2) IDS Ingegneria Dei Sistemi, via Livornese 1019, Pisa, Italy, r.guidi@ids-spa.it ABSTRACT Satellite uplink antennas for SHF band communications may require high resolution adaptive nulling capability to provide sufficient pattern gain to desired users while maintaining pattern nulls on interference sources in close proximity to the users. Multiple beams antennas (MBA) consisting of an aperture illuminated by a collection of feeds located in its focal plane and a beam-forming network (BFN) for combining the outputs of the feed array are well-suited as nulling antennas for geosynchronous satellites. Demanding nulling performances in terms of interfering signals cancellation requires an accurate pattern prediction down to sidelobe level and a high cross-polar isolation of the radiated element beams. To meet these requirements, design methods and analysis tools have been employed that take into account the electromagnetic interaction among the feeders and the satellite structures. In the qualification phase of an SHF nulling MBA at AASI, the pattern measurements have shown an unpredicted cross-polar level due to the interaction of primary radiated field with the surrounding structures. This paper reports the main steps of the AASI and IDS activity in optimizing the antenna position and the shape of some antenna-farm structures in order to improve the cross-polar performance while considering mechanical constraints. The electromagnetic analyses have been carried out employing different numerical techniques to validate the results and reduce the risks of satellite structural modifications. The numerical techniques, the optimization procedure and measured results are reported and discussed. 1. INTRODUCTION Multiple Beam Antennas (MBA) are frequently employed aboard of geosynchronous communication satellites for their intrinsic ability to accommodate communication requirements and suppress interference signals by providing variable pattern shaping [1]. Modern defense satellite communications at SHF and EHF bands demands for antenna systems with reconfigurable radiation pattern to receive uplink signal so that good gain can be developed in the direction of user terminal while simultaneously providing nulls in the direction of uplink jammers [2]. To meet the requirement of a variable pattern shaping, the antenna system shall provide a number of independent output ports and a suitable Beam Forming Network (BFN) that performs the beam-forming by properly weighing and combining the signals outgoing at the antenna ports, with a set of amplitude an phase excitations computed by the beamforming algorithms. One of the major constraint in the design of a variable pattern antenna, imposed by the usually severe space, weight and power restrictions for satellite payloads, is the allowable number of output ports that should be controlled by the BFN [3], [4]. A single aperture Multiple Beam Antenna composed by a reflector surface fed by an array of primary radiating elements offers the large aperture needed for good nulling resolution and gain on the assigned geosynchronous coverage, while keeping the number of signal ports for the beamforming at a tractable number. Interference sources within and just surrounding the coverage area are nulled with appropriate pattern shaping; interference sources located far from the coverage area shall be minimized by designing the antenna system to have low sidelobe out-of-area rejection [3], [4]. As is somewhat unpractical for a nulling antenna system to operate the beam control on the spurious cross-polar radiation pattern, interference rejection requirements generally demand also for a good cross-polar isolation of the radiated beams. For a MBA with uniform beams arranged in a hexagonal grid fashion, the optimum beam spacing is constrained by the key requirements of nulling resolution and coverage area gain; as a consequence, if the antenna belong to single aperture / single horn per beam concept, the optimum beam spacing limits the maximum allowable aperture of the primary radiating elements located along the focal-plane of the reflector [2]. The limitations on maximum horns diameter lead to a wide beamwidth radiation pattern of the feed array element, increasing the possibility of interaction of the primary field with the surrounding structures when the antenna is installed on the satellite. In addition the less than uniform excitations of the feed array elements often required to reach the desired pattern shaping when nulling constraints are imposed, results in a complex shaped primary pattern with many lobes that points outside the reflector angle of view and that can strongly interfere with the mechanical structures surrounding the antenna. When a similar MBA is accommodated aboard of a satellite in a

2 complex antenna farm composed of many other antennas and mechanical support structures, the interaction of the primary radiated field with the near scattering structures is almost unavoidable. For these critical installations the standard electromagnetic analysis techniques that consider only the primary source and the reflector scattering, are unable to accurately predict the element beam pattern for both the cross-polar component and the co-polar component down to low sidelobe level. It is the purpose of this paper to present the optimization steps and design solutions carried out to accurately predict and improve the radiated performances of an SHF nulling MBA developed at Alcatel Alenia Space Italia (AAS-I) for a defense satellite program, w.r.t. the electromagnetic interaction with the antenna-farm structures, taking into account the severe mechanical constraints. The first antenna pattern measurements performed in AAS-I on a breadboard model of the MBA, have shown an unpredicted cross-polar level due to the interaction with the mechanical structures surrounding the feed array. In the next design phase, a number of analyses and optimization activities have been undertaken within the framework of an AAS-I and IDS collaboration with the scope of developing an accurate EM model of the antenna and improve the radiated performances. In the next sections the design steps, the numerical techniques and experimental performance are addressed. 2. ANTENNA SYSTEM DESCRIPTION The SHF nulling uplink antenna system is composed by a radiating MBA unit capable to generate 16 element beams arranged in a hexagonal grid fashion; the shape of the grid has been optimized to properly overlap the specified coverage area, the beams are circularly polarized and are required to have an adjacent beam overlap of about 3 db. The outcoming signal at the 16 antenna output ports fed the inputs of an active reconfigurable Beam Forming Network that provide low noise amplification, amplitude and phase weighing and RF combining of the 16 beams to give a composite shaped antenna beam at the payload interface. The radiating system belongs to the single-aperture / single horn per beam concept and utilizes an offset paraboloid of 1,6 m in diameter fed by an array of primary radiating elements located along the focal plane of the reflector. The 16 primary radiating elements are circular waveguide horns operating in single circular polarization and optimized for high aperture efficiency and purity of polarization. The outputs of the 16 horn elements are fed to the BFN inputs by mean of a complex waveguide system. The antenna system is aligned on an antenna-farm module that interfaces the satellite top floor. The reflector is supported by the base panel of the antenna module via the Antenna Deployment Mechanism (ADM) (see Fig.1). The antenna module is also provided of a tower structure that supports all the antenna-farm feeding chains. The tower is composed by two shelves sustained by a rod s lattice. The antenna feed cluster is located on the top shelf and the tower provide the required support and alignement for the 16 waveguide runs. TOP-SHELF Figure 1. Structure of the SHF nulling antenna installed on the antenna module. Due to physical and mechanical constraints the edge of the top shelf drop in a position very near to the focal region of the reflector and is strongly illuminated by the primary pattern radiated by most of the feed elements. 3. ANTENNA PERFORMANCE The stringent requirements on the antenna radiation pattern force the verification of the antenna performance both in free space as in installed configuration. During a first measurement campaign, AAS-I found an unpredicted increase in cross-polar level of more than 10 db on the coverage area caused by the interaction between the antenna and the tower structure. Fig. 3 and Fig. 4 show the antenna pattern measured both in free space (red lines) and in installed (blue lines). The data relate to feeders F1 and F7 (see Fig. 2). Blue Feeder: F1 Red Feeder: F7 FEED -ARRAY TOWER STRUCTURE BASE Top shelf Figure 2. Feeder Enumeration REFLECTOR

3 The same have been simulated in order to verify if the same phenomenon was also evident from the electromagnetic model. The analyses results are reported in Fig. 5 and Fig. 6. The differences between simulated and measured results have been ascribed to some geometrical differences existing between the measured mock-up and the CAD satellite configuration. radiation pattern is due to the shelf on the satellite tower located near the feed array. Figure 5. Feeder F1 simulated data. Co-polar and cross-polar components. Free space and installed Figure 3. Feeder F1 measured data. Co-polar (continuous line) and cross-polar (dotted line) components. Free space and installed Figure 6. Feeder F7 simulated data. Co-polar and cross-polar components. Free space and installed Figure 4. Feeder F7 measured data. Co-polar (continuous line) and cross-polar (dotted line) components. Free space and installed 4. PATTERN DISTORTION ANALYSIS These distortion effects due to the satellite structures are not compatible with the antenna requirements. Consequently AAS-I and IDS started an activity with the scope of finding out modifications to the antenna location or to the shape of satellite structures that reduce these effects. ADF EMS (Antenna Design Framework ElectroMagnetic Satellite) [5] has been used, by applying full-wave, asymptotic and hybrid methods to the Cad models provided by AAS-I. Both the simulation and the measurement activities highlighted that the main distortion contribution to Therefore a set of simulations was performed to further understand the physical phenomenon by varying the shelf size and shape. In particular, the following (see Fig. 7 have been analyzed: original shelf configuration (a); shelf with no thickness (b); upper and lower surface of the shelf joined with a cylindrical surface (c); upper surface shortened, lower surface extended and oblique connection between upper and lower surface (d); upper surface extended, lower surface shortened and oblique connection between upper and lower surface (e); sheet metal covering the shelf shape close to feed array (f). Fig. 8 and Fig. 9 show a sub-set of the analyses for clarity. In particular, the figures show co/cross-polar patterns for feeds F1 and F7, for various shelf shapes. The simulations highlight that the increase in the cross polar component of the antenna pattern is mainly due to the currents induced on the joining surface connecting

4 the upper and lower surfaces of the shelf. Such currents cause an unexpected incident field on the antenna reflector with a consequent increase in the cross-polar component in the coverage area. (a) (b) Fig. 10 shows the final optimized shaping of the shelf. This solution is not the best one from an electromagnetic point of view, but it also takes into account mechanical constraints. The results obtained with the final configuration are shown in Fig. 11 and Fig. 12. It is worth noting that an average reduction of the cross-polar component of 6-9 db is obtained with this shelf configuration, providing a maximum value of the cross-polar component of less than -32 db with respect to the co-polar one. (c) (d) (e) (f) Figure 7. Different shelf Figure 10. Optimized shelf configuration Figure 8. Feeder F1 simulated data. Co-polar and cross-polar components for various shelf Figure 11. Feeder F1 simulated data. Co-polar and cross-polar components. Optimized and nominal Figure 9. Feeder F7 simulated data. Co-polar and cross-polar components for various shelf Figure 12. Feeder F7 simulated data. Co-polar and cross-polar components Optimized and nominal

5 Moreover, in order to achieve a deeper confidence in the results a Multi-Method approach has been used. In fact, the simulation have been carried out using an IDS proprietary tool based on Physical Optics with an ITD (Incremental Theory of Diffraction) extension, and they have been further checked using an another IDS tool for mixed Method of Moment-PO/ITD. The comparisons reported in Fig. 13 and Fig. 14 show a good agreement between the two models. (i.e. the same configuration modelled through more than one electromagnetic modelling method) has been applied in order to gain confidence about the results. 6. REFERENCE 1 H.Jasik, R.C.Johnson, Antenna Engineering Handbook (2 nd Edition), Mc Graw Hill, K.S.Rao, G.A. Morin, M.Q.Tang, K.K.Chan, Development of a 45 GHz Multiple -Beam Antenna for Military Satellite Communications, IEEE Trans. Antennas Propagation, Vol.43, No.10, Oct J.A.Mayhan, Area Coverage Adaptive Nulling from Geosynchronous Satellites: Phased Arrays Versus Multiple-Beam Antennas, IEEE Trans. Antennas Propagation, Vol.34, No.3, Mar J.A.Mayhan, Nulling Limitations for a Multiple- Beam Antenna, IEEE Trans. Antennas Propagation, Vol.24, No.6, Mar Official web site Figure 13. Feeder F1 simulated data. Co-polar and cross-polar components varying computational method Figure 13. Feeder F7 simulated data. Co-polar and cross-polar components varying computational method 5. CONCLUSION An antenna/satellite interaction problem responsible of unacceptable performance degradations, which was put in evidence through testing activities on a breadboard, has been faced and solved through a working procedure based on numerical simulation. A modified CAD shape of the satellite structure, responsible of the problem, has been designed and directly provided to the AAS-I mechanical antenna division for the structural and thermal analyses. Due to the required high accuracy, a Multi-Method approach

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