The Implementation Of RFSoC Based Software Defined Radio For Deep Space Communication

Among the various implementations of miniaturized transponders for deep space communication,the software-defined radio transponder solution has become the primary solution for satellite communication payloads because it can fully utilize the hardware capability to implement multiple communication standards in the same hardware.In the thesis,the development of a RFSo C based deep-space communication transponder will be carried out with the measurement and control data communication payload of the solar-terrestrial L1 orbiting NEO surveillance microsatellite as the object of study,and the following research will be conducted on the implementation of a general-purpose RFSo C-based software radio platform and the engineering problems faced by the deepspace highly dynamic communication system.Sun-Earth L1 orbit NEO surveillance microsatellite Adopting a variable orbit scheme of electric transfer from GTO to Sun-Earth L1 orbit,different scientific missions are carried out in the near-Earth section and deep space section,in order to maximize the flexibility of the SDR platform,the communication payload designed in this project can provide high bandwidth communication capability in the near-Earth section of GTO and transfer orbit,and establish a highly reliable communication payload is designed to provide high bandwidth communication capability in GTO orbit and near-Earth transfer orbit,and to establish highly reliable low-rate communication links in Sun-Earth L1 orbit.In order to meet the high dynamic requirements of the same communication system,a high dynamic bandwidth and reconfigurable SDR architecture is developed,and the RFSo C adopts the high dynamic bandwidth characteristics to meet the high dynamic requirements of the communication link,and the development process and hardware and software structure are ”high cohesion and low coupling”.The RFSo C-based SDR platform provides the development of standardized and modularized digital processing units,programms an automated simulation and testing system,which significantly reduces the development difficulty.Secondly,the modulation and demodulation algorithm layer,which is the core of the architecture,is developped.The content is the modulation and demodulation algorithm of traditional digital transceiver implemented in FPGA.The QPSK modulation transmitter part uses the orthogonal coherent modulation method and implements the QPSK modulator and pulse shaping filter module.The QPSK demodulated receive part first uses a polyphase clock synchronization algorithm to complete the matching filter and clock synchronize,then completes the carrier synchronization through the polar Costas loop,and completes the demodulated receive function through the matching verdict.In recent years,the design of micro-nano-satellite systems are supported by the onorbit reconfigurable technology.The on-orbit parameters,function changes,and software error repair can be realized through the injection of applications on the TT&C channel.However,when the satellite enters the deep-space,the traditional reconfiguration method under the bandwidth-constrained channel,is impossable transmitting the large capacity of image.To address this problem,the RFSo C partial reconfiguration method research is carried out,which separates the interface from the communication algorithm in the architecture and uses the FPGA configuration interface to achieve partial configuration reflash,which significantly reduces the file size of the image and achieves the reduction of the transmission data volume.