The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
Apr. 21, 2025
Filed:
Dec. 04, 2024
Shenzhen Polytechnic University, Guangdong, CN;
Xuan Peng, Guangdong, CN;
Shan Lu, Guangdong, CN;
Zhijiang Lou, Guangdong, CN;
Sen Xie, Guangdong, CN;
Fengli Dai, Guangdong, CN;
Shenzhen Polytechnic University, Shenzhen, CN;
Abstract
The invention provides an aircraft attitude tracking control method, system and computer equipment, which belongs to the field of aircraft attitude control, comprising: obtaining aircraft operating parameters and establishing a kinematic model of the attitude tracking error of the aircraft. A specified time performance constraint function and attitude error boundary based on the hyperbolic cosecant composite function are then constructed. A constrained attitude error conversion function and its inverse function are utilized to obtain an unconstrained attitude tracking conversion error. Virtual control instructions are solved in kinematics using a sigmoid tracking differentiator to obtain a numerical derivative. The control moment in the dynamics is solved and the complete form of the attitude tracking algorithm is given for the aircraft attitude tracking system. This method provides a computationally efficient means of controlling aircraft to ensure that error convergence is achieved within a preset time.