This disclosure provides a method for controlling a hoisting mechanism used to lift an aircraft in
near space, comprising: setting the
ultimate load that the aircraft must meet under target operating conditions based on risk factors that may cause abnormalities in the aircraft; establishing a finite
element model to characterize the aircraft to be lifted and the hoisting mechanism used to lift the aircraft, and using the
ultimate load as the excitation input of the finite
element model to calculate the mechanical
simulation under the target operating conditions to obtain displacement
simulation data of the aircraft under the target operating conditions; manufacturing a
solid scale-down model including the aircraft and the hoisting mechanism; adjusting the hoisting
rope structure with the structural strength of the
solid scale-down model of the aircraft as the limit, so that the
solid scale-down model of the aircraft can switch between
multiple target operating conditions, and constructing the allowable force envelope of each hoisting
rope of the hoisting
rope structure; controlling the hoisting mechanism carrying the aircraft based on the allowable force envelope of each hoisting rope, so that the aircraft can switch between
multiple target operating conditions, from the lifting stage to the release stage.