The article presents selected results of analytical and design works undertaken at the Air Force Institute of Technology (AFIT) in the field of building a computer support and software lifecycle management system that is critical for flight safety. The aim of the work undertaken is to develop methods and carry out verification and testing in order to detect errors in the developed avionics software for compliance with the requirements of the DO-178C standard and its production, certification, and implementation on board aircraft. The authors developed an original computer system within the implemented requirements used in the construction and certification of avionic onboard devices and their software (among others, DO-254, DO-178C, AQAP 2210, ARP 4761, ARP 4754A). The conducted analysis involved three basic groups of avionics software development processes, i.e., software planning, creation, and integration. Examples of solutions implemented in the constructed computer system were presented for each of these process groups. The theoretical basis of the new method for predicting vulnerabilities in the software implemented within integrated avionic systems using branching processes is discussed. It was demonstrated that the possibility of predicting vulnerabilities in future software versions could have a significant impact on assessing the risk associated with software safety in the course of its lifecycle. It was indicated that some of the existing quantitative models for analyzing software vulnerabilities were developed based on dedicated software data, which is why actual scenario implementation may be limited. DO-178C standard requirements for the process of developing avionics software were implemented in the helmet-mounted flight parameter display system constructed at AFIT. The requirements of the DO-178C and AQAP 2210 standards were shown to be met in the example of the software developed for a graphics computer, managing the operating modes of this system.

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.

This paper presents modern, electronically integrated avionics systems, manufactured by the Air Force Institute of Technology (AFIT) and intended for Polish military airplanes and helicopters. These systems are designed to support pilot's operations and situational awareness in the scope of data management on board the aircraft and automation of control processes regarding particular aircraft systems during training flights and combat missions. The presented systems are the result of works conducted by the AFIT within the process of modernization of selected airplanes and helicopters currently operated by the Polish Air Force. In the first part, the paper presents the Integrated Avionics System for the W-3PL “Głuszec” helicopter and a proposal of such an integrated system for helicopters of the Mi-8/Mi-24 series. In the second part, the paper presents two integrated avionics system architectures designed for the modernization of PZL-130 “Orlik” and TS-11 “Iskra” aircraft to the glass cockpit version.