SYNCHRONIZATION OF A MOBILE SATELLITE SYSTEM WITH SATELLITE SWITCHING

Abstract: An approach for timing synchronization in a satellite system involving synchronizing a master clock onboard an orbiting satellite with a time standard; synchronizing a plurality of terrestrial gateways with the master clock; and synchronizing a plurality of wireless transceivers with the master clock; whereby each of the plurality of gateways and each of the plurality of wireless transceivers are synchronized with the master clock onboard the orbiting satellite.

Description: SYNCHRONIZATION OP A MOBILE SATELLITE SYSTEM WITH SATELLITE SWITCHING This application claims priority to U.S. Provisional patent application Serial No. 60/052,443, of , et al.; filed July 14, 1997, for I incorporated herein by reference. This patent document relates to a common air interface described in a series of patent documents filed concurrently herewith. Related patent documents are: U.S. Patent Application Serial No. 09/ , filed July 13, 1998, of Soleimani, et al.; for SIGNALING MAINTENANCE FOR DISCONTINUOUS INFORMATION COMMUNICATIONS, now U.S. Patent No. ; U.S. Patent Application Serial No. 09/ , filed July 13, 1998, of Joshi, et al.; for SYSTEM AND METHOD FOR IMPLEMENTING TERMINAL TO TERMINAL CONNECTIONS VIA A GEOSYCHRONOUS EARTH ORBIT SATELLITE, now U.S. Patent No. ; U.S. ' Patent Application Serial No. 09/ , filed July 13, 1998, of Roos, et al.; for MOBILE SATELLITE SYSTEM HAVING AN IMPROVED SIGNALING CHANNEL, now U.S. Patent No. ; U.S. Patent Application Serial No. 09/ , filed July 13, 1998, of Noerpel, et al.; for SPOT BEAM SELECTION IN A MOBILE SATELLITE COMMUNICATION SYSTEM, now U.S. Patent No. ; U.S. Patent Application Serial No. 09/ , filed July 13, 1998, of Noerpel, et al.; for PAGING RECEPTION ASSURANCE IN A MULTIPLY REGISTERED WIRELESS TRANSCEIVER, now U.S. Patent No. ; U.S. Patent Application Serial No. 09/__ , filed July 13, 1998, of Joshi, et al.; for IMMEDIATE CHANNEL ASSIGNMENT IN A WIRELESS SYSTEM, now U.S. Patent No. ; and U.S. Patent Application Serial No. 09/ , filed July 13, 1998, of Joshi, et al.; for ERROR AND FLOW CONTROL IN A SATELLITE COMMUNICATIONS SYSTEM, now U.S. Patent No. , all of which are incorporated herein by reference. BACKGROUND OF THE INVENTION The present invention relates to wireless communication, and more particularly to synchronization in wireless transceivers. Even more particularly, the" present invention relates to synchronization of a wireless transceiver with satellite switching. Wireless communications have revolutionized how we utilize both leisure and work related times. By freeing us from wired communication systems, wireless communications systems allow us to conduct business at many locations heretofore unusable for such purposes. As we strive to expand our horizon of wireless connectivity, we push beyond the boundaries defined by land based wireless infrastructure. As a result, demand has emerged for wide coverage systems not employing land based infrastructure. Specifically, satellite based wireless communications systems are now being implemented that allow persons to carry on communications, both voice and data, nearly anywhere on the globe. Satellites employed in satellite communications systems have typically functioned as bent pipes, meaning that they do not themselves process the information they are receiving or transmitting, but rather pass this , information through unchanged from gateways to wireless transceivers and from wireless transceivers to gateways. As satellites become more sophisticated, and begin to process information received from wireless transceivers and/or gateways, it becomes necessary for the satellite to maintain timing synchronization with the gateways and the wireless transceivers. For example, a satellite with an on-board time slot interchange switch requires that timing be maintained at the satellite. (A satellite of this type is described below.) This requirement of timing synchronization at the satellite, however, proves to be a valuable door to features such as direct wireless transceiver to wireless transceiver communications; i.e., not through an earth-based gateway. This allows the communications to take place with minimal delay by assuring a single hop between wireless transceivers via the satellite as opposed to double hop (wireless transceiver satellite link gateway/network satellite link to wireless transceiver), as required by conventional -1 " systems . SUMMARY OF THE INVENTION The present invention advantageously addresses the needs above as well as other needs by providing an approach to synchronization of a satellite system including a plurality of wireless transceivers, a plurality of gateways, and an orbiting satellite. In one embodiment, the present invention can be characterized as a method of timing synchronization in a satellite system. The method has steps of synchronizing a master clock onboard an orbiting satellite with a time standard; synchronizing a plurality of terrestrial gateways with the master clock; and synchronizing a plurality of wireless transceivers with the master clock; whereby each of the plurality of gateways and each of the plurality of wireless transceivers ' are synchronized with the master clock onboard the orbiting satellite. In a variation of the method the synchronizing of the plurality of wireless transceiver with said master clock involves synchronizing said plurality or wireless transceivers with respective ones of the plurality of terrestrial gateways. BRIEF DESCRIPTION OF THE DRAWINGS The above and other aspects, features and advantages of the present invention will be more apparent from the following more particular description thereof, presented in conjunction with the following drawings wherein: FIG. 1 is a schematic block diagram of an exemplary satellite architecture, incorporating a timeslot interchange switch, with which teachings of the present invention may be employed; FIG. 2 is a schematic diagram of a satellite system with which teachings of one embodiment of the present invention may be employed; FIG. 3 is a functional block showing components of the one embodiment of the present invention useable on the satellite system of FIG. 1; FIG. 4 is a detailed functional block diagram showing a time slot interchange switch, and other physical components within a satellite link, such as depicted in FIG. 1, that introduce known timing delays/errors; and Corresponding reference characters indicate corresponding components throughout the several views of the drawings. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS The following description of the presently contemplated best mode of practicing the invention is not to be taken in a limiting sense, but is made merely for the purpose of describing the general principles of the invention. The scope of the invention should be determined with reference to the claims. Referring to FIG. 1, the present embodiment makes use of unique features of a satellite 1 having a timeslot interchange switch. An exemplary satellite 1 employing a time slot interchange switch allows a plurality of data pathways through the satellite to be selectively established under programmatic control: from the feederlink 2 to the mobile link 3 via a feederlink Low Noise Amplifier (LNA) /Down Converter (DC) 4, a forward processor 5 (comprising a channelizer 6, mobile- to-mobile switching 7, and beam forming and frequency channelization 8) , multiple solid state power amplifier (SSPA's) 9, a hybrid matrix 11, and a multiple diplexed element feed array 13; from mobile 3 link to feederlink 2 via the diplexed element feed array 13, multiple low noise amplifier elements 15, a return processor 17 (comprising beam forming and frequency channelization 19, mobile-to-mobile switching 17, and a channelizer 23) , ''a feederlink Upconverter (UC) and travelling wave tube (TWT) amplifier 25; from feederlink to feederlink via the feederlink low noise a plifier/downconverter 4, a feederlink-to-feederlink connection 27, and the feederlink up converter/travelling wave tube amplifier 25; and from mobile to mobile via the diplexed element fixed array 13, the multiple low noise amplifier elements 15, the return - rocessor 17 (namely beam forming and frequency channelization 19, and mobile-to-mobile switching 21) , the forward processor 5 (namely mobile-to- mobile switching 7 and beam forming and frequency channelization 8) . The timeslot interchange, switch is embodied in the mobile-to-mobile switch 7, 21, which is able to switch both frequency and time between two parts of the mobile-to-mobile switch 7, 21. Specifically, the mobile- to-mobile switch 7, 21 can switch a particular time division multiple access (TDMA) timeslot, in a particular frequency, in a particular beam in the uplink to any other downlink timeslot, frequency and beam. Referring first to FIG. 2, a schematic diagram shows a satellite wireless communications system 10 including a gateway/network 12, satellite link 14, a first wireless transceiver 16 and a second wireless transceiver 18. In this context, the wireless transceiver 16, 18 may be fixed, with the teachings of the present embodiment applying equally well to fixed and mobile wireless transceivers. The satellite link 14 includes a time slot interchange switch that translates signals coming from the first wireless transceiver into signals going to a second wireless transceiver 18, thus effecting a single satellite hop, from wireless transceiver 16 to wireless transceiver 18 communication. The uplink and downlink signals passed between the two wireless transceivers 16, 18 may be both time and frequency shifted by the time slot interchange switch and accompanying hardware and software. As a result, both" the time and the frequency of the wireless transceiver¬ 's- originated signals must be equalized at the satellite link 14 so that the time slot interchange switch can interchange the burst times and frequency correctly. An absolute frequency reference in each satellite network in accordance with the present embodiment is governed by a Rubidium or equivalent standard in the administrative operations center of the satellite network 10. A master oscillator in the satellite link 14 is calibrated against this standard and is updated as required by a spacecraft operations center. All other time and frequency synchronization is done against the satellite's master oscillator frequency in accordance with the teachings of the present embodiment. The gateways 12 synchronize themselves to the satellite link 14 and the wireless transceivers 16, 18 in turn synchronize themselves against the overhead control channels emanating from the gateway 12 with which they are communicating. The goal of time synchronization is to center mobile link and feederlink uplink transmissions in a nominal burst slot time as referenced to the satellites frame timing. The goal of frequency synchronization is to center mobile link and feederlink uplink transmission frequencies on the nominal frequencies as perceived by the satellite's processor filters. As mentioned above, the spacecraft master oscillator frequency is calibrated against the ground based Rubidium (or similarly accurate) reference. Adjustments to this oscillator are made very gradually so that frequency control loops can track changes accurately. Referring next to FIG. 3, a box diagram is shown of hierarchy and timing references that may be employed in an embodiment of the satellite communications system of FIG. 2. The satellite link 14 is the master of all system timing, subject to calibration by the Rubidium standard reference. The satellite transmits a processor synchronization signal that establishes the location of the frame boundaries and the time slot interchange switch of its payload processor. All timing from the ground, both gateways and mobile terminals, must achieve frame timing synchronization with the processor synchronization signal. Gateways achieve timing synchronization by transmitting a Gateway Frame Reference (GFR) signal via the feederlink uplink and comparing its timing against the processor synchronization signal. This closed loop process tracks satellite movement and ensures that the gateway can always transmit a burst precisely located with respect to the start of the frame in the satellite payload processor. In addition to frame synchronization, gateways need to be in multiframe synchronization. This is achieved by having every gateway, including the administrative operations center transmit the frame number of each gateway frame reference burst. Other gateways can then set their frame numbers to match those of the administrative operations center. The gateways are not synchronized to the public switch telephone network timing. There is a slip buffer in each voice circuit in the gateway that is used to buffer voice transmission over the public switch telephone network. The buffer is reset at the beginning of each call or if a frame slip occurs. Gateways transmit overhead control channels to the mobile link downlinks that wireless transceivers use to establish their coarse timing references. Embedded within the overhead control channel are messages containing the offset that, if the terminal were in the center of the beam, would allow the terminal to transmit with accurate timing back to the satellite. Because of the timing differences across the beam, this offset is only a coarse indicator of the desired offset: The terminal wireless transceivers must initially ""' transmit in a wide window with sufficient guard time on either side of the nominal burst position to prevent the transmissions from interfering with other bursts. The gateway can then measure the error and notify the terminal of any correction. After its initial correction, the gateway continues to monitor burst positions, sending occasional corrections as required. The gateway observing the synchronization downlink signal must know certain delays through various paths in the spacecraft to successfully time align forward, return and wireless transceiver to wireless transceiver traffic at the spacecraft interfaces. Bursts arriving at the spacecraft from the forward and reverse links must be aligned and assigned timeslots within the time division multiple access frame. The frame reference timing is provided by the processor synchronization signal on the feederlink downlink. The digital payload must be able to process user slot data within a frame for routing and gain adjustments. Referring next to FIG. 4, a block diagram is shown of the payload processor with the various path delays designated as: T AB is path delay in the forward link to the input of the time division multiple access multiplexor; T BC is path delay from the input of the multiplexor to the mobile link downlink; T DE is path delay in the reverse link to the mobile to mobile switch; T DF path delay in the reverse link mobile to feeder downlink; T SH path delay between when a processor synchronization signal synchronized pulse marks the start of a frame in the time slot multiplexor and the transmission of the last symbol of the unique word. 1. T ΞH is used by the gateway to align RXSOF with respect to the detection of the processor synchronization signal unique words. The administrative operations center and the gateway generate receive start of frame (RXSOF) markers as follows: RXSOF = {detection of processor synchronization signal unique word} + 40 ' "' milliseconds - T 5H . 2. T AB is used by the gateway to establish TXSOF for transmission in mobile to feeder paths TXSOF = Dn - 3. T lψ is the amount by which the gateway must point wireless terminal in the mobile to mobile path to adjust transmission in addition to the slot assignment pointer. 4. T is the fixed amount by which the gateway must point user terminals in the mobile to mobile path to adjust transmission in addition to the slot assignment pointer. Having the one-time measurements noted in the previous paragraph, the satellite can perform the following and achieve synchronization: the administrative operations center achieves timing synchronization with the satellite, each gateway achieves timing synchronization with the satellite; and wireless transceivers achieve timing synchronization with the satellite. Once synchronization has been achieved, the administrative operations center and gateways maintain synchronization by monitoring their frame references and gateway frame references respectively. Each wireless transceiver engaged in a call is monitored by the gateway that is controlling that wireless transceiver, and as it drifts in time, the gateway sends it small corrections. The administrative operations center startup process includes receiving the processor synchronization signal from the satellite in establishing the received start frame (RXSOF) ; the administrative operations center checks for other active gateways' GFR's to deduce the present state of the frame count, the administrative operations system performs a majority vote; if the majority is evenly split, the administrative operations center chooses one side, if there are no active gateways, the administrative operations center begins counting frames arbitrarily; the administrative operations center transmits network frame reference (NFR) bursts in its assigned feederlink frequency beginning in the first time slot after the RXSOF and repeating in subsequent frames, the NFR contains a frame number count; the administrative operations system measures received NFR timing relative to the RXSOF; the administrative operations center calculates Dn, the time delay required from RXSOF to TXSOF, to be the difference in time between receipt of NFR and processor synchronization signal talk starter frame; the Dn is adjusted by the amount calculated in the previous section; the administrative operations center adjusts its TXSOF by Dn (note that subsequent GFRs will be offset relative to the processor synchronization signal by an amount) , all other feederlink signals will be properly framed in time as they" pass through the satellite payload; and the administrative operations center moves the NFR to its assigned frequency and * time slot, freeing up the acquisition frequency for other gateways' use. Frame number, frequency, and timing synchronization in the system is achieved through the use of Network Frame Reference (NFR) and Gateway Frame Reference (GFR) bursts. Both the Advanced Operation Center and the gateways use NFR and GFR the same way for frequency and timing synchronization as described previously. Frame number information is also carried by the, NFR and GFR; the only difference is in the treatment of the frame numbering information: NFR frame numbers supersede those that might be present on the OFR(s) . Network synchronization begins with the Advanced Operations Center and its NFP. The NFR is transmitted in a feederlink frequency band that is looped back at the satellite to the Advanced Operation Center, A dedicated frequency is used to initially transmit the NFR so that it will not interfere with other signals that may be present on the feederlink. The AOC compares the frequency and timing of the received NFR with that of the processor synchronization signal and adjusts the timing and frequency of the NFR to bring it into alignment with the PSS timing and frequency, but the frequency is offset to prevent the two signals from interfering with each other. Once frequency and timing synchronization have been achieved, the NFR burst can be moved to a specified frequency and timeslot to allow the Advanced Operations Center to maintain frequency and timing synchronization, since the new timing and frequency are known amounts offset from the PSS reference. Each gateway must also achieve frequency and time synchronization via their GFRs. The same technique is used, namely, that a dedicated frequency is used for initial acquisition. Once acquisition has been achieved, the GFR can be moved to another specified frequency and timeslot. Thus, many gateways can be accommodated efficiently by placing the OFRs in sequential timeslots on specified frequencies. The network also requires that all gateways have the same frame number. There are two methods that can be used to ensure this: 1. Insert a frame number into the PSS signal. Every gateway then will receive the proper frame number in synchronism with the PSS. 2. Broadcast the frame, number in the NFR and OFRs. Each gateway and the AOC will then have to negotiate the correct frame number. There are several ways of ensuring that the right number is broadcast by every gateway; those are well known in the art. Each gateway achieves timing and synchronization with the satellite as follows: the gateway receives the processor synchronization signal and sets RXSOF; the gateway examines the frame count in the NFR and all other GFR's, if there is no NFR or GFR, the gateway may set the frame arbitrarily and rely on the synch maintenance procedures to resolve any subsequent problems; the gateway performs the majority voting on the frame counts to establish a frame count, if there was only one other gateway and the administrative operations center is visible in a different frame count, the administrative operations center frame count dominates; the gateway transmits a GFR in an unused feederlink frequency beginning in a first time slot after RXSOF and repeats in subsequent frames, the GFR contains the frame number count; the gateway measures received GFR timing relative to RXSOF; the gateway calculates Dn, the time delay required from RXSOF to DXSOF, to be the difference in time between receipt of GFR and processor synchronization signal at the start of frame; Dn is adjusted by the same amount as for the administrative operations center; the gateway adj ' usts its TXSOF by Dn; and the gateway moves its GFR to its assigned frequency and time slot. Terminals achieve timing synchronization with the satellite as follows: terminals fluctuate for open control channels and establish RXSOF; overhead channels broadcast for each beam the nominal Dn for terminals close to the center of that beam, TXSOF is set to Dn later than RXSOF; when a terminal needs to transmit after a period of idleness, it transmits in the nominal center of the random access channel (RACH) based on its TXSOF; the gateway, upon detecting the RACH bursts, measures its timing relative to RXSOF at the gateway and calculates error from nominal; the gateway, in its response to the terminal in the access grant channel (AGCH) , also sends the Dn correction; and the terminal updates its Dn accordingly. The frequency synchronization begins with the master oscillator in the satellite. The processor synchronization signal generated from this master oscillator is transmitted from the satellite at a radio frequency that is proportional to that of the master oscillator. On the ground the carrier frequency of this signal is measured very accurately using Rubidium or similar references. Any offset is due to a combination of satellite frequency error and downlink Doppler. The second measure of Doppler plus satellite frequency error is obtained by monitoring the feederlink to feederlink loop back frequency offset. These two measurements are used to solve for Doppler (uplink or downlink) and satellite frequency by solving the following simultaneous equations: Fpss_meas = Dl + Fpss (1 + err) F feeder_meas = D2 + D3 + F feeder_up + Fxlate (1+err) where err is the error in the master oscillator frequency in parts per unit, Fpss_meas is the measured value of the processor synchronization signals center frequency, F feeder_meas is the measured value of the feeder downlink used for the GFR signals that leave the satellite (before it experiences downloading Doppler) , Fpss is the nominal value of the processor synchronization signal carrier frequency, F feeder_up is the nominal value of the feeder uplink used before the GFR signal; Fxlate is the nominal value of the feeder to feeder transition frequency, Dl is the Doppler present in the downlink at Fpss (1 + err) (Note that Fpss (1 + err) is the actual Fpss emerging from the satellite) , D2 is the Doppler presently on the uplink at F feeder_up, which = Dl x (F feeder_up / or over (Fpss (1 = err))), F feeder_down is the actual value of the feeder downlink used for the GFR signal, which = F feeder_up + D2 + Fxlate (1 + err) , and D3 is the Doppler present on the downlink at F feeder_down, which = Dl x (at F feeder_down/ (Fpss (1 + err))). Of these elements, all are known except for Dl and its derivatives and err. Solving both equations simultaneously fills the desired results. The fractional Doppler and the satellite reference oscillator are estimated using the following: Fgfr ip j " _ [ , Fgfrjip \ ( Fxlate • Fpss neas _ . Fgfr iown ) W F Fggfftr iown j Fgfrjiown ) Fgfrdown • Fpss SMDC ■ ■ Fgfrjφ Fgfr iown Fpssjneas SRDC - Fpss(SMDC + \ ) where SMDC is the fractional Doppler and SRDC is the satellite reference oscillator error. The fractional Doppler (Dl/ frequency of transmitted signal) varies depending on the elevation angle of the gateway station or the wireless transceiver and satellite motion. The satellite reference oscillator variations are due to physical and atmospheric characteristics. To compensate for both, the frequency of the administrative operations center or gateway is set as Fχ _ Fχfrjψ * (SRDC + \ ) (SMDC + 1 ) The estimation error of SMDC is dependent on the magnitude (i.e., the elevation angle). The frequency error after the compensation is directly proportional to the magnitude of the SRDC. Against this background, the steps followed in order to achieve system frequency synchronization are: 1. Estimate the satellite Doppler and master oscillator error as perceived by each gateway and the administrative operations center; 2. For each gateway transmit all signals with the Doppler and master oscillator errors applied so that the signals are received by the satellite at its norma 1 ! sender frequency, which should be the absolute nominal frequency adjusted by the master oscillator error; 3. Each terminal locks its internal reference to received overhead control channel frequency, which will have the mobile link downlink Doppler link on it; and 4. When a terminal is to transmit, its frequency is corrected by measurement in the gateway, thereafter, the terminals frequency is corrected as required via messages from the gateway. This is true from terminal to gateway as well as terminal to terminal calls. When the administrative operations center first attempts to synchronize with the network, it must first estimate the satellite Doppler so ' that its transmissions reach the satellite at approximately the right frequency. This involves: 1. Measuring the processor synchronization signal center frequency, F p ; 2. Assuming the error is entirely due to Doppler; and 3. Initially transmitting the NFR with an offset of These bursts will reach the satellite with a slight error due to over or under compensating the Doppler by ignoring the satellite master oscillator error. The next step is to measure the NFR center frequency in the downlink, solve the equations above simultaneously, and derive at a master oscillator and Doppler error components. Gateways start up the same way as the administrative operations center. Wireless transceivers start up as follows: 1. Scan the frequencies for overhead control channels. The algorithm is up to the particular wireless transceiver vendor, but is greatly speeded up if the wireless transceiver has access to a default ' list of most-recently-used frequency. 2. When an overhead control channel has been located, lock the wireless transceiver local reference oscillator to the FCCH found therein. This establishes a frequency reference for the terminal, albeit one with Doppler error present. Note that aeronautical terminals cannot simply lock their oscillator, because the Doppler may be too high. They must maintain their own absolute reference. 3. Perform a beam selection algorithm, and relock the local reference frequency to the overhead control channel of the selected beam. 4. Wait until it is time to do a registration or make a call. 5. When it is time to do a registration or make a call, transmit a random access burst at the nominal transmit frequency. Note that this transmission will have essentially double Doppler on it at the satellite. One Doppler offset due to the downlink Doppler on the overhead control channels to which the terminal is locked and another Doppler offset in the same direction due to the uplink Doppler. 6. When the gateway acknowledges that random access burst, it will indicate an adjustment to the transmit frequency that the terminal is to make in future transmissions. 7. During the course of a call, the gateway will monitor frequency offset of the terminal bursts and transmit corrections periodically. Because all wireless transceivers use gateways as their frequency references, any frequency error in the gateways transmit frequency is reflected in the terminals transmit frequency. If the errors are small and slowly changing, there is no impact to TtG calls, i.e., terminal to gateway calls. For terminal to terminal calls, however, the errors have greater significance. When two terminals are connected to go through the satellite mobile to mobile switch, any residual error between them may cause poor acquisition performance. If the errors are large, there could be some adjacent channel interference and distortion due to channel filters. Under normal operating conditions, feederlink fades can cause gateways to lose visibility to its own or other gateways' GFRs. During these times, it is not necessary to shut down gateway operations, but it is desirable to maintain frequency synchronization by "free wheeling" through the fade. For most fades lasting several minutes, the satellite master oscillator can be assumed to be perfectly stable (within parts in 10 10 ) and the Doppler can be assumed to be changing steadily. Gateways and the administrative operations center have been stable and accurate references against which to compare the satellite Doppler master oscillator error. They can also examine each others frequencies relative to themselves to see if there is any discrepancy. If a discrepancy is found, an alarm should be raised. If a gateway finds itself in disagreement with two or more other gateways or the administrative operations center, it can reasonably assume that itself is at fault until the cause of the discrepancy has been found by manual intervention. If the magnitude of the discrepancy is within the limits of the frequency budget below, no alarm need be raised. If the discrepancy is between the maximum of the budget and two or three times the budget, performance will be impaired and an alarm should be raised. If the discrepancy exceeds two or three times the budget, the gateway should cease transmission until the problems can be resolved. The wireless transceivers are subject to significant Doppler errors due to their motion and their oscillators stability. Therefore, if a wireless transceiver loses contact with a gateway for prolonged periods of time, the terminal shall cease transmission until the gateway is again visible. Assuming a reasonable terminal stability, the frequency can drift for a time before link. The terminal should therefore cease transmission after a period of time without any visibility to the gateway. The satellite should preferably maintain an onboard master oscillator that has a. short-term stability comparable to that in the following table, including all effects of in-orbit temperature variations, allan variances, gravitational effects, and the like and assuming operation in typical satellite frequency bands: In particular, the rate of change of frequency over 10 seconds will average less than 10 per second due to all effects, including temperature changes during the eclipse. The time delays through various parts through the satellite must be accurately known. The nominal frequency of the processor synchronization signal must be known exactly, i.e., the ratio of the processor synchronization to all other relevant frequencies, which are locked to the master oscillator, must be known. The feeder to feeder translation nominal frequency must be known exactly, i.e., the ratio of the feeder to feeder translation nominal frequency to the processor synchronization carrier frequency must be known. The spacecraft operations center (SOC) must provide a means for adjusting the oscillator frequency either automatically or upon manual command. The administrative operations center should preferably provide a system reference operator whose accuracy is at least one part in 10 10 . The administrative operation center should also measure the frequency of the master oscillator onboard the spacecraft with an accuracy of better than 1 part in 10 10 relative to the administrative operations center reference frequency. Effects of Doppler and short term stability should also be compensated for. The administrative operations center should also provide a human interface that allows an administrative operations center operator to inform the spacecraft operations center operator that the frequency onboard the satellite needs to be tested. While the invention herein disclosed has been described by means of specific embodiments and applications thereof, numerous modifications and variations could be made thereto by those skilled in the art without departing from the scope of the invention set forth in the claims.

Claims: CLAIMS What is claimed is: 1. A method of timing synchronization in a satellite system comprising: synchronizing a master clock onboard an orbiting satellite with a time standard; synchronizing a plurality of terrestrial gateways with the master clock; and synchronizing a plurality of wireless transceivers the master clock; whereby each of the plurality of gateways and each of the plurality of wireless transceivers are synchronized with the master clock onboard the orbiting satellite. 2. The method of Claim 1 wherein said synchronizing of said plurality of wireless transceivers with said master clock comprises: synchronizing said plurality or wireless transceivers with respective ones of the plurality of terrestrial gateways. 3. The method of Claim 1 wherein said synchronizing of said master clock onboard said orbiting satellite comprises: synchronizing said master clock onboard said orbiting satellite with a Rubidium time standard. 4. The method of Claim 1 wherein said synchronizing of said master clock onboard said orbiting satellite comprises: synchronizing said master clock onboard said orbiting satellite with a Global Positioning System time standard. 5. The method of Claim 1 further comprising: buffering data frames transmitted to another communications network having differing timing. 6. The method of Claim 5 wherein said suffering includes buffering data frames to a public switched telephone network. 7. A method of frequency synchronization in a satellite system comprising: synchronizing a master clock onboard an orbiting satellite with a time standard; synchronizing a plurality of terrestrial gateways with the master clock; and synchronizing a plurality of wireless transceivers the master clock; whereby each of the plurality of gateways ,and each of the plurality of wireless transceivers are frequency synchronized with the master clock onboard the orbiting satellite. 8. The method of Claim 7 wherein said synchronizing of said plurality of wireless transceivers with said master clock comprises: synchronizing said plurality or wireless transceivers with respective ones of the plurality of terrestrial gateways. 9. The method of Claim 7 wherein said synchronizing of said master clock onboard said orbiting satellite comprises: synchronizing said master clock onboard said orbiting satellite with a Rubidium time standard. 10. The method of Claim 7 wherein said synchronizing of said master clock onboard said orbitiH'g satellite comprises: synchronizing said master clock onboard said orbiting satellite with a Global Positioning System time standard.

Inventors: ROOS DAVID A, SOLEIMANI MOHAMMAD, ROOS, DAVID, A., SOLEIMANI, MOHAMMAD
Applicants: HUGHES ELECTRONICS CORP, HUGHES ELECTRONICS CORPORATION
Application year: 1998
Main classification: H04B7
IPC codes: H04B7, H04W74, H04W76, H04W84, H04W99