摘要
用分析和模型试验方法难以确定可靠的尾翼载荷,所以要求通过飞行试验获取尾翼载荷数据,但因测载技术复杂,精确地测定尾翼载荷亦是困难的。我们经过多年的工作,最终用应变法得到了可贵的某型飞机尾翼机动载荷测量结果。本文叙述了测量方法,并给出了垂尾载荷的部分测量结果。根据该结果对垂尾的受载情况提出了值得重视的看法。
Airplane tail loads are difficult to determine accurately by means of model tests and theoretical analysis.In order to obtain reliable tail load data,it should be determined by flight tests. In this paper the technique for determining tail loads of a fighter under different flight conditions are presented.Correlations between tail load and strain response of some specific points of the tail structure are found by calibration tests on the ground. The strain responses of these specific points in flight tests uader some maneuver flight conditions are recorded.The maneuver loads on the tail are then found from the correlation equations. Some load data of the ve-rtical tail of this fighter are also given.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1989年第10期B474-B478,共5页
Acta Aeronautica et Astronautica Sinica
