The invention discloses a rapid
analysis method for the sensitivity of a carrier
rocket first-stage and second-stage separation model, and aims to efficiently and accurately analyze the influence of key parameters on the overall performance in the carrier
rocket first-stage and second-stage
separation process. The method comprises the following specific steps: firstly, establishing a carrier
rocket first-stage and second-stage separation model by utilizing Mworks
software, wherein the model comprises a plurality of models such as a carrier rocket first-stage
rigid body model, a carrier rocket second-stage
rigid body model, a thrust model and a separation mechanism model; secondly, through an FMU interface, the Mworks model is imported into an
MATLAB environment, and
simulation setting is carried out on the Mworks model through Simulink; thirdly, performing parameter setting on a plurality of key parameters (such as thrust change,
centroid offset,
mass size and the like) in the first-stage and second-stage
separation process; fourthly, calling a Simulink model to obtain a
simulation result; and finally, analyzing the sensitivity of different parameters to the first-stage and second-stage separation results of the carrier rocket through a Sobol
global sensitivity analysis method. The method not only improves the speed and precision of
sensitivity analysis, but also simplifies the working process through seamless integration of Mworks and
MATLAB. In addition, the invention also provides
visual sensitivity analysis result
visualization, so that designers can visually understand the influence of parameter change on the
separation process, thereby accelerating the design and iterative optimization process of the carrier rocket. In conclusion, the rapid
sensitivity analysis method for the first-stage and second-stage separation model of the carrier rocket is efficient and accurate, and powerful
technical support is provided for design and performance optimization of the carrier rocket.