A method for calculating aircraft mission profile performance based on inverse integral

Abstract

This invention discloses a method for calculating aircraft mission profile performance based on inverse integration, belonging to the field of flight control technology. The method includes: first, constructing an original computational model of the UAV, configuring the mission profile matrix, and determining the unknown free segments and computational priorities; obtaining the initial key parameter attribute matrix of the unknown free segment through forward integration, and obtaining the final key parameter attribute matrix of the unknown free segment through inverse integration; solving for the performance of the unknown free segment based on the initial and final parameters; and finally, superimposing the parameter matrices of each stage to complete the mission profile combination modeling and obtain the overall flight performance. This invention combines forward and inverse integration, requiring only the construction of a lightweight parameter model, resulting in high computational efficiency, good accuracy, and strong versatility. It can efficiently solve the mission profile performance of various aircraft and is suitable for scenarios with rapid generation and real-time changes in mission profiles.

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