在轨组装天线模块单元变形调节策略OA

Objective On-orbit assembly represents a promising approach for constructing large-aperture space antennas,which are essential for advanced communication,Earth observation,and deep space exploration.However,the modular assembly process inherently introduces cumulative errors,such as surface deviations and potential module interference,due to assembly gaps and alignment inaccuracies.These errors can compromise overall surface accuracy and assembly feasibility.This study aims to develop a deformation adjustment strategy for module units to suppress error propagation,mitigate interference risks,and ensure high assembly precision and system performance. Methods A comprehensive modeling and analysis framework was established.First,a parabolic antenna model incorporating assembly gaps was developed.Using a planar projection method,nodal coordinates of the module units were generated.A gap conversion model was iteratively ap-plied to determine the spatial positions of modules in each concentric ring.A three-point circumferential docking mechanism and a unidirectional assembly sequence(from the center outward)were designed,resulting in six distinct error propagation chains.Second,an assembly error analysis was conducted based on the concepts of error chains and error balls.A six-degree-of-freedom error model was constructed using the product-of-exponential(POE)method.Random displacement and rotational errors were generated at virtual assembly centers,simulating error propagation along the chains.A 61-module antenna was analyzed to quantify the effects of assembly gap size(100～300 mm)and maximum allowable dis-placement error(10～40 mm)on cumulative error.Finally,a deformable module configuration was proposed to counteract error accumulation.By releasing nodal degrees of freedom and integrating actuators on the reflective surface,the module could achieve graded adjustment capabili-ties,from single-face to six-face deformation.A scenario-based adjustment scheme was formulated,dynamically modifying module edge lengths and angles according to the number of contact faces and interference conditions.The feasibility of the design and adjustment strategy was vali-dated through simulations using simplified planar models of the deformable modules. Results and Discussions The error analysis revealed that assembly errors accumulate progressively along the error chains,with a positive correlation with both assembly gap size and maximum allowable displacement error.For instance,with a 200 mm assembly gap and a 10%maximum displace-ment error allowance,the maximum displacement error at the assembly center reached 16.99 mm.Error accumulation accelerated with increasing mod-ule ring numbers,highlighting the risk of exceeding docking mechanism tolerances and causing module interference.Simulation results for deformable modules under various adjustment scenarios(two-,three-,four-,and six-sided adjustments)demonstrated effective shape adaptation to target configura-tions.Actuator stroke distances and directions were successfully determined for each case.For example,in the two-sided adjustment scenario,one face extended by 50 mm while the other contracted by 24.93 mm,achieving the desired interface matching.The simulations confirmed that the proposed module design and adjustment logic can effectively compensate for misalignments and prevent interference. Conclusions This study presents a systematic approach to modeling,analyzing,and mitigating assembly errors in modular on-orbit assembled an-tennas.The key conclusions are:1)Assembly errors accumulate along error chains and are proportional to assembly gap size and maximum al-lowable displacement error.2)A deformable module unit configuration capable of one-to six-sided adjustments effectively counteracts error-induced misalignments and interference.3)A scenario-based adjustment scheme enables dynamic module reshaping according to contact and in-terference conditions.4)Simplified model simulations verify the feasibility of both the deformable module design and the adjustment strategy.The proposed strategy offers a viable solution for managing error accumulation in large-scale in-space antenna assembly,enhancing both assem-bly feasibility and operational performance.Future work will focus on detailed freedom analysis and mechanical redesign of deployable hexago-nal modules to realize the proposed deformation capabilities in engineering practice.