Patent Application
20170127323
The present invention relates generally to satellite communication, and particularly to methods and systems for handover between satellites.
Some satellite communication networks use a constellation of multiple non-geostationary satellites that jointly provide communication services to terrestrial satellite communication terminals or earth stations. From the point of view of a terrestrial terminal or earth station, a given non-geostationary satellite occasionally rises above the horizon, moves across the sky and then sets below the horizon. As such, communication via such a network typically involves tracking the angular positions of satellites, and handing-over from one satellite to another as needed to retain service.
An embodiment of the present invention that is described herein provides a method for communication including, in a first earth station that transmits signals to a second earth station via a first satellite, initiating a handover from the first satellite to a second satellite by transmitting the signals via both the first satellite and the second satellite, including transmitting a handover command and a synchronization signal. The handover command is received in the second earth station via the first satellite. In response to the handover command, a switch is made to receive the signals via the second satellite and synchronize to the signal received via the second satellite using the synchronization signal.
In some embodiments, receiving the signals, the handover command and the synchronization signal in the second earth station are performed by a single receive modem, which receives the signals via no more than one of the first and second satellites at any given time. In an embodiment, transmitting the signals includes transmitting the handover command and the synchronization signal with a time separation therebetween, and switching to receive the signals via the second satellite is performed in the second earth station during the time separation, so as to receive the synchronization signal via the second satellite after the switching.
In some embodiments, transmitting the handover command includes reporting one or more parameters of the second satellite, and synchronizing to the signal received via the second satellite includes acquiring the synchronization signal using the reported parameters. The reported parameters may include at least one parameter type selected from a group of types consisting of an identifier, a timing offset, a center frequency, a frequency offset and a phase offset relating to the second satellite.
In another embodiment, transmitting the handover command includes indicating to the second earth station a time at which to switch to receive the signals via the second satellite. In yet another embodiment, the method includes directing an antenna of the second earth station toward the second satellite in response to the handover command. In still another embodiment, transmitting the signals includes buffering payload data in a memory buffer and, in preparation for the handover, generating the signals for transmission by interleaving the buffered payload data, the handover command and the synchronization signal.
There is additionally provided, in accordance with an embodiment of the present invention, a communication system including first and second earth stations. The first earth station is configured to transmit signals via a first satellite, and to initiate a handover from the first satellite to a second satellite by transmitting the signals via both the first satellite and the second satellite, including transmitting a handover command and a synchronization signal. The second earth station is configured to receive the handover command via the first satellite and, in response to the handover command, to switch to receive the signals via the second satellite and to synchronize to the signal received via the second satellite using the synchronization signal.
There is further provided, in accordance with an embodiment of the present invention, an earth station including a transmitter and a control unit. The control unit is configured to transmit signals using the transmitter via a first satellite, and to initiate a handover from the first satellite to a second satellite by transmitting the signals using the transmitter via both the first satellite and the second satellite, including transmitting a handover command and a synchronization signal, so as to cause a remote earth station to receive the handover command via the first satellite and, in response to the handover command, to switch to receive the signals via the second satellite and to synchronize to the signal received via the second satellite using the synchronization signal.
There is also provided, in accordance with an embodiment of the present invention, an earth station including a receiver and a control unit. The control unit is configured to receive signals using the receiver via a first satellite, including receiving a handover command and a synchronization signal, and, in response to the handover command, to switch to receive the signals using the receiver via the second satellite and to synchronize to the signal received via the second satellite using the synchronization signal.
The present invention will be more fully understood from the following detailed description of the embodiments thereof, taken together with the drawings in which:
Embodiments of the present invention that are described herein provide improved methods and systems for handover between satellites. The disclosed techniques enable two Earth Stations (ESs) to perform a coordinated and seamless handover process, in which the receiving ES receives no more than one of the satellites at any given time. Thus, the receiving ES may comprise only a single receive modem.
In some disclosed embodiments, a first ES transmits signals to a second ES via a first satellite, and at some point decides to hand-over to a second satellite. In preparation for the handover, the first ES begins to transmit in parallel via both satellites. In particular, the first ES transmits a handover command and, after a certain time separation, a preamble comprising a synchronization signal.
The second ES has its receiver initially switched to receive via the first satellite. In response to receiving the handover command, the first ES switches its receiver to start receiving via the second satellite. After switching, the second ES acquires and locks on the signal received from the second satellite, using the preamble. The time separation between the handover command and the preamble is designed to allow the second ES sufficient time for switching between the satellites.
In some embodiments, the handover command also conveys parameters of the second satellite, in order to assist the second ES in synchronizing rapidly following the switch. Other disclosed embodiments relate to antenna steering in the two ESs before, during and after handover. Some implementation issues relating to the lengths of the various time intervals in the communication protocol, and to data buffering in the first ES, are also addressed.
The example of
In the present example, ES-A plays the role of a transmitting ES, and ES-B plays the role of a receiving ES. Generally, however, any ES may serve as a transmitting ES, receiving ES, or both. The present example describes a unidirectional link from ES-A to ES-B, for the sake of clarity. Generally, however, ES-A and ES-B may conduct bidirectional communication with one another.
The embodiments described herein focus on a handover scheme from SAT1 to SAT2. Initially, ES-A transmits to ES-B via SAT1 over a path 30A. At a certain point in time, ES-A and ES-B switch in a coordinated manner to communicate via SAT2 over a path 30B. As will be explained below, the entire handover process, as well as communication before and after the handover, are conducted using a single receive modem in the receiving ES.
In the example of
ES-B typically has a similar structure to ES-A. In the present example ES-B comprises antennas 32C and 32D, denoted ANT1 and ANT2, for communicating via SAT1 and SAT2, respectively. ES-B further comprises a receiver (RX) 40B, a transmitter (TX) 44B, a switch 36B for selecting between ANT1 and ANT2 on reception, and a CU 48B.
The configurations of system 20 and ESs 28A and 28B shown in
The different elements of ESs 28A and 28B may be implemented using suitable hardware, e.g., using one or more Application-Specific Integrated Circuits (ASICs) or Field-Programmable Gate Arrays (FPGAs), using software, or using a combination of hardware and software elements.
In some embodiments, CUs 48A and 48B comprise general-purpose processors, which are programmed in software to carry out the functions described herein. The software may be downloaded to the processors in electronic form, over a network, for example, or it may, alternatively or additionally, be provided and/or stored on non-transitory tangible media, such as magnetic, optical, or electronic memory.
In a typical non-geostationary satellite network, satellites 24 orbit the earth in predefined non-geostationary orbits. From the point of view of a given ES, each satellite 24 occasionally rises above the horizon, moves across the horizon and sets. With proper coverage, at least one satellite, and typically more than one, should be visible to an ES at any given time.
In some embodiments, ESs 28 switch (“handover”) from one satellite 24 to another in order to retain communication. Typically, CUs 48 have access to information regarding the satellite positions and parameters, and possibly to current received-signal parameters such as Signal-to-Noise Ratio (SNR). Using this information, the CUs are able to direct the ES antennas to point toward the appropriate satellites, to predict when the currently-used satellite is about to set, to select a new satellite to switch to, and to initiate the handover process at the correct time. The entire process is performed using only a single RX modem in the receiving ES.
The transmitted signal stream comprises payload blocks denoted D0, D1, D2, . . . , a command (CMD) block and a preamble block. The payload blocks contain the data transmitted to ES-B, e.g., transport stream, data packets or any other suitable payload. The CMD block is typically inserted by ES-A into the transmitted signal stream in preparation for handoff, and is not present at other times. The CMD block typically comprises a handover command that notifies ES-B of the approaching handover, plus one or more handoff parameters such as the time to switch and parameters of the new satellite. The time to switch may be specified, for example, in absolute time units, in terms of a number of symbols from the CMD block, or using any other suitable convention recognized by ES-B. The satellite parameters may comprise, for example, satellite identification, transmission frequency, expected latency, expected Doppler shift, and/or any other suitable parameter for facilitating acquisition of the new satellite signal.
The preamble block comprises a predefined synchronization signal waveform or sequence for enabling RX 40B of ES-B to acquire and lock to the received signal from the new satellite. Acquisition and lock typically involves acquisition of latency and sampling time, frequency offset and phase correction. The synchronization signal in the preamble block may comprise, for example, a Zadoff-Chu Constant Amplitude Zero Auto-Correlation (CAZAC) sequence or any other suitable synchronization signal.
In an embodiment, the preamble block does not immediately follow the CMD block, but is separated from the CMD block by at least one payload block (D1 in the present example). This time separation gives ES-B sufficient time to decode the CMD block and prepare for the handover.
A bar 76 at the bottom of the figure shows the signal at RX 40B of ES-B before, during and after the switch from SAT1 to SAT2. Initially, CU 48B of ES-B sets switch 36B to ANT1, and thus RX 40B receives the signal from SAT1. At a certain point in time, CU 48B switches switch 36B to ANT2. The switching interval is denoted “switching” in the figure. During this interval RX 40B is not assumed to receive a signal from any of the antennas. Following the switching interval, RX 40B receives the signal from SAT2 via ANT2.
The relationship between the signals received by ANT1 and ANT2 (bars 68 and 72) and the signal provided to RX 40B is depicted in
The time periods in which RX 40B is locked on the satellite signal are marked as “locked” in the figure. Before the handover and up to the beginning of the “switching” interval, RX 40B is locked on the signal from SAT1. After the “switching” interval, RX 40B receives at least part of the preamble block, and uses the synchronization signal to acquire and lock on the timing, frequency and phase of the signal from SAT2.
As can be seen in the figure, the time difference between transmission of the CMD block and transmission of the preamble block is typically designed such that the preamble block will be received by RX 40B immediately following the end of the “switching” interval. Moreover, it can be seen that RX 40B is fully locked on the satellite signal during the entire durations of payload blocks D0, D1, D2, . . . Therefore, the handover process is seamless and no data is lost.
At a certain point in time, CU 48A of ES-A triggers the handover process, at a handover triggering step 84. CU 48A may initiate handover, for example, in response to detecting that SAT1 is about to set and lose line-of-sight with ES-A, or for any other reason.
In preparation for the handover, CU 48A sends a handover command to TX 44A, notifies TX 44A of the parameters of the new satellite to switch to (SAT2), and directs ANT2 toward SAT2.
In response to the handover command, TX 44A of ES-A inserts the CMD and preamble blocks into the transmitted signal stream, at a handoff signal generation step 88. At this stage, TX 44A begins to transmit the transmitted signal stream simultaneously via both ANT1 and ANT2.
At this stage, ES-B still receives the signal from SAT1 via ANT1. RX 40B of ES-B decodes the CMD block and conveys the decoded block to CU 48B, at a CMD decoding step 92, and CU 48B detects the approaching handover.
In response to the handover command in the CMD block, ES-B prepares for the handover, at a handover preparation step 96. As part of the preparation, CU 48B directs ANT2 toward SAT2, and notifies RX 40B of the parameters of SAT2. The parameters of SAT2 may be obtained, for example, from satellite data stored in ES-B and/or from parameters received in the CMD block. RX 40B sets its timing, frequency and phase offset according to the expected SAT2 parameters.
At a switching step 100, CU 48B switches switch 36B from ANT1 to ANT2, so that RX 40B begins to receive the signal from SAT2 via ANT2. The timing, frequency and phase offsets in RX 40B are pre-tuned to the parameters of SAT2. At an acquisition step 104, RX 40B finds the preamble block in the received signal, and acquires and locks on to the signal from SAT2.
From this point onwards, the handover process is completed, and ES-A transmits to ES-B via SAT2, at a post-handoff communication step 108. The ESs communicate over path 30B, and both ESs use ANT2 and point ANT2 toward SAT2. ANT1 of ES-A is free for other suitable uses.
In some embodiments, the various time intervals in the disclosed communication protocol are designed to allow sufficient time for RX 40B to acquire and lock on the signal of the new satellite. The time intervals involved comprise the propagation delay difference between paths 30A and 30B (denoted Δτ), the acquisition time needed for RX 40B to lock on the synchronization signal in the preamble block (denoted τacq), the switching time (denoted τsw, corresponding to the length of the “switching” interval in
In an example eight-satellite constellation, the propagation delay difference Δτ may be up to 30 mS. A typical acquisition time τacq (excluding the preamble) may be up to 106 symbols, e.g., 100 mS for a symbol rate of 10 Msps. Alternatively, any other suitable values can be used.
The switching time τsw typically comprises the settling time of the switch, as well as that of oscillators and other circuits in RX 40B. The acquisition time τacq typically comprises the time needed to achieve frequency lock (including center frequency and Doppler shift), as well as the time needed for timing lock.
The example of
In a second possible scenario, the received signal in ANT2 precedes the received signal in ANT1. In this scenario, switching from ANT1 to ANT2 occurs within the preamble block of the signal received via ANT2. In order to provide RX 40B sufficient acquisition time in this scenario, the length of the preamble block should be at least τpre=max{Δτ}+τsw+τacq. This preamble length is the length to be used, in an embodiment, since it represents the worst-case between the two scenarios. This preamble length also corresponds to the buffer size that should be used for storing the transmitted signal stream in TX 44A of ES-A to allow for insertion of the preamble block.
The maximal latency expected from the beginning of the switching interval until RX 40B resumes data decoding is τlat =max{Δτ, τsw}+τpre for the first scenario, and τlat=τpre for the second scenario.
Typically, input stream 118 is written into buffer 114 at the input symbol rate. The buffer is read at a rate that is higher than the input symbol rate by a factor of (TNHO+TCMD+TPRE), wherein TNHO denotes the time between handovers, TCMD denotes the length of the CMD block, and TPRE denotes the length of the preamble block. This higher rate enables TX 44B to insert CMD block 122 and preamble block 126 at the appropriate times.
The switching and acquisition times described above have a direct impact on the size of buffer 114 and on the overall system latency, and should therefore be reduced as much as possible. The acquisition time of RX 40B can be reduced, for example, by using a-priori information regarding the new satellite before handover. Such information can be stored in ES-A and sent to ES-B in the CMD block, accumulated at ES-B during operation, and/or computed according to the known satellite data. A-priori information may comprise, for example, the center frequency of the new satellite, expected Doppler shift, clock synchronization shifts if applicable, timing and delay information, and/or any other suitable information.
Although the embodiments described herein mainly address non-geostationary satellite networks, the methods and systems described herein can also be used in other applications, such as in handover between geostationary satellites.
Additionally or alternatively, the disclosed techniques can be used in non-stationary ESs, e.g., in satellite terminals installed in aircraft. In such a moving terminal, the disclosed techniques can be used for handover between satellites, as well as for handover between spot beams (usually on different frequencies) on the same satellite.
In yet another embodiment, the disclosed techniques can also be implemented using a single antenna per ES. This sort of implementation would typically require a larger buffer size, a longer preamble, and means for compensating for the possible delays and antenna movement.
It will thus be appreciated that the embodiments described above are cited by way of example, and that the present invention is not limited to what has been particularly shown and described hereinabove. Rather, the scope of the present invention includes both combinations and sub-combinations of the various features described hereinabove, as well as variations and modifications thereof which would occur to persons skilled in the art upon reading the foregoing description and which are not disclosed in the prior art. Documents incorporated by reference in the present patent application are to be considered an integral part of the application except that to the extent any terms are defined in these incorporated documents in a manner that conflicts with the definitions made explicitly or implicitly in the present specification, only the definitions in the present specification should be considered.
This application claims the benefit of U.S. Provisional Patent Application 61/984,788, filed Apr. 27, 2014, whose disclosure is incorporated herein by reference.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/IB2015/052930 | 4/22/2015 | WO | 00 |
| Number | Date | Country | |
|---|---|---|---|
| 61984788 | Apr 2014 | US |
