一引言固体火箭发动机的喷管通过控制排气的膨胀使燃烧室产生的燃气能量有效地转换为动能,因而给飞行器提供推力。飞行器约65～75%的推力是将燃烧室产物在喷管喉部加速到声速所产生的,其余的推力是通过喷管扩散段产生的。通常喷管设计的目的是控制其膨胀程度使整个飞行器的航程和有效载荷在一定的外形、重量和成本的限度内达到最大。因此,喷管是飞行器的组成部分,不能独立于该系统使喷管最佳化。由于这种相互 I. INTRODUCTION The nozzle of a solid rocket motor effectively converts the gas energy produced by the combustion chamber into kinetic energy by controlling the expansion of the exhaust gas, thereby providing thrust to the aircraft. Approximately 65-75% of the thrust of the aircraft is generated by accelerating the product of the combustion chamber to the speed of sound at the throat of the nozzle, with the remainder of the thrust produced by the diffuser. The purpose of the nozzle design is usually to control its degree of expansion to maximize the range and payload of the entire aircraft within certain limits of shape, weight and cost. As a result, lances are an integral part of the aircraft and can not be optimized independently of the system. Because of this mutual