ACOUSTIC EXPRESS METHOD FOR MEASURING ELASTIC METAL CONSTANTS OF HIGH-LOADED CONSTRUCTIONS WORKING IN EXTREME CONDITIONS. PART 1

2020 ◽  
pp. 46-63
Author(s):  
V. T. Bobrov ◽  
V. M. Bobrenko ◽  
A. V. Gulshin

A review of contingencies related to the failure of potentially hazardous equipment of the aviation and space-rocket complexes showed that they lead to explosions, fires, deaths and destruction of infrastructure. The causes of accidents and disasters are errors in the selection of technical solutions and materials during design, imperfection of algorithms and software for flight control systems, malfunctions in on-board computers and security systems, navigation systems, engine failure, defects in components and assemblies. Examples of accidents and disasters related to technical failures leading to a violation of the tightness of the aircraft fuselage and depressurization of spacecraft are given. It is shown that the main types of damage to the units are corrosion damage, fatigue and metal wear. The conclusion is made about the negative impact of the “human factor” regarding the adoption of erroneous decisions, failure to comply with regulatory requirements and actions in extreme situations. There is a risk of fatigue cracks and degradation of the properties of stringer metal, landing gear struts, wing tail trim, fuel tanks, engine pylon flanges, and imperfect methods, equipment, and technology for monitoring fatigue defects of critical components and mechanisms of aircraft, helicopters, and space systems. It is shown that modern achievements are poorly used in research and development of physical methods and diagnostics of elastic constants of metals working under high pressure, their changes in conditions of wide temperature drops, cosmic vacuum, vibration and other influences. It is proposed to combine efforts with scientists and experts in the field of strength, resource assessment and operational safety of aviation and space technology.

Author(s):  
Д.А. Смирнов ◽  
В.Г. Бондарев ◽  
А.В. Николенко

Проведен краткий анализ как отечественных, так и зарубежных систем межсамолетной навигации. В ходе анализа были отражены недостатки систем межсамолетной навигации и представлен актуальный подход повышения точности системы навигации за счет применения системы технического зрения. Для определения местоположения ведущего самолета предлагается рассмотреть в качестве измерительного комплекса систему технического зрения, которая способна решать большой круг задач на различных этапах, в частности, и полет строем. Систему технического зрения предлагается установить на ведомом самолете с целью измерения всех параметров, необходимых для формирования автоматического управления полетом летательного аппарата. Обработка изображений ведущего самолета выполняется с целью определения координат трех идентичных точек на фоточувствительных матрицах. Причем в качестве этих точек выбираются оптически контрастные элементы конструкции летательного аппарата, например окончания крыла, хвостового оперения и т.д. Для упрощения процедуры обработки изображений возможно использование полупроводниковых источников света в инфракрасном диапазоне (например, с длиной волны λ = 1,54 мкм), что позволяет работать даже в сложных метеоусловиях. Такой подход может быть использован при автоматизации полета строем более чем двух летательных аппаратов, при этом необходимо только оборудовать системой технического зрения все ведомые самолеты группы The article provides a brief analysis of both domestic and foreign inter-aircraft navigation systems. In the course of the analysis, we found the shortcomings of inter-aircraft navigation systems and presented an up-to-date approach to improving the accuracy of the navigation system through the use of a technical vision system. To determine the location of the leading aircraft, we proposed to consider a technical vision system as a measuring complex, which is able to solve a large range of tasks at various stages, in particular, flight in formation. We proposed to install the technical vision system on the slave aircraft in order to measure all the parameters necessary for the formation of automatic flight control of the aircraft. We performed an image processing of the leading aircraft to determine the coordinates of three identical points on photosensitive matrices. Moreover, we selected optically contrasting elements of the aircraft structure as these points, for example, the end of the wing, tail, etc. To simplify the image processing procedure, it is possible to use semiconductor light sources in the infrared range (for example, with a wavelength of λ = 1.54 microns), which allows us to work even in difficult weather conditions. This approach can be used when automating a flight in formation of more than two aircraft, while it is only necessary to equip all the guided aircraft of the group with a technical vision system


2022 ◽  
pp. 1-20
Author(s):  
Amin Basiri ◽  
Valerio Mariani ◽  
Giuseppe Silano ◽  
Muhammad Aatif ◽  
Luigi Iannelli ◽  
...  

Abstract Multi-rotor Unmanned Aerial Vehicles (UAVs), although originally designed and developed for defence and military purposes, in the last ten years have gained momentum, especially for civilian applications, such as search and rescue, surveying and mapping, and agricultural crops and monitoring. Thanks to their hovering and Vertical Take-Off and Landing (VTOL) capabilities and the capacity to carry out tasks with complete autonomy, they are now a standard platform for both research and industrial uses. However, while the flight control architecture is well established in the literature, there are still many challenges in designing autonomous guidance and navigation systems to make the UAV able to work in constrained and cluttered environments or also indoors. Therefore, the main motivation of this work is to provide a comprehensive and exhaustive literature review on the numerous methods and approaches to address path-planning problems for multi-rotor UAVs. In particular, the inclusion of a review of the related research in the context of Precision Agriculture (PA) provides a unified and accessible presentation for researchers who are initiating their endeavours in this subject.


1981 ◽  
Vol 25 (1) ◽  
pp. 590-590
Author(s):  
D. B. Beringer

Many contemporary human-machine systems are becoming increasingly automated. In some instances this automation is complete (robot-operated assembly lines). The Japanese automobile industry is a prime example of this type of implementation. In 1965 approximately 68 working hours were required to produce one subcompact automobile. Automation of press forming of sheet metals, casting, forging, welding, and engine assembly had reduced that number to approximately 25 by 1977. The military has also followed the trend towards automation with the development of the Patriot missle system, designed to identify targets, make engagement decisions, assign weapons, and lock on to and engage the target, all without human intervention. Other systems have been designed at the semi-automation level, allowing major portions of the overall task to be performed by machine/computer subsystems. This is evidenced in petrochemical plants where some control loops are closed and others are left open, requiring some intevention on a continuous basis by the operators. This same situation exists in airborne flight control and navigation systems. Although many of the subtasks are fully automated, the overall task requires some human intervention for successful completion. Reliability of these complex systems is less than perfect, however. In 1977 a test of the Worldwide Military Command and Control System (WMCCS) indicated a 62% failure rate. In 1980 the avionics systems on the F111-D managed to endure for an average of only 3 hours between failures, requiring an average of 33.6 maintenance man-hours per sortie. Perhaps one of the most recent, and memorable, examples was the episode during which the Space Shuttle onboard computers had such a serious argument that they refused to speak to one another… In some systems this eventual failure, ranging from slight performance decrement to catastrophic malfunction, can be dealt with by shutting down the system and affecting repairs. This luxury is usually not available in air transport where airborne failures require manual intervention for successful task completion. If the operator of a system has been removed from continuous or semi-continuous control for too long, serious degradation in skills is likely. Evidence of this problem has been observed in aviators; first officers qualified in a highly semi-automated aircraft experience difficulty when promoted to captain in an aircraft lacking these semi-automated systems. Similar problems have been observed in the petroleum industry when computers providing advisory information fail, forcing the operators to make production and process adjustments unaided. The operators, in both instances, have become dependent upon the automated subsystems through disuse of skills. Thus it would seem reasonable to assume that the quality of human intervention would be positively correlated with frequency of intervention, suggesting that the more reliable systems should suffer significantly during operator interventions. The three major operational skill categories involved in aircraft pilotage, continuous manual control, procedural control, and communications, should be examined in relation to three major areas of concern. First, it is necessary to determine how rapidly these skills deteriorate when unused and what factors (previous learning, skill category) influence that deterioration. Second, one must discover what measures may be effective in the prevention or reduction of such deterioration. This includes assessment of simulator utility, both part- and whole-task. Finally, means must be devised to assess the quality of skill retention in order to assure that the implementation of skill-retention strategies continues to be effective. The goal of the current program in this area is to establish task, training, and system design criteria that will allow the system operator to maintain a high level of proficiency without imposition of elevated workloads or meaningless “busy-work” tasks.


Author(s):  
Norma B. Crosby

It has been more than half a century since humans first ventured into space. While competing in being the first to land on the Moon, they learned to utilize space for human needs on Earth (e.g., telecommunications, navigation systems). Many space technologies were later applied to basic needs on Earth. Space research and development led to the “transfer of technology” in non-space sectors and became better known as “spin-offs.” They have improved global modern life in many ways. This paper discusses the cost-benefit of space technology spin-offs, as well as the relationships between various space agencies, spin-offs, and commercial enterprises. Other benefits that have come out of space exploration such as psychological, political and environmental effects are also reviewed, as well as the potential future benefits of going to space. Technologies developed for harsh environments on Earth and for those in space benefit all and collaborating both ways is the future.


Author(s):  
K M Holford ◽  
R Pullin ◽  
S L Evans ◽  
M J Eaton ◽  
J Hensman ◽  
...  

Structural health monitoring (SHM) is of paramount importance in the aircraft industry: not only to ensure the safety and reliability of aircraft in flight and to ensure timely maintenance of critical components, but also increasingly to monitor structures under test for airworthiness certification of new designs. This article highlights some of the recent advances in the acoustic emission (AE) technique as applied to SHM, and the new approaches that are crucial for the successful use of AE data for diagnostic purposes. These include modal analysis, enhanced location techniques, and novel signal processing approaches. A case study is presented on a landing gear component undergoing fatigue loading in which a linear location analysis using conventional techniques identified the position of fracture and final rupture of the specimen. A principal component analysis approach was used to separate noise signals from signals arising from fatigue cracks, which identified and located further fatigue crack positions, subsequently confirmed by magnetic particle inspection. Kernel probability density functions are used to aid visualization of the damage location.


2014 ◽  
Vol 488-489 ◽  
pp. 66-69
Author(s):  
Xu Dong Li ◽  
Zeng Jie Cai ◽  
Zhi Tao Mu

This paper investigates the growth behavior of fatigue cracks initiated at corrosion pits in laboratory coupons of LC9 aluminum alloy subjected to a transport aircraft loading spectrum. Corrosion pits were introduced by exposing the coupons to EXCO solution for a variety of periods to produce corrosion damage varying from mild to severe. In general, the presence of corrosion damage reduced the fatigue lives of components to a severe extent. It was found that the depth of the corrosion pit was a suitable parameter for characterizing the corrosion damage and for predicting the fatigue life of the coupons using commercial fatigue crack growth software


Aviation ◽  
2007 ◽  
Vol 11 (2) ◽  
pp. 23-30 ◽  
Author(s):  
Jan Gruszecki ◽  
Andrzej Tomczyk ◽  
Boguslaw Dołega ◽  
Tomasz Rogalski ◽  
Pawel Rzucidło

The development of informatics and sensor techniques has extended the possibilities of flight parameter measurement. It allows for extensive modification of control and navigation systems in air vehicles. This advance can also be noticed in the research of the Department of Avionics and Control at the Faculty of Mechanical Engineering and Aeronautics, Rzeszow University of Technology. Research in the area of digital flight control systems was initiated at the Department of Avionics and Control over twenty years ago.


2019 ◽  
Vol 33 ◽  
pp. 11-18 ◽  
Author(s):  
A.M. Al-Mukhtar

Fatigue plays a significant role in the crack growth of the fuselage skin structures. In addition, the fuselage may suffer also from the corrosion damage, and the wear defects. The proper maintenance and scheduled test intervals can avoid the sudden skin failure. Therefore, the inspection interval has to be shortened. Nevertheless, the young machines may be also suffering from the unexpected skin rupture. The cracks are emanating from the rivets and the holes under cyclic loading. The stress concentration around the notch has an effective role under the effect of cyclic loading. The cracks propagate toward the high stressed area such as the notches or other crack locations. The propagation into a critical crack size is rather fast and causes a sudden aircraft fuselage cracking. Hence, the number of cycles to failure will be decreased dramatically. During the last decades, the fracture toughness, design, and the new alloying element have been enhanced. The previous fuselage failures show that the inspections against the cracking are recommended even after a few thousand of cycles. To prevent the crack extending, the crack arresting is recommended to use around the fuselage.


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