Solar Array Composite Structures Improvement And The Experiment Verification

A spacecraft after the success of the launch, after several days flying already complete,when in the last on-orbit action, it was found that the spacecraft on the solar arraycomposite structure in the crack phenomenon, the main cause is the spacecraft onlarge-scale stretch composite structure, together with the spacecraft in orbit the action, dueto the heavy weight, behavior and the long, will produce very big part of the overload,when beyond the composite structure of the carrying capacity, appeared this breakdownphenomenon.In order to avoid subsequent spacecraft orbiting no longer happen during a similarproblem, need to be combined with the solar array by the orbit loads on the structuraldesign of the composite was improved, and by using the finite element methods to improvethe bearing capacity of composite structure analysis, calculation, and through the staticload test and fatigue tests to verify the effectiveness of the product design, make the finalproduct improvement to meet requirements after on-orbit use, to long life and high reliableresults.