A manned aircraft landing auxiliary decision-making system and method

By using the aircraft status and environmental information perception module and the trajectory planning and decision-making system, the problem of inaccurate aircraft landing trajectories has been solved, enabling precise flight control and safe landing, adapting to various complex scenarios, and reducing the risk of human error.

CN119882814BActive Publication Date: 2025-12-02SHENYANG AEROSPACE UNIVERSITY
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Patent Information

Application Number
CN202510056542.9
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2025-01-14
Publication Date
2025-12-02
Estimated Expiration
2045-01-14

AI Technical Summary

Technical Problem

Traditional aircraft landings rely on pilot experience, which is subject to uncertainty and human factors, resulting in inaccurate landing trajectories and increased risks. Existing automated assistance systems are not perfect in complex scenarios.

Method used

Design a landing assistance decision system for manned aircraft, including an aircraft status and environmental information perception module, a landing trajectory planning and command decision module, and a data interaction module. It uses multiple sensors to acquire accurate data, adopts an exponentially flattened trajectory method and a command decision algorithm to plan the optimal glide path, and provides flight decision suggestions through a data visualization interface.

Benefits of technology

It enables precise planning and stable control of aircraft landing trajectories, reduces the risk of human error, improves landing accuracy and safety, adapts to complex and ever-changing scenarios, reduces pilot workload, and enhances comfort and safety.

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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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