防区外机载布撒器总体设计关键技术研究

【作者】 李健；

【导师】 谷良贤；

【作者基本信息】 西北工业大学 ， 飞行器设计， 2003， 硕士

【摘要】 本文是结合某型防区外机载布撒器的战术技术要求开展的防区外机载布撒器总体设计方面的一些预研工作。完成的工作主要包括两个方面：一是非圆截面弹身飞行器的空气动力估算的方法研究；二是弹用涡轮发动机计算机辅助稳态性能计算与分析系统设计。这是防区外机载布撒器总体方案初步设计阶段需要解决的两个关键技术。 本文第二章在分析了非圆截面弹身飞行器气动特性的基础上，建立了一套非圆截面弹身飞行器气动估算方法：用等效圆截面弹身飞行器的气动特性来等效非圆截面弹身飞行器的气动特性，并引入非圆截面修正因子（非圆因子、翼身干扰因子修正系数和牛顿修正因子）加以修正。然后利用细长体理论推导出了非圆因子F_SB和翼身干扰因子修正系数足K_c的表观面积表达式，并通过构造了一种基本解——二维常值偶极子分布线元，建立了任意形状截面表观面积的计算模型。最后用算例验证了本文所提出的表观面积计算方法和非圆截面修正因子计算方法，证明了这种方法的正确性和准确性。 本文第三章首先建立了弹用涡轮发动机（包括涡喷和涡扇发动机）稳态性能计算的数学模型，然后以此为基础设计开发了弹用涡轮发动机计算机辅助稳态性能计算与分析系统，给出了系统的功能设计、程序结构、操作步骤。最后用两个算例验证了这一系统的正确性和方便实用性，这一系统可以用于导弹总体方案初步设计阶段发动机稳态性能的计算。更多还原

【Abstract】 This paper is some advanced research work on conceptual design of standoff airborne spreader according to tactical and technical requirements of a certain standoff airborne spreader. The completed work includes two aspects: one is the method study of aerodynamic estimation of aircraft with noncircular shape cross section body; the other is the design and development of computer-aided steady-state performance analysis system of turbine engines used in missiles. These two aspects are key technology need to be solved in the phase of overall project preliminary design of standoff airborne spreader.In chapter 2, a set of aerodynamic estimation methods of aircraft with noncircular shape cross section body are established based on the analysis of aerodynamic characteristic of aircraft with noncircular shape cross section body. The methods used the aerodynamic estimation method of aircraft with circular shape cross section body to calculate the aerodynamic characteristic of aircraft with noncircular shape cross section body by inducing noncircular shape cross sectionadjustment factors (including noncircular shape factor FSB , coefficient Kc of correction of the interference factor between wing and body Kc, and Newton adjustment factor Fm.). Then the mathematic expressions of calculating Fsa andKc are derived, and the computational model to calculate the apparent area ofarbitrary shape cross section is established by constructing a new basic solution: two-dimensional constant dipole distributing linear element. The examples in this chapter validate the correctness and accuracy of the methods.In chapter 3, the computational model to calculate the steady-state performance of turbine engines (including turbojet engine and turbofan engine) used in missiles is established firstly, and then the computer-aided steady-state performance analysis system of turbine engines used in missiles is designed and realized, and the functional design, program structure and operational procedure of the system are given. And finally the system is proved to be correct, convenient and practical by two examples given in this paper, and so it can be used for the steady-state performance calculation of turbine engine in the phase of overall project preliminary design.更多还原