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- Herausgeber: John Wiley & Sons
- Kategorie: Wissenschaft und neue Technologien
- Sprache: Englisch
This book addresses a broad range of topics on antennas for space applications. First, it introduces the fundamental methodologies of space antenna design, modelling and analysis as well as the state-of-the-art and anticipated future technological developments. Each of the topics discussed are specialized and contextualized to the space sector. Furthermore, case studies are also provided to demonstrate the design and implementation of antennas in actual applications. Second, the authors present a detailed review of antenna designs for some popular applications such as satellite communications, space-borne synthetic aperture radar (SAR), Global Navigation Satellite Systems (GNSS) receivers, science instruments, radio astronomy, small satellites, and deep-space applications. Finally it presents the reader with a comprehensive path from space antenna development basics to specific individual applications.
Key Features:
- Presents a detailed review of antenna designs for applications such as satellite communications, space-borne SAR, GNSS receivers, science instruments, small satellites, radio astronomy, deep-space applications
- Addresses the space antenna development from different angles, including electromagnetic, thermal and mechanical design strategies required for space qualification
- Includes numerous case studies to demonstrate how to design and implement antennas in practical scenarios
- Offers both an introduction for students in the field and an in-depth reference for antenna engineers who develop space antennas
This book serves as an excellent reference for researchers, professionals and graduate students in the fields of antennas and propagation, electromagnetics, RF/microwave/millimetrewave systems, satellite communications, radars, satellite remote sensing, satellite navigation and spacecraft system engineering, It also aids engineers technical managers and professionals working on antenna and RF designs. Marketing and business people in satellites, wireless, and electronics area who want to acquire a basic understanding of the technology will also find this book of interest.
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Contents
Cover
Title Page
Copyright
Preface
Acknowledgments
Acronyms
Contributors
Chapter 1: Antenna Basics
1.1 Introduction
1.2 Antenna Performance Parameters
1.3 Basic Antenna Elements
1.4 Arrays
1.5 Basic Effects of Antennas in the Space Environment
References
Chapter 2: Space Antenna Modeling
2.1 Introduction
2.2 Methods of Antenna Modeling
2.3 Fast Algorithms for Large Space Antenna Modeling
2.4 Case Studies: Effects of the Satellite Body on the Radiation Patterns of Antennas
2.5 Summary
Acknowledgments
References
Chapter 3: System Architectures of Satellite Communication, Radar, Navigation and Remote Sensing
3.1 Introduction
3.2 Elements of Satellite System Architecture
3.3 Satellite Missions
3.4 Communications Satellites
3.5 Radar Satellites
3.6 Navigational Satellites
3.7 Remote Sensing Satellites
3.8 Architecture of Satellite Command and Control
3.9 The Communications Payload Transponder
3.10 Satellite Functional Requirements
3.11 The Satellite Link Equation
3.12 The Microwave Transmitter Block
3.13 Rx Front-End Block
3.14 Received Power in the Communications System's RF Link
3.15 Additional Losses in the Satellite and Antenna
3.16 Thermal Noise and the Antenna Noise Temperature
3.17 The SNR Equation and Minimum Detectable Signal
3.18 Power Flux Density, Saturation Flux Density and Dynamic Range
3.19 Full-Duplex Operation and Passive Intermodulation
3.20 Gain and Gain Variation
3.21 Pointing Error
3.22 Remaining Elements of Satellite System Architecture
3.23 Orbits and Orbital Considerations
3.24 Spacecraft Introduction
3.25 Spacecraft Budgets (Mass, Power, Thermal)
3.26 Orbital Mission Life and Launch Vehicle Considerations
3.27 Environment Management (Thermal, Radiation)
3.28 Spacecraft Structure (Acoustic/Dynamic)
3.29 Satellite Positioning (Station Keeping)
3.30 Satellite Positioning (Attitude Control)
3.31 Power Subsystem
3.32 Tracking, Telemetry, Command and Monitoring
References
Chapter 4: Space Environment and Materials
4.1 Introduction
4.2 The Space Environment of Antennas
4.3 Selection of Materials in Relation to Their Electromagnetic Properties
4.4 Space Materials and Manufacturing Processes
4.5 Characterization of Mechanical and Thermal Behaviour
4.6 Acknowledgements
References
Chapter 5: Mechanical and Thermal Design of Space Antennas
5.1 Introduction: The Mechanical–Thermal–Electrical Triangle
5.2 Design of Antenna Structures
5.3 Structural Modelling and Analysis
5.4 Thermal and Thermoelastic Analysis
5.5 Thermal Control Strategies
5.6 Acknowledgements
References
Chapter 6: Testing of Antennas for Space
6.1 Introduction
6.2 Testing as a Development and Verification Tool
6.3 Antenna Testing Facilities
6.4 Case Study: SMOS
References
Chapter 7: Historical Overview of the Development of Space Antennas
7.1 Introduction
7.2 The Early Days
7.3 Larger Reflectors with Complex Feeding Systems
7.4 Array Antennas
7.5 Conclusions
Acknowledgements
References
Chapter 8: Deployable Mesh Reflector Antennas for Space Applications: RF Characterizations
8.1 Introduction
8.2 History of Deployable Mesh Reflectors
8.3 Design Considerations Specific to Mesh Reflectors
8.4 The SMAP Mission – A Representative Case Study
8.5 Conclusion
Acknowledgments
References
Chapter 9: Microstrip Array Technologies for Space Applications
9.1 Introduction
9.2 Basics of Array Antennas
9.3 Passive Arrays
9.4 Active Arrays
9.5 Summary
Acknowledgements
References
Chapter 10: Printed Reflectarray Antennas for Space Applications
10.1 Introduction
10.2 Principle of Operation and Reflectarray Element Performance
10.3 Analysis and Design Techniques
10.4 Reflectarray Antennas for Telecommunication and Broadcasting Satellites
10.5 Recent and Future Developments for Space Applications
Acknowledgments
References
Chapter 11: Emerging Antenna Technologies for Space Applications
11.1 Introduction
11.2 On-Chip/In-Package Antennas for Emerging Millimeter-Wave Systems
11.3 Integrated Planar Waveguide Technologies
11.4 Microwave/mmW MEMS-Based Circuit Technologies for Antenna Applications
11.5 Emerging THz Antenna Systems and Integrated Structures
11.6 Case Study: Low-Cost/Complexity Antenna Technologies for Land-Mobile Satellite Communications
11.7 Conclusions
References
Chapter 12: Antennas for Satellite Communications
12.1 Introduction and Design Requirements
12.2 UHF Satellite Communications Antennas
12.3 L/S-band Mobile Satellite Communications Antennas
12.4 C-, Ku- and Ka-band FSS/BSS Antennas
12.5 Multibeam Broadband Satellite Communications Antennas
12.6 Antennas for Non-geostationary Constellations
Acknowledgments
References
Chapter 13: SAR Antennas
13.1 Introduction to Spaceborne SAR Systems
13.2 Challenges of Antenna Design for SAR
13.3 A Review of the Development of Antennas for Spaceborne SAR
13.4 Case Studies of Antennas for Spaceborne SAR
13.5 Ongoing Developments in SAR Antennas
Acknowledgments
References
Chapter 14: Antennas for Global Navigation Satellite System Receivers
14.1 Introduction
14.2 RF Requirements of GNSS Receiving Antenna
14.3 Design Challenges and Solutions for GNSS Antennas
14.4 Common and Novel GNSS Antennas
14.5 Spaceborne GNSS Antennas
14.6 Case Study:1 Dual-Band Microstrip Patch Antenna for Spacecraft Precise Orbit Determination Applications
14.7 Summary
References
Chapter 15: Antennas for Small Satellites
15.1 Introduction to Small Satellites
15.2 The Challenges of Designing Antennas for Small Satellites
15.3 Review of Antenna Development for Small Satellites
15.4 Case Studies
15.5 Conclusions
References
Chapter 16: Space Antennas for Radio Astronomy
16.1 Introduction
16.2 Overview of Radio Astronomy and the Role of Space Antennas
16.3 Space Antennas for Cosmic Microwave Background Studies
16.4 Space Radio Observatories for Submillimeter/Far-Infrared Astronomy
16.5 Low-Frequency Radio Astronomy
16.6 Space VLBI
16.7 Summary
Acknowledgments
References
Chapter 17: Antennas for Deep Space Applications
17.1 Introduction
17.2 Telecommunications Antennas
17.3 Case Study I – Mars Science Laboratory
17.4 Case Study II – Juno
Acknowledgments
References
Chapter 18: Space Antenna Challenges for Future Missions, Key Techniques and Technologies
18.1 Overview of Chapter Contents
18.2 General Introduction
18.3 General Evolution of Space Antenna Needs and Requirements
18.4 Develop Large-Aperture Antennas
18.5 Increase Telecommunication Satellite Throughput
18.6 Enable Sharing the Same Aperture for Multiband and Multipurpose Antennas
18.7 Increase the Competitiveness of Well-Established Antenna Products
18.8 Enable Single-Beam In-Flight Coverage/Polarization Reconfiguration
18.9 Enable Active Antennas at Affordable Cost
18.10 Develop Innovative Antennas for Future Earth Observation and Science Instruments
18.11 Evolve Towards Mass Production of Satellite and User Terminal Antennas
18.12 Technology Push for Enabling New Missions
18.13 Develop New Approaches for Satellite/Antenna Modelling and Testing
18.14 Conclusions
18.15 Acronyms
Acknowledgements
References
Index
This edition first published 2012
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Library of Congress Cataloging-in-Publication Data
Space antenna handbook/editors, William A. Imbriale, Steven Gao, Luigi Boccia.
p. cm.
Includes bibliographical references and index.
ISBN 978-1-119-99319-3 (cloth)
1. Antennas (Electronics) 2. Space vehicles–Radio antennas. 3. Artificial satellites in telecommunication. I. Imbriale, W. A. (William A.) II. Gao, Steven.
III. Boccia, Luigi.
TK7871.6.S63 2012
629.47'43—dc23
2011046036
A catalogue record for this book is available from the British Library.
ISBN: 978-1-119-99319-3
Preface
Due to the special environment of space and the launch vehicle dynamics to get there, spacecraft antenna requirements and design are quite different from those of terrestrial antennas. There are few books focusing on the special needs of space antennas. One such work is Spaceborne Antennas for Planetary Exploration (John Wiley & Sons, Inc., 2006), which covers the work from JPL/NASA only. Thus, there is a need for a comprehensive book which presents an up-to-date development of space antennas from leading engineers around the world.
This book addresses a broad range of topics on antennas for space applications. The aim of the book is two-fold. First, it introduces the reader to the fundamental methodologies of space antenna design, modeling, and analysis along with the state of the art and future technological developments. Each of the topics is specialized and contextualized to the space sector. Furthermore, case studies are provided in chapters to demonstrate how to design and implement antennas in practical scenarios. Next, the book presents a detailed review of antenna designs for some popular applications such as satellite communications, spaceborne synthetic aperture radar (SAR), global navigation satellite system (GNSS) receivers, radio astronomy, small satellites, and deep space applications.
Since the book covers such a wide range of topics, from basic principles to technologies and practical case studies, it is suitable for a wide range of audiences including beginners, students, researchers, and experienced engineers. The technical terms in the text assume that the reader is familiar with basic engineering and mathematical concepts as well as material typically found in a senior-level course in electromagnetics.
The book is divided into three sections: antenna development; space antenna technology; and space antennas for specific applications. The first section covers antenna basics and modeling as well as the specialized needs for space antennas with respect to the environment and materials including the mechanical and thermal considerations required for space antennas. There is also a chapter on system architecture depicting the critical role antennas play in the overall spacecraft design. The second section describes in detail technologies associated with mesh reflector antennas, array antennas, and printed reflectarray antennas. It provides a historical perspective as well as highlighting the emerging technologies. The third section covers the specific applications of satellite communications, spaceborne SAR, GNSS receivers, radio astronomy, small satellites, and deep space. The concluding chapter provides a broad outlook into the future development of space antennas. Thus the reader is provided with a comprehensive and logical path from the basics of space antenna development to the specific aspects related to individual applications.
William A. Imbriale, Steven (Shichang) Gao and Luigi BocciaFebruary 2012
Acknowledgments
The editors would like to express their thankfulness to all chapters' authors whose valuable contribution had brought the book project to reality. The support from Richard Davies, Anna Smart, Susan Barclay, and Tiina Ruonamaa from Wiley was also extremely important and it is most appreciated. The editors are also grateful to Abhishan Sharma, Neville Hankins and to all typesetters for their careful work.
William Imbriale would like to thank his wife Carol for her patience and understanding during the editing of the book. Steven Gao would like to express his deep appreciation to his wife, Jun, and his daughter, Karen, for their support. Luigi Boccia would like to manifest his gratitude and admiration to his wife, MariAntonietta, his son, Antonio Francesco, and his daughter, Caterina Dilia, for their encouragement and loving care. He also would like to honorably mention his parents for their guidance and strength.
William A. Imbriale, Steven (Shichang) Gao and Luigi BocciaFebruary 2012
Acronyms
ABCAbsorbing Boundary ConditionsAFRArray-Fed ReflectorAITAssembly, Integration and TestAIT-AIVAssembly, Integration and Test–Assembly, Integration and ValidationAMSU-A/BAdvanced Microwave Sounding Unit version A/BBFNBeam-Forming NetworkCALISTOCryogenic Aperture Large Infrared Space Telescope ObservatoryCEMComputational ElectromagneticsCFIECombined Fields Integral EquationCFRPCarbon Fibre Reinforced PlasticCFRSCarbon Fibre Reinforced SiliconCMBCosmic Microwave BackgroundCOBECosmic Background Explorer SatelliteCTECoefficient of Thermal ExpansionCWContinuous WaveDARSDigital Audio Radio ServiceDBDistribution BoardDBFDigital Beam FormingDGRDual-Gridded ReflectorDKDielectric ConstantDLGADescent Low Gain AntennaDMBDigital Multimedia BroadcastingDMRDifferential Microwave RadiometerDOADirection Of ArrivalDOSDenial Of ServiceDRADirect Radiating ArraysDTHDirect To HomeDUHFDescent Stage UHFDUTDevice Under TestDVBDigital Video BroadcastingEBGElectronic Band GapEFIEElectric Field Integral EquationEGNOSEuropean Geostationary Navigation Overlay ServiceEGSEElectrical Ground Support EquipmentEHPEqualisation Heat PipesEIRPEquivalent Isotropic Radiated PowerEMElectro MagneticEMCElectro Magnetic CompatibilityEOSEarth Observing SystemESDElectro Static DischargeFAFRFocal Array Fed ReflectorFCSFeeding Control SystemFDTDFinite Difference Time DomainFEMFinite Element MethodFFFar FieldFMMFast Multipole MethodFOVField Of ViewFSSFrequency-Selective SurfaceG/TGain over TemperatureGBASGround-based augmentation systemsGDGroup DelayGEOGeostationary Earth OrbitGFRPGlass Fibre Reinforced PlasticGLONASSGLObal NAvigation Satellite SystemGNSSGlobal Navigation Satellite SystemsGOGeometrical OpticsGPSGlobal Positioning SystemHFIHigh Frequency InstrumentHGAHigh Gain AntennaHMPAHybrid Matrix Power AmplificationHPHeat PipesHPAHigh-Power AmplifierHPBWHalf-Power BeamwidthHTCCHigh Temperature Cofired CeramicsHWHard WareI/FInter FaceICUInterface Control UnitIMInter ModulationINETInput NETworkInSARInterferometric Synthetic Aperture RadarITUInternational Telecommunication UnionLAASLocal Area Augmentation SystemLDALarge Deployable AntennaLEOLow Earth OrbitLFILow Frequency InstrumentLGALow Gain AntennaLHCPLeft Hand Circular PolarisationLHPLoop Heat PipesLNALow Noise AmplifierLOLocal OscillatorLTCCLow Temperature Cofired CeramicsMCCMMuti Chip Complex ModuleMCMMulti Chip ModuleMEMSmicro-electromechanical systemsMEOMedium Earth OrbitMFIEMagnetic Field Integral EquationMFPBMultiple feed per beamMGAMedium Gain AntennaMHSMicrowave Humidity SounderMLFMAMultilevel Fast Multipole MethodMLIMulti Layer InsulatorMLSMicrowave Limb SounderMMICMonolithic Microwave Integrated CircuitMOMMethod Of MomentsMPAMedium Power AmplifierMPAMulti-Port Amplifier (chapter 18)MSAMechanically Steered AntennaMSASMulti-functional Satellite Augmentation SystemMSGMeteosat Second GenerationMSSMobile Satellite SystemMSUMicrowave Sounding UnitMTGMeteosat Third GenerationMTIMultiple Target IndicatorNFNoise figureOBFNOptical Beam Forming NetworksOBPOn-Board digital ProcessorOMTOrthomode TransducerONETOutput NETworkOSROptical Solar ReflectorPAAPhase Array AntennaPAEPower-Added EfficiencyPCBPrinted Circuit BoardPECPerfectly Electrically ConductingPECPatch Excited Cup (chapter 15)PFDPower Flux DensityPIMPassive Inter ModulationPIMPPassive Inter Modulation ProductsPLGAParachute Cone Low Gain AntennaPMLPerfectly Matched LayersPNFPlanar Near FieldPOPhysical OpticsPRNPseudo Random NoisePSUPower Supply UnitPTDPhysical Theory of DiffractionPUHFParachute Cone UHFQHAQuadrifilar Helix AntennaQoSQuality of ServiceRFRadio FrequencyRFCBRadio Frequency and Control BoardRHCPRight Hand Circular PolarisationRHGARover High Gain AntennaRLGARover Low Gain AntennaRWGRao–Wilton–GlissionSAPShorted Annular PatchSARSynthetic Aperture RadarSBASSatellite-based augmentation systemsSBRShooting and Bouncing RayS/CSpace CraftSEUSingle-Event UpsetSELSingle-Event Latch-upSEBSingle-Event BurnoutSFBSingle Feed per BeamSFPBSingle Feed Per BeamSGHStandard Gain HornSiGesilicon–germaniumSIWsubstrate integrated waveguideSLISingle layer InsulatorSLLSide Lobe LevelSNFSpherical Near FieldSSPASolid State Power AmplifierSSSLSuspended Substrate Strip LineSWSoftwareT/RTransmit/ReceiveTHPTransport Heat PipesTLGATilted Low Gain AntennaTPSThermal Protection SystemTT&CTelemetry, Tracking and CommandTWTTravelling Wave TubesTWTATravelling Wave Tube AmplifierUHFUltra High FrequencyUMTSUniversal Mobile Telecommunication SystemUVUltra VioletUTDUniform Theory of DiffractionVHFVery High FrequencyVLBIVery Long Baseline InterferometryVSATVery Small-Aperture TerminalVSWRVoltage Standing Wave RatioWAASWide Area Augmentation SystemWMAPWilkinson Microwave Anisotropy ProbeXPCrosspolarXPDCross-Polar DiscriminationXPICrosspolar IsolationContributors
Eduardo Alonso, EADS CASA Espacio, Spain
David Álvarez, EADS CASA Espacio, Spain
Eric Amyotte, MDA, Canada
Silvia Arenas, EADS CASA Espacio, Spain
Luigi Boccia, University of Calabria, Italy
Olav Breinbjerg, Technical University of Denmark, Denmark
Paula R. Brown, Jet Propulsion Laboratory, California Institute of Technology, USA
Miguel Bustamante, EADS CASA Espacio, Spain
Jennifer Campuzano, EADS CASA Espacio, Spain
Pasquale Capece, Thales Alenia Space Italia, Rome, Italy
Francisco Casares, EADS CASA Espacio, Spain
Chi-Chih Chen, The Ohio State University, USA
Jacqueline C. Chen, Jet Propulsion Laboratory, California Institute of Technology, USA
Keith Clark, Surrey Satellite Technology Ltd, UK
Luis E. Cuesta, EADS CASA Espacio, Spain
Tie Jun Cui, School of Information Science and Engineering, Southeast University, Nanjing, People's Republic of China
L. Salghetti Drioli, European Space Research and Technology Centre (ESTEC) – European Space Agency (ESA), The Netherlands
Jose A. Encinar, Technical University of Madrid, Spain
Mohammad Fakharzadeh, Center for Intelligent Antenna and Radio Systems (CIARS), Department of Electrical and Computer Engineering, University of Waterloo, Canada
Paolo Focardi, Jet Propulsion Laboratory, California Institute of Technology, USA
Luis F. de la Fuente, EADS CASA Espacio, Spain
Steven (Shichang) Gao, Surrey Space Centre, University of Surrey, UK
Quiterio Garcia, EADS CASA Espacio, Spain
Vicente García, EADS CASA Espacio, Spain
Paul F. Goldsmith, Jet Propulsion Laboratory, California Institute of Technology, USA
Richard E. Hodges, Jet Propulsion Laboratory, California Institute of Technology, USA
William A. Imbriale, Jet Propulsion Laboratory, California Institute of Technology, USA
Jerzy Lemanczyk, European Space Research and Technology Centre (ESTEC) – European Space Agency (ESA), The Netherlands
Cyril Mangenot, European Space Research and Technology Centre (ESTEC) – European Space Agency (ESA), The Netherlands
Moazam Maqsood, Surrey Space Centre, University of Surrey, UK
Luís Martins Camelo, MDA, Canada
Kevin Maynard, Surrey Satellite Technology Ltd, UK
Fernando Monjas, EADS CASA Espacio, Spain
Antonio Montesano, EADS CASA Espacio, Spain
Margarita Naranjo, EADS CASA Espacio, Spain
Xue Wei Ping, School of Information Science and Engineering, Southeast University, Nanjing, People's Republic of China
Yahya Rahmat-Samii, University of California at Los Angeles (UCLA), USA
Heiko Ritter, European Space Research and Technology Centre (ESTEC) – European Space Agency (ESA), The Netherlands
Antoine G. Roederer, Delft University of Technology – IRCTR, The Netherlands
Safieddin Safavi-Naeini, Center for Intelligent Antenna and Radio Systems (CIARS), Department of Electrical and Computer Engineering, University of Waterloo, Canada
J. Santiago-Prowald, European Space Research and Technology Centre (ESTEC) – European Space Agency (ESA), The Netherlands
José Luis Serrano, EADS CASA Espacio, Spain
Hans Juergen Steiner, Astrium GmbH, Germany
Michael A. Thorburn, Space Systems/Loral, USA
Andrea Torre, Thales Alenia Space Italia, Rome, Italy
Ana Trastoy, EADS CASA Espacio, Spain
Jiadong Xu, Northwestern Polytechnical University, Xi'an, People's Republic of China
Wen Ming Yu, School of Information Science and Engineering, Southeast University, Nanjing, People's Republic of China
Jan Zackrisson, RUAG Aerospace, Sweden
Jian Feng Zhang, School of Information Science and Engineering, Southeast University, Nanjing, People's Republic of China
Xiao Yang Zhou, School of Information Science and Engineering, Southeast University, Nanjing, People's Republic of China
Chapter 1
Antenna Basics
Luigi Boccia1 and Olav Breinbjerg2
1 University of Calabria Italy
2 Technical University of Denmark Denmark
1.1 Introduction
Antennas radiate and receive electromagnetic waves by converting guided waves supported by a guiding structure into radiating waves propagating in free space and vice versa. This function has to be accomplished by fulfilling specific requirements which affect the antenna design in different ways. In general, a number of antennas are installed in a satellite and their requirements vary depending on the application and on the mission. They can be roughly classified into three types: antennas for telemetry, tracking and control (TT&C), high-capacity antennas, and antennas for space instruments or for other specific applications. Several examples of the latter class are reported in the third section of this book.
This chapter provides an overview of the basic antenna parameters and antenna types, and it presents other basic concepts related to the space environment which will introduce the reader to the development of antennas for space applications. Although many basic definitions are presented, the chapter is not intended to provide a comprehensive background to antennas. For this reason, the reader should refer to the extensive literature available on the subject, some of which we list as references.
The chapter is organized as follows. In the first part, the main antenna parameters will be given in accordance with the IEEE Standard Definition of Terms for Antennas [1] and with the IEEE Standard Test Procedures for Antennas [2] which will be adopted throughout the book. In the second part of the chapter, basic antenna types commonly employed in spaceborne applications will be presented. In the third part of the chapter, antenna development will be related to the space environment by introducing fundamental concepts such as multipaction and outgassing.
1.2 Antenna Performance Parameters
Numerous parameters exist for characterizing the performance of antennas and in the following subsections the most significant of these are reviewed. The relevance of these antenna parameters will be seen in Chapter 3 where they are combined into the Friis transmission formula which links the available power of the transmitter to the received power of the receiver in a radio communication system.
1.2.1 Reflection Coefficient and Voltage Standing Wave Ratio
For a multi-port antenna as shown in Figure 1.1, the scattering parameters, , relate the equivalent voltage of the outgoing wave at port i, , to the equivalent voltage of the incoming wave at port j, , that is, [3]. The reflection coefficient at the i′ port is
(1.1)
Figure 1.1 Arbitrary multi-port antenna.
For a single-port antenna, or for a multi-port antenna with all other ports matched (thus for ), the reflection coefficient equals the scattering coefficient and, if the antenna is passive, the magnitude of the reflection coefficient is then less than or equal to 1. Note that the reflection coefficient is defined in terms of equivalent voltage which requires the existence of a well-defined mode in the port of the antenna. Furthermore, the voltage is defined at a specific position – the reference plane – in the antenna port, and the reflection coefficient is thus referenced to that position.
The voltage standing wave ratio (VSWR) is the ratio of the maximum and minimum voltages on the transmission line connected to the antenna, and it follows directly from the reflection coefficient Γ as
(1.2)
The scattering parameters are the main representation of antenna behavior with respect to the circuit to which the antenna is connected. This is particularly true for passive antennas while more complex parameters are required for active antennas.
1.2.2 Antenna Impedance
The input impedance of an antenna ZA is the ratio of the voltage V and current I at the port of the antenna when the antenna is isolated in free space; that is, without the presence of other antennas or scattering structures. Thus, this is sometimes referred to as the isolated input impedance. Since voltage and current are not practical quantities at radio frequencies (RFs), the input impedance is usually determined from the reflection coefficient Γ and the characteristic impedance ZC of the transmission line connected to the port of the antenna; that is,
(1.3)
For a linear multi-port antenna the voltage at the ith port can be related to the currents at all ports as
(1.4)
where Zii is the self-impedance of the ith port and Zij is the mutual impedance between the ith and jth ports. The input impedance of the ith port is then
(1.5)
which is seen to depend on the excitations (currents) of the other ports and therefore differs from the isolated input impedance. Thus, the input impedance of a port in a multi-port system is sometimes referred to as the active input impedance. Even the self-impedance, which is seen from above to equal the active input impedance when all other ports are open-circuited (zero current), is generally different from the isolated input impedance since the open-circuited ports may still act as scattering structures. For an antenna array, see Section 1.4, with identical antenna elements and thus identical isolated input impedances, the active input impedances may differ due to the mutual coupling. Furthermore, if the excitation of the ports is changed, for example, to scan the main beam in a phased array, the active input impedance of an individual port can vary drastically and become very poorly matched to the transmission line characteristic impedance.
If the scattering parameters are arranged in a scattering matrix and the self- and mutual impedances in an impedance matrix , the relationship between these, for a multi-port antenna with the common characteristic impedance of the transmission lines on the ports ZC, can be expressed as ( is the unit matrix)
(1.6)
(1.7)
1.2.3 Radiation Pattern and Coverage
The radiation pattern is a ‘mathematical function or graphical representation of the radiation properties of the antenna as a function of space coordinates’ [1]. In the most common case, antenna radiation patterns are determined in the far-field region [4]. This region is ‘where the angular field distribution is essentially independent of the distance from a specified point in the antenna region’ [1]. Typically, the far-field region is identified by those distances greater than , D being the maximum overall dimension of the antenna and λ the free-space wavelength. In the far-field region of any antenna the radiated field takes a particularly simple form. For time-harmonic fields, and using phasor notation with the suppressed time factor exp(jωt) with ω the angular frequency and t time, the far-field can be expressed as
(1.8)
Thus, the radiated electric field E at the position of the position vector r can be expressed as the product of a pattern function P that depends only on the direction of the position vector and the term that depends only on the length r of the position vector. Furthermore, the pattern function P has only transverse components w.r.t. ; that is, . The position vector r is referenced to the origin of the antenna coordinate system. Note that the pattern function P defines all radiation properties that are particular for the antenna.
The parameter represented by the radiation pattern is typically a normalized magnitude of the pattern function or one of its components, the directivity or partial directivity, or the gain or partial gain – but it may be the phase of a polarization-phase vector component, the axial ratio, or the tilt angle as well; these parameters are reviewed in the following subsections. The graphical representation may be two or three dimensional with the transmission/reception direction typically expressed by the polar and azimuthal coordinates of the antenna coordinate system for a full-sphere pattern or the projected coordinates and for a hemispherical pattern.
An antenna can be defined as directional when it can ‘radiate or receive electromagnetic waves more effectively in some directions than in others’ [1]. In order to discriminate between directional and non-directional antennas, the half-wave dipole is normally taken as reference while the antenna directivity is generally compared to the ideal isotropic radiator [5]. Normally, the portion of the radiation pattern of a directive antenna where the radiation intensity is maximum is defined as the main lobe. Side, minor, back and grating lobes can also be identified. The first three types are related to the direction and to the intensity of radiation while the last one can be present only in an antenna array environment.
1.2.3.1 Half-Power Beamwidth
The half-power beamwidth (HPBW) is identified in a cut of a radiation pattern as the angle between the two directions in which the radiation intensity is half of its maximum value (see Figure 1.2a). HPBW characterizes the behavior of the antenna in its main lobe but it does not take into account the amount of power radiated out of the main beam. For this reason, parameters are normally used to more accurately evaluate the antenna's directional performance.
Figure 1.2 Radiation pattern: (a) half-power beam width (HPBW); (b) footprint example (1 dBi per circle).
1.2.3.2 Coverage
The coverage C of an antenna is the range of transmission/reception directions over which one or more antenna parameters meet certain specifications. In most cases, the coverage C refers to the directivity or gain, or the co-polarized partial directivity or gain, and is thus the range over which the relevant parameter is larger than a specified minimum value; this could be 3 dB below the maximum value. When the antenna points towards the Earth, it is convenient to express the coverage in terms of Earth footprint, which is the projection of the satellite antenna pattern onto the Earth's surface (see Figure 1.2b). The footprint is that portion of the Earth's surface where the antenna points with a given gain. For some applications the footprint corresponds simply to a circle in a coordinate system, calling for a pencil-beam antenna, while for other applications the coverage is the projected shape of a country, calling for a shaped-beam antenna. Clearly, both the footprint and the coverage C can be determined from the radiation pattern and thus the pattern function P.
1.2.4 Polarization
The polarization of an antenna in a given direction is the polarization of the plane wave transmitted (or received) by the antenna in the far field. Polarization is classified as linear when the electric field in a given direction is always directed along a line. Pure linear polarization is an ideal case as all antennas generate both a co-polarization field, that is, the polarization the antenna is intended to radiate, and a cross-polarization field, that is, in the case of linearly polarized fields, the component of the electric field orthogonal to the desired polarization. For this reason, the electric field vector normally describes an ellipse and the polarization is classified as elliptical. If the axes of the ellipse are equal, then the polarization is referred to as circular. It is worth noticing that the polarization of an antenna is normally defined by taking into account the radiating wave. Satellite–Earth communication links typically adopt circularly polarized (CP) signals. Indeed, the use of linear polarization would lead to high polarization mismatches arising from alignment issues or from the Faraday rotation effect of the ionosphere [6–8].
Antenna polarization can be described in terms of the polarization-phase vector, , that is, a unit vector that represents the polarization as well as the phase of the radiated field of an antenna. The simple distance dependence of the phase due to the term is not included in the polarization-phase vector, and from the pattern function P the polarization-phase vector is thus defined as
(1.9)
The pattern function P can be decomposed w.r.t. two orthogonal polarization unit vectors referred to as the co- and cross-polarization unit vectors; that is,
(1.10)
where the polarization unit vectors, and , are typically the linearly polarized and unit vectors of the standard spherical coordinate system, the linearly polarized unit vectors according to Ludwig's third definition [9], or the circularly polarized unit vectors defined from either of these linearly polarized unit vectors. Obviously, the polarization-phase vector can be decomposed in the same manner; that is, .
The polarization-phase vector can also be represented in terms of the polarization ellipse with its axial ratio, tilt angle, and sense of rotation. In each direction of observation , a local right-hand orthogonal, rectangular xyz coordinate system is defined with the unit vectors and transverse to, and the unit vector parallel to, the direction of observation . The polarization-phase vector is now decomposed as . The axial ratio (AR) can then be expressed as
(1.11)
while the tilt angle (TA) w.r.t. the direction is
(1.12)
and the sense of rotation (SOR) is
(1.13)
Alternatively, the AR can be determined from the magnitude of the right- and left-hand circularly polarized components of the electric field, and respectively. The expression for AR can thus be cast in the form
(1.14)
Differences between the polarization of the incident wave and the receiving antenna are normally referred to as polarization mismatch. In general, they can cause strong link losses which can be taken into account by using different figures of merit. One possibility is to use co-polarization and cross-polarization field patterns. Alternatively, the polarization efficiency ep could be defined as [1]
(1.15)
where and are the polarization vectors of the incident wave and of the receiving antenna respectively. If the polarization of the incident wave and that of the receiving antenna are the same, the inner product defined in Equation (1.15) is equal to 1.
1.2.5 Directivity
The directivity D of an antenna is the ratio of the far-field radiation intensity in a given direction to the average radiation intensity over the radiation sphere. The radiation intensity in a given direction, U, is the radiated power per solid angle and thus with being the free-space intrinsic impedance and the power radiated in a given direction. Thus the directivity D in a given direction can be expressed as
(1.16)
Prad is the total radiated power, which can be calculated by integrating the power radiated in a given direction over the entire radiating sphere. When the direction is not specified, the maximum directivity is usually taken.
Antenna directivity can be discriminated in terms of polarization by defining partial directivities. The partial directivities, and , in a given direction for the co- and cross-polarized components can then be expressed as
(1.17)
1.2.6 Gain and Realized Gain
The gain G of an antenna in a given direction is the ratio of the radiation intensity to the average radiation intensity over the radiation sphere if all accepted power is radiated isotropically. In mathematical form, this can be written as
(1.18)
where is the power accepted in input by the antenna. The antenna gain can be related to the directivity by taking into account the antenna radiation efficiency, ecd which can be defined as the ratio of the radiated power to the accepted power. Using the definitions of directivity and gain, it can thus be expressed as
(1.19)
For a lossless antenna where all accepted power is also radiated, and , the gain G equals the directivity D. However, for most practical antennas the loss is non-negligible, and ecd < 1, and it is important to distinguish between gain and directivity. When the direction of radiation is not stated, the direction of maximum radiation is normally presumed. In analogy to partial directivity, partial gain can be defined to discriminate the antenna gain w.r.t. the polarization of the radiated fields.
According to IEEE standards, the definition of antenna gain does not include reflection losses and polarization mismatches. The realized gain of an antenna is the ratio of the radiation intensity to the average radiation intensity over the radiation sphere if all incident power is radiated; it thus includes the effect of the impedance mismatch at the antenna terminals and can be expressed as
(1.20)
where is the overall antenna efficiency. The relevance of realized gain is clear from the Friis transmission formula that comprises the product of the gain and the impedance mismatch factor for both the transmitter and the receiver (see Chapter 3 for further details). However, since the loss and the mismatch are two completely different mechanisms, it is still important to use gain and reflection coefficients separately and to distinguish between gain and realized gain.
1.2.7 Equivalent Isotropically Radiated Power
Equivalent isotropically radiated power (EIRP) in a given direction is defined as ‘the gain of a transmitting antenna multiplied by the net power accepted by the antenna from the connected transmitter’ [1]. EIRP can be written as
(1.21)
where is the net power accepted by the antenna from the transmitter and is the gain of the transmitting antenna. In order to include transmitter output power, , and interconnection losses between transmitter and antenna, , Equation (1.21) can be changed to
(1.22)
The EIRP definition is important because it allows calculation of absolute power and field strength values and it makes possible comparisons between different emitters regardless of the type of configuration.
1.2.8 Effective Area
The effective area of a receiving antenna is the ratio of the available power at the terminals of the antenna to the power density of a polarization-matched incident plane wave. The effective area can be measured itself, but in most situations it is found from its reciprocity-based relation to the gain G as
(1.23)
1.2.9 Phase Center
In IEEE standards, the phase center is defined as ‘the location of a point associated with an antenna such that, if it is taken as the center of a sphere whose radius extends into the far-field, the phase of a given field component over the surface of the radiation sphere is essentially constant’. As the size of real antennas is not null, the phase center depends on the observation direction. In general, the phase center is calculated experimentally by measuring the phase pattern at different cut planes [10].
For some applications, knowing the location of the phase center is very important. For example, in a reflector antenna the phase center of the feed needs to be located at the focal point of the paraboloid. Another example where the phase center location is critical is the global navigation satellite system (GNSS) [11]. Indeed, one of the parameters which defines the accuracy of high-precision GNSSs is the invariance of the phase center which should be highly stable in order to minimize positioning errors.
1.2.10 Bandwidth
The bandwidth (BW) of an antenna is the range of frequencies over which one or more antenna parameters meet certain specifications. In most cases, BW refers to the reflection coefficient and is thus the range over which is less than a specified maximum allowable value, , with the tacit assumption that other parameters remain within their specifications too. BW depends strongly on the value of and it is important that this be stated explicitly. With and denoting the upper and lower limits of the frequency range, respectively, the fractional bandwidth (FBW) is
(1.24)
with the condition that the center frequency coincides with the frequency of operation.
When multiple antenna parameters have to be considered, BW is given by the minimum range of frequencies over which specifications are satisfied. Typically, link budget calculations pose stringent requirements on the antenna gain and coverage, on the polarization efficiency, and on the reflection coefficient over the system bandwidth.
1.2.11 Antenna Noise Temperature
The antenna noise temperature of a receiving antenna is the temperature (in kelvin) that, through the formula , gives the noise power at the terminals of the antenna; K is Boltzmann's constant and BW the bandwidth [12]. In terms of the background noise temperature over the radiation sphere of the antenna, expressing the noise from the sky, the satellite structure and the Earth, and the antenna physical temperature , the antenna noise temperature in the radio frequency range can be expressed as
(1.25)
While all previous antenna parameters relate only to the antenna itself, and any influence of the surroundings on these is considered parasitical, the antenna noise temperature relates equally to the antenna and its surroundings and it is particular also for the latter. Equation (1.25) shows that the antenna noise temperature can be calculated from the directivity D, the radiation efficiency and the background temperature .
1.3 Basic Antenna Elements
Depending on the electrical and physical requirements, spacecraft antenna design can be based on different classes of radiators. In this section a basic overview of some of the most common antenna types is provided and includes references to relevant chapters of this book.
1.3.1 Wire Antennas
The dipole antenna is the most representative type of wire radiator. In the most common case, it consists of a linear wire with a feed point at the center as shown in Figure 1.3a. The radiation properties depend on the current distribution along its main axis, this current being mainly related to the dipole length. Some radiation occurs in all directions with the exception of the dipole axis itself. Due to the rotational symmetry of the dipole around its main axis (z-axis in Figure 1.3a), the radiation pattern is symmetrical over the azimuthal coordinate. In Figure 1.3b, c the radiation pattern of an ideal half-wavelength dipole is shown. Its maximum directivity is 2.15 dB and its HPBW is equal to 78̊. The behavior of a dipole antenna changes when the dipole interacts with the spacecraft. For this reason, the ideal pattern shown on Figure 1.3b, c is valid only for isolated dipoles and it does not take into account the interactions with the spacecraft as shown in the examples of Chapter 2.
Figure 1.3 Dipole and monopole antennas: (a) dipole antenna geometry; (b) 3D normalized amplitude radiation pattern (dB) of a dipole antenna;(c) elevation plane normalized amplitude pattern (dB); (d) monopole antenna geometry.
The monopole antenna is formed by replacing one-half of a dipole with an infinite ground plane perpendicular to the dipole axis as shown in Figure 1.3d. Using image theory [13], the fields above the ground plane can be found by substituting the ground plane with image currents forming the missing half of the dipole. The radiating behaviour of these two wire antennas is similar, but the monopole radiation below the ground plane is ideally null. For this reason, the directivity of a monopole antenna of length l is twice that of the equivalent dipole antenna of double length, 2l.
Since the early spacecraft missions (see Chapter 7), wire antennas have been widely used in space exploration. Due to their omnidirectional radiation properties, dipole and monopole antennas are generally used to send or receive telemetry and command signals during launch, when the spacecraft attitude is out of control or in other circumstances when the high-directivity antennas cannot be employed.
1.3.2 Horn Antennas
Another important type of antenna which has found wide application in space missions is the horn antenna. In general, horn antennas are employed in satellite missions to produce wide-beam coverage such as Earth coverage or to feed reflector antennas. Horn antennas are designed to provide a smooth transition between the feeding waveguide and a wider aperture which serves to focus the main lobe. Horn antennas belong to the category of aperture antennas, their radiation characteristics being determined by the field distribution across the aperture. The most common type of horn antenna is the pyramidal horn shown in Figure 1.4a. The horn provides a transition of length d between a feeding section of rectangular waveguide of height a and width b and a radiating aperture of height A and width B. In the most common case, the waveguide is excited by a single TE10 mode. In this case the dominant horn polarization would be linear with the main electric field component directed along the z-axis. Horn polarization can also be circular or dual linear depending on the modes excited in the waveguide section. Knowing the waveguide dimensions and the gain specifications, the pyramidal horn geometry can be defined through simple analytical formulas derived from the hypothesis of an aperture terminating in an infinite flange [14]. In general, the finiteness of the terminating flange can lead to inaccuracies which can be overcome through full-wave analysis. As a general rule, for a given horn length, d, as the aperture width, B, increases, the gain increases until it reaches a maximum after which it starts to decrease.
Figure 1.4 Pyramidal horn antenna: (a) geometry; (b) electric field distribution on the antenna aperture; (c) typical 3D normalized amplitude radiation pattern (dB) of a horn antenna; (d) typical gain pattern on the E- and H-plane of a vertically polarized pyramidal horn.
Figure 1.4 shows the field patterns of a pyramidal horn simulated through full-wave software [15]. Results were obtained from a rectangular horn antenna with A = 120 mm, B = 90 mm and d = 120 mm at a frequency of 10 GHz. The horn is fed through a standard section of WR102 waveguide excited in its fundamental mode. As can be observed in Figure 1.4b, the electric field vector on the antenna aperture is polarized along the y-axis. The y–z plane is thus referred to as the E-plane as it contains the E-field vector and the maximum direction of maximum radiation. Similarly, the x–z plane is referred to as the H-plane. The dominant polarization is linear (vertical) polarization. For the proposed example, the gain is around 19 dB at10 GHz while the HPBW is equal to 19̊ and 20̊ in the H- and E-plane, respectively. The asymmetry of the beam amplitude in the two main planes is a common problem of pyramidal horn antennas. Another limitation is related to the diffraction arising from the horn flanges and, in particular, from those that are perpendicular to the electric field vector. In general, such diffraction produces back radiation and sidelobes which are indeed more evident in the E-plane.
Another important type of horn antenna is the conical horn whose geometry is shown in Figure 1.5. The conical horn aperture is circular and, in the most typical configuration, is fed by a section of circular waveguide which is typically excited by a TE11 mode. The behavior of a conical horn is similar to that of a pyramidal horn. The directivity can be expressed as [16]
Figure 1.5 Conical horn antenna: (a) geometry; (b) electric field distribution of a smooth-walled conical horn aperture.
(1.26)
where a is the aperture radius and is the aperture efficiency. Although the conical horn is geometrically symmetric, its pattern is asymmetric and it suffers from similar limitations to that of pyramidal horns. In particular, the conical horn can present high cross-polar levels, which can be easily explained by looking at the transverse electric field distribution on the antenna aperture as shown in Figure 1.5b for vertical polarization. As can be observed, components of the electric field are also present along the y-axis. In the far field, such components would give rise to an electric field horizontally polarized with peaks of intensity at ±45°. Poor polarization performance can be a severe limitation both in radio astronomy applications and in satellite communication systems as reported in Section 12.4.
The lack of symmetry in pyramidal and conical horn antennas can cause severe limitations in terms of efficiency, increasing losses when global coverage is required and generating spillover losses when horns are used as reflector feeds. A common way to improve the field distribution across the horn aperture is to employ grooved walls [17]. Corrugations perpendicular to the walls are designed to provide a capacitive reactance which inhibits surface wave propagation thus avoiding spurious diffraction from the edges. For pyramidal horns, the corrugations are usually placed only on the E-plane walls as edge currents on the H-plane walls are negligible. However, most corrugated horns are conical horns, this type of antenna being easier to fabricate. An example of a conical corrugated horn is shown in Figure 1.6a. As the groove response is polarization independent, the fundamental mode of a corrugated horn is the hybrid mode HE11 that can be associated to a combination of a TE11 and TM11 modes in a smooth circular waveguide. In general, the two modes are optimally phased to yield a highly symmetric field distribution across the aperture which, in turn, generates a symmetric radiation pattern ideally with very low sidelobes [18]. The performance of this type of radiator can be further optimized by using a Gaussian profiled conical horn [19]. In this case, the radius increases longitudinally following the expansion law of a Gaussian beam. As a result, the field distribution at the horn mouth is almost perfectly Gaussian, thus generating a far-field pattern ideally without sidelobes.
Figure 1.6 Dual-hybrid-mode feed horn: (a) geometry; (b) normalized radiation patterns [22].
Another technique which can be employed to improve the horn pattern is to use a multimode approach. In this case, higher order modes can be deliberately excited with a specific phase and amplitude relationship, improving the horn radiation performance [20]. When even more demanding performance is required, multi-hybrid-mode corrugated horn antennas can be designed as shown in [21] and in [22] for Deep Space Network antennas.
1.3.3 Reflectors
Reflector antennas are by far the most common antenna element for applications requiring high gain and directivity. This class of antennas has been widely employed in space missions since the early days of space exploration (see Section 7.2). Over the years, their concepts evolved both mechanically and functionally to meet technical requirements of increasing complexity. In this section only a basic review of this type of antenna is provided, the interested reader being directed to following chapters and to the referenced literature [16, 22–25] for further study.
1.3.3.1 Main Reflector Parameters
Although reflector antennas can be made in different types, shapes and configurations, they all essentially consist of a passive reflecting surface illuminated by a smaller primary feed. Reflector antenna performance is influenced by several parameters, as follows.
Spillover and Aperture Illumination Efficiency
Reflector efficiency is highly influenced by the feed radiation characteristics. In particular, an ideal reflector should be uniformly illuminated and all power should be focused on the reflecting surface. The portion of the feed power that does not reach the reflector is referred to as spillover loss while the ability to uniformly feed the parabola is referred to as illumination efficiency. Since primary feeds have a tapered radiation pattern, a compromise between spillover losses and illumination efficiency must be considered to maximize the aperture gain.
Aperture Blockage
Feed and mechanical support structures located in front of the aperture, partially block field radiation in the far field. This phenomenon is referred to as aperture blockage and its main effect is to reduce the on-axis gain and to increase the sidelobe amplitude level. The reduction of efficiency due to aperture blockage varies depending on the feed configuration and aperture size.
Axial and Lateral Defocusing
Axial and lateral defocusing are the errors generated by displaced feed positions along the reflector axis and orthogonally to the reflector axis respectively. Axial displacements generate a broader beamwidth while lateral defocusing causes beam squints [26, 27].
Reflector Surface Deviation
Deviations from the curvature surface cause a distortion of the reflector antenna radiation pattern [28]. The effect of surface deviation can be significantly high in deployable reflector antennas as outlined in Chapter 5.
Feed
Feed selection and design have a major role in the correct and efficient operation of a reflector system. In general, the feed type depends on the system requirements in terms of frequency band, radiation characteristics and efficiency. Although simpler antenna types can be used, the best performance is usually achieved through horn antennas with Gaussian beam characteristics [29].
1.3.3.2 Basic Reflector Types
Some of the most common reflector systems are shown in Figure 1.7. The simplest form of reflector antenna is the parabolic reflector shown in Figure 1.7a. This configuration benefits from the geometrical properties of the parabola since spherical waves radiated by a source placed at the focal point are transformed into plane waves directed along the aperture rotation axis. This type of reflector generates a pencil beam whose characteristics are mainly controlled by the aperture diameter, D, the focal length, F, the reflecting surface curvature, F/D, and the pattern and size of the feed antenna. The electrical performance of this elementary reflector system is limited by the effect of aperture blockage [30]. As a possible solution to this problem, configurations employing an offset feed and a sectioned parabolic reflector [31] can be considered as illustrated in Figure 1.7b. In this case, the blockage effect of the feed is negligible and the direction of maximum radiation can be controlled by optimally shaping the reflector surface. The absence of feed blockage can be particularly important for those applications where multiple-feed systems are needed. Compared to the axisymmetric configuration, the main drawbacks of this type of reflector system are related to the large cross-polar fields for linear polarization [32]. Depolarization effects are due to reflector curvature and they can be reduced by selecting a relatively large F/D ratio [33]. However, when it is not possible to increase the reflector curvature, polarization rotation can be cancelled by using a polarization grid [34] or by optimally designing the primary feed [35]. When offset reflector antennas are illuminated by a circularly polarized primary feed, high cross-polar fields generate angular displacements of the main beam [32, 36]. Beam squinting can be counteracted by using reflectors with large curvatures or by employing compensation techniques at feed level [37, 38].
Figure 1.7 Reflector antenna configurations: (a) on-focus parabolic reflector; (b) off-axis reflector; (c) Cassegrain reflector; (d) Gregorian reflector.
For larger apertures, a more compact feed arrangement can be realized by employing smaller subreflectors. Classical axisymmetric geometries for the Cassegrain and Gregorian reflector types are shown in Figure 1.7c and d respectively. In both systems, the primary feed is located on the rear of the main paraboloidal reflector. In the Cassegrain arrangement the subreflector is a section of a hyperboloid located within the focus of the main reflector, while in the Gregorian configuration the subreflector is an ellipsoid located outside the focus of the main reflector. Both systems have similar electrical features but Cassegrain designs are more commonly used in satellite applications.
Shaped Reflectors
Dual reflectors have higher efficiency and reduced sidelobes with respect to the on-focus fed parabolic reflector [39]. In particular, it has been demonstrated [40] that aperture efficiency can be improved by controlling the shape of the main and sub-reflector surfaces to improve aperture energy distribution. Varying the shape of the reflector surface has a direct impact on the illumination function which can be controlled in both amplitude and phase, thus reducing both spillover losses and illumination efficiency.
Cross-polarization Reduction
Offset dual-reflector antennas can be designed to have very limited cross-polar components. In particular, the optogeometrical condition for eliminating cross-polarization [41] depends on whether the subreflector surface is concave or convex, on the eccentricity and on the angles of the axes of the main reflector surface and subreflector surface, and on the axis of the primary radiation.
Contoured- or Multiple-Beam Reflectors
Contoured- or multiple-beam configurations can be obtained through specific offset dual-reflector arrangements. In the most conventional approach, contoured-beam patterns can be achieved using a multi-feed dual-reflector system [42]. In this case, the desired coverage contour is achieved by superposing overlapping spots generated by different feeds whose fields are then combined through a beam-forming network. This approach is also used when multiple beams have to be generated from a single antenna. In this latter case, individual beam-forming networks for each beam have to be implemented. Digital beam forming can also be employed for implementing beam scanning capabilities [43].
Alternatively, it is also possible to generate contoured beams by using a single feed and by shaping the reflector surface [44]. Shaped reflectors are the most common design approach for single-beam applications in satellite applications due to lower weight and lower spillover losses w.r.t. a single-feed design [45].
Deployable Reflector Antennas
Reflector antennas have evolved significantly over the years, boosted by space-related research. In particular, significant improvements have been achieved in terms of aperture size through the employment of deployable structures which can be larger than 20 m, as described in Chapter 8. Space-related research continues to lead the technological development of reflector antennas as is evident from the list of future configurations reported in Section 18.4.
1.3.4 Helical Antennas
Helical antennas are widely used in satellite communication systems mainly because of their circular polarization and wide-band features. In its simplest form, a helical antenna consists of a conducting wire wound in the form of a helix as shown in Figure 1.8a. Generally, this type of antenna is fed through a coaxial transition and includes a ground plane. The radiation characteristics of this antenna and its input impedance depend on the helix diameter, d, on the wire diameter, t, on the pitch, p, and on the number of turns, N.
Figure 1.8 Helical antenna: (a) monofilar helical antenna geometry; (b) typical radiation pattern of a helical antenna operating in normal mode; (c) typical co-polar gain pattern of a helical antenna operating in axial mode; (d) short-circuited quadrifilar helical antenna (QHA).
The helix antenna has different modes of radiation. In normal mode (or broadside mode) the helix length is short compared to the wavelength and its behavior is similar to a short dipole [16]. This type of antenna radiates in directions normal to its axis (Figure 1.8b) and can be designed to operate in linear polarization or circular polarization. In this configuration, the helix behavior is highly sensitive to the antenna dimensions.
In axial mode (or end-fire mode) the helical antenna has a main lobe directed along its axis, as shown in Figure 1.8c. This operating mode is achieved when both the helix diameter, d, and the pitch, p, are large fractions of the wavelength [46]. Helical antennas operating in axial mode are circularly polarized and they are normally installed on a ground plane. However, when the diameter of the ground plane of a conventional helical antenna is less than the diameter of the helix, the helix radiates with its main beam in the backfire direction when the pitch angle is small [47].
The helix radiation characteristics can be controlled by changing the geometrical parameters of the antenna or by varying the number of wires [48–50]. For example, quadrifilar helical antennas (QHAs) (Figure 1.8d) are widely used for TT&C [51]. QHAs consist of four helical wires equally spaced and circumferentially located 90̊ apart from each other and sequentially fed with 90° of phase shift.
1.3.5 Printed Antennas
In the past few decades, microstrip antennas [52] have been one of the most commonly used antennas for space applications and, in all likelihood, will play a key role also in the coming years. In its most classical configuration, a microstrip radiator consists of a metallic patch element printed on a thin insulating dielectric layer placed above a ground plane. Figure 1.9 shows the two most popular microstrip antenna configurations: the rectangular patch antenna and the circular patch antenna. Since their first introduction [53, 54], printed antennas have become a very popular research topic gaining the attention of both the industrial and the academic communities. Thousands of papers have been published on this subject, introducing many improvements and contributing to a rapid evolution of the early concept and widespread diffusion in many applications.
Figure 1.9 Basic types of microstrip antennas: (a) rectangular patch; (b) circular patch.
1.3.5.1 Features and Limitations
The diffusion of microstrip radiators is mainly due to their unique features, which are outlined below. Microstrip antennas are very low profile, of light weight and can be conformal to the mounting surface. These characteristics can be extremely important in several military, commercial or space applications where physical constrains are of prime concern. Depending on the type of materials, on the configuration and on the required fabrication process, microstrip antennas can also be low cost when compared to other types of antenna elements. Microstrip technology is naturally flexible, making possible the design of antennas of different shapes and configurations using single or multilayer arrangements and covering multiple bands. Furthermore, integration of printed antennas in microwave integrated circuits (MICs) is straightforward and high degrees of integration levels can be reached.
The main operational limitations of microstrip antennas are due to their narrow bandwidth. Indeed, a classical microstrip antenna would normally have a bandwidth of a few percent. Moreover, when compared to other radiators (e.g., horns, reflectors), the efficiency of microstrip antennas is much lower and the gain of a single patch is usually around 5–7 dBi. Another major disadvantage of printed radiators is related to their low power handling capability. This limitation is due to the small distance between the radiating patch and the ground plane. Depending on the substrate material characteristics and thickness, and on the thickness of metal layers, a microstrip radiator can be designed to handle hundreds of watts [55]. However, due to the multipacting breakdown effect [56], microstrip power handling in space is significantly reduced with respect to the expected value of the Earth's atmosphere. This aspect will be reconsidered in Section 1.5.1.
1.3.5.2 Basic Characteristics
In this subsection a rectangular patch antenna is taken as reference to discuss the basic radiation characteristics of microstrip antennas. A rectangular patch antenna consists of a rectangular patch of width W and length L printed on a substrate having relative dielectric permittivity of thickness h as shown in Figure 1.9. Generally, dielectric thickness is a fraction of wavelength ( where is the free-space wavelength) [16] while metal layers are tens of microns thick. The relative dielectric constant depends on the type of dielectric material. It mainly influences the resonant patch length L, the bandwidth and the patch efficiency.
A microstrip antenna designed to operate in its fundamental mode can be related to a half-wavelength resonator with two radiating edges. As can be observed in Figure 1.10
