Research On In-orbit Thermal Performance Of Fine Aim Control Subsystem In High-orbit Satellite Optical Communications

There have been growing interests to develop satellite laser communication technology around the world,due to the higher data transmission rate,higher security,the smaller size and lighter weight.The countries,such as America,Europe and Japan,have already devoted to implementation of the satellite laser communication technology in engineering,and successfully carried out the Satellite/Ground and Intersatellite laser communication experiments.Our country has also taken great efforts to explore satellite laser communication technology,and made a plan of space engineering realization in nearly 5 to 10 years.In the satellite laser link,generally,tracking precision is harshly high,due the to narrow beam divergence angle and transmission distances.As one of the important part of satellite laser communication,fine aim control subsystem mainly works for ensuring the tracing precision in the laser link,correcting pre-point process of control system,and pointing error caused by the satellite drift.Thus,highly precise and real-time pointing,acquisition and tracking system(PAT)system of laser communication link can be established.The space thermal working conditions of high orbit satellite are extremely complicated.Therefore,it is very important to study thermal working effects on the controlling precision,and improve the performance of tracking and link quality of laser communication.Currently,there are rarely reports on space thermal effect on fine aim control subsystem.Thus,we devote to analysis,designing and experimentally studying the in-orbit thermal environment adaptability of fine aim control subsystem,according to the earth synchronous orbit satellite(thermal balance and thermal cycle).Firstly,we have researched the working mechanism of Piezoelectric ceramic deflection mirror,and analyzed temperature effects on working precision.Then we designed and established an optimized model,which was proved by the finite element simulation.Finally,we have done the thermal balance and thermal cycle experiments to validate the design,according to the high-orbit space thermal environment.In summary,we have studied the in-orbit thermal performance of fine aim control subsystem in high-orbit satellite optical communication.And the model of thermal analysis and design we proposed,have been fully validated both by theoretical and experimental ways.The design can suffer from the temperature I standard,which provides necessary reference for in-orbit operation in further.