基于T型平尾结构的抖振载荷测量技术研究  

RESEARCH ON BUFFETING LOAD MEASUREMENT TECHNOLOGY BASED ON T-SHAPED FLAT TAIL STRUCTURE

作　　者：高通锋 张海涛[1] GAO Tongfeng;ZHANG Haitao(Chinese Flight Test Establishment,Xi'an 710089,China)

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《力学与实践》2023年第3期565-572,共8页Mechanics in Engineering

摘　　要：抖振载荷是飞机在进行高速、大机动飞行过程中经常遇到的一种载荷形式。针对T型平尾布局飞机,充分考虑结构的传力形式,采用应变法进行抖振载荷测量。基于抖振载荷特殊性,在工况设计时充分考虑了非对称载荷工况,建立的非对称载荷方程相比对称载荷方程精度有所提高,通过飞行试验分别计算了飞机在进行水平失速与30°转弯失速过程中结构抖振载荷,平尾根部最大剪力达到结构限制载荷的76.1%,弯矩达到限制载荷的61.6%,中央翼盒滚转力矩达到限制载荷的13.26%,获取的载荷数据不仅保证了飞机在进行大机动飞行科目时的飞行安全,同时为飞机结构设计提供了数据支持,此种方法同样满足于其他类似结构抖振载荷测量。The buffeting load is one of the load forms that are frequently present in the aircrafts during high-speed,large maneuvering flight.In considering the buffeting load characteristics and the force transmission form of a T-shaped tailplane aircraft,a non-symmetric load equation was proposed based on the buffeting load measured by the strain method.The calculation accuracy of this non-symmetric load equation was improved compared to the traditional symmetric equation.In this way,the structural buffeting loads during the horizontal stall test and 30°turning stall test of the aircraft were measured and calculated.Results show that the maximum shearing stress and the bending moment at the root of the tailplane reached 76.1% and the 61.6% of the limit,respectively.And the rolling moment of the central wing box was 13.26% of the limit.The load data obtained by the measurement and calculation not only ensures the flight safety of the aircraft when conducting the big maneuver flight subject,but also provides data support for the structural design of aircrafts.The proposed non-symmetric load equation is also suitable for the calculation of other similar structural buffeting load measurement.

关 键 词：抖振载荷 T型平尾 应变法 非对称 载荷方程 

分 类 号：V217.32[航空宇航科学与技术—航空宇航推进理论与工程]