Board Aircraft Research Articles

A Study on Passengers’ Safety Awareness Regarding Items Carried on Board Aircraft

A Study on Passengers’ Safety Awareness Regarding Items Carried on Board Aircraft

Quantification of Methane Emissions from Cold Heavy Oil Production with Sand Extraction in Alberta and Saskatchewan, Canada.

Cold heavy oil production with sand (CHOPS) is an extraction process for heavy oil in Canada, with the potential to lead to higher CH4 venting than conventional oil sites, that have not been adequately characterized. In order to quantify CH4 emissions from CHOPS activities, a focused aerial measurement campaign was conducted in the Canadian provinces of Alberta and Saskatchewan in June 2018. Total CH4 emissions from each of 10 clusters of CHOPS wells (containing 22-167 well sites per cluster) were derived using a mass balance computation algorithm that uses in situ wind data measurement on board aircraft. Results show that there is no statistically significant difference in CH4 emissions from CHOPS wells between the two provinces. Cluster-aggregated emission factors (EF) were determined using correspondingly aggregated production volumes. The average CH4 EF was 70.4 ± 36.9 kg/m3 produced oil for the Alberta wells and 55.1 ± 13.7 kg/m3 produced oil for the Saskatchewan wells. Using these EF and heavy oil production volumes reported to provincial regulators, the annual CH4 emissions from CHOPS were estimated to be 121% larger than CHOPS emissions extracted from Canada's National Inventory Report (NIR) for Saskatchewan. The EF were found to be positively correlated with the percentage of nonpiped production volumes in each cluster, indicating higher emissions for nonpiped wells while suggesting an avenue for methane emission reductions. A comparison with recent measurements indicates relatively limited effectiveness of regulations for Saskatchewan compared to those in Alberta. The results of this study indicate the substantial contribution of CHOPS operations to the underreporting observed in the NIR and provide measurement-based EF that can be used to develop improved emissions inventories for this sector and mitigate CH4 emissions from CHOPS operations.

A Study on Countermeasures for Disruptive Passengers on Board Aircraft

Unlawful acts and unauthorized disruptions by passengers on aircraft have been on the rise post-pandemic with the increased air travel demand. In recent years, the number of such incidents involving passengers has not only increased but also diversified. Depending on the severity of these actions, they can potentially have serious consequences for aviation safety. Therefore, there is a pressing need for strong intervention regardless of means used in some cases. This situation highlights the crucial role of cabin crew more than ever before. However, despite the importance of addressing actions that may pose a safety threat by passengers promptly and decisively, there is a growing confusion in practical scenarios regarding the use of tasers. To address this and enhance aviation safety and security, this study examined the appropriateness of taser usage based on the types of threats posed. As a result of this, a taser usage matrix was developed, taking into account the legal positions, roles of in-flight security personnel and special law enforcement officers of cabin crews on board. The outcome of this research is expected to provide clear and comprehensive guidelines for taser usage, thus improving efficiency in responding to unruly passengers. Also, the intention of the study is to establish specific taser usage regulations for in-flight tasks, deriving practical solutions needed in the field. Through these efforts, the aviation industry will be able to enhance aviation safety and security by equipping itself with more effective means to counter illegal disruptions and ensure the safety of passengers and crew members. Key Words: Tasers, Cabin Crew, Aviation Security, Unruly Passenger, Air Rage, Tasers Usage Manual

Next-generation ice-nucleating particle sampling on board aircraft: characterization of the High-volume flow aERosol particle filter sAmpler (HERA)

Abstract. Atmospheric ice-nucleating particle (INP) concentration data from the free troposphere are sparse but urgently needed to understand vertical transport processes of INPs and their influence on cloud formation and properties. Here, we introduce the new High-volume flow aERosol particle filter sAmpler (HERA) which was specially developed for installation on research aircraft and subsequent offline INP analysis. HERA is a modular system consisting of a sampling unit and a powerful pump unit, and it has several features which were integrated specifically for INP sampling. Firstly, the pump unit enables sampling at flow rates exceeding 100 L min−1, which is well above typical flow rates of aircraft INP sampling systems described in the literature (∼ 10 L min−1). Consequently, required sampling times to capture rare, high-temperature INPs (≥ −15 ∘C) are reduced in comparison to other systems, and potential source regions of INPs can be confined more precisely. Secondly, the sampling unit is designed as a seven-way valve, enabling switching between six filter holders and a bypass with one filter being sampled at a time. In contrast to other aircraft INP sampling systems, the valve position is remote-controlled via software so that manual filter changes during flight are eliminated and the potential for sample contamination is decreased. This design is compatible with a high degree of automation, i.e., triggering filter changes depending on parameters like flight altitude, geographical location, temperature, or time. In addition to presenting the design and principle of operation of HERA, this paper describes laboratory characterization experiments with size-selected test substances, i.e., SNOMAX® and Arizona Test Dust. The particles were sampled on filters with HERA, varying either particle diameter (300 to 800 nm) or flow rate (10 to 100 L min−1) between experiments. The subsequent offline INP analysis showed good agreement with literature data and comparable sampling efficiencies for all investigated particle sizes and flow rates. Furthermore, the collection efficiency of atmospheric INPs in HERA was compared to a straightforward filter sampler and good agreement was found. Finally, results from the first campaign of HERA on the High Altitude and LOng range research aircraft (HALO) demonstrate the functionality of the new system in the context of aircraft application.

Aircraft overrun warning systems capabilities and disadvantages

Currently, attention of the aviation community and authorities is being increasingly focused on flight safety in the landing phase. It is accounted for the increased frequency of incidents in the final phase of flight and significant threats associated with the consequences of these events. The statistics of aviation accidents reveals that from 1959 to 2019, 55% of aircraft crashes in the world occurred in the phases of landing and takeoff. The given crashes resulted in 51% of all fatalities on board aircraft. In most cases, causes of these aviation accidents are involved with some kind of human error. Off-design conditions at an aerodrome also have a significant adverse effect on the aviation accident potential and severity. The increasing intensity of flights, airspace congestion, strict ATC-imposed restrictions, the necessity to perform a variety of procedures and general flight crew stress in conjunction with dynamically changing external conditions can disorient a flight crew and lead to a landing with a flight envelope overrange. The search for a solution in terms of preventing aircraft overruns is actively being conducted both by aviation authorities and aircraft manufacturers and operators. Within the framework of this review, the major external and operational factors, affecting the dynamics and the nature of the aircraft roll via the runway, are analyzed, including the context of several accidents that have occurred in recent years. In addition, the article emphasizes the methods to prevent and anticipate aircraft overruns based on the principles of active protection. In particular, the article examines the main operation aspects of onboard avionics systems installed on Boeing and Airbus aircraft and highlights the focus areas of their upgrading. Special attention is paid to the influence of the pilot and the possibility of taking his actions into account to predict an outcome of landing.

A proposal of AHRS yaw angle correction with the use of roll angle

PurposeAttitude and heading are very important measurements on board aircraft. In modern solutions they are measured by the attitude and heading reference system (AHRS). In some small unmanned systems, the GPS track angle is used for heading corrections instead of the magnetometer; then, the system measures the track angle instead of heading. With a temporary lack of correction signals, the measurement error increases very quickly. Similarly, a quick increase in the measurement error is observed when a magnetic heading sensor used for correction stops working properly. This study aims to propose measurement of the roll angle for yaw angle correction.Design/methodology/approachAHRS algorithms were designed; typical maneuvers were analyzed. The method was verified by simulation and in flight testing analysis. For quantitative analyses, a performance index was proposed.FindingsThe method enables reduction of the yaw angle error caused by the gyros bias error. This study presents the idea, results of simulations and flight testing data analysis and discusses advantages and limitations of the presented method.Practical implicationsThe presented methodology can be implemented in AHRS systems for manned and unmanned aircraft.Originality/valueThis study enables more accurate measurement of the yaw angle in the case of missing correction signals.

ВОЗДЕЙСТВИЕ ПОРТАТИВНЫХ ЭЛЕКТРОННЫХ УСТРОЙСТВ НА БОРТОВОЕ ОБОРУДОВАНИЕ ВОЗДУШНОГО СУДНА

The article is devoted to the topical problem of analyzing the risks that arise during the operationof aircraft in cases where portable electronic devices are on board the aircraft, and thechoice of methods for checking the resistance of onboard equipment to the effects of such devices.The article considers all possible ways of propagation of spurious and intentional emissions fromportable electronic devices to avionics systems and analyzes two main aspects of the impact ofportable electronic devices on aircraft avionics. The first aspect defines the aircraft system andqualification guidelines for radio-exposed equipment that provide immunity to radio emissionsfrom intentionally transmitting portable electronic devices. This is usually interpreted as protectionagainst the impact of portable electronic devices "through the back door." The second aspectdefines acceptable interference that causes bandwidth loss between aircraft radios and spuriousportable electronic devices. This is commonly referred to as "front door" protection against portabledevices. Based on an analysis of the main risks associated with interference from portableelectronic devices to aircraft systems, aircraft systems have been identified for which a demonstrationof compliance with the resistance to the effects of portable electronic devices must be performed.In order to demonstrate the suitability of the front door immunity of aircraft equipment, itis necessary to assess the levels of possible interference from portable electronic devices in thereception band of aircraft equipment. Demonstrating the compliance of aircraft equipment for“through the back door” exposure is similar to demonstrating resistance to high-intensity electromagneticfields and indirect lightning strikes. It is necessary to perform one of the two proposedmethods to establish their susceptibility to radio emission and control levels of the susceptibility ofaircraft systems to radio emission. The first method is related to the delivery of equipment to thetest bench for RF emissions, the second method is to test the systems that are installed on the applicableaircraft. Recommendations have been developed on the choice of methods for verifyingthe resistance of aircraft systems to the impact of portable devices. The impact aspects analyzedwill help determine the scope and methodology for conducting tests to remove restrictions on theuse of portable electronic devices on board aircraft.

Thermal Management Technologies Used for High Heat Flux Automobiles and Aircraft: A Review

In recent years, global automotive industries are going through a significant revolution from traditional internal combustion engine vehicles (ICEVs) to electric vehicles (EVs) for CO2 emission reduction. Very similarly, the aviation industry is developing towards more electric aircraft (MEA) in response to the reduction in global CO2 emission. To promote this technology revolution and performance advancement, plenty of electronic devices with high heat flux are implemented on board automobiles and aircraft. To cope with the thermal challenges of electronics, in addition to developing wide bandgap (WBG) semiconductors with satisfactory electric and thermal performance, providing proper thermal management solutions may be a much more cost-effective way at present. This paper provides an overview of the thermal management technologies for electronics used in automobiles and aircraft. Meanwhile, the active methods include forced air cooling, indirect contact cold plate cooling, direct contact baseplate cooling, jet impingement, spray cooling, and so on. The passive methods include the use of various heat pipes and PCMs. The features, thermal performance, and development tendency of these active and passive thermal management technologies are reviewed in detail. Moreover, the environmental influences introduced by vibrations, shock, acceleration, and so on, on the thermal performance and reliability of the TMS are specially emphasized and discussed in detail, which are usually neglected in normal operating conditions. Eventually, the possible future directions are discussed, aiming to serve as a reference guide for engineers and promote the advancement of the next-generation electronics TMS in automobile and aircraft applications.

A Detection Method of Atmospheric Neutron Profile for Single Event Effects Analysis of Civil Aircraft Design

High-energy particles such as neutron act as serious threats to electronic equipment on board aircraft via Single Event Effects (SEE), but atmospheric neutron flux profile which could cover civil aviation altitude is rarely observed. To address the representative of atmospheric radiation data in SEE analysis, we propose a new method of detecting atmospheric neutron profile for civil aviation altitude. Using the sounding balloon carrying one nuclear radiometer, the radiation dose could be observed with high accuracy. Subsequently, the profile of atmospheric neutron flux can be derived on the basis of the conversion equation between radiation dose and the neutron flux. We implement two experiments, and the results show that this low-cost method could reliably obtain the vertical distribution of atmospheric neutron and might be integrated into SEE analysis of civil aircraft design.

Study on the Tooth Profile Parameters Design Method of Crown Gear Coupling for Helicopter Tail Folding Device

Shipboard helicopter folding technology can increase the number of helicopters parked on board aircraft carriers. Crown gear coupling is the trend in helicopter tail rotor folding technology due to its ability to automatically and quickly engage and disengage helicopter tail rotors. This paper presents a method for the design of tooth parameters for crown gear coupling for folding devices. The model of the relationship between tooth shape parameters and angular displacement of the crown gear coupling and the model of the relationship between angular displacement and shaft line angle of the crown gear coupling were established, respectively, and the basic parameters of tooth shape and modified parameters of the crown gear coupling were designed. The correctness of the design method of the tooth parameters of the crown gear coupling for the folding device was also verified through motion simulation. The results of the study provide a theoretical basis for the design and optimization of crown gear couplings for folding devices.

JURISDICTION OF CRIMES ON BOARD

We have often viewed various Media that depict various criminal activities occurring on board Planes. However, much like most popular media, a large amount of misinformation about such activities and any jurisdiction that may govern them have been caused as a direct result. The paper attempts to simplify and clarify exactly who holds the jurisdiction to trial over any crimes committed on board Aeroplanes. Much like with crimes committed aboard sea vessels in the high seas, it is often assumed that the captain, or otherwise highest ranked Individual is considered the ultimate authority in such cases. Such misconceptions need clarification, and this paper will attempt to do so. The main question and purpose of this paper, will be to simplify, and attempt to answer specifically exactly what jurisdiction exists that may cover any crimes committed on board aeroplanes. Much of the legislation on the topic is contained within the Convention on Offences and Certain Other Acts Committed on Board Aircraft, Signed at Tokyo, on 14 September 1963, Popularly known as the Tokyo Convention of 1963. The need for such a convention was in response to the wave of hijackings in 1958 where aircrafts were hijacked and used to divert to the US and vice versa in the 1961 wave of Hijackings there was a wave of diversions of aircraft from the United States to Cuba. To prevent further aircraft diversions, the Legal Committee of the ICAO met in Rome in 1962 to draft a convention on the subject of crimes committed on board an air-craft in international flight. This draft known as the Rome Draft was submitted to the States of the world for comment and a diplomatic conference was convened in Tokyo in the year 1963 for final approval.

ANALYSIS OF WING SEPARATION AND MID-AIR BREAKUP IN LIGHT TRAINING AIRCRAFT

Despite increasing discussions concerning the recently published wing spar airworthiness directive (AD) that affects many training aircraft and several current ADs for wing struts, there remains limited objective literature on incidents of wing separation or mid-air breakup. This paper attempts to report and analyse instances of wing separation and mid-air breakup of light training aircraft. A careful review of the United States National Transportation Safety Board (NTSB) aircraft accident database revealed that wing separations were more likely occur as mid-air breakup in PA28s than 172s/182s (OR: 3.06, 95 % CI: 1.3682 to 6.8536, p = .008). Additionally, wing separations were less likely to occur as mid-air breakups in the strutted 172s/182s than 177s/210s that don’t have a wing strut (OR: 0.11, 95 % CI: 0.04 to 0.29, p = <.001). This implies that non-strutted wing designs may be more susceptability to mid-air breakup than the strutted design of similar aircraft.

FEATURES OF THE DEVELOPMENT OF PROFESSIONALLY IMPORTANT CHARACTERISTICS IN NOVICE AND EXPERIENCED CIVIL AVIATION FLIGHT ATTENDANTS

The article examines the professionally important characteristics of civil aviation flight attendants. The study found that novice and experienced flight attendants have differences in the level of development of the professionally important characteristics that provide safety and service on board aircraft.

Scientific basis for the trainer aircraft anti-g equipment requirements

The design process of a new aircraft (AC) is always associated with the issue of choosing its basic technical parameters, or, in other words, the formation of its conceptual design. In case of a civil aircraft, the choice of these parameters is defined by the requirements for operational safety, market conditions, norms that specify the tolerable harmful impact of the aircraft on the environment, etc. In case of a military aircraft, its outlay mostly depends on the concept of potential military threats, ways of using the military aircraft in military conflicts. Some of these requirements are formulated in regulatory documents – the Aviation Requirements for Civil Aircraft and the General Tactical and Technical Requirements of the Air Force for Military Aircraft. For example, Part 25 of the Aviation Requirements for Civil Aircraft defines the Airworthiness Standards for transport aircraft. It should be noted that the stated above requirements are often a tool of competition, for example, when tightening the aircraft noise abatement procedures provides advantages for particular manufacturers, not admitting other manufacturers to enter the market, whose aircraft do not conform to the new standards. Thus, complying with the requirements virtually involves additional costs both in the aircraft development and during its operation. In addition, the implementation of the requirements stated above can lead to the deterioration of the aircraft’s performance, and hence, to the decrease of its competiveness and combat effectiveness. Therefore, each requirement of the regulatory documents should have a profound scientific rationale. This article analyzes one of the regulatory documents requirements referring to the necessity of anti-g system on board aircraft. The authors propose the approach to specify the existing criterion to provide the scientific basis for the anti-g system on board aircraft by assessing the actual level of pilot load when maneuvering. The subject under study is of particular importance for the Yak-152 trainer aircraft. The actual level of loads during pilotage of the Yak-152 trainer aircraft does not require the use of the anti-g system but if to be based on a formal criterion, namely, in terms of the maximum operational overload value, the aircraft should be fitted out with such a system.

Angular Rate Sensor Based on a Solid-State Wave Gyroscope with a Metal Resonator for Attitude Control, Stabilization and Navigation Systems

The article describes the methods and test results of a solid-wave gyroscope (SVG) — an angular rate sensor (ARS), developed at the Department of Control Devices, Tula State University and manufactured by the serial plant of JSC "Michurinsky Plant" Progress "according to the technology it worked out. The metal resonator SVG-ARS is made of an elinvar alloy and has a cylindrical structure of different thickness, the lower part of which, with a smaller wall thickness, acts as a suspension for the upper cylinder, the resonator itself, which has a conical shape, providing better vibration localization at its end edge. Technological manufacturing defects, different frequencies and variability, are eliminated by balancing " by mass" based on the removal of excess metal at certain points on the end edge of the resonator. The electronic module provides the second mode of primary and secondary oscillations of the resonator edge arising during rotation and creates a signal to compensate for the Coriolis and quadrature components of the output signal at the nodes. The maximum amplitudes of the excitation and compensation signals do not exceed 10 V. Therefore, at large values of mechanical influences, the compensation circuit may not work out the increased signal and the SVG-ARS loses its operability. The total processing time of the compensation signal does not exceed 1 μs. The maximum power consumption of the electronic module is not more than 4 W. When testing for mechanical and temperature effects, the norms were used that are typical for similar devices (angular rate sensors) used on board aircraft. The tests were carried out on the bench equipment of a specialized enterprise. The stability of the zero signal and the scale factor was determined under the simultaneous action of the measured speed and temperature on the SVG-ARS. The values of the random walk and the instability of the zero signal were obtained from the Allan deviation plots. Their values provide a basis for the conclusion about the possibility of using the developed SVG for several hours on board dynamic aircraft in orientation, stabilization and navigation systems. It was found that SVG-ARS possesses impact strength and restores its measuring ability after impact. Tests for vibration resistance revealed resonance frequencies and frequency rangesin which the tested VTG-DUS sample can be used without significant modification. The results of vibration tests can be used to refine the design and control electronics for the operating conditions of a particular aircraft.

Providing on board aircraft security

This article presents the threats to civil aviation, which may be committed on board aircraft. There are also described solutions, which implemented can increase the security of aircraft. This directly influences the security of the entire civil aviation sector. Many procedures can be introduced by airlines (air carriers) on board aircraft, within the aircraft while its layover, or stand on the airport’s surfaces for protection against threats.

CONSIDERATIONS ON ALGORITHMS OF SELECTION AND COMPONENTS FORMING OF ON-BOARD INFORMATION AND MEASURING COMPLEXES AND REGISTRATION SYSTEMS. PECULIARITIES OF THEIR APPLICATION

On-board information and measuring complexes and registration systems are intended to control the parameters of both systems and components of the prototype and the sample of automotive and armored vehicles in general to obtain qualitative and quantitative characteristics to assess their compliance with specifications of technical development requirements.
 At present stage, there is often a need to improve methods for optimizing the development of on-board systems for collecting and processing information to ensure conducting of testing works, which take into account particulars of the electronic equipment development and are based on a unified approach to the optimal use of resources of collection and information processing systems.
 Analysis of the problem of rational use of resources of standard means of measurement, registration and indication in the system of onboard measurements and further processing of the results in automated systems for collecting and processing information for their use in testing mass produced (modernized) aircraft was previously considered by Soviet, Ukrainian and foreign scientists. But they do not give a complete picture of the algorithm, completeness and quality of tests using standard measuring instruments installed on board aircraft and do not answer a number of questions related to the optimization of the computational process.
 In particular, the potentials of standard means of measurement, registration and indication as part of the on- board measurement system for testing mass produced (modernized) aircraft and installed components, units and systems under test are not fully explored. The issue of building optimal data collection programs that implement the inquiry of measuring channels with restrictions on the frequency of channel inquiry and information processing speed is insufficiently studied.
 The novelty of the research consists in the developing of an algorithm for capabilities analysis and procedure for incorporating standard measuring, registration and indication instruments in the on-board measuring system within a single measuring and information field for testing mass produced (modernized) samples of weapons.
 Approbation and implementation of the abovementioned algorithms will allow test teams to minimize time spent on the development (selection) of the onboard measurement system to ensure research and testing of both modernized aircraft, vehicles and armored vehicles and newly created with advanced information systems.

Medical Events on Board Aircraft: Reducing Confusion and Misinterpretation in the Scientific Literature

INTRODUCTION: A topic in aviation medicine that attracts much attention from the scientific community as well as from the media concerns medical incidents on board commercial airline flights. It was noticed that many papers on the subject were written by authors whose specialization was outside that of aviation medicine and that they sometimes made basic errors concerning the application of scientific principles of the subject. A review was undertaken to determine if there were any patterns to the observed errors and, if so, to consider whether recommendations might be provided that could reduce their frequency.METHOD: A literature search was undertaken of MEDLINE using PubMed for English-only articles published between January 1, 1974, and February 1, 2019, employing the following search terms: air emergency, air emergencies, air passenger, air travel, aircraft, airline, aviation, commercial air, flight, and fitness to fly. In addition, other relevant papers held in the personal collection of the authors were reviewed.RESULTS: Many cases of misinterpretation or misunderstanding of aviation medicine were found, which could be classified into eight main categories: references; cabin altitude; pressure/volume relationship; other technical aspects of aircraft operations; regulations; medical events; in-flight deaths; and automated external defibrillator.CONCLUSION: Papers were identified as having questionable statements of fact or of emphasis. Such instances often appeared to result from authors being unfamiliar with the subject of aviation medicine and/or the commercial aviation environment. Simple steps could be taken by authors to reduce the future rate of such instances and recommendations are provided.Thibeault C, Evans AD. Medical events on board aircraft: reducing confusion and misinterpretation in the scientific literature. Aerosp Med Hum Perform. 2021; 92(4):265273.

AIRDOS — open-source PIN diode airborne dosimeter

This article introduces a new open-source dosimeter AIRDOS intended for measurements on board aircraft. In-flight measurement of a mixed radiation field is a challenging deal that requires a small low-power-consumption battery-operated lightweight device with long endurance. A new innovative electronic design with a silicon PIN diode used as a sensor is presented, including full description and manufacturing documentation. The device was verified by measurements and compared with reference dosimeters widely used in aircraft dosimetry, such as Liulin MDU and HAWK TEPC. A comparison of the measurements with a computation model CARI 7 was performed as well. All the comparisons yield positive results within known errors. The new design of the dosimeter has a very satisfactory performance in terms of battery life and does not need calibration after manufacturing or recalibration after a long time of usage. Open-source design predetermines AIRDOS for future improvements and open-science.

Computer Life-Cycle Management System for Avionics Software as a Tool for Supporting the Sustainable Development of Air Transport

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.