机动飞机／发动机设计参数的一体化选择  

AN INTEGRATED SELECTION OF DESIGN PARAMETERS FOR AIRPLANE/ENGINES WITH HIGH MANEUVERABILITY

作　　者：张津[1] 陈大光[1] 汪家芸 朱一锟 朱之丽[1] 

机构地区：[1]北京航空航天大学动力系

出　　处：《推进技术》1996年第6期18-23,共6页Journal of Propulsion Technology

摘　　要：发展了一种机动飞机／发动机设计参数的一体化选择方法和软件。根据机动飞机的飞行任务要求，确定设计目标和约束，其中包括飞机性能约束和发动机部件设计约束，并以此对飞机的主要设计参数和发动机循环参数进行一体化优选。该软件由飞机几何、飞机质量、飞机气动性能、发动机非安装和安装性能、发动机质量和外廓尺寸、飞机性能、优化等模块组成。此软件已应用于已有机动飞机／发动机的改型方案论证和未来高机动飞机／发动机方案的分析研究，本文给出部分计算实例。使用此软件的经验表明，计算结果合理，计算精度和所需时间适合于飞机／发动机系统方案论证和初步设计。An integrated design parameter selection method and software for the airplane/engines with high maneuverability were developed. Determining design merits and constraints including flight performance constraints and engine component design constraints on the basis of the mission requirements for fighter, the integrated selection and optimization of airplane/engine design Parameters were conducted. The software consists of airplane geometry and weight, airplane aerodynamics, engine uninstalled and installed performance, engine weight and overall dimension, flight performance and optimization modules.The software has been applied to the concept demonstration for the existing airplane/engine modification, analysis and study of the integrated design for future airplane/engines with high maneuverability. borne examples are presented. It is shown with experience that the calculating results were reasonable, accuracy and the executing time were suitable to concept demonstration and preliminary design for airplane/engine system.

关 键 词：航空发动机 发动机设计 一体化设计 参数最优化 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] V221.6