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Experimental Investigation on Indicated Pressure and Heat Release for Direct Hydrogen Injection in a Dual Fuel Diesel Engine

100%

Siadkowska K. , Barański G. , Sochaczewski R. , Wendeker M.

tom Vol. 16, no 3

54--66

This paper presents the research results for a diesel and hydrogen fueled engine. The research object is a four-cylinder, four-stroke ADCR engine with a displacement of 2,636 cm3. In the experiments, glow plugs were replaced with compressed hydrogen injectors and a special adapter. Hydrogen was supplied directly into a combustion chamber using a test injector. A hydrogen dose in the tests was changed at selected test points and ranged from 0 to 160 dm3/min. The research were conducted at 1,500 rpm. A hydrogen injection start angle and maximum hydrogen dose were specified from the preliminary experiments. The following parameters were analyzed: indicated mean effective pressure, maximum pressure, crank angle of maximum cylinder pressure occurrence and heat release. The obtained results were statistically analyzed. The conducted analysis focused on determining whether there are significant differences between early and late injection and how these changes affect the measured parameters.

Deformation measurement system for UAV components to improve their safe operation

75%

Czyż Z. , Jakubczak P. , Podolak P. , Skiba K. , Karpiński P. , Droździel-Jurkiewicz M. , Wendeker M.

tom Vol. 25, no. 4

art. no. 172358

The paper presents the authors’ method and test rig for performing the deformation analysis of unmanned aircraft fuselages. To conduct the analysis, the DIC system was used, as well as a test rig designed and constructed by the authors, equipped with a dedicated control and load control system. The article presents a description of the research capabilities of the test rig developed for testing the deformation of unmanned aircraft fuselages. Due to the specific operating conditions of the designed fuselage,the test rig developed allows the simulation of loads corresponding to different flight conditions. In addition, it is possible to change the forces acting on the fuselage simultaneously for all servos or each of them separately. Finally, results showing the displacement of component control points for the considered fuselage versions are presented. The tests carried out using the developed test rig allowed the verification of the maximum deformations. The two versions of the composite fuselage of an aerial vehicle have been compared in the paper. The created measurement system and performed analyzes have enabled us to identify and quantitatively analyze the weaknesses of the construction. The results have enabled us to geometrically modify the constructionso the mass of the fuselage reduced by 19% and a coefficient of construction balance increased by 22%.