Research On Cell Star Reconstructing Antenna Of Orbiting Reflector And Its Formation Process

Modern communication technology requires on-orbit antenna to have the function of beam reconstruction.However,the existing deployable antenna has fixed reflector shape,focal diameter ratio and observation angle,which is difficult to meet the requirements of the current development of satellite communication.With the development of on-orbit assembly and on-orbit manufacturing technology,the scheme of constructing large transmitting plane antennas using isomorphic elements splicing will play a greater potential in the construction of large and even super-large space structures in the future.The large number of isomorphic splicing elements,complex splicing links,coupled vibration of multi-body motion and inevitable fault modes will affect the shape accuracy of the whole reflection surface.In order to reconstruct the reflector antenna on orbit with high accuracy and stability,the relevant assembly parameter calculation,dynamic modeling and analysis and typical fault handling countermeasures are the key technologies that need to be made priority.In view of this,aiming at the on-orbit configuration stage of cell star splicing and reconstruction of reflector antenna,this paper carried out reflector fitting method design,structural dynamics modeling and fault mode analysis with flat plate reflector and rotating hinge joint as specific objects,aiming at ensuring the completion quality of on-orbit configuration task of reflector antenna.The main research contents include:The design method of cell star reconstruction reflector antenna was proposed,including element shape design,fitting node selection,fitting mode analysis and shape surface accuracy calculation.The antenna design program is written,and the typical on-orbit reflector antenna is reconstructed and splice by using this method.The results show that the cell star with side length of 200-500 mm can splice the reconstructed reflector antenna of 30-90 GHz band communication.The modal superposition method was used to describe the deformation of the reflection panel,the three-dimensional joint constraint equation was established for the cell star dynamic rotating joint,the penalty function was used to characterize the locking moment of the joint,and finally the dynamic model of the arm system was established based on the virtual work principle and Lagrange equation.The simulation results show that the quintic polynomial interpolation function has the best motion stability.Based on the flexible arm system model,the multi-body dynamics model considering hinge joint friction is improved.Lu Gre dynamic friction model was used to describe the equivalent torque of the dynamic hinge.The friction compensation controller is designed,and the numerical simulation results show that the friction compensation controller can effectively eliminate the influence of joint friction.The typical fault modes of cell star reconstruction reflector antenna were analyzed,the causes of the fault were summarized,and the countermeasures of small angle adjacent maneuver and large angle correction fitting were proposed for the hinge stuck fault.A seven-cell satellite arm test platform was built to measure joint angle and joint torque.The test shows that splicing and reconstruction of reflector antenna is feasible.