Installation for combined loading of shell structures of aircraft and rocket in static strength and hardness tests

Abstract

The process of designing and creating aircraft and missiles consists of a complex set of calculation and experimental studies. The need to substantiate the strength of the structure is one of the key tasks during certification and commissioning. Therefore, the final stage in the preparation of the conclusion on airworthiness is full-scale static testing of the experimental model of the apparatus. Thus, the calculation-experimental approach is a continuous and interconnected process of working out strength. The principle of operation of the installation for combined loading of shells during strength and stiffness tests, which uses four loading devices, is considered. As a result of the analysis of shortcomings, the task of increasing the efficiency of the installation was set due to more efficient use of the power of loading devices and expansion of opportunities in the implementation of real load conditions of structures by ensuring the possibility of changing the relationship between force factors over time directly during the combined load, as well as simplifying the control system. A distinctive feature of such an installation is the possibility of carrying out all simple and combined loads sequentially in time on the same shell without reassembling the installation. The effectiveness of the considered installation consists in the ability to simulate different calculated cases of operational load on the same material part in time. This, on the one hand, increases the reliability of the obtained experimental information about the stress-deformed state of the shell structure and, on the other hand, reduces the number of products allocated for experimental work-up of strength and reliability, which saves material and financial resources.