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- Herausgeber: John Wiley & Sons
- Kategorie: Wissenschaft und neue Technologien
- Sprache: Englisch
Comprehensive guide to the fundamentals and advanced engineering of the Beidou satellite system * The first book specifically describing the Chinese Beidou timing/navigation system - an increasingly important contributor to the GNSS * Introducing the 'user location information sharing' demands, technologies and development trends * Highlights the technical features and broad application prospects of navigation, positioning and short message communication of the Beidou satellite system * Enhances understanding of the fundamentals and theories of radio navigation and positioning satellite systems * Offers guidelines as to how to implement their design and construction * A comprehensive reference on the subject for those who are doing scientific or engineering research in this area
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Seitenzahl: 513
Veröffentlichungsjahr: 2017
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Table of Contents
Cover
Title Page
Copyright
Preface
Chapter 1: Overview
1.1 Origin of GLONASS
1.2 Development and Future Plans for the GPS System
1.3 Development and Future Plans for GLONASS
1.4 Development and Future of the Chinese Navigation Satellite System
1.5 Galileo Navigation Satellite System
1.6 Indian Navigation Satellite System
1.7 Japanese Regional Navigation Satellite System
Chapter 2: Concept and Application Prospects of Satellite Positioning Reporting Engineering
2.1 Satellite Positioning Reporting Service
2.2 Type of Service and Frequency Assignment
2.3 System Interference Analysis and Strategy
2.4 Service Optimization of Satellite Positioning Reporting Engineering
2.5 RDSS Application
Chapter 3: Principles of Satellite Positioning Reporting
3.1 Theory of Positioning Reporting
3.2 Main Factors Affecting Positioning Accuracy
3.3 Accuracy of MCC Time Delay Measurement
3.4 Space Propagation Time Delay Error
3.5 Geometric Figure and Positioning Accuracy
3.6 User Elevation and Positioning Accuracy
Chapter 4: Engineering Design of the Satellite Positioning Reporting System
4.1 System Composition
4.2 System Function Design
4.3 System Technical Index Design
4.4 Signal System Design
4.5 System Frequency Design
4.6 Engineering Design of Positioning Reporting Satellites
4.7 MCC Engineering Design
4.8 RDSS Application Terminal Design
Chapter 5: Comprehensive Theory of RDSS and Engineering Design
5.1 Definition of CRDSS
5.2 Theory of CRDSS
5.3 CRDSS system Engineering Design
5.4 CRDSS Navigation Positioning Satellite
5.5 CRDSS Ground System
5.6 Typical Application Scheme
Chapter 6: Anti-Interference and Low Exposure Technology of the Satellite Positioning User
6.1 Self-Adaptive Spatial Filtering Principle
6.2 Basic Algorithm of Self-Adaptive Filtering
6.3 Self-Adaptive Nulling Antenna Engineering Design
6.4 Low Exposure Transmission Array Antenna Design
Chapter 7: Concept of Satellite Navigation and the Principle of Positioning and Velocity Measurement
7.1 Concept of Satellite Navigation
7.2 Satellite Navigation Principle
7.3 Geometric Precision Factor
7.4 Satellite Navigation Velocity Measurement Principle
7.5 Positioning Velocity Measurement Precision
7.6 Distance Difference and Radial Velocity Difference
7.7 Combined Method
7.8 Carrier Phase Difference Method
Chapter 8: Performance Demand and General Design of RNSS
8.1 Essential Performance of RNSS
8.2 Mission and Procedure of the General Design
8.3 Mission and Procedure of Engineering Design
Chapter 9: System Design of Satellite Navigation
9.1 System Design Principle and Content
9.2 Service Mode and Content
9.3 Satellite Orbit and Constellation Selection
9.4 Signal Frequency and Modulation Coding Mode
9.5 Time Standard and Timing Pattern of Satellite Navigation
9.6 Navigation Satellite Trajectories and Ephemeris Expressions
Chapter 10: Design of the Satellite Navigation Operation Control System
10.1 Mission and Composition of the Satellite Navigation Operation Control System
10.2 Satellite Time Synchronization and Timing
10.3 Correction of Navigation Signal Spatial Propagation Delay
10.4 Determination of Precise Orbit and Satellite Clock Error
10.5 Integrity Monitoring and Prediction
10.6 Integration of Operation Control System
10.7 Operation and Control of Multi-System Joint Wide Area Augmentation System
Chapter 11: Navigation Satellites and Navigation Payload
11.1 Satellite and Navigation Payload History
11.2 Navigation Satellite Platform
11.3 Navigation Payload Requirements
11.4 GPS Satellite Navigation Payload
11.5 GLONASS Navigation Satellite and Navigation Payload
11.6 Galileo Navigation Satellite and Alternative Schemes of Navigation Payload
11.7 Compass Satellite Navigation and Payload
11.8 Comparison and Development Direction of Navigation Payload
Chapter 12: Satellite Navigation User Receiver
12.1 Relative Motion Characteristics Between the User and the Satellite
12.2 Pseudorange Measurement and Error Analysis
12.3 Positioning and Filtering Processing
References
Further Reading
Index
End User License Agreement
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Guide
Cover
Table of Contents
Preface
Begin Reading
List of Illustrations
Chapter 3: Principles of Satellite Positioning Reporting
Figure 3.1 Principle of positioning.
Figure 3.2 Chart for positioning system signal flow.
Figure 3.3 Schematic drawing of geodial surface.
Chapter 4: Engineering Design of the Satellite Positioning Reporting System
Figure 4.1 System composition.
Figure 4.2 Format of the outbound signal.
Figure 4.3 Inbound signal format.
Figure 4.4 Link frequency assignment.
Figure 4.5 Satellite-ground frequency adjustment scheme flow diagram.
Figure 4.6 Fast acquisition principle.
Figure 4.7 Combination of orbit determination distance and observation quantity.
Chapter 5: Comprehensive Theory of RDSS and Engineering Design
Figure 5.1 Selection of positioning satellite and principle of positioning of CRDSS.
Figure 5.2 Service comparison between RDSS and RNSS.
Figure 5.3 Coverage diagram of two GEO satellites.
Figure 5.4 Global rescue coverage based on GEO4 and GEO5 as well as Asia-Pacific coverage based on GEO1, GEO2, and GEO3.
Figure 5.5 Ionosphere grid calculation diagram.
Figure 5.6 Weakening diagram of multiple narrow correlators on multipath error.
Figure 5.7 Guidance service system composition.
Figure 5.9 S/L beam coverage.
Figure 5.8 C/S, L/S transponder configuration.
Figure 5.10 CRDSS positioning satellite selection and positioning principle.
Figure 5.11 Pseudorange double difference RDSS positioning principle.
Figure 5.12
R
ua
distance sum signal flow chart.
Figure 5.13 Pseudorange double difference measurement.
Figure 5.14 Basic design requirement of inbound signal.
Figure 5.15 Block diagram of a double module user terminal.
Chapter 6: Anti-Interference and Low Exposure Technology of the Satellite Positioning User
Figure 6.1 Improvement of the main lobe.
Figure 6.2 Suppression of the main lobe.
Figure 6.3 N antenna array digital beam formation block diagram.
Figure 6.4 Schematic diagram of the uniform circular path delay.
Chapter 7: Concept of Satellite Navigation and the Principle of Positioning and Velocity Measurement
Figure 7.1 Positioning principle of transit.
Figure 7.2 Schematic diagram of pseudorange and clock error.
Chapter 8: Performance Demand and General Design of RNSS
Figure 8.1 Block diagram of system architecture and engineering procedures.
Figure 8.2 Engineering design of the system.
Chapter 9: System Design of Satellite Navigation
Figure 9.1 Schematic diagram of satellite altitude.
Figure 9.2 Angle of visibility of satellite.
Figure 9.3 Track of sub-satellite point.
Figure 9.4 Example of a track of GPS sub-satellite point.
Figure 9.5 Track of the sub-satellite point of IGSO.
Figure 9.6 Relationship of vertical location accuracy (99.7% availability) and the number and altitude of MEO satellites.
Figure 9.7 Relationship of vertical accuracy and the number and altitude of satellites (with 3 GEO satellites, each curve corresponding to a different altitude: from 20,500 to 30,500 km, with a step length of 2000 km).
Figure 9.8 Relationship of vertical accuracy and the number and altitude of planes (MEO 24 satellites).
Figure 9.9 Relationship of vertical accuracy and the number of planes and the satellite altitude (30 satellites).
Figure 9.10 Occupation condition of navigation frequency.
Figure 9.11 Mutual spectral interference between CCNS and GPS.
Figure 9.12 The m-sequence register with linear feedback.
Figure 9.13 Gold code sequence.
Figure 9.14 Variation block diagram of a GPS p-code generator.
Figure 9.15 Block diagram of super long code generated using the compound method.
Figure 9.16 Block diagram of super long code generated using the parameter control method.
Figure 9.17 Allocation scheme for the same PR code.
Figure 9.18 Allocation scheme for different PR codes.
Figure 9.19 Block diagram of a normal QPSK modulator.
Figure 9.20 Power spectrum relationship between m code and C/A code, P code.
Figure 9.21 Block diagram of a linear subcarrier signal generator.
Figure 9.22 Block diagram of BOC signal generation.
Figure 9.23 BOC (10, 5) baseband signal.
Figure 9.24 Block diagram of CRC coding.
Figure 9.25 Geocentric coordinate system.
Chapter 10: Design of the Satellite Navigation Operation Control System
Figure 10.1 Transient process of orbital maneuver.
Figure 10.2 Schematic diagram of correlated characteristics.
Figure 10.3 Concept of the multi-system joint wide area augmentation system.
Figure 10.4 Ephemeris error of augmentation satellite.
Figure 10.5 Instance diagrams of estimated ephemeris errors under over-determined and underdetermined conditions.
Figure 10.6 Composition of the joint monitoring station.
Figure 10.7 Diagram of software processing function for the foreign satellite system.
Figure 10.8 Internal data flow of the system.
Chapter 11: Navigation Satellites and Navigation Payload
Figure 11.1 Antenna beam width and path loss values [15].
Figure 11.2 Horizontal link transponder and data unit block diagram.
Figure 11.3 AUTONAV processing block diagram.
Figure 11.4 Block diagram of Galileo MEO/GEO satellite subsystems.
Figure 11.5 Block diagram of TT&C system (I).
Chapter 12: Satellite Navigation User Receiver
Figure 12.1 Satellite navigation user receiver.
Figure 12.2 Geometrical relationship of pseudorange.
Figure 12.3 Typical DLL delay locked loop.
Figure 12.4 Navigation processor with α/β Tracker.
Figure 12.5 Navigation processor with Kalman tracker.
Figure 12.6 Conversion from pseudorange to the user state coordinate.
Figure 12.7 Relationship between processed noise and measurement noise and its influence on the predicted, the actual, and the observed pseudoranges.
Figure 12.8 Flow chart of Kalman filter implementation.
List of Tables
Chapter 2: Concept and Application Prospects of Satellite Positioning Reporting Engineering
Table 2.1 Comparison between satellite positioning reporting engineering and satellite navigation engineering
Table 2.2 US 1618 MHz frequency spectrum management
a
Table 2.3 US 2492 MHz frequency spectrum management
a
Table 2.4 US 5100 MHz frequency spectrum management
a
Chapter 4: Engineering Design of the Satellite Positioning Reporting System
Table 4.1 Channel Level with Bandwidth of 16 MHz in 6 GHz Frequency Band from MCC to Satellite
Table 4.2 Typical 2491.75 MHz Frequency Signal Level from Satellite to User
Table 4.3 Typical 1618.25 MHz Link Level with Bandwidth of 16.5 MHz from User to Satellite
Table 4.4 4 GHz Frequency Band 16.5 MHz Bandwidth Link Level from Satellite to MCC
Chapter 5: Comprehensive Theory of RDSS and Engineering Design
Table 5.1 Position reporting performance comparison between CRDSS and GPS
Table 5.2 Typical signal level of 2483.5∼2500 MHz from satellite to user
Table 5.3 Typical signal level of 1610∼1626.5 MHz from user to satellite
Table 5.4 CAT-I requirement proposed by the ICAO
Table 5.5 Precision positioning service indexes
Table 5.6 Standard point positioning and single reference station pseudorange differential positioning error Table (in m)
Table 5.7 WASS pseudorange differential positioning error assignment (in m)
Table 5.8 Calculation of outbound link level
Table 5.9 Inbound link level calculation
Table 5.10 Link level calculation under antenna aperture D = 1.3 m
Table 5.11 L link level calculation under antenna aperture D = 1.3 m
Table 5.12 Assignment of 1.0 m accuracy design parameter
Chapter 7: Concept of Satellite Navigation and the Principle of Positioning and Velocity Measurement
Table 7.1 Civil aviation requirement proposed by the ICAO [6]
Table 7.2 Galileo A-level public and professional application service performance requirement [7]
Table 7.3 Galileo B-level service performance requirement [7]
Chapter 8: Performance Demand and General Design of RNSS
Table 8.1 Safeguarding requirements for Russian radio aviation navigation
Table 8.2 Russian index requirements for the descent stage of flight landing
Table 8.3 Safeguarding requirements for Russian radio navigation of marine vessels
Table 8.4 Planning requirements for Russian radio navigation.
*
Table 8.5 Federal Radio Navigation Proposal Requirements of the United States Department of Transportation
Table 8.6 US Federal Aviation Administration FAA Navigation System Precision Standard
Table 8.7 Requirements of the US Radio Technical Commission for Aeronautics RTCASC 159 for the RAIM Integrity Recommendation
Chapter 9: System Design of Satellite Navigation
Table 9.1 Galileo Business Characteristics [7]
Table 9.2 UERE of the first action
Table 9.3 UERE of the second action
Table 9.4 Walker/GPS performance comparison
Table 9.5 E5 signal
Table 9.7 E2–L1-E1 signal
Table 9.8 Examples of main parameters for BOC
Table 9.9 Requirements and content of GPS navigation data
Table 9.10 Signal structures of Compass global system
Table 9.11 GPST-UTC clock correction parameters (taken from p. 18 of GPS telex message sub-frame 4)
Table 9.12 Comparison of ephemeris expressions and selection criteria
Table 9.13 Parameters of ephemeris expression [15]
Table 9.14 Definition of ephemeris expressions
Table 9.15 Scale factors for ephemeris parameters
Chapter 10: Design of the Satellite Navigation Operation Control System
Table 10.1 GPS ionosphere parameters [14]
Table 10.2 Basic relationship between ionosphere correlation properties and distance
Table 10.3 Grid point 1GP number demonstration
Chapter 11: Navigation Satellites and Navigation Payload
Table 11.1 Initial GPS launch history
Table 11.2 GLONASS unfolding phase
Table 11.3 Navigation data grouping
Chapter 12: Satellite Navigation User Receiver
Table 12.1 Analog computation of relative motion dynamic characteristics for Beijing static users
Table 12.2 Analog computation of relative motion dynamic characteristics for Sanya static users
Table 12.3 Pseudorange measurement accuracy for the two code element widths and different correlation space
Table 12.4 Functional relationship between α and the deviation error caused by variance reduction rate and acceleration
GNSS Systems and Engineering
The Chinese Beidou Navigation and Position Location Satellite
Shusen Tan
Beijing Satellite Navigation Center, Beijing, China
This edition first published 2018 by John Wiley & Sons Singapore Pte. Ltd under exclusive licence granted by National Defense Industry Press for all media and languages (excluding simplified and traditional Chinese) throughout the world (excluding Mainland China), and with non-exclusive license for electronic versions in Mainland China.
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Preface
The contemporary satellite navigation system has become an important infrastructure in the main developed countries. The US Global Positioning System (GPS) and the Russian Global Navigation Satellite System (GLONASS), established in the middle 1990s, are not only important military equipment but also widely used in the fields of global navigation and positioning, high precision time transfer, spacecraft tracking telemetry and control, and so on. The European Union started building the Galileo Satellite Navigation System at the end of the twentieth century. China has started building the China Compass Navigation Satellite System since the mid-1990s. The Compass Satellite Navigation and Positioning Reporting System was successfully built on December 27, 2012, realizing the service capability in Asia-Pacific Region. The author, starting from the Compass Satellite Navigation and Positioning Reporting System and engineering practice and taking the Radio Determination Satellite System (RDSS) and Radio Navigation Satellite Service (RNSS) as the important content, wrote GNSS Systems and Engineering: The China Compass Navigation and Position Location Satellite.
This book consists of three parts, 15 chapters in total. The first part includes four chapters introducing the theory and engineering design of Radio Determination Satellite Service (RDSS) mainly including basic concepts, fundamental principle, engineering design, user equipment technology, and so on. Chapter 5, Theory and Engineering Design of Navigation and Determination Satellite Service, serves as a link between the previous and following chapters introducing the theory and design of Radio Navigation and Determination Satellite Service integrating RDSS and RNSS. The third part includes the next nine chapters that introduce the theory and engineering design of Radio Navigation Satellite Service (RNSS), mainly including basic concepts, fundamental principle, engineering design, application examples, user equipment testing, and so on.
During writing and compiling of this book, departments at all different levels and relevant experts provided care and support. I would like to thank Xu Qifeng and Xie Youcai for their valuable revision comments; Wang Gang, researcher, for providing the analog computation result of the relative motion features of the static-state user; and to thank the China Aerospace Science and Technology Corporation (CASC) for providing the GLONASS document. I express my sincere thanks to Dr. Chen Xiangdong, Senior Engineer Zhao Wenjun, Zhang Aiyong, Mo Zhongqiu, Qu Wenke, Shen Fei, Yang Hua, Wei Gang, Li Yanyan, Jiao Cheng, Zhu Weigang, Zhao Jing, Hou Li, Yan Jianhua, Luo Keke; they made great effort in manuscript preparation, printing, and illustration preparation. At the same time, I express special thanks to Dr. Chen Xiangdong, Dr. Li Lin, Dr. He Feng, Dr. Sun Li, Dr. Ma Min, Dr. Li Min, Dr. Hu Caibo, Dr. Hu Zhirui, Dr. Tang Bin, Dr. Yang Huafeng, Tang Yun, Wang Sen, Shi Xin, Wang Chuhan, Zhang Linfeng, Zhang Hui, Dou Changjiang, Sha Hai, Dr. Wang Dongxia, Xin Jie, and Li Yanjie, for their great effort in translating the book.
Chapter 1Overview
The term “satellite navigation” is a short version of Radio Navigation Satellite Service (RNSS). The service that obtains the position vector under the fixing time of the Earth coordinate system by determining the traveling distance and rate of distance change of the radio signal transmitted by satellite is called the “RNSS,” where (X, Y, Z) is the user's coordinate in the Earth-fixed coordinate system; is the user's velocity component; and T is the moment when the user is located at the coordinate (X, Y, Z). The satellite navigation system consists of the satellite that realizes the radio navigation target, the ground operation control system, and the application terminal.
Transit and цикaɑa, built by USA and the Soviet Union successively in the 1960s, can only obtain the position coordinate (X, Y, Z) of the user under static state conditions. Movement velocity of the ship must be given to obtain the position coordinates in motion. The second generation of satellite navigation positioning systems, Global Positioning System (GPS) and Global Navigation Satellite System (GLONASS), built by the USA and Russia, respectively, can realize high-accuracy timing, spatial 3D positioning, and measurement of kinematic velocity for aerospace, aviation, navigation, and ground users at any point on Earth or in terrestrial space. Compared with the first generation of satellite navigation systems, the difference is significant in terms of the name of the system, positioning principle, positioning method, and so on. The first generation of Chinese satellite navigation positioning system utilized a positioning principle totally different from the one mentioned here. The confirmation of radio navigation parameter and position calculation required by user positioning is accomplished by ground control center other than the user, in fact, both positioning of the user terminal and positioning report from the user terminal to ground control center are completed, therefore it is called the Radio Determination Satellite Service (RDSS). RNSS is a subset of RDSS. China Compass is a multi-functional aerospace application system integrating satellite radio positioning, navigation, communication, location reporting, and identification.
In the corresponding chapters of this book, the system that can only confirm the position coordinate of the user is called the satellite positioning system, and the system that can completely confirm position vector of the user is called the satellite navigation system. However, RDSS is a complete system that accomplishes navigation, positioning, location reporting, and short message communication. This system was created originally by China Compass. Its function of location reporting has the features of lower systematic complexity and cost as well as shorter responding time of positioning reporting and higher security than RNSS positioning, which are the advantages of Compass and also the future directions for GLONASS development.
1.1 Origin of GLONASS
GLONASS, which originated from satellite positioning, has been through the development of satellite navigation. On December 27, 2012 regional deployment of Compass Satellite Navigation System positioning was accomplished; and the system integrating satellite navigation and positioning reporting pushed the GLONASS to its zenith. The development process can be divided into the three stages that follow.
1.1.1 Stage 1: Satellite Radio Positioning
This originated in the 1960s. Typical systems were the Transit (the US Navy Satellite Navigation System) and Russian цикaɑa. Their principles originated from Professor Shekbusavidge's team of former Soviet Union Leningrad Marjongski Airforce Engineering Academy of Science and Frank T. McClure, George C. Wesabah, and William H. Jill of the Institute of Applied Physics at Johns Hopkins University, USA. In principle, the space-borne transmitting signal is the navigation signal and the receiver of the Earth station receives the satellite signal. Through measurement of the Doppler frequency of electricity generated by satellite signal under relative movement, as well as the orbital parameter given by the satellite navigation signal, the location of the receiver, the user's positioning can be confirmed and accomplished. Determination of orbital parameters is realized through the reverse operation of the Doppler measurement after the satellite navigation signal is received by the fixed station on the Earth. This kind of system can only achieve the user's point positioning. Continuous navigation requires phase assistance. Therefore, the early stages of satellite navigation development only accomplished positioning.
1.1.2 Stage 2: RNSS
The RNSS originated in the 1970s. Typical systems are the US GPS and the Russian GLONASS. The principle roots can be found in the US Navy Research Council's (NRC) “Timation,” the EZIB Program by the Air Force's SAMSO Organization, and the former Soviet Union's research program. The fundamental principle is that the user uses the radio signal transmitted by satellite to determine the position vector under the Earth's fixed time coordinate system through measurement of the distance and rate of distance change: this is referred to as the RNSS, where (X, Y, Z) is the position coordinate of the Earth-fixed coordinate system of the user; is the velocity component of the user; and T is the moment when the user is located at coordinate (X, Y, Z). RNSS is the English terminology.
The satellite navigation system consists of the satellite that realizes the radio navigation target, the ground operation control system, and the application terminal. The application terminal provides not only the user's location but also the velocity, heading, distance to the destination, and trip time of the user. Therefore, the system that provides the RNSS signal service is also called the satellite navigation system. It can continuously provide the positioning velocity determination parameter.
1.1.3 Stage 3: Satellite Navigation Positioning Reporting
This originated in the 1990s. A typical system is China Compass Satellite Navigation Positioning System. As the information era progresses, the user not only needs to know his own location, velocity, and time, but also needs to share location, velocity, and duration of voyage with other users. In 1994, a Compass testing system was started to realize positioning, location reporting, and short message communication. In 1994, the “Double Satellite Navigation Positioning System” was approved. By taking two satellites as the space segment and taking the ground user electron height as the third material, it constitutes two spherical surfaces with the two satellites as the center of sphere and distance of the user as the radius, and the third spherical surface where the Earth's core is the center of sphere and the user's distance from surface of referenced ellipse sphere to the Earth's core plus height is the radius. The cross point of the three spherical surfaces is the location of the user; therefore, its principle is similar to the three-sphere positioning principle. The location reporting to the central control system is accomplished during the positioning of the user and it can realize short message communication between users. Compass provides the complete RNSS service at the same time; it is an integrated GLONASS system integrating navigation, positioning, location reporting, and short message communication. It has a greater number of outstanding advantages in achieving double satellite positioning reporting and triple satellite positioning reporting so as to avoid positioning reporting failure caused by conditions where four positioning satellites cannot be received, such as in the city among high-rise buildings and in cliff/remote gorge environments.
1.2 Development and Future Plans for the GPS System
In 1973, the United States Department of Defense approved the proposal of GPS and named it the NAVSTAR Global Positioning System, [1] which aimed to (1) deliver weapons accurately and (2) provide uniform navigation positioning to reverse the booming kinds of military navigation. The proposed constellation was a total of 24 satellites distributed on three circular orbital planes, with eight satellites on each orbital plane with a dip angle of 63°. The orbital planes were distributed with uniform space along the equator with an orbit height of 10,980 sea miles. Such an orbit height was a semi synchronous orbit, which was able to produce the repeated ground track. The large-scale antenna with an uplink injection station set in the mainland of the USA could accomplish the injection to the satellite according to the plan orientation safely and reliably. This selection of the three orbital planes not only features in good coverage but also facilitates backup satellite distribution with one backup satellite on each orbital plane and accomplishes the backup of the failure satellite. This constellation allows users to observe 6–11 satellites anytime in any place.
Two L-frequency band radio navigation signals are transmitted by each satellite, with L1 of 1575.42MHz and L2 of 1227.6MHz. L1 modulates two orthorhombic spreading code signals. I-subcircuit is a C/A code, named the coarse code or acquisition code with a code rate of 1.023 Mbps and used for civilian navigation; the Q-subcircuit is a precise distance measurement code, also called the P code with a code rate of 10.23 Mbps and used for authorized users. L2 only modulates P code, and is only used for authorized users. During the implementation of the engineering, due to concern about the prospect of GPS, financial expenditure is a constraint. In order to guarantee the effective experiment set up in Yuma Proving Grounds, three orbital planes were changed to six orbital planes to reflect the limited experimental satellite on the proving ground. There were four satellites on each plane and this had a good effect on the experiment but made the constellation layout difficult. In order to not waste the quantity of satellites or form a blank area in coverage, six orbital planes remain as they currently are. However, the three-orbital-plane scheme is still recommended by the GPS Modernization Plan, and a new civilian navigation signal has been added to L2.
From the proposal approved in 1973, GPS was mainly used for military purposes. Two navigation frequencies can be used for calibrating ionosphere propagation delay. However, there is only one navigation frequency L1 for civilian use. In order to meet civilian needs, calibration parameters of the ionosphere are provided in the L1 navigation message. Under the support of the model, 70% of ionosphere propagation deflection can be calibrated through these ionosphere calibration parameters. Therefore, for civilian users, they can only achieve positioning accuracy to a few tens of meters. Early US government protocols only allowed provision of positioning with an accuracy of 100 m (95%) to the civilian user and added SA measurement that reduced the accuracy on the civilian navigation signal. Due to the increase in civilian demand, various difference navigation positioning technologies have appeared that might improve accuracy to the meter-level. The Wide Area Augmentation System (WAAS) scheme provided by the Federal Aviation Administration (FAA) was typical of this. The US President released the SA Policy of reducing accuracy in 2000, and increased civilian accuracy to 25 m. In order to further expand the civilian market, the civilian navigation frequency was actively advocated and it was decided to modulate the civilian signal on L2 too, in order to carry out the I/Q reused QPSK modulating method. However, as for this proposal, military and civilian users were still on the same frequency for reuse, which brought about difficulties to war navigation implementation. Therefore, the US government took the lead in proposing to use the L5 frequency, that is, 1176.45 MHz, as the working frequency, which was registered in the ITU. At the World Radio Conference in 2000 (WRC-2000), it was proposed that satellite radio navigation frequency should include downlink frequency 1260∼1300 MHz, 5010∼5030 MHz, and the newly added uplink frequency included 1300∼1350 MHz, 5000∼5010 MHz, 1164∼1215 MHz; downlink navigation frequency lump power flux-density should be no greater than −121.5 dBW/(m2•MHz). Now, GPS actually occupies three frequency bands; 1575.42±12 MHz, 1227.6±12 MHz, and 1176.45±12 MHz. Although the navigation frequency is so abundant it cannot implement effective war navigation, the increase in military signal in a war zone inevitably affects the civilian one. The interference with the civilian signal will also affect the military one. Therefore, BOC modulation emerges. Reuse of navigation frequency was increased by utilizing space spectrum frequency division. The ideal solution is that military and civilian users, respectively, have two independent navigation frequencies, which is favorable to civilians. However, the current frequency source is limited and it is difficult to find another frequency source on the L-frequency band.
Another technological problem in GPS with any big change is encryption of the military P Code. The initial phase is precise pseudo-code of P code that has a relatively high security property. In order to increase the difficulty of theft, it was changed to a Y Code after adding scrambling code and then M Code.
The latest development in GPS is to continuously improve the navigation performance of GPS on the original track and frequency resource, and the navigation war performance is mainly improved. For instance, a reinforcing measure of the military code war zone is adopted, and control of civilian code is enhanced. The time Keeping System (TKS) and autonomous navigation (Auto-NAV) are added on the BLOCK-IIR satellite. This has autonomous working ability for 180 days without requiring ground system intervention. Autonomous navigation performs distance measurement and information exchange through UHF inter-satellite links, autonomously updating ephemeris on board, and accomplishing the calibration of the satellite clock. The time system is maintained by using a highly stable cesium atomic clock and rubidium atomic clock. It also has the reprogrammable performance of satellite space; namely, that an operative flight program could be completely newly programmed according to ground command. After cold start, the processor will execute the program stored in PROM (Programmable Read-Only Memory), which will maintain the working routine through beam uplink.
The GPS III Program was launched in 2000. Its fundamental target up until 2020 is: (1) to realize the navigation signal's capability of penetrating vegetation; (2) to reach positioning accuracy of 1 m; (3) to realize full ILS capability through a wide area differential; (4) to improve timing accuracy to 1 ns; (5) to possess excellent war navigation performance – in a war zone at least, the navigation signal could be enhanced by 30 db (1000 times); and (6) to fully realize an automatic early warning navigation signal.
1.3 Development and Future Plans for GLONASS
Based on the Soviet Union's successful low orbit system, цикaɑa, which began in the 1970s, Russia's GLONASS improved the orbit forecast accuracy and long-term stability of an atomic clock in space and digital signal processing techniques of propagation time delay correction accuracy of the troposphere and ionosphere. The purpose of study was to provide continuous and high-accuracy timing, spatial (three-dimensional) positioning, as well as movement velocity vectors for spaceflight, aviation, and ground users at any point on Earth or in near Earth space. GLONASS also consists of three parts:
1.
Satellite system, consisting of 24 satellites on three orbital planes.
2.
Monitoring control system, consisting of a ground monitoring station and a control station.
3.
User equipment.
Just like as GPS, navigation positioning of GLONASS automatically performs location and velocity calculations through measurement of non-inquiring pseudo-range and the radial pseudo-velocity is finished by user equipment, which is a typical RNSS positioning system. The pre-conditions for this positioning system had been accomplished in ΛBBИA research led by B. C. Sebusa in the period of 1955–1957 before the first man-made Earth satellite was launched.
The rationality and feasibility of a radio navigation system based on the conformance to the requirement of high accuracy for the ground user, offshore user, and air and space user was demonstrated 1 year after the launch into orbit of the first satellite цикaɑa used by a non-dynamic user. After the first GLONASS (TLOHACC) satellite, namely KOCMOC 1413, was launched on October 12, 1982, 65 satellites had been launched up until the middle of 1995. As of December 14, 1995, one rocket with three satellites was successfully launched by Russia that brought the total number of satellites in the GLONASS constellation to over 24. On January 18, 1990, the establishment of GLONASS was announced. The suggestion made in the ICAO 10th Airborne Navigation Conference was approved by the Russian government, which proposed to provide a standard accuracy channel of GLONASS to world aviation users and promised that the positioning accuracy would meet the parameters in Table 1.1. From the successful launch of the first GLONASS satellite to the establishment of the system, 73 GLONASS satellites in total had been launched, 67 of which were successful. Due to the conflict between short lifetime of satellite and long networking period, the satellites had been in orbit for 12 years. GLONASS promises not reduce accuracy.
Table 1.1 GLONASS accuracy properties
Measurement Accuracy
Parameters
GPS (P = 0.95)
GLONASS (P = 0.997)
Horizontal Plane, m
100 (72/18) (C/A Code)300 (P = 0.9999) (C/A Code)18 (P Code. Y Code.)
60 (CT Code)(39)
Vertical Plane, m
<200 (C/A Code)20 (P Code. Y Code)
75 (CT Code)(39)
Velocity, cm/s
<200 (C/A Code)20 (P Code. Y Code)
15 (CT Code)
Accelerated Velocity, cm/s
2
8 (C/A Code)<19 (C/A Code)
–
Time, µs
0.34 (C/A Code)0.18 (C/A Code)
1 (CT Code)
A GLONASS satellite has a lifetime of at least 3 years. Since the year 2000, satellite lifetime has been anticipated to be 5 years.
GLONASS adopts the frequency division (FDMA) identification system. Each satellite uses a fixed frequency bandwidth. The purpose of the design is to enhance jamming (intentional interference) rejection capability. However, due to the small frequency space of each satellite, which is only 0.5625 MH2, the resistance ability to modern bandwidth disturbance is very limited, and burdens the design of receivers more to provide a different reference frequency to each satellite. Since L1 frequency of GLONASS uses the radio astronomy operating frequency band, it has been suggested by the World Radio Conference this must change, which also makes the design of GLONASS satellite frequency more difficult. The only solution is sharing one frequency between two satellites corresponding to Earth, which undoubtedly will cause difficulty in the identification of low elevation of satellites. Is FDMA suitable for the navigation system? Many people disagree with this viewpoint. The Galileo System in Europe is still using a CDMA system. GLONASS frequency assignment is listed in Table 1.2.
Table 1.2 GLONASS frequency assignment
Channel
Frequency (MH
2
)
No.
L
1
L
2
00
1602.0
1246.0
01
1602.5625
1246.4375
02
1603.125
1246.875
03
1603.6825
1247.3125
04
1604.25
1247.75
05
1604.8125
1248.1875
06
1605.325
1248.625
07
1605.9325
1249.0625
08
1606.5
1249.5
09
1607.0625
1249.9375
10
1607.625
1250.375
11
1608.1875
1250.8125
12
1608. 75
1251.25
13
1609.3125
1251.6875
14
1609.875
1252.125
15
1610.4375
1252.5625
16
1611.0
1253.0
17
1614.5625
1253.4375
18
1612.125
1253.875
19
1612.6875
1254.3125
20
1613.25
1254.75
21
1613.8125
1255.1875
22
1614.375
1255.625
23
1614.9375
1256.0625
24
1615.5
1256.5
It was decided in WRC-87 in 1987 and WRC-92 in 1992 that 1610–1626 MHz was assigned to the satellite mobile mss ground to spatial service. By 1998, GLONASS had conceded 1610.6–1613.8 MHz to radio astronomy. Therefore, from 1998 to 2005, GLONASS satellites only used Channels 0–12 (1602.0–1608.25, 1246.0–1251.25 MHz). Using Channel 13 is an exception. After the year 2005, GLONASS-M satellite transmitted a channel frequency of K = −7–4, the high-end frequency of which is 1604.25 + 5.11 MHz = 1069.36 MHz. At the same time, the GLONASS-M satellite radiated navigation signals of frequencies L1 and L2 for civilian users, in which radiant power of an L2 civilian user is 12 W. Antenna gain along the direction of axis of a satellite pointing to the ground is 8.8 dB, and corresponding angle of GLONASS relative to this axis is 15°, 11 dB, 19°, 9 dB. The civilian ranging code of L2 is the pseudorandom sequence of maximal length the same as L1. The polynomial is and the period is 1 m; pseudo-code velocity is 5.11 Mbps. In the message, representation of the difference Δτn of L1 and L2 frequencies satellite time delay equipment is added. When L2 signal is lagging behind L1 signal, Δτn>0. When L1 signal is lagging behind L2 signal, then Δτn<0, and the deflection <.
Besides Δτn in the navigation message of GLONASS-M satellite, n parameters for improving the user positioning reliability were introduced.
The difference between representation system master clock time scale transmitted by a GLONASS satellite and time UTC (SU) time scale is τc. Satellite ranging code phase position is subject to the system master clock, while UTC (SU) is the Russian time frequency standard, and ephemeris of navigation satellite adopts UTC (SU) for calculation.
In order to fit in the astronomical time, UTC (SU) time scale can be corrected once or twice a year, with 1 s for each correction. The correction can be performed at 00:00 of the night from December 31 to January 1, March 31 to April 1, June 30 to July 1, and September 30 to October 1.
The correction features of UTC (SU) time scale introduced in GLONASS-M satellite navigation message are:
10 – Pending time correction
00 – No correction
01 – Correction with +1 second
11 – Correction with −1 second
Under the condition that UTC (SU) time scale is prepared for correction, this information shall be introduced into the navigation message not less than 2 months before correction.
The features of the satellite remodel are prepared to be introduced into the navigation message:
00 – GLONASS Satellite
01 – GLONASS-M Satellite
In a GLONASS-M satellite, the time scale difference between GPS and GLONSS planned to transmit is . Phase position of the ranging code is subject to the time scale of GPS and GLONASS. The maximum numerical range transmitted by this parameter is .
GLONASS will contribute to improve the long-term stability of the satellite clock. The GLONASS-M satellite will be installed with a new type of cesium clock, which will improve maximum day-and-night instability from to . The GLONASS-M satellite will adopt two methods to improve reliability and integrity: Method 1: Autonomous monitoring of basic functions is continuously performed on the satellite. When a phenomenon that affects the quality of navigation quality is found, sign Bn, which automatically connects in the downlink navigation message, means that this satellite cannot be used for navigation. Method 2: Monitoring network is setup by the ground control system to inspect the navigation signal. When the navigation signal is found to possess deviation affecting positioning quality, sign Cn introduced in the navigation message means that this satellite cannot be used for navigation.
1.4 Development and Future of the Chinese Navigation Satellite System
Originating from RDSS, the Chinese satellite navigation system has a weakness in continuous and autonomous navigation, but it was full of advancements – integration of positioning and positioning reporting, which means the integration of navigation and communication was accomplished; and the first generation of the Compass Navigation Positioning System, which was built in 2000. From 2000 to 2004, the three-step development planning of the China Compass was completed. The second generation of the satellite navigation system was launched in 2004. On December 27, 2012, Phase 1 of the Compass Second Generation Project covering China and some regions of Asia-Pacific was formally announced to start running, which completed the creation and perfection of the positioning reporting system of China Compass so as to provide RDSS and RNSS services to the user. The third step of development planning was launched in 2011. It aims to complete the global Compass system around 2020 to provide RDSS and RNSS services to users.
The Compass Navigation System, built in 2012, had navigation signals of three frequencies for the ionospheric calibration and improvement in carrier phase service efficiency. At the same time, it also provides calibration parameters in grid and model representations of ionosphere propagation delay of the user of single frequency, which contains eight model parameters of the ionosphere, αn and βn, 8 bits each, 64 bits in total; see to Table 1.3. (Refer to Table 1.4 for the ionosphere grid.)
Table 1.3 Calibration parameters of the ionosphere of the compass system
Parameter of Ionosphere
Parameter
Bit
Quantization Unit
Unit
α
0
8
s
α
1
8
s/π
α
2
8
s/π
2
α
3
8
s/π
3
β
0
8
2
11
s
β
1
8
2
16
s/π
β
2
8
2
16
s/π
2
β
3
8
2
16
s/π
3
Note: Parameters marked “1” are the complement of “2.” The most significant bit (MSB) is sign bit.
Table 1.4 Ionosphere parameter error tab information arrangement
Parameter
IGP
Δτ
i
GIVE1
Bit
8
9
4
IGP is the grid point number.
Δτ
i
is the vertical delay of ionosphere of grid point.
The system distance is 0.125 m.
GIVE1 is the ionosphere vertical delay correction error tab of this grid point.
Satellite broadcasts the integrity sign of self-test and the ground test to improve the reliability and integrity of positioning.
In order to meet the needs of multi-system compatibility, it successively broadcasts the time conversion parameters of GPS, GLONASS, Galileo systems (see Table 1.5 and Table 1.6), satellite integrity, and precision positioning clock correction parameter as well as satellite position correction parameters (see Table 1.7).
Table 1.5 Conversion parameters of compass time and GPS time
Parameter
Bit
Unit
A
0
GPS
14
1
0.1 ns
A
1
GPS
16
1
0.1
ns
/
s
Note: Parameters marked “1” are the complements of “2.” The MSB is sign bit.Conversion formula:Wherein ΔtGPS=A0GPS+A1GPStE is the BDT of user's calculation
Table 1.6 Conversion parameters of compass time and Galileo time
Parameter
Bit
Unit
A
0
Galileo
14
1
0.1 ns
A
1
Galileo
16
1
0.1
ns
/
s
Note: Parameters marked “1” are the “2.” The MSB is a sign bit.Conversion formula:Wherein ΔtGalileo=A0Galileo+A1GalileotE is the BDT of user's calculation
Table 1.7 Satellite clock errors, ephemeris correction parameter, and GPS error information
Parameter
T
PRN
Δ
x
Δ
y
Δ
z
EPREI
IOD
Bit
9
6
11
11
11
13
8
8
8
8
4
8
Note: T is the corresponding time of the parameters, expressed with integral minute of the same day in units of 3 min; and PRN is the satellite number of GPSΔχ, Δy, Δz are the correction of broadcast ephemeris of the satellite in unit of 0.25 m., , are the change rates of Δχ,Δy,Δz in unit of 0.0025 m/s., are the slow varying correction of satellite clock error. is the clock offset in unit of 0.5 ns; is the clock rate in unit of 0.005 ns/s. Clock error correction is relative to the satellite clock error correction in GPS navigation message. Broadcasting value of the navigation message shall be added in user's calculation.IOD is the date of data issuance. EPREI is the state parameter pointer of equivalent range error of the satellite ephemeris correction. (Omitted).
For time synchronization and satellite orbit determination of Compass Navigation System, the unique method for missions accomplished in the station setup in the home country alone that was mentioned previously is considered, which creates conditions for regional high-accuracy navigational positioning.
The Compass Navigation System is an independent satellite navigation system boasting advantages such as application compatibility with the advanced satellite navigation system, which will become a component of international GLONASS.
1.5 Galileo Navigation Satellite System
The Galileo Satellite Navigation System has been in planning for a long time. From March of 2005, it officially learned to use the (27+3) MEO constellation instead of the GEO satellite constellation. A specific frequency plan was announced officially to the consultative country of the frequency (see Section 9.4.1.) The first navigation experimental satellite, Giove A, was launched on December 28, 2005. Giove B, another experimental satellite, was planned for launch in 2006. Before 2011, another two satellites would be launched adopting at least four work stars to perform the experiment in orbit. And then the remaining 26 satellites would be launched to form the full constellation.
Galileo measurement and control adopts the S frequency band. Uplink injection is L-frequency band of 1300∼1350 MHz. Signal monitoring is in the C frequency band of 5000∼5010 MHz.
1.6 Indian Navigation Satellite System
The Indian government officially approved implementation of the Indian Regional Navigation Satellite System (IRNSS) on May 9, 2006. A space segment consisted of 7–8 satellites including three GEO satellites and four IGSO satellites with an inclination angle of 29°. It was changed to six IGSO satellites in 2012. Therefore, it consisted of nine satellites in total. In September of 2007, Naill, an official of the Indian Space Research Organization said at an International Spaceflight Conference that 16 billion Rupees would be spent on the setup of the IRNSS system. A navigation satellite would transmit navigation signal of three frequencies. One is BPSK (1) with the center frequency of 1575.42 MHz. The other one is BOC (5, 2) with the center frequency of 1176.45 MHz, and BPSK (1). The third one is the signal of S frequency band with the center frequency of 2491.005 MHz, EIRP = 35.5 dBw. The plan was to finish deployment of seven satellites in 2012 with service regions of 35°E–130°E, 45°S–45°N.
At the same time, India implemented the GPS Aided GEO Augmented Navigation based on the GPS satellite based augment, which is similar to US WAAS. The space segment includes GPS satellites and one GEO (INMARSAT-4F1) satellite. The GEO satellite adopts the C and L bands as the working frequencies. The two L band signals are the same as L1 and L5 of GPS. It is fully compatible with the EU's Galileo and the Japanese GPS Augmented System, MSAS, based on MTSAT.
1.7 Japanese Regional Navigation Satellite System
The Japanese Navigation System serves as a regional navigation satellite system (Quasi Zenith Satellite System) and satellite based augmentation system (multi-function satellite augmentation system). The Multi-Function Satellite Augmentation System is an augmentation system of GPS, which is similar to the US WAAS. Its satellite is the multi-purpose satellite (MTSAT) launched by Japan. Two GEO satellites are located at 140°E and 145°E covering the Asia-Pacific Area. It has possessed the initial service ability since 2007. Ground stations are located in Hawaii, USA; Canberra, Australia, and the Philippines, with the broadcasting signal covering the Asia-Pacific Area.
The QZSS (Quasi Zenith Satellite System) was primarily defined as a multi-mission satellite system providing cell phone communication and broadcasting service with an angle measurement (70°) and positioning service with a rotation angle of 30°. Once the GPS system signal is interrupted, it can still possess reliable navigation positioning and communication capabilities.
The space segment consists of three GEP satellites and four asymmetrical IGSO satellites. At least four satellites at the optimum location within 2500 km around the Japanese archipelago can be observed, among which is at least one has an elevation angle of 70°. This is to improve anti-occluding capability in cities among high rises and mountainous regions to maintain smooth communication, broadcasting, and position reporting.
The navigation signal transmitted by QZSS is completely compatible with GPS, including L1: 1575.42 MHz, L2: 1227.6 MHz, L5: 1176.45 MHz. The broadcasting service signal is 2605 MHz-2630MHz (S frequency band). Low velocity communication service signal frequency is 2170–2200MHz (S frequency band) and the LEX signal with a center frequency of 1278.75 MHz and a modulation system of BPSK (5) is compatible with Galileo E6CS. The minimum received power is −155.7 dBw. Centimeter-level surveying and mapping augmentation information is broadcast at a data rate of 2 kbps through the L-frequency band spiral array antenna with the Reed–Solomon error correcting code (255,233). The broadcasting parameter is ionospheric delay using a ruled surface to match actual measurement at each penetration point, which is vastly superior to the accuracy of Klobuchar model ionospheric correction.
Chapter 2Concept and Application Prospects of Satellite Positioning Reporting Engineering
2.1 Satellite Positioning Reporting Service
There are two ways of determining a satellite radio service user's location. One is the Radio Navigation Satellite System (RNSS), which is widely known. Positioning and parameter calculation of navigational speed and voyage are accomplished autonomously by the user through the radio satellite navigation signal received. The other is the Radio Determination Satellite System (RDSS). The user's position can be determined through the measured pseudorange as well as change rate of pseudorange by the user, or the user can be informed through the same system after the distance measurement and location calculation performed by external system. Mainly, the latter method aims to provide the location information of user and it's difficult to provide the navigation parameters such as velocity, course error, and prediction time to the destination. The engineering design and equipment manufacturing engineering of this satellite positioning service is named satellite positioning reporting engineering, a feature of which is to complete location reporting upon positioning. Refer to Table 2.1 for the performance of satellite positioning reporting engineering and satellite navigation engineering.
Table 2.1 Comparison between satellite positioning reporting engineering and satellite navigation engineering
Name Performance
Satellite Positioning Reporting Engineering
Satellite Navigation Engineering
Principle
User receiver to determine the location of user non-autonomously (informed by MCC)
User receiver to determine the location and velocity autonomously.
Available satellite constellation
Geostationary orbit (GEO) satellite constellation
Geostationary orbit (GEO) satellite constellation, MEO satellite constellation, IGSO satellite constellation.
Service
Positioning, time service, location reporting, communication
Positioning, velocity measurement, time service
User to transmit signal response
Required
Not required
Observed quantity
Distance sum from user to control center system through satellite
Satellite-earth pseudorange, value of Doppler measurement
Complexity of satellite load
Simple
Complicated
Coverage performance
Region + Region …
Regional and global integrated design
User dynamic adaptability
Medium and low dynamic user single one-time service
Low, medium and high dynamic continuous service
Application
Positioning, location reporting, communication, rescue
Navigation, weapon guidance
2.2 Type of Service and Frequency Assignment
Satellite positioning engineering adopts two GEO satellites to realize the accurate positioning of all kinds of mobile carrier or fixed carrier. It can also conveniently realize user's bidirectional data communication and precise time synchronization. According to classification method of radio satellite service of International Telecommunication Union (ITU), satellite positioning engineering can operate Radio Determination Satellite Service (RDSS), and Mobile Satellite Service (MSS). It also operates fixed satellite service for the feed link. It is always a tough mission to arrange the RDSS radio frequency spectrum range. The frequency range suitable for mobile user positioning is jammed. RDSS service, being as important as it is, is directly related to life-saving and rescue so that L and S frequency bands are the first choice. Scramble between RDSS frequency spectrum and MSS frequency spectrum is very intense. In 1985, based on the Geostar “Three-star” commercial concept created by O'Neill, the Federal Communication Commission officially affirmed RDSS technique standard based on the spread spectrum code division multiple access modulation and authorized three companies to build the RDSS system. Official redistribution [2] of RDSS spectrum is introduced in Tables 2.22.3, and 2.4, respectively.
Table 2.2 US 1618 MHz frequency spectrum managementa
Governmental Frequency Assignment (MHz)
Non-Governmental Frequency Assignment (MHz)
1610∼1626.5Aviation radio navigation
1610∼1626.5Aviation radio navigation
a 1610∼1626.5 MHz frequency is assigned to ground-to-air of RDSS at the same time.
Table 2.3 US 2492 MHz frequency spectrum managementa
Governmental Frequency Assignment (MHz)
Non-Governmental Frequency Assignment (MHz)
User designated by FCC
Planning Portion
Unused Frequency
2450∼2483.5
2450∼2483.5Fixed mobile radio positioning
Auxiliary broadcasting (74)Private operation-fixed (94)Private operation-mobile (90)
2450 ± 50 MHzIndustrial frequency, scientific frequency and medical frequency
2483.5∼2500
2483.5∼2500Radio positioning reporting (air-to-ground)
Satellite communication (25)
a Auxiliary broadcasting services and private radio stations with a license on July 25, 1985 could keep operating on the basis that they are mainly used on RDSS.
Table 2.4 US 5100 MHz frequency spectrum managementa
Governmental Frequency Assignment (MHz)
Non-Governmental Frequency Assignment (MHz)
User designated by FCC
Planning Portion
Dedicated Frequency (MHz)
5000∼5250Aviation radio navigation
5000∼5250Aviation radio navigation
Aviation (87)
a 5117∼5183 MHz sub-band is assigned to fixed satellite service air-to-ground transmission, which is connected with the RDSS operated in frequency band of 1610∼1626.5 MHz and 2483.5∼2500 MHz for use. All of the total power flux density reached to the earth surface shall not be greater than −159 dBW/m2/4 kHz.
Under the arrangement of Federal Council, an approach to affirm RDSS service is found. However, it is not in conformance with international radio frequency assignment. Therefore, the effort of fighting for frequency assignment has been made by the International Telecommunication Union (ITU). Through coordination with the ITU, CCIR, IMO, and ICAO, it endeavored to be listed in the agenda of WARC MOB-87 held in Geneva in October 1987. In July 1985, before the conference, the Executive Committee of ITU decided formally to list the assignment of RDSS frequency into the conference agenda. And in early 1986, some countries formulated unanimous standards for RDSS on the CCIR working team conference. The RDSS frequency spectrum was approved in 1987.
Frequency bands used by RDSS include:
Central station to satellite
6525∼6541.5 MHz
