title: Ð Ð°ÑÑÐµÑ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ¸ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ ÑÑÑÐµÐ»Ð¾Ð²Ð¸Ð´Ð½Ð¾Ð³Ð¾ ÐÐÐÐ
title: Ð²ÑÐ¿ÑÑÐºÐ½Ð°Ñ ÐºÐ²Ð°Ð»Ð¸ÑÐ¸ÐºÐ°ÑÐ¸Ð¾Ð½Ð½Ð°Ñ ÑÐ°Ð±Ð¾ÑÐ° Ð±Ð°ÐºÐ°Ð»Ð°Ð²ÑÐ°
titleType: Subtitle
title: Calculation of the structural strength of a swept UAV
Creators: name: ÐÐ¾ÑÑÑÑÐºÐ¾Ð², ÐÐ°Ð²ÐµÐ»
Publisher: name: Ð¡Ð°Ð½ÐºÑ-ÐÐµÑÐµÑÐ±ÑÑÐ³ÑÐºÐ¸Ð¹ Ð¿Ð¾Ð»Ð¸ÑÐµÑÐ½Ð¸ÑÐµÑÐºÐ¸Ð¹ ÑÐ½Ð¸Ð²ÐµÑÑÐ¸ÑÐµÑ ÐÐµÑÑÐ° ÐÐµÐ»Ð¸ÐºÐ¾Ð³Ð¾
Year: 2024
Subjects: Ð±ÐµÑÐ¿Ð¸Ð»Ð¾ÑÐ½ÑÐ¹ Ð»ÐµÑÐ°ÑÐµÐ»ÑÐ½ÑÐ¹ Ð°Ð¿Ð¿Ð°ÑÐ°Ñ
Ð¿Ð¾Ð»Ð¸Ð¼ÐµÑÐ½ÑÐµ ÐºÐ¾Ð¼Ð¿Ð¾Ð·Ð¸ÑÐ¸Ð¾Ð½Ð½ÑÐµ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð»Ñ
ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð²Ð½Ð¾-ÑÐ¸Ð»Ð¾Ð²Ð°Ñ ÑÑ ÐµÐ¼Ð°
ÐºÐ¾Ð½ÐµÑÐ½Ð¾-ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ½ÑÐ¹ Ð°Ð½Ð°Ð»Ð¸Ð·
ÑÑÐ°ÑÐ¸ÑÐµÑÐºÐ¾Ðµ Ð½Ð°Ð³ÑÑÐ¶ÐµÐ½Ð¸Ðµ
Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÑ
ÐºÑÐ¸ÑÐµÑÐ¸Ð¹ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ¸
ÑÑÑÐ¾Ð¹ÑÐ¸Ð²Ð¾ÑÑÑ
unmanned aerial vehicle
polymer composite materials
structural and power scheme
finite element analysis
static loading
strength
strength criterion
stability

description: Ð Ð´Ð°Ð½Ð½Ð¾Ð¹ ÑÐ°Ð±Ð¾ÑÐµ Ð¿ÑÐ¾Ð²ÐµÐ´ÑÐ½ ÑÐ°ÑÑÐµÑ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ¸ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ ÐÐÐÐ Ð³Ð¸Ð±ÑÐ¸Ð´Ð½Ð¾Ð¹ ÐºÐ¾Ð¼Ð¿Ð¾Ð½Ð¾Ð²ÐºÐ¸ Ñ Ð¿ÑÐ¸Ð¼ÐµÐ½ÐµÐ½Ð¸ÐµÐ¼ ÐºÐ¾Ð½ÐµÑÐ½Ð¾-ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ½Ð¾Ð³Ð¾ Ð°Ð½Ð°Ð»Ð¸Ð·Ð°. ÐÐ¾ÑÑÑÐ¾ÐµÐ½Ð° ÐºÐ¾Ð½ÐµÑÐ½Ð¾-ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ½Ð°Ñ Ð¼Ð¾Ð´ÐµÐ»Ñ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð²Ð½Ð¾-ÑÐ¸Ð»Ð¾Ð²Ð¾Ð¹ ÑÑÐµÐ¼Ñ Ð»ÐµÑÐ°ÑÐµÐ»ÑÐ½Ð¾Ð³Ð¾ Ð°Ð¿Ð¿Ð°ÑÐ°ÑÐ°. ÐÑÐ¾Ð²ÐµÐ´ÐµÐ½Ð¾ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ðµ Ð¿Ð¾Ð²ÐµÐ´ÐµÐ½Ð¸Ñ Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð¿Ð¾Ð»Ð¸Ð¼ÐµÑÐ½Ð¾Ð³Ð¾ ÐºÐ¾Ð¼Ð¿Ð¾Ð·Ð¸ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð»Ð° Ð¿ÑÐ¸ ÑÐ°ÑÑÑÐ¶ÐµÐ½Ð¸Ð¸, ÑÐ¶Ð°ÑÐ¸Ð¸ Ð¸ ÑÐ´Ð²Ð¸Ð³Ðµ. Ð ÑÐ¾Ð´Ðµ ÑÐ°Ð±Ð¾ÑÑ ÑÐµÑÐ°Ð»Ð¸ÑÑ ÑÐ»ÐµÐ´ÑÑÑÐ¸Ðµ Ð·Ð°Ð´Ð°ÑÐ¸: 1. ÐÐ·ÑÑÐµÐ½Ð¸Ðµ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ½ÑÑ ÑÐ²Ð¾Ð¹ÑÑÐ² Ð¼Ð¾Ð´ÐµÐ»Ð¸ Ð¿Ð¾Ð»Ð¸Ð¼ÐµÑÐ½Ð¾Ð³Ð¾ ÐºÐ¾Ð¼Ð¿Ð¾Ð·Ð¸ÑÐ¸Ð¾Ð½Ð½Ð¾Ð³Ð¾ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð»Ð°. 2. Ð¡Ð¾Ð·Ð´Ð°Ð½Ð¸Ðµ ÑÐ°Ð·Ð»Ð¸ÑÐ½ÑÑ ÑÐ¸Ð¿Ð¾Ð² ÑÐºÐ»Ð°Ð´ÐºÐ¸ ÐºÐ¾Ð¼Ð¿Ð¾Ð·Ð¸ÑÐ½ÑÑ Ð¼Ð°ÑÐµÑÐ¸Ð°Ð»Ð¾Ð² Ð² ÑÑÐ½Ð´Ð²Ð¸Ñ-Ð¿Ð°Ð½ÐµÐ»ÑÑ Ð¸ Ð¼Ð¾Ð½Ð¾Ð»Ð¸ÑÐ½ÑÑ ÑÐ³Ð»ÐµÐ¿Ð»Ð°ÑÑÐ¸ÐºÐ°Ñ. 3. Ð Ð°Ð·ÑÐ°Ð±Ð¾ÑÐºÐ° ÐºÐ¾Ð½ÐµÑÐ½Ð¾-ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ½Ð¾Ð¹ Ð¼Ð¾Ð´ÐµÐ»Ð¸ ÐÐÐÐ Ð´Ð»Ñ Ð¸ÑÑÐ»ÐµÐ´Ð¾Ð²Ð°Ð½Ð¸Ñ ÐµÐ³Ð¾ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ½ÑÑ ÑÐ°ÑÐ°ÐºÑÐµÑÐ¸ÑÑÐ¸Ðº. 4. ÐÑÐµÐ½ÐºÐ° Ð¿Ð¾Ð»ÑÑÐµÐ½Ð½ÑÑ ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐ¾Ð² Ð¿Ð¾ ÐºÑÐ¸ÑÐµÑÐ¸Ñ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ¸ Ð¦Ð°Ñ-ÐÑ. ÐÑÑÐ¸ÑÐ»ÐµÐ½Ð¸Ñ Ð¿ÑÐ¾Ð²ÐµÐ´ÐµÐ½Ñ Ð½Ð° Ð¾ÑÐ½Ð¾Ð²Ðµ Ð³Ð¾ÑÑÐ´Ð°ÑÑÑÐ²ÐµÐ½Ð½ÑÑ ÑÑÐ°Ð½Ð´Ð°ÑÑÐ¾Ð² Ð¸ Ð½Ð¾ÑÐ¼Ð°Ñ Ð»ÐµÑÐ½Ð¾Ð¹ Ð³Ð¾Ð´Ð½Ð¾ÑÑÐ¸ Ð´Ð»Ñ Ð±ÐµÑÐ¿Ð¸Ð»Ð¾ÑÐ½ÑÑ Ð°Ð²Ð¸Ð°ÑÐ¸Ð¾Ð½Ð½ÑÑ ÑÐ¸ÑÑÐµÐ¼ [1 â 3, 7]. Ð ÑÐµÐ·ÑÐ»ÑÑÐ°ÑÐµ ÑÐ°ÑÑÐµÑÐ¾Ð² Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ð¾ Ð½Ð°Ð¿ÑÑÐ¶ÐµÐ½Ð½Ð¾-Ð´ÐµÑÐ¾ÑÐ¼Ð¸ÑÐ¾Ð²Ð°Ð½Ð½Ð¾Ðµ ÑÐ¾ÑÑÐ¾ÑÐ½Ð¸Ðµ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ Ð¿ÑÐ¸ Ð´ÐµÐ¹ÑÑÐ²Ð¸Ð¸ ÑÐ°ÑÑÐµÑÐ½Ð¾Ð¹ Ð½Ð°Ð³ÑÑÐ·ÐºÐ¸, Ð¾Ð¿ÑÐµÐ´ÐµÐ»ÐµÐ½Ñ Ð·Ð°Ð¿Ð°ÑÑ ÑÑÐ°ÑÐ¸ÑÐµÑÐºÐ¾Ð¹ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ¸, Ð·Ð°Ð¿Ð°ÑÑ Ð¿ÑÐ¾ÑÐ½Ð¾ÑÑÐ¸ Ð¿Ð¾ ÑÑÐ»Ð¾Ð²Ð¸ÑÐ¼ ÑÑÑÐ¾Ð¹ÑÐ¸Ð²Ð¾ÑÑÐ¸ ÑÐ»ÐµÐ¼ÐµÐ½ÑÐ¾Ð² ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸, Ð½ÐµÑÑÑÐ°Ñ ÑÐ¿Ð¾ÑÐ¾Ð±Ð½Ð¾ÑÑÑ ÐºÐ¾Ð½ÑÑÑÑÐºÑÐ¸Ð¸ ÐÐÐÐ.
description: In this paper, the calculation of the design of a hybrid UAV layout for strength using finite element analysis is carried out. A finite element model of the structural and power circuit of the aircraft is constructed. The behavior of a polymer composite material model under tension, compression and shear has been studied. In the course of the work, the following tasks were solved: 1. Study of the strength properties of the polymer composite material model. 2. Creation of various types of laying composite materials in sandwich panels. 3. Development of a finite element model of a UAV to study its strength characteristics. 4. Evaluation of the results obtained according to the Tsai-Wu strength criterion. The calculations were carried out on the basis of state standards and airworthiness standards for unmanned aircraft systems [1-3, 7]. As a result of calculations, the stress-strain state of the structure under the action of the design load was determined, reserves of static strength, reserves of strength under the conditions of stability of structural elements, and the bearing capacity of the UAV structure were determined.