Jiri Hlinka

This study presents a comprehensive approach to operational estimation of the zones of danger for the Unmanned Aerial Systems (UASs) generated at low altitudes in presence of buildings, aimed at ensuring their safer operation. The main tasks are three. The first one is the definition of an inboard measurement methodology appropriate and feasible for UAS that allows Eddy Dissipation Rate (EDR) estimation. An inboard setup with a lightweight and low-cost anemometer operating at a 1 Hz sampling rate, immediately usable on UAS, is proposed. The second one is the definition of empirical equations to estimate the size of dangerous areas for the UAS flights around buildings through numerical simulation. The third one is the validation of the empirical formulas in a real-world case, through the numerical simulation of a group of buildings belonging to a research centre. Results show a good resemblance in the size of the danger zones, highlighting that this multi-faceted approach contributes to enhanced safety protocols for UASs operating in urban environments.

With the aim of increasing the efficiency of maintenance and fuel usage in airplanes, structural health monitoring (SHM) of critical composite structures is increasingly expected and required. The optimized usage of this concept is subject of intensive work in the framework of the EU COST Action CA18203 “Optimising Design for Inspection” (ODIN). In this context, a thorough review of a broad range of energy harvesting (EH) technologies to be potentially used as power sources for the acoustic emission and guided wave propagation sensors of the considered SHM systems, as well as for the respective data elaboration and wireless communication modules, is provided in this work. EH devices based on the usage of kinetic energy, thermal gradients, solar radiation, airflow, and other viable energy sources, proposed so far in the literature, are thus described with a critical review of the respective specific power levels, of their potential placement on airplanes, as well as the consequently necessary power management architectures. The guidelines provided for the selection of the most appropriate EH and power management technologies create the preconditions to develop a new class of autonomous sensor nodes for the in-process, non-destructive SHM of airplane components.

Aircraft leading edge is one of the most important subjects of aircraft scheduled maintenance. Leading edge as part of the slot on transport aircraft is not critical to fatigue stress in most of the cases. However, leading edge is extremely vulnerable to the accidental damage in combination with environmental damage. Maintenance is usually provided by visual inspection before every flight. Nevertheless, development of anti-icing system based on contact electrical heating opens possibility to thermographic Nondestructive Testing (NDT) methods usage. These methods could detect minor damages, which are visually undetectable especially in the case of composite materials. This paper describes possibility of thermographic methods (using anti-icing system) application as mean of leading edge minor damage detection.

This paper deals with an innovative approach for SHM with piezoelectric elements utilized as active sensors. The increasing interest in reduction of maintenance costs of aircrafts can be solved by embedding permanent and self-sufficient monitoring networks into the structure of the aircraft in order to prevent structural failures. Piezoelectric elements are currently undergoing a rapid development and due to their inexpensive and non-intrusive nature, they can be used to assemble such monitoring networks. The proposed method utilizes a virtual model of the structure to pinpoint suitable locations for the sensors with respect to the requirement of local and global SHM, serving as an initial point for further research to describe behaviour of the structure during operation and predict any inadmissible state.

The paper describes activities related to the safety assessment of a futuristic personal plane concept, done by researchers at the Institute of Aerospace Engineering (IAE), Brno University of Technology, as a part of the FP7 PPlane research project. Activities under the PPlane project were carried out in joint cooperation with an international research team led by ONERA (France). The aim of the FP7 EU project PPlane (Personal Plane) is to identify new potential concepts and technologies for future air transport, namely to create a future Personal Air Transport System (PATS). The personal air vehicle is understood to be analogous to a private car in terms of accessibility and ease of operation. Such a novel transportation system could help to reduce congestion on roads and enable more efficient transportation of passengers to their destinations. The introduction of PATS is a long-term goal which requires considerable progress beyond the current state-of-the-art technology as well as in related areas. The major enabling technology is believed to be a high level of automation in new air vehicles which would require either no or minor piloting skills of passengers.

The paper deals with an accumulator for experimental fully electric airplane VUT051RAY with rated power 55kW. The preliminary requirements on accumulator capacity and its weight were defined according to a precisely specified flight profile.

The purpose of the paper was to provide the reader with basic insight into practical problems solved in the Czech aerospace industry and with a list of requirements and recommendations of civil airworthiness regulations on the field of reliability. This includes a short historical introduction, a list of basic requirements, and recommendations of the regulations for different aircraft categories. The general aviation category (sport airplanes and small transport airplanes) is covered in more depth. Recommended procedures for reliability analyses are also covered (with a focus on the design and certification process), including a brief summary of their utilization in the Czech aerospace industry. Special attention is paid on the activities of the Brno University of Technology (and its Institute of Aerospace Engineering). A practical example of safety assessment based on an electronic avionic system for small GA aircraft is also provided.