Cross-Correlation Interference Effects in Multiaccess Optical Communications

The effects of the cross correlation between user codes in an opticalcode-division multiple-access communication system are investigated. The system model is a multiaccess satellite repeater in which the uplink and downlink channels are direct-detection, optical-polarization modulation links. The error probability is derived in terms of the cross correlation between the intended and interfering user codes. It is shown that the system error rate can be minimized by using code sequences in which the normalized second moment of the cross correlation between codes is small. The signalto- noise ratio (SNR) on the uplink is shown to be proportional to 1/K while the SNR on the downlink is proportional to 1/K1/2, where K is the number of users which are simultaneously accessing the system.     

Packet Radio Monitoring Via Repeater-On-Packets

The packet radio network (PRNET) is a store-and-forward packet switching system consisting of switching nodes which share a single radio communication channel. Recent studies have shown that PRNETs can easily be saturated and become unstable unless efficient routing and flow control algorithms are used. To enable point-to-point packet transportation, network stations assign a code (label) to each repeater; the process of assigning such labels is referred to as "network initialization." The initialization procedure assumes that the network topology is now known a priori and is changing with time. Thus the initialization procedure involves mapping of network topology, determining network structure (labels for repeaters), and transmitting labels to the repeaters. Although many authors have developed analytical models to study channel access schemes, no one has yet addressed the initialization issue. We present a Markov chain model which enables one to obtain in close form the optimal rates at which repeaters and station must transmit repeater-on-packets (ROPs) and label packets (LLPs) to minimize the network initialization time in a one-hop network, finite buffer station. Our most important result is that the network initialization time is relatively insensitive to the station transmission rate, but the repeater transmission rate must be carefully chosen to achieve rapid initialization.     

Future Trends in Military Communication Satellite Repeaters

The future development trends in military communication satellite repeaters will be dictated by greater spacecraft capability in terms of payload size, weight, power, and complexity, and attempts to better satisfy the satellite user's needs and desires. This paper presents the basic repeater configurations that have been employed and those that can be expected in the future, along with the user and development constraints on advanced repeater designs. The discussion points out the diverging trends in RF frequency to allow easy user pointing and provide greater capacity, the trend toward channelization within the repeater, and the various methods used to reduce susceptibility to interference. Examples are given of advanced repeaters, which demodulate and process received signals, which transmit and receive on the same frequency, and which route RF signals between antennas. Also discussed is the possibility of employing a large processing ground station and the impact of future repeater configurations on terminal designs.     

基于VLBI的上行组阵标校技术研究

天线组阵能否完全替代大口径天线有一个关键性难题,就是天线阵是否支持上行链路组阵。深空航天器无法将不同地面天线的上行信号对齐,所以上行链路信号的调整必须在地面完成。针对上行组阵发射机相位调整问题,提出一种基于VLBI(Very Long Baseline Interferometry,甚长基线干涉测量)技术的接收模式天线上行组阵标校方案,并对标校精度进行了简要分析。将上行链路时延分解为几何时延和发射系统时延,建立了几何时延模型,通过标定接收时延和发射时延,便可以得到天线阵元间的相位标校值。理论分析结果表明,该方案具有一定的可行性,对上行组阵相位标校的研究具有一定的借鉴意义。     

基于CCSDS标准的航天器上行遥控链路 协议体系与可靠性技术

针对航天测控领域中上行遥控业务的协议体系选择与可靠性设计问题,在对我国现行国军标技术指标要求与现有航天测控系统天地基遥控技术特点进行归纳梳理的基础上,基于空间段信息传输无线链路特点与CCSDS(Consultative Committee for Space Data Systems,空间数据系统咨询委员会)标准规范,研究给出了适用于我国航天测控任务的空间段遥控协议体系与可靠性措施,利用梳理统计方法对上行遥控体制进行了数学建模分析,并与CCSDS给出的应用算例进行了对比分析.分析结果表明,所涉及的上行遥控体制与CCSDS标准规范的工作效能基本相当,能够满足我国航天任务上行遥控任务使用需求.     

Transmission Characteristics of an FM Signal Through a Hard Limiting Repeater

The response of an FM detector to an FM signal which is passed through a hard limiting repeater together with additive Gaussian noise is described. A general expression of the output SNR is derived that enables the determination of the threshold behavior. To clarify the feature of a transmission characteristic, a comparison with a linear repeater is also made. The output SNR is found to be larger than that of the linear system for all practical values of input CNR's.     

分布式单星转发的定位测速模型及其应用

在城市峡谷中通过接收导航卫星信号以实现连续的定位与测速一直是卫星导航应用中的一个难题。针对此问题,借鉴卫星导航对抗中转发式欺骗干扰的定位控制基本原理,提出了通过分布式单星转发来解决城市峡谷中实现连续卫星导航的新方法,并构建了分布式单星转发的定位测速模型。在此基础上详细讨论了转发器天线对被遮挡卫星的指向跟踪、转发器相关参数的获取、转发器收发之间的有效隔离、直达信号与转发信号的同时利用等应用性问题。所提出方法的可行性得到了仿真试验的有效验证,从而为城市峡谷中的卫星导航应用提供了新的参考。     

Single Channel Per Carrier Satellite Repeater Capacity, Part 2

This paper analyzes the performance of a number of speech processing techniques that have been considered for single voice channel per carrier transmissions via satellite. This transmission mode is applicable to demand assigiment systems, which make possible the most efficient loading of the satellite transponder applications where the traffic at individual earth terminals is not sufficient to justify a substantial number of dedicated channels. The analysis basically determines the operating point for the satellite transponder which minimizes the required earth terminal G/T. Both analog and digital modulation techniques are considered, and the effects of syllabic companding and voice actuation of carriers are demonstrated. The results are presented in general analytic form, applicable to any modulation technique for which carrier-to-noise density ratio, channel width, and guardband width may be specified. Full carrier modulation is assumed. Curves are also furnished showing the required G/T and uplink per carrier EIRP as a function of the number of voice channels per transponder and the transponder gain. "CCIR/CCITT type" speech quality is assumed, together with a transponder El RP and bandwidth typical of current domestic satellite configurations.     

The Tactical Communications Satellite

Early in 1969 the U. S. Air Force placed into synchronous orbit the largest communications satellite built to date. This vehicle, the tactical communications satellite (TACSAT), together with a variety of ground terminals, is designed to test experimentally and develop tactical communications concepts for all military services. This paper describes the spacecraft design focusing on the communications repeater. Measured performance characteristics affecting communications utilization of the spacecraft are presented.     

Geolocation of frequency-hopping transmitters via satellite

An analysis of satellite-communications terminal geolocation performed by means of interception of ground terminal uplink transmissions in which a number of spaceborne interceptors transpond the frequency band of interest to terrestrial location for processing is presented. Interception regions for prototypical terminals and satellites are calculated and the results are presented parametrically as a function of uplink signal-to-noise ratio (SNR). The optimum angular separation of the interceptor satellites is found, and the effect of nonoptimal separation is discussed, as are the practical limitations involved in implementing this geolocation system     

Single Channel Per Carrier Satellite Repeater Channel Capacity

This paper analyzes the performance of a number of modulation and speech processing techniques that have been considered for single voice channel per carrier transmissions via satellite. This transmission mode is applicable to demand assignment systems, which make possible the most efficient loading of the satellite transponder in applications where the traffic at individual Earth terminals is not sufficient to justify a substantial number of dedicated channels. The analysis basically determines the operating point for the satellite transponder which minimizes the required Earth terminal G/T. The fraction of the total link noise allocated to uplink noise is treated as a parameter, so that the cost of improving G/T may be traded against the cost of providing increased Earth terminal transmitter power. Both analog and digital modulation techniques are considered, together with various practical combinations of syllabic companding, voice-actuated carriers, and error-correcting codes. The results are presented in general analytic form, applicable to any modulation technique for which carrier-to-noise density ratio, channel width, and guardband width may be specified. Curves showing required G/T as a function of the total number of voice channels per transponder are also presented for the above-mentioned signal processing techniques, assuming "CCIR/CITT type" speech quality and transponder EIRP and bandwidth typical of current domestic satellite configurations.     

ATS-6 Interferometer

The Applications Technology Satellite-6 (ATS-6) RF interferometer is utilized primarily as a precision 3-axis attitude sensor having an unambiguous field of view of 350°. This function requires two separated ground transmitters, each using one of the two available frequency channels or sharing a single channel by time multiplexing. For 3-axis control, one uplink transmitter can provide 2-axis attitude (pitch and roll) with other sensors (e.g., a Polaris tracker) providing yaw attitude. By utilizing two uplink transmitters and the Earth sensor or three time multiplexed uplink transmitters, the interferometer can also provide measurements of ATS-6 spacecraft orbit position. Uplink frequencies are 6.150 and 6.155 GHz. The receiving antennas are spaced at 19.95 wavelengths (?) for the vernier baseline and 1.66 ? for the coarse baseline. Spacecraft system weight is 8.39 kg (18.5 lb) and power requirement is 15.5 W. Flight evaluation results are given for the interferometer including R F link budgets, modulation of uplink carrier, signal-to-noise ratio, and dropout behavior. A hardware calibration model is described, containing major biases in the phase measurements. Techniques for flight calibration as both an attitude and spacecraft position sensor are outlined . Flight testing has shown that on-line calibration of receiver/converter biases must be performed on a short term routine basis. Interferometer resolution was found to be 0.00140 space angle with negligible noise (jitter) at transmitted power levels above 72 dBW. As an attitude sensor, the interferometer has demonstrated the ability to provide stabilization to better than 0.     

Time delay techniques for satellite interference location system

Describes the development of a system for inferring the position of uplink ground stations, using existing domestic satellites, with minimal disruption of normal operation. The system uses the differential time delay of a single uplink signal passing through two adjacent spacecraft to infer the relative position of the uplink transmitter. A system for the measurement of such differential time delays is described. Since this technique alone does not provide an unambiguous determination of uplink transmitter location, the use of an interferometer to resolve such ambiguities is discussed     

A satellite interference location system using differential timeand phase measurement techniques

The design and development of a system for inferring the position of terrestrial satellite uplink stations using existing domestic satellites with minimal disruption to normal satellite operation are described. Two methods are presented by which a quantity measured at a terrestrial receiving site is mapped into a curve of possible uplink locations on the Earth's surface. One method involves measuring differential time delays of a single uplink signal observed through two adjacent spacecraft. The other uses a short baseline interferometer composed of the two cross-polarized and spatially separated antenna feeds aboard an affected satellite. A unique location is obtained by using an appropriate combination of the two methods. A system for measurement of the required differential delays and phases and experimental work performed to demonstrate the feasibility of the location methods are described     

基于高级在轨系统的测控数传一体化方案

针对测控与数据传输信道一体化的需求,采用AOS(Advanced Orbiting System,高级在轨系统)空间链路层的等时业务,设计了一种测控数传信道一体化方案,可在上下行信道采用非相干信息帧同时传输测量信息及高速载荷数据.该方案设计了2种工作模式,模式一在上下行信道同时使用AOS传输帧,双向数据传输速率最高3 Mbit/s,测距精度优于2 m;模式二上行信道使用遥控扩频帧,可进行多站测距,抗多址干扰能力不低于15 dB,抗单频干扰能力不低于23 dB,下行信道使用AOS传输帧,最高数据传输速率3 Mbit/s,测距精度优于1 m.     

应答机测距转发性能分析

分析了采用视频AGC（自动增益控制）、射频AGC和限幅器等3种测距转发模式的应答机性能,分析结果表明：视频AGC模式下,应答机测距通道的输出功率恒定,测距转发性能不随上行信号强度变化而变化;射频AGC模式下,应答机测距通道的输出功率不恒定,测距转发性能随着上行信号强度变化而变化;而限幅器模式可看作射频AGC的一种特殊情况。仿真分析了我国研制的限幅器和射频AGC两种模式应答机的性能,结果表明理论计算的性能与实测结果一致,理论分析正确且理论分析结果可作为链路计算的依据。     

深空探测多天线组阵的增益损失研究

为定量分析上行天线组阵增益损失的影响因素,提出一种通过建立数学模型分析合成损耗的估计方法.首先基于天线原理和电磁波传输理论建立了天线组阵上行链路信号的数学模型,以统计学理论对数学模型进行分析,得到了影响上行链路信号的若干因素.通过分析得出,深空探测信号在远距离传输中因大气相位扰动引起的误差是造成天线组阵增益损失的最主要因素.再通过对大气相位扰动误差的进一步分析,构建S频段和X频段下大气相位扰动的空间自相关模型和时间自相关模型,得到组阵基线长度和工作仰角同合成损耗的关系.经过对各误差源的分析可知,在目前的技术水平下,能够满足上行天线组阵工程应用的精度要求.     

Satellite inclination effects on UHF Satcom operation

The cause, magnitude, and time variance of satellite inclination are examined in light of the effects on military UHF SATCOM operation. The effects on required demodulator acquisition range, earth coverage footprint, and user terminal antenna pointing accuracy are considered. It is shown that the allowable satellite inclination to maximize on-orbit lifetime is not based on earth-terminal antenna pointing accuracy, but on allowable loss of high-latitude satellite coverage area. Worst-case Doppler shift for a UHF military satellite is 85-Hz uplink and 67-Hz downlink for a 5° SATCOM user elevation angle and 10° of satellite inclination. This amount of inclination is a reasonable allowance for station-keeping, to minimize thruster fuel and thus maximize satellite life. It is also shown that uplink Doppler frequency shift due to satellite inclination may be corrected based on satellite ephemeris data and rough user terminal location data     

测控中的星载计算机快速切换

针对低轨卫星长期管理与测控中的星载计算机所需要的切换、维护的测控时间相对较长的问题,在分析原有主、备星载计算机的时间比对方法的基础上,直接针对备机建立新的时间同步模型,并进行公式推导和理论误差分析;然后建立新的测控事件调度模型,实现时间同步数据与主备机一致性数据的同时注入,优化工作流程,并有效缩短测控时间;最后编写新的遥控作业,在测控中进行实践.应用结果表明,采用新方法可以在一个测控圈次内完成在轨星载计算机的切换与维护,MTTR(Mean Time To Repair,平均恢复时间)小于8 min,时间同步精度优于1 ms,所需测控圈次相对于原方法减少83％以上,适用于在轨卫星长期管理与测控.     

科学实验卫星高速上行链路设计

为保障在卫星与地面之间开展空间量子科学实验的条件,必须为科学实验载荷建立一条星—地高速数据双向传输链路.通过跟踪CCSDS-SLS-NGU（空间数据系统咨询委员会-空间链路业务-下一代上行链路）工作组对NGU的研究进展,结合科学实验卫星有效载荷建立高速上行链路的需求,采用高带宽利用率调制技术、高效信道编码方式及适用的链路数据传输协议,设计了一种传输速率为1Mbit/s、误码率优于1×10-9的高速上行链路方案,并给出星载设备实现方案和地面初步测试结果.该方案在技术体制上兼容已有CCSDS规范,便于地面站及星载接收机实现,完全满足开展空间量子科学实验的需要.