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The purpose of this paper is to discuss the importance of testing avionics systems during the development phase according to standard procedures outlined in documents such as RTCA DO-160G. Specifically, it focuses on the necessity of correctly designing electronic devices to successfully pass tests for environmental conditions.

During the development of the flight reconfiguration system (FRS) within the Clean Sky 2/Clean Aviation cost optimized avionics System (COAST) project, this paper applied solutions for input power protection in electronic design. The methods discussed are aimed at protecting circuits from input power disturbances following Sections 16 and 17 of DO-160G. The approach includes both computer simulations and laboratory testing to analyze the effectiveness of the applied methods.

The paper presents the findings of the applied methods for input power protection in the electronic design of the FRS. Through computer simulations and laboratory tests, it was observed that the developed electronic eqty -35uipment worked correctly after completing environmental and input power testing. The achieved results indicate that the applied methods of circuits’ protection ensured proper functionality.

The findings of this study have practical implications for the design and development of airborne electronic equipment. By adhering to standard procedures outlined in DO-160G and implementing appropriate input power protection methods, electronic devices can reliably operate in harsh environmental conditions encountered during aircraft operations.

This paper contributes to the field by presenting practical solutions for input power protection in electronic design, specifically within the context of the FRS by discussing methods of circuits’ protection in accordance with DO-160G and providing analysis of computer simulations and laboratory test results, this paper offers valuable insights into ensuring the proper functionality of avionic equipment in challenging environmental conditions.

The purpose of this paper is to outline a novel concept of radio altimeter CRW-13 that has been designed and developed in the Lukasiewicz Research Network – Institute of Aviation as a result of the need to update the outdated structure of RWL-750M.

The new design of the device consists of integral antennas and signal processor for smart digital signal filtering.

As a result of a number of laboratory tests and flight tests of the device installed on MP-02 “Czajka” ultralight aircraft promising results were achieved. They allow to move on to the next stage of implementation and preparation for the device certification.

The CRW-13 meets with great interest of civilian and military potential customers. It is an ideal solution for airplanes, helicopters, unmanned and guided missiles. The universal design enables installation on many different platforms where exact height measurement is needed and crucial.

At the origin of the new concept was the need to replace the separate transmitting and receiving antennas with one unit comprising two planar microstrip antennas placed directly next to each other on a common plate block in the transceiver. This solution eliminates thick antenna cables and coaxial connectors, which are the most unreliable and problematic elements of radio altimeters. The new concept of integral antennas and the use of signal processors for smart digital signal filtration made it possible to take the technology to the next level.

This paper aims to describe the idea and partial result of research on flight reconfiguration system (FRS) which is to be used in case of pilot incapacitation while performing the single-pilot operations for defining and guiding an aircraft to a safe destination.

Multiple problems with the development of emergency systems which could deal with crisis on-board occurs, e.g. definition of emergency destination which is dealing with the thread, ensuring that route to an emergency destination is safe, avoiding of air traffic and making sure that aircraft performance limitations would not be exceeded. FRS is a sophisticated hardware design, gathering data from aircraft on-board systems, commanding autopilot where to go and informing air traffic on crisis on-board. Developed algorithm analyzes data from onboard systems, internal database to calculate potential safe places and best routes to them. Multi-criteria decision-making is used to choose the best of them and execute it when needed.

Algorithms and hardware were tested in a simulated environment. An exemplary research experiment oriented on finding emergency destination and flying to it in the Software-In-The-Loop environment was presented.

Currently, the use of the system is limited to use on-board of well-equipped CS-23 class aircraft and is limited to use in good weather conditions.

The use of FRS will in case of emergency constitute a new category of emergency maneuver, used for dealing with no-human pilot available on-board situations – autonomous emergency destination finding and route execution.

This study helps in the introduction of multi-stage decision-making to autonomously reconfigure route.