基于有限设计指标的通用飞机起飞质量估算研究  

A Research on Take-off Weight Estimation of General Aircraft Based on Limited Design Requirements

作　　者：戴礼涛 周梅芳[1] DAI Litao;ZHOU Meifang(Jinhua Polytechnic,Jinhua 321007,China)

机构地区：[1]金华职业技术学院,浙江金华321007

出　　处：《金华职业技术学院学报》2024年第3期59-64,共6页Journal of Jinhua Polytechnic

摘　　要：飞机起飞质量是飞机初始设计的首要参数之一。在给出装载重量、最大航程、巡航速度和巡航高度等设计指标后,确定飞机的燃油质量比;结合经验公式,获得飞机的空机质量比,从而进一步迭代计算得到飞机的起飞质量。使用通用教练机DA42及公务机比奇“星舟”验证了估算方法有效性,结果显示估算的相对误差绝对值均在15%左右。所提出的估算方法结合了相关经验图表,在有限的设计指标下估算飞机起飞质量,且对机型没有过多的约束,可为新构型通用飞机的初步设计提供技术参考。The take-off weight of an aircraft is one of the primary parameters in the preliminary design of an aircraft.After giving the design requirements such as the payload,maximum range,cruising speed,and cruising altitude,the fuel mass ratio of the aircraft is determined by obtaining the mass ratio for each task segment.Combined with empirical formulas,the empty weight ratio of the aircraft is obtained,then the takeoff weight of the aircraft can be calculated iteratively.In the end,the effectiveness of the estimation method is validated by using the general training aircraft DA42 and business aircraft Beech Starship as examples.The absolute values of the relative errors are all around 15%.In this study,proposed estimation method combined with empirical charts are used to estimate take-off weight under limited design requirements without too much constraint on the aircraft type.It can provide technical references for the preliminary design of a new general purpose aircraft.

关 键 词：通用飞机 初步设计 起飞质量 飞机空重 燃油质量比 

分 类 号：V221.5[航空宇航科学与技术—飞行器设计]