Abstract
For aircraft which move in the atmosphere, the angle of attack and angle of sideslip cannot be measured precisely. This limits the precision of guidance and control systems, so the flush air data sensing system module with navigation and temperature information is designed for atmosphere parameter calculation. In this work the traditional parameter calculation method is improved, and a new algorithm which combines pressure data, temperature data and navigation data to calculate the atmosphere parameters is proposed. A ground experiment test scheme with a simulated flight environment is designed and the measured data is fitted and filtered to complete the experiments. The flush air data sensing module gets pressure data and temperature data of the atmosphere with sensors, and the measured data is integrated with navigation information to calculate the aircraft parameters of the angle of attack, angle of sideslip, dynamic pressure, static pressure, Mach number and so on. Calculated parameters can be transmitted to guidance and control systems to improve the attitude and trajectory precision for an aircraft. Experimental results show that the software and hardware of the flush air data system module with navigation and temperature information work well, and communication of various devices is normal. The flight status of aircraft can be precisely calculated online, which provides a useful reference for prospective wind tunnel experiments and flight tests.
Highlights
The flush air data sensing module can be installed in front of a missile, so when the aircraft flies with different velocities and attitudes, the flow field near the pressure sensors will change according to the distributed position, the angle of attack, angle of sideslip, dynamic pressure, static pressure and Mach number can be derived by an algorithm
Taking measured data to verify if the data communication of the flush air data sensing module is normal or not, the system workflow can be verified, which provides a reference for prospective wind tunnel experiments and flight tests
Design and a verification scheme of a flush air data sensing module is proposed, and an overall composition scheme is designed in detail, simulation analysis and experimental verification are completed by proposed new algorithm with navigation information and temperature information
Summary
Publisher’s Note: MDPI stays neutral with regard to jurisdictional claims in published maps and institutional affiliations. The angle of attack and angle of sideslip are very important flight parameters [8]. Precise calculation of the angle of attack and angle of sideslip has great significance for the guidance, navigation and control of an aircraft. Airplanes generally use weathervane sensors to measure the angle of attack and angle of sideslip [9,10]. How to obtain flight parameters such as the angle of attack and angle of sideslip of missiles and rockets accurately is a difficult task at present, which has attracted many scholars to the study if this topic. A new algorithm is proposed with pressure sensors, temperature sensors and integrated navigation system, with which the angle of attack, angle of sideslip, dynamic pressure, static pressure and Mach number can be calculated online. The experimental results show that the proposed algorithm is reasonable and the whole system works according to the design plan, which can provide a reference for prospective wind tunnel experiments and flight tests
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
