A manned aircraft landing auxiliary decision-making system and method

Abstract

This invention provides a landing assistance decision system and method for manned aircraft, relating to the field of aviation technology. The method specifically includes: acquiring the aircraft's current state data in real time and planning the aircraft's landing trajectory using an exponentially flattened trajectory method to determine the optimal glide path; based on the aircraft's current state data and optimal glide path, calculating the aircraft's desired attitude angles and desired thrust changes using a command decision algorithm, and performing attitude control on the aircraft according to the desired attitude angles, generating flight decision suggestions; wherein the attitude control is divided into two parts: one part uses angle control to calculate the desired three-dimensional angles and three-axis attitude angular velocities; the other part uses angular velocity control to calculate the three-axis attitude angular accelerations; the pilot controls the aircraft's flight trajectory according to the generated flight decision suggestions to ensure the aircraft lands along the optimal glide path. This invention aims to solve the problem of inaccurate landing trajectories during aircraft landing.

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