机身壁板在拉伸、压缩、剪切、气压等多种载荷形式下的静强度及耐久性/损伤容限是飞机强度研究中的重要课题，以往的试验技术仅能模拟机身壁板在以上几种载荷单独或联合作用下的均匀应力/应变场。然而飞机机身在舱门或舷窗等大开口结构周围的应力分布十分复杂，单一载荷或少数几种载荷的叠加无法准确模拟复杂的应力场。为了实现对机身壁板大开口结构周围应力分布的准确模拟，开展了大型机身壁板复杂应力场试验技术研究，研发了一套多载荷联合施加试验装置，具有单独或联合施加轴向（拉伸/压缩）、弯曲、面内剪切、端部剪切、地板梁（轴力和弯曲）及气压载荷的能力，各载荷施加系统相互解耦无干涉，通过优化计算各类载荷比例，并按比例联合施加各载荷可使考核区的应力/应变分布与全机有限元解保持一致。经静力和疲劳试验验证，本试验技术和装置能够实现对机身壁板复杂应力/应变状态的准确模拟。
The static strength and durability/damage tolerance of fuselage panels under various forms of loads such as tension,compression, shear, and air pressure are important topics in aircraft strength research. The previous test technology can only simulate the uniform stress/strain field of fuselage panels under the above loads alone or combined. However, the complex stress distribution of aircraft fuselage around large openings such as hatches or portholes makes it difficult to accurately simulate the complex stress field by a single load or the superposition of a few loads. To realize accurate simulation of the stress distribution around the large opening structure of the fuselage panel, the complex stress field test technology of large fuselage panels was studied, and a set of multi-load joint application test facility was developed to independently or jointly apply axial (tension/compression), bending, in-plane shear, end shear, floor beam (axial force and bending) and air pressure loads. Each load application system is decoupled from each other without interference. The stress/strain distribution in the test area can be consistent with the finite element solution of the complete aircraft by optimizing the proportion of various loads and applying them together according to the proportion. The static and fatigue tests show that the test technology and facility can accurately simulate the complex stress/strain state of fuselage panels.
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