Avionics Equipment Research Articles

A Multimode Fusion-Based Aviation Communication System

This paper presents a new design for a multimode fusion communication system, aimed at tackling the complexities of modern aeronautical communication. The system integrates multiple communication technologies, such as ad hoc networking, 5G, BeiDou satellite, RTK positioning, and ADS-B broadcasting. This integration effectively solves the problem of increasing the size and weight of aviation communication equipment while also improving the efficiency and security of data communication. The study demonstrates that the implementation of this fusion communication system can lead to the development of more efficient and intelligent avionics equipment in the future, thereby offering robust technical support for flight safety.

Development of Visual System for Flight Simulation Training Device

The complexity of avionics systems and aircraft equipment is increasing day by day. To operate the avionics equipment, rigorous training is required. The training of pilots to handle these advanced equipment is quite costly. To address this issue a novel flight simulation training device is proposed in this paper. The proposed flight simulator can train the pilot on the ground. The development of visual system for Flight Simulation Training Device (FSTD) is discussed in detail in this paper. The visual system for FSTD is designed using DAQ cards, multifunctional displays, serial communication interface, pilot controls and commercially available off-the-shelf (COTS) controller. This proposed system displays various flight parameters. OpenGL is used to create graphics pages to display flight parameters. DAQ cards were utilizedto connect the analog and digital signals of cockpit to the FSTD’s visual system. A visual system was used in development of actual FSTD by assimilating symbols developed in OpenGL and creating typical pages for simultaneous display on four display surfaces.

Determination of a total and partial operational readiness for a complex technical system on the example of a mobile medical module

The article presents a proposal for a method to determine a total and partial operational readiness for a mobile medical module as a complex technical system. A new approach to determine the readiness factor characterizing the functional readiness of a complex technical system is proposed as parameter not only for the system in a state of full usability, but also in states of partial usability enabling the performance of selected functions required by the user. The communication system is discussed as the main system determining the operation of the mobile medical module. Markov chain modeling (expanded into semi-Markov chains) was used to determine the value of the readiness factor of this system. Due to the structural complexity of the mobile medical module (carrier platform, drive, basic and additional avionics equipment and basic and extended medical equipment), a total and partial operational readiness can be determined for a simple object (in a simplified version as full) or a complex system (as a total and partial).

Determination of reliability for a complex technical system on the example of a mobile medical module

The article presents a proposal for a method to determine a total and partial reliability for a mobile medical module as a complex technical system. The dedicated functions of such a module are to evacuate the wounded from the battlefield (in the basic version) and to ensure the maintenance of his vital functions and the performance of necessary medical procedures (in the extended version). Work on developing the concept or advanced construction of such modules using unmanned aerial vehicles as transport drones has been carried out for several years by many countries and aviation companies, including: DARPA agency (USA) and AFIT (Poland). Even though there is no fleet of such machines in Poland yet, this comes from experience in managing aircraft in the Armed Forces RP results from the need to simultaneously secure the operation of such modules in an IT support system using algorithms and mathematical relationships in determining a total and partial reliability . Due to the structural complexity of the mobile medical module (carrier platform, drive, basic and additional avionics equipment and basic and extended medical equipment), a total and partial reliability can be determined for a simple object (in a simplified reliability version as full) or a complex system (as a total and partial reliability).

AR-Assisted Guidance for Assembly and Maintenance of Avionics Equipment

The assembly and maintenance of products in the aviation industry constitute a crucial aspect of the product life cycle, with numerous tasks still reliant on manual operations. In order to solve the problem of narrow operation spaces and blind areas in the processes of manual assembly and maintenance, we proposed an augmented reality (AR) assistant guidance method specifically designed for such scenarios. By employing a multi-modality anti-occlusion tracking algorithm, pose data of assembly parts can be obtained, upon which AR guidance information is displayed. Additionally, we proposed an assembly step identification method to alleviate user interaction pressure. We developed an AR visualization assistant guidance system and designed and conducted a user evaluation experiment to measure the learnability, usability, and mental effort required. The results demonstrate that our method significantly enhances training efficiency by 128.77%, as well as improving assembly and maintenance efficiency by 29.53% and 27.27% compared with traditional methods. Moreover, it has significant advantages in learnability, usability, and mental effort, providing a feasible and effective resolution for addressing blind areas during assembly and maintenance within the aviation industry.

Avionics Laboratory Tools and Equipment at PhilippineState College of Aeronautics Basa Campus as Determinants of Student Performance

Avionics Laboratory Tools and Equipment at PhilippineState College of Aeronautics Basa Campus as Determinants of Student Performance

Optimization of Spacecraft Thrusters Configuration Under Fault Diagnosability and Recoverability Constraints

This paper investigates the problem of optimal placement (position and orientation) of spacecraft thrusters, under fault diagnosability and fault recoverability constraints. Avionics equipment contamination and plume impingement are also considered. The goal is to find the thrusters configuration with the minimal number of thrusters required for a given spacecraft architecture, so that it is guaranteed that it is possible to equip the control unit with a model-based fault diagnosis and fault-tolerant control solution, able to accommodate any single thruster's fault. This includes total loss of controllability of the faulty thruster. The proposed solution is a model-based solution in the sense that it is based on the spacecraft attitude and translational dynamics. With the help of the zonotope concept and its so-called H-representation, it is shown that this problem can be formulated as a nonlinear constrained optimization problem, which can be solved efficiently using hybrid optimization techniques. The proposed solution is assessed on a generic spacecraft architecture that performs a proximity maneuver.

Expandable Optimum Avionics Architecture Solution with Advantage in terms of Cabling Weight for a Helicopter

One of the biggest problems that the aviation industry focuses on in helicopter platforms is that the payload is not at the desired level. Another of these problems is the integration problem experienced in the process of integrating current technological equipment into the helicopter avionics architecture later throughout the product life cycle of the helicopter. Increasing the payload allows to carry more personnel, ammunition, etc. An expandable avionics architecture concept enables this if it is desired to integrate new avionics equipment throughout the life of the helicopter. In this context, R&D activities are organized in order for avionics equipment to be fast, expandable and reliable, and to transfer data via lighter ways. In this study, avionic architectural concepts from the past to the present were examined and a comparative analysis was made in terms of the cabling weight that will be formed on the helicopter platform in its possible use. While creating this concept, distributed, federated, integrated and distributed integrated architectures were examined, as well as RS-422/485, ARINC-429/629, AFDX, MIL-STD-1553 and FIBRE Channel protocols within the scope of communication protocols. By examining the superiority of the mentioned concepts to each other, the cabling weight created by different avionics architectures on the platform was calculated, and the optimum avionics architecture concept, which could be expanded to create a minimum cabling weight for a military type helicopter, was proposed.

AdaptIDS: Adaptive Intrusion Detection for Mission-Critical Aerospace Vehicles

Aerospace and defense industries are particularly vulnerable to cyber threats given their sensitive nature, significantly extending the consequences of security breaches to the national level. Aerospace vehicles are augmented by cooperative control, intelligent, connected, and autonomous systems. The risk against such systems is further amplified due to commonly relying on the MIL-STD-1553 communication bus developed with a high focus on reliability and fault tolerance, albeit with security as a second priority. MIL-STD-1553 (a.k.a., STANAG 3838 by NATO) is a standard that describes a serial data communication bus primarily used in aerospace vehicles for military and civilian applications, including avionics, aircraft, and spacecraft data handling. In the absence of core security measures such as authentication, authorization, and encryption, the bus connecting sensitive functions, including autopilot, GPS, fuel valve switches, and other avionics equipment, is easily vulnerable to a wide range of attacks. This paper proposes, AdaptIDS, a novel adaptive intrusion detection system as a security analytics framework for the MIL-STD-1553 communication bus. AdaptIDS mainly adopts data science principles and leverages advanced deep learning techniques (i.e., the stacking ensemble) to boost its generalization capabilities for detecting unseen patterns of attacks in the dynamic changing environment of aerospace vehicles. Extensive experiments are conducted using two datasets generated from an open-source simulation system, reflecting dynamic real-life scenarios. The evaluation results demonstrate that our solution outperforms existing solutions with high detection effectiveness of 0.99 F1-measure and computational time efficiency.

Project for a reconnaissance unmanned aerial vehicle

Abstract The paper presents the process of designing an unmanned Micro class aircraft, from the analysis of the dynamically developing market and the condition of the Polish Armed Forces to construction of objects and flight test. The possibilities and limitations of using miniature UAVs on the modern battlefield were determined. For the designed UAV the propulsion was selected based on tests carried out on the engine test bench. The avionics equipment was selected based on components readily available on the market. The object was then made and inspected in flight. During the flight tests, the aircraft performance was verified and compared with the assumptions. It has been shown that the developed object is able to fulfill the reconnaissance tasks entrusted to it, while maintaining the assumed simplicity of construction and low cost of execution and service.

Characteristics of thermal storage heat pipe charged with graphene nanoplatelets enhanced organic phase change material

The challenge on the thermal management of highly integrated electronic devices and avionics equipment has grown continuously. To meet fully passive and highly reliable requirements, a novel thermal storage heat pipe (TSHP) charged with phase change material (PCM) is designed. Paraffin RT70HC and graphene nanoplatelet (GNP) are used as energy storage material and heat transfer enhancer, respectively. The microstructure, chemical and thermophysical properties of RT70HC/GNP composite are systematically characterized through Scanning Electron Microscope (SEM), Fourier Transform Infrared Spectroscopy (FT-IR), X-Ray Diffraction (XRD), Differential Scanning Calorimeter (DSC) and thermal conductivity analyzer. A visualization experimental investigation is conducted to study the effects of nano-enhanced phase change material (NEPCM) on the thermal performance of TSHP at different heat fluxes. Results show that the thermal conductivity of PCM is improved maximally 21.6% by adding GNP, whereas the latent heat of fusion decreased 10.5%. It is also observed that the TSHP with NEPCM has better thermal management performances, which effectively lowers the temperature rising speed of the chipset, and extends the sustainable time to reach the chip permitted highest temperature of 85 °C. Finally, the saturation pressure of NEPCM during the melting process is measured and discussed.

공지통신 무전기 성능개량 간 안테나 추가에 따른 최적위치 설계 연구

In this study, we propose an antenna optimal positioning method for improving air-to-ground communication radios. To maximize the RF performance of communication radios and perform effective communication, a comprehensive and systematic process is developed by considering the structural impact, cable harness, and RF performance of additional antenna installation. The proposed method is applied to aircraft subjected to IFF performance improvement to optimally design IFF and GPS antennas. In addition, AIMS platform certification and development test evaluation are performed. Designing optimal antenna location is an effective method that can be applied to improve the performance of air-to-ground communication radios as well as to avionics equipment remodeling projects by reducing schedule and cost.

WAYS OF DEVELOPMENT A COMPLEX OF AVIONICS FOR HELICOPTERS OF MI-8 TYPE OF THE AIR FORCES OF UKRAINIAN ARMED FORCES

Perspective directions of development of the onboard equipment complexes built on the principles of integrated modular avionics are considered. Features of architecture and interfaces of the complex, possibilities of unification and modernization of components of integrated modular avionics are analyzed, new functional possibilities, principles of reliability and safety failure of the complex are described, possibilities of realization of systems of electronic equipment on the basis of integrated modular avionics are considered. Possibilities of development of highly integrated onboard systems are analyzed.
 The main conclusions and prospects for the use of research results. A necessary condition for further improvement of avionics equipment helicopter complexes of the Armed Forces of Ukraine is to conduct systematic pre- project military research and external design at the conceptual stage of formation of their technical accounting. These studies and preliminary design developments should include substantiation of the general concept (basic idea) of creation and combat application of the avionics equipment complex, which is planned for development, optimization of its performance characteristics values and design parameters that determine the technical accounting of the complex.

Cost Optimized Avionics System – Navigation Solution for Small Aircraft Transportation Segment

Modern navigation systems represent an inherent part of avionic equipment onboard all aircraft categories. The standard navigation performance typically defined by accuracy, integrity, availability, and continuity is now complemented by the system’s ability to reduce CO2 emissions and fuel consumption. This article describes current navigation system development executed by Honeywell International for SAT (Small Aircraft Transportation) segment defined by CS-MMEL ATA 34 Navigation. The proposed solution is based on INS/GNSS hybridization extended by other aiding sensors available onboard the aircraft. To create a technological solution that meets the system operational requirements of the segment and at the same time comply with SWAP-C (Size, Weight, And Power Consumption Related to Cost) requirements is the aim of this research activity. The article describes proposed integration architecture based on hybridized core and other aiding sensors, such as radar altimeter and magnetometer. The assessment of previously mentioned aiding sensors was performed and impact on navigation performance was determined. The emphasis was mainly put on Inertial Measurement Unit (IMU) meeting the low-cost requirement for the overall architecture. The IMU error model definition and long-term thermal chamber measurements are the main tools for understanding the stochastic behaviour of the IMU’s. The accuracy improvement is further supported by implementing SBAS corrections in INS/GNSS hybridization. This is not a usual navigation solution for SAT segment, since, typically, standalone GNSS receiver with SBAS is used instead. The Monte Carlo simulations were performed to compare the performance of the proposed solution against system and operational requirements. A proprietary Honeywell tool for these large-scale simulations is capable to simulate the navigation exercise anywhere on the Earth using pre-defined trajectories with specific duration and simulated GNSS constellation to reflect the impact of the satellite geometry.

Remaining Useful Life for Aircraft Engine Forecasting Based on Data-driven

As for the low forecasting precision problem about time series in avionics complex system, a time series combined forecasting model of complex systems was established based on GM (grey model is referred to as GM). However, using the traditional GM(1, 1) model to predict complex system failures might result in huge forecasting errors. To solve the drawbacks of the traditional GM(1, 1) model, this work developed the traditional GM(1, 1) model (abbreviated as DGM(1, 1)), which can predict non-geometric sequences more correctly. To reduce such mistakes, a PS-DGM (1, 1) forecast model was created by combining DGM(1, 1) with the particle-swarm optimization process. The DGM(1, 1) model was utilized to generate the forecasting sequence, and then the particle-swarm optimization approach was employed to further alter them, resulting in the degradation trend prediction of avionics complex system characteristic parameters. The experimental results show that the PS-DGM(1, 1) model’s validity was confirmed by tracking and forecasting avionics equipment experiment data in a real-world setting, and that the suggested model achieves higher precision than the old one.

ИССЛЕДОВАНИЕ ВАРИАНТОВ ОРГАНИЗАЦИИ ЦЕПЕЙ ПОСТАВОК ЗИП ДЛЯ ПОДДЕРЖАНИЯ ИСПРАВНОСТИ ОБЪЕКТОВ АВИОНИКИ

The presented study deals with the organization of supply chains for spare serviceable avionics equipment from the perspective of decision makers, heads of instrument-making enterprises. An extremely important issue is the determination of key parameters of avionics spares objects. On the basis of the conducted research, the element base of the serviceable avionics equipment facilities and conditions of operation, recovery of serviceability are considered. Due to the complexity of approaches to avionics objects, the article provides a fixation of key parameters, defines the distinctive features of exactly the avionics spare serviceable avionics equipment, which will determine new requirements and conditions of building the future supply chain. As a result of the conducted research, the article presents a classification of methods for calculating serviceable avionics equipment, based also on the theory of recovery processes. On the basis of the performed system approach to the objects of avionics inventory and spare parts management, examples of supply chain organization variants are given. The presented research is of practical significance both when designing a new chain of supply of spares, and when modernizing the existing supply chains for spare serviceable avionics equipment.

히트파이프를 이용한 항공전자장비용 냉각장치 열전달 성능 연구

항공전자장비의 고성능화가 요구됨에 따라 전자소자의 방열설계는 중요한 요소가 되어가고 있다. 특히 전자소자의 발열량을 제어하지 못할 경우 온도가 상승하여 운용 중 성능저하 및 영구적 손상이 발생할 수 있다. 본 연구에서는 항공전자장비의 방열을 위한 냉각장치를 제작하여 해석과 시험을 통해 비교하였다. 냉각장치 열전달부를 히트파이프, 알루미늄, 구리를 이용하였으며 시험 결과, 히트파이프의 최고온도가 142.3°C로 나타나 알루미늄 대비 18.0°C 낮았고, 구리 대비 12.7°C 낮았다. 온도 편차는 알루미늄 대비 27.2°C, 구리 대비 17.0°C 가량 낮게 나타나 히트파이프의 열전달 성능이 가장 우수한 것을 확인하였으며, 작동 유체의 안정성을 검증하였다.

Research on the Effect of New Computer Data Processing Technology on the Development of Modern Avionics Equipment

For now, the continuous advancement of computer data processing technology has brought about earth-shaking improvements in the infrastructure and basic technology models of various industries in our society. In the course of the development of modern avionics equipment, the application of data processing skills has firmly grasped the air control authority of aviation electronic equipment. For the future progress of modern avionics, this is an epoch-making breakthrough in computer skills. This article analyzes the development of various aspects of avionics equipment from different perspectives. In addition, this article also conducts a rough analysis and exploration of computer skills related to equipment that can break through modern avionics to help study the practicability of the equipment assisted by it.

Research on typical fault classification method of DC-DC converter

DC-DC converter is the core component of power conversion module of integrated modular avionics. Condition monitoring and fault diagnosis of DC-DC converter can effectively improve the reliability of avionics equipment, reduce the maintenance cost and greatly improve the use efficiency of aircraft. In this paper, firstly, a typical DC-DC converter model based on SEPIC topology is designed in PSPICE environment, and the failure modes of DC-DC converter are analyzed. Secondly, the typical fault types of DC-DC converter are simulated, and the corresponding original data are obtained through simulation. Finally, the processing framework including data preprocessing, feature extraction and selection, and multi model fusion is used to do fault classification of the DC-DC converter. The fault diagnosis of the converter is simulated. Simulation results show the effectiveness of the proposed method.

Physics Based Degradation Models for Electrolytic Capacitor Prognostics under Thermal Overstress Conditions

Electronics subsystems play an increasingly important role in safety critical systems for monitoring, control, and enhanced functionality. Electrolytic capacitors are an important component in ,amy subsystems that range from power supplies on safety critical avionics equipment to power drivers for electro-mechanical actuators. These capacitors are ideal forpassing or bypassing low-frequency signals in power supplies but are known to have lower reliability compared to ceramic and tantalum capacitors, and given their criticality in electronicssubsystems they are a good candidate for component level monitoring and prognostics. Prognostics provides a way to assess remaining useful life of components and systems based on their current state of health and their anticipated future use and operating conditions. Past experiences have shown that capacitor degradation and failures are quite prevalent under high electrical and thermal stress conditions that they experience during operations. Our focus in this work is on deriving a physics-based degradation model for electrolytic capacitors under thermal stress conditions. As part of our methodology, we study the effects of accelerated aging due to thermal stress on a batch of capacitors stored at high ambient temperature conditions. This provides a framework for supplementing theoretical modeling with data collected from simultaneous experiments, which is then used to validate the derived models. This work represents a first step toward combining data driven and physics-based approaches for modeling capacitor degradation. The case study shows how the proposed technique is applied to a batch of identically manufactured capacitors.