Evaluation of the Launch Vehicle Stiffened Bay Primary Structure Elements Longitudinal Sizes Effect on Their Endurance Limit

Аuthors

Zalyaev R. A.

Samara National Research University, Moskovskoe shosse, 34, Samara, Russia

e-mail: zalyaeffruslann@gmail.com

Abstract

The author studies the issue of the endurance limit dependence on the longitudinal dimensions of the space rocket-carrier stiffened section frame structural elements. Particularly, the lengthwise stiffeners (stringers) are considered as an example.
The article presents a brief overview of the existing studies. The said overview attests that the previous research inferences are of a limited range of application (such as concentration on a particular technical object or a branch of industry), as well as based on an experimental data with considerable amount of outliers while a simple least squares linear approximation approach applying to them. 
Besides, geometry of the unified fatigue samples was modeled with the SolidWorks CAD system to abide the rest equal conditions. Their dimensions correspond to the State Standard 25.502-79 except for the gauge zone length. The length-to-sample diameter ratio is assumed as 1–150, which is statistically equal to the range of the motor section height of a middle-class space intended rocket. Corresponding fatigue symmetrical bending tests were conducted with the SolidWorks Simulation structural strength analysis application. This program accounted for the plastic deformations impact on the dynamic behavior in case of sample large gauge lengths as well as probability of buckling in a bending form. The results revealed no clear dependence of the fatigue characteristics on the sample length. 
Checking calculation was performed in the final part of the work. The variable length I-shaped rectangular equal-flange beams have been tested under the identical loading conditions. The heavy-section stringers of such cross-section are being applied while re-mating the skin sections of high-tech rocket bays, attained by the optimal structural partition, the so called paneling. Virtual fatigue testing demonstrated that endurance limits for the beams of various lengths remained within a short range of approximately ±4% of the median, thus determining a good correlation between the unified and structural specimen results.
Thus, the research-based inference is that the structural endurance limit of a space rocket carrier stiffened section frame abstract element is basically constant and independent from its longitudinal dimensions if the length-to-transverse dimension ratio happens to be within the 1–150 interval. 

Keywords:

space intended rocket, motor section, frame, cyclic loading by the engine thrust, beam endurance limit, beam fatigue, longitudinal dimensions of the frame elements, virtual fatigue tests

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