In this paper a system for measuring temperature in an FPGA structure is proposed. In this arrangement the Spartan-3 XC3S200 programmable FPGA device was tested and the popular small educational microcomputer Raspberry Pi, was employed as a control unit for the whole system. Part of the system was implemented inside the tested structure. There was an array of ring oscillators as temperature sensors and a structure for controlling the array. Ring oscillators are often implemented in FPGA devices. They are used both as single elements or an array of sensors for measuring the chip's temperature or path delay of SUT. The sensors can be located in different areas of the chip. In the case of this tested device 36 sensors were used, but generally, their number depends on the designer. The ring oscillator's frequency depend on the temperature, and the frequency of the activated sensor was measured outside with an oscilloscope. The Raspberry Pi controlled the measurement process via an SPI and the results were collected from the oscilloscope via a UART/RS232 interface. 2D and 3D visualizations of the frequency to temperature relationship were made using Gnuplot and Scilab. The results should visualize the temperature distribution inside the device, but first, the right calibration of sensors should be performed.

The paper has been intended to present a research/testing tool used in the Air Force Institute of Technology (AFIT) to build, actuate, test, and optimise integrated communication systems as far as both a set of devices the system is composed of and the applied software are concerned. Particular attention has been paid to the so-called integration station (built under the Mi-8, Mi-17, Mi-24 upgrade project), i.e. the laboratory equipment to optimise and unify communication systems integrated on the basis of digital data buses (following the MIL-1553B standard, among other ones). Such equipment has allowed AFIT to integrate new communication devices/systems while upgrading the W-3PL helicopter. Some selected tasks performed with this equipment engaged have been discussed. Also, problems arising while actuating and testing the developed software to integrate communication devices/systems (including digitally controlled radio stations of the RRC, HARRIS, and MR6000 types, communication control panels of the PSŁ-1 type and multifunction displays of the MW-1 type) have been given consideration in the scope of the software functionality and reliability. Presented are also additional monitoring and measuring systems used to test this software, just to mention the M230 rugged laptop computer used to diagnose the system and prepare plans of the radio communication.

The paper has been intended to present research tools used at the Air Force Institute of Technology (AFIT) to activate and test hardware and software implemented in the integrated avionics systems. Particular attention has been paid to the research stand (built under the R&D project of the Ministry of Science and Higher Education) intended to optimize avionics systems integrated with digital data buses employed (according to, among other things, MIL-1553B and ARINC-429 standards). Specialized research equipment/test devices used to test software, including - apart from other things - test-patterns generators (within the range of display capability of the secondary head-up display (SHUD)) and information efficiency testers (for the SHUD and up-front control panel (UFCP) thereof) have also been presented.

The article presents the use of ground power sources for aircraft ground support. Both military and civil aircraft (A/C) require high-performance and reliable Ground Power Units (GPUs) to ensure safe operation in diverse environmental conditions. The power quality provided by these GPUs plays a crucial role in determining the reliability, cost efficiency and operational safety of the aircraft. The main objective of the article is to signal and propose a solution to the problems associated with the operation of GPUs in the Polish Armed Forces (PAF), resulting from the diversity of the equipment used (type, duration of operation, defects occurrence, etc.). Currently, the PAF utilize various types of GPUs to provide electrical power to aircraft while they are on the ground. Many of those devices have already been in service for many years. The presented statistics of defects registered in the airworthiness management system showed several dozen A/C failures or defects related to the operation of GPU. The authors highlight the importance and feasibility of diagnosing these ground-based power sources. The presented sample test results confirm that, following the methodology outlined in the article, it is possible to conduct comprehensive diagnostic assessment of the GPU systems currently in use by the PAF, as well as evaluate the quality of the electrical power they deliver in both steady and transient states.

The paper presents selected results of the work carried out at the Air Force Institute of Technology (AFIT) in the scope of computer diagnostic tests of the SWPL-1 Cyklop helmet mounted flight parameters display system. This system has been designed in such a way that it warns the pilot of dangerous situations occurring on board the helicopter and threatening the flight safety (WARN) or faults (FAIL), which inform about a failure in given on-board equipment. The SWPL-1 system has been awarded the Prize of the President of the Republic of Poland during the 17. International Defense Industry Exhibition in Kielce.