Thrust and Thermal Characteristics of Electromagnetic Launcher Based on Permanent Magnet Linear Synchronous Motors

• Published in: IEEE transactions on magnetics Vol. 45; no. 1; pp. 358 - 362
• Main Authors: KOU BAO QUAN, HUANG XU ZHEN, WU, Hong-Xing, LI, Li-Yi
• Format: Journal Article Conference Proceeding
• Language: English
• Published: New York, NY IEEE 01.01.2009; Institute of Electrical and Electronics Engineers; The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
• Subjects: Acceleration; Aircraft; Circuit analysis; Cross-disciplinary physics: materials science; rheology; Current density; Electromagnetic launching; Electromagnetism; EML; Exact sciences and technology; Launchers; linear motor; Magnetic analysis; Magnetic circuits; Magnetism; Materials science; Mathematical models; Other topics in materials science; Permanent magnets; Physics; Poles; Rockets; Studies; Synchronous motors; Temperature; Temperature distribution; temperature rise; Thrust; thrust force; Two dimensional; Electromagnetic devices; Temperature; Electromagnetic launchers; EML; temperature rise; Synchronous motors; Permanent magnets; Launching; thrust force; Magnetic properties; linear motor
• ISSN: 0018-9464; 1941-0069
• DOI: 10.1109/TMAG.2008.2008883

Compared with steam catapult system, electromagnetic launcher (EML) system is highly integrated, and it has high and well matching performance. It will be widely used aircraft carriers ejection, rocket launchers etc in future. Double-side tabular permanent magnet linear synchronous motor (PMLSM) for electromagnetic launcher can meet the requirements of big thrust and high efficiency etc. It can accelerate the launcher at the expected speed in short time. The thrust characteristic of the launcher is essential to the whole electromagnetic launcher system. Large thrust and small thrust ripple are both expected. This paper studies thrust characteristic of different pole arc coefficients, compares the series and parallel magnetic circuit structures, and analyses the method of staggering a certain distance between poles on both sides. In order to achieve the goal of large thrust, the launcher is often designed with high current density. As a result, it is of great loss and has quick temperature rise. This paper establishes numerical model of the two-dimensional (2D) primary transient temperature field. The temperature field of the short-term system is analyzed. The calculated and experimental results of the electromagnetic launchers can provide a basis for optimum design.