Journal articles: 'Small aircraft'

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Rogalski, Tomasz, and Boguslaw Dołęga. "THE METHOD OF EVALUATION OF THE AIRCRAFT CONTROL SYSTEM." Aviation 9, no. 2 (June 30, 2005): 29–34. http://dx.doi.org/10.3846/16487788.2005.9635901.

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The dynamical development of general aviation demands compilation of new aircraft control methods. Those methods allow people without special airborne qualifications to pilot these aircrafts. The main goals of such a control system are to reduce a pilot's load, to improve control precision, and to protect an aircraft against dangerous situations. There are many criterions applied to grading and describing an aircraft's flying characteristics and the handling qualities of general aviation airplanes equipped with classical mechanical control systems. But a modern, small, transport aircraft should be equipped with fly‐by‐wire control systems, and there are no clear, straight, rules rate and describe the handling qualities of small airplanes with fly‐by‐wire control systems. This paper presents a methodology created by the authors that classifies and compares the handling qualities of general aviation aircraft equipped with fly‐by‐wire control systems. It takes into consideration two parameters: pilot's effort during realization of ordered tasks and precision of his control.

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Srinivas, G., and Srinivasa Rao Potti. "Computational Analysis of Fighter Aircraft Wing under Mach Number 0.7 for Small Sweep Angles." Applied Mechanics and Materials 592-594 (July 2014): 1020–24. http://dx.doi.org/10.4028/www.scientific.net/amm.592-594.1020.

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Fighter aircraft wings are the leading lift generating components for any aerospace vehicle. The recital of any flying vehicle largely depends on its wing design. Missiles and the fighter aircrafts which are having propulsion system mostly have fins to control and maneuver. In this present paper work an attempt has been made to design a fighter aircraft wing configuration which will be used in some air launched air to surface guided weapons fighter aircraft. The main focus of this paper agreement in determining the Sweep-back effects on fighter aircraft wing under transonic condition at different angles of attack (AoA) from 0 to 5 degrees. For this the fighter aircraft wing performance for various flow conditions and sweep angles are obtained based on the empirical, semi-empirical and CFD simulation results. Hence by studying these computational results would help in the optimizing geometry for better performance, an finest wing design for the air launched air to surface body with conservative wing can be obtained.

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Radchenko, L. K., and E. A. Vegner. "Aeronautical mapping for small aircraft." Geodesy and Cartography 911, no. 5 (June 20, 2016): 14–18. http://dx.doi.org/10.22389/0016-7126-2016-911-5-14-18.

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Ashley, Steven. "New Aircraft, Big and Small." Scientific American 293, no. 6 (December 2005): 60–61. http://dx.doi.org/10.1038/scientificamerican1205-60.

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Xie, Naiming. "Estimating civil aircraft’s research and manufacture cost by using grey system model and neural network algorithm." Grey Systems: Theory and Application 5, no. 1 (February 2, 2015): 89–104. http://dx.doi.org/10.1108/gs-12-2014-0054.

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Purpose – The purpose of this paper is to propose novel civil aircraft cost parameters’ selection method and novel cost estimation approach for civil aircraft so as to effectively simulate or forecast civil aircraft cost under poor information and small sample. Design/methodology/approach – Based on existent cost estimation indexes, this paper summarized civil aircraft research and manufacturing cost impact index system and adopted grey relational model to select most important impact factors. Consider civil aircrafts’ cost information could not be easily collected, the author must estimate their costs with limited sample and poor information. A combination model of GM (0, N) model and BP neural network algorithm is proposed. Both advantages of simulation of BP neural network algorithm and poor information generation of GM (0, N) were effectively combined. Then steps of combined model were given out. Finally, nine types of aircrafts were used to test the validity of proposed model. As comparing with the traditional multiple linear regression model and simple GM (0, N) model, results indicated that proposed model can do the work better. Findings – Grey relational model can be applied for parameters’ selection and combined GM (0, N) model and BP neural network algorithm can estimate aircraft’s cost as well. Results show that novel combined model could get high forecasting accuracy. Practical implications – Cost estimation is key problem in production management of civil aircraft. Effective cost management could promote competitiveness of aircraft manufacturing company. Proposed combined model can be applied for civil aircraft cost estimation. Similarly, it could be applied for other complex equipment cost estimation. Originality/value – The paper succeeds in proposing grey relational model for cost parameters’ selection and constructing a combination model of GM (0, N) model and BP neural network algorithm. Algorithm of the proposed model was discussed and steps were given out.

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Henne, Preston A. "Case for Small Supersonic Civil Aircraft." Journal of Aircraft 42, no. 3 (May 2005): 765–74. http://dx.doi.org/10.2514/1.5119.

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Sedunov, Alexander, Alexander Sutin, Hady Salloum, and Nikolay Sedunov. "Passive acoustic localization of small aircraft." Journal of the Acoustical Society of America 134, no. 5 (November 2013): 4076. http://dx.doi.org/10.1121/1.4830889.

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Kozeruk, S. O., and O. V. Korzhyk. "Detection Small Aircraft by Acoustic Radiation." Visnyk NTUU KPI Seriia - Radiotekhnika Radioaparatobuduvannia, no. 76 (March 30, 2019): 15–20. http://dx.doi.org/10.20535/radap.2019.76.15-20.

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Kozeruk, S. O., and O. V. Korzhyk. "Correlation direction finder for small aircraft." Visnyk NTUU KPI Seriia - Radiotekhnika Radioaparatobuduvannia, no. 79 (December 30, 2019): 41–47. http://dx.doi.org/10.20535/radap.2019.79.41-47.

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Kiyak, Emre, and Gulay Unal. "Small aircraft detection using deep learning." Aircraft Engineering and Aerospace Technology 93, no. 4 (June 2, 2021): 671–81. http://dx.doi.org/10.1108/aeat-11-2020-0259.

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Purpose The paper aims to address the tracking algorithm based on deep learning and four deep learning tracking models developed. They compared with each other to prevent collision and to obtain target tracking in autonomous aircraft. Design/methodology/approach First, to follow the visual target, the detection methods were used and then the tracking methods were examined. Here, four models (deep convolutional neural networks (DCNN), deep convolutional neural networks with fine-tuning (DCNNFN), transfer learning with deep convolutional neural network (TLDCNN) and fine-tuning deep convolutional neural network with transfer learning (FNDCNNTL)) were developed. Findings The training time of DCNN took 9 min 33 s, while the accuracy percentage was calculated as 84%. In DCNNFN, the training time of the network was calculated as 4 min 26 s and the accuracy percentage was 91%. The training of TLDCNN) took 34 min and 49 s and the accuracy percentage was calculated as 95%. With FNDCNNTL, the training time of the network was calculated as 34 min 33 s and the accuracy percentage was nearly 100%. Originality/value Compared to the results in the literature ranging from 89.4% to 95.6%, using FNDCNNTL, better results were found in the paper.

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Mirjafari, Masoumeh, Alireza Rashidi Komijan, and Ahmad Shoja. "An integrated model for aircraft routing and crew scheduling: Lagrangian Relaxation and metaheuristic algorithm." WPOM-Working Papers on Operations Management 11, no. 1 (January 24, 2020): 25. http://dx.doi.org/10.4995/wpom.v11i1.12891.

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<p>Airline optimization is a significant problem in recent researches and airline industrial as it can determine the level of service, profit and competition status of the airline. Aircraft and crew are expensive resources that need efficient utilization. This paper focuses simultaneously on two major issues including aircraft maintenance routing and crew scheduling. Several key issues such as aircraft replacement, fairly night flights assignment and long-life aircrafts are considered in this model. We used the flight hours as a new framework to control aircraft maintenance. At first, an integrated mathematical model for aircraft routing and crew scheduling problems is developed with the aim of cost minimization. Then, Lagrangian relaxation and Particle Swarm Optimization algorithm (PSO) are used as the solution techniques. To evaluate the efficiency of solution approaches, model is solved with different numerical examples in small, medium and large sizes and compared with GAMS output. The results show that Lagrangian relaxation method provides better solutions comparing to PSO and also has a small gap to optimum solution.</p>

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Zhou, Liming, Haoxin Yan, Yingzi Shan, Chang Zheng, Yang Liu, Xianyu Zuo, and Baojun Qiao. "Aircraft Detection for Remote Sensing Images Based on Deep Convolutional Neural Networks." Journal of Electrical and Computer Engineering 2021 (August 11, 2021): 1–16. http://dx.doi.org/10.1155/2021/4685644.

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Aircraft detection for remote sensing images, as one of the fields of computer vision, is one of the significant tasks of image processing based on deep learning. Recently, many high-performance algorithms for aircraft detection have been developed and applied in different scenarios. However, the proposed algorithms still have a series of problems; for instance, the algorithms will miss some small-scale aircrafts when applied to the remote sensing image. There are two main reasons for the problem; one reason is that the aircrafts in the remote sensing image are usually small in size, leading to detecting difficulty. The other reason is that the background of the remote sensing image is usually complex, so the algorithms applied to the scenario are easy to be affected by the background. To address the problem of small size, this paper proposes the Multiscale Detection Network (MSDN) which introduces a multiscale detection architecture to detect small-scale aircrafts. With the intention to resist the background noise, this paper proposes the Deeper and Wider Module (DAWM) which increases the perceptual field of the network to alleviate the affection. Besides, to address the two problems simultaneously, this paper introduces the DAWM into the MSDN and names the novel network structure as Multiscale Refined Detection Network (MSRDN). The experimental results show that the MSRDN method has detected the small-scale aircrafts that other algorithms missed and the performance indicators have higher performance than other algorithms.

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Bell, Robin E., Bernard J. Coakley, and Robert W. Stemp. "Airborne gravimetry from a small twin engine aircraft over the Long Island Sound." GEOPHYSICS 56, no. 9 (September 1991): 1486–93. http://dx.doi.org/10.1190/1.1443170.

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In January 1990, a test of the feasibility of airborne gravimetry from a small geophysical survey aircraft, a Cessna 404, was conducted over the Long Island Sound using a Bell Aerospace BGM-3 sea gravity meter. Gravity has been measured from large aircraft and specially modified de Havilland Twin Otters but never from small, standard survey aircraft. The gravity field of the Long Island Sound is dominated by an asymmetric positive 30 mGal anomaly which is well constrained by both marine and land gravity measurements. Using a Trimble 4000 GPS receiver to record the aircraft’s horizontal position and radar altimeter elevations to recover the vertical accelerations, gravity anomalies along a total of 65 km were successfully measured. The root mean square (rms) difference between the airborne results and marine measurements within 2 km of the flight path was 2.6 mGal for 15 measured values. The anomalies recovered from airborne gravimetry can also be compared with the gridded regional free air gravity field calculated using all available marine and land gravity measurements. The rms difference between 458 airborne gravity measurements and the regional gravity field is 2.7 mGal. This preliminary experiment demonstrates that gravity anomalies, with wavelengths as short as 5 km, can be measured from small aircraft with accuracies of 2.7 mGal or better. The gravity measurements could be improved by higher quality vertical and horizontal positioning and tuning the gravimeter’s stabilized platform for aircraft use.

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Papa, Umberto, and Salvatore Ponte. "Preliminary Design of an Unmanned Aircraft System for Aircraft General Visual Inspection." Electronics 7, no. 12 (December 14, 2018): 435. http://dx.doi.org/10.3390/electronics7120435.

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Among non-destructive inspection (NDI) techniques, General Visual Inspection (GVI), global or zonal, is the most widely used, being quick and relatively less expensive. In the aeronautic industry, GVI is a basic procedure for monitoring aircraft performance and ensuring safety and serviceability, and over 80% of the inspections on large transport category aircrafts are based on visual testing, both directly and remotely, either unaided or aided via mirrors, lenses, endoscopes or optic fiber devices coupled to cameras. This paper develops the idea of a global and/or zonal GVI procedure implemented by means of an autonomous unmanned aircraft system (UAS), equipped with a low-cost, high-definition (HD) camera for carrying out damage detection of panels, and a series of distance and trajectory sensors for obstacle avoidance and inspection path planning. An ultrasonic distance keeper system (UDKS), useful to guarantee a fixed distance between the UAS and the aircraft, was developed, and several ultrasonic sensors (HC-SR-04) together with an HD camera and a microcontroller were installed on the selected platform, a small commercial quad-rotor (micro-UAV). The overall system concept design and some laboratory experimental tests are presented to show the effectiveness of entrusting aircraft inspection procedures to a small UAS and a PC-based ground station for data collection and processing.

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Rohacs, Jozsef, Istvan Jankovics, Istvan Gal, Jerzy Bakunowicz, Giuseppe Mingione, and Antonio Carozza. "Small Aircraft Infrared Radiation Measurements Supporting the Engine Airframe Aero-thermal Integration." Periodica Polytechnica Transportation Engineering 47, no. 1 (March 12, 2018): 51–63. http://dx.doi.org/10.3311/pptr.11514.

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The large, EU Supported ESPOSA (Efficient Systems and propulsion for Small Aircraft) project has developed new small gas turbines for small aircraft. One of the important tasks was the engine - airframe aero-thermal radiation integration that included task of minimizing the infrared radiation of the small aircraft, too. This paper discusses the factors influencing on the aircraft infrared radiation, its possible simulation and measurements and introduces the results of small aircraft infrared radiation measurements. The temperature of aircraft hot parts heated by engines were determined for validation of methodology developed and applied to engine - aircraft thermal integration.

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Pachter, Meir, John Hansen, David Jacques, and Paul Blue. "Optimal Guidance of a Relay Aircraft to Extend Small Unmanned Aircraft Range." International Journal of Micro Air Vehicles 2, no. 3 (September 2010): 157–80. http://dx.doi.org/10.1260/1756-8293.2.3.157.

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17

Helbing, Kyle, Theresa Spaeth, and John Valasek. "Improving Aircraft Sequencing and Separation at a Small Aircraft Transportation System Airport." Journal of Aircraft 43, no. 6 (November 2006): 1636–42. http://dx.doi.org/10.2514/1.20637.

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Garcia, Gonzalo, and Shahriar Keshmiri. "Adaptive and Resilient Flight Control System for a Small Unmanned Aerial System." International Journal of Aerospace Engineering 2013 (2013): 1–25. http://dx.doi.org/10.1155/2013/289357.

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The main purpose of this paper is to develop an onboard adaptive and robust flight control system that improves control, stability, and survivability of a small unmanned aerial system in off-nominal or out-of-envelope conditions. The aerodynamics of aircraft associated with hazardous and adverse onboard conditions is inherently nonlinear and unsteady. The presented flight control system improves functionalities required to adapt the flight control in the presence of aircraft model uncertainties. The fault tolerant inner loop is enhanced by an adaptive real-time artificial neural network parameter identification to monitor important changes in the aircraft’s dynamics due to nonlinear and unsteady aerodynamics. The real-time artificial neural network parameter identification is done using the sliding mode learning concept and a modified version of the self-adaptive Levenberg algorithm. Numerically estimated stability and control derivatives are obtained by delta-based methods. New nonlinear guidance logic, stable in Lyapunov sense, is developed to guide the aircraft. The designed flight control system has better performance compared to a commercial off-the-shelf autopilot system in guiding and controlling an unmanned air system during a trajectory following.

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Kloet, N., S. Watkins, and R. Clothier. "Acoustic signature measurement of small multi-rotor unmanned aircraft systems." International Journal of Micro Air Vehicles 9, no. 1 (February 9, 2017): 3–14. http://dx.doi.org/10.1177/1756829316681868.

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This work describes the testing involved in generating an acoustic signature profile of a small multi-rotor unmanned aircraft system. A typical multi-rotor unmanned aircraft system, with a weight of approximately 2.1 kg, was used for sound pressure level measurements. This study established a relationship between distance, altitude and sound pressure level, finding that the sound decays approximately in line with 6 dB(A) reduction for a doubling of distance. The effect of the orientation of the multi-rotor unmanned aircraft system was also investigated. It was determined that the sound profile does not vary significantly around the periphery of the multi-rotor unmanned aircraft system in the propeller-plane. However, when measured with the observer underneath the multi-rotor unmanned aircraft system, the sound pressure level was found to vary by as much as 10 dB(A), with the greatest sound pressure level at approximately 45° from horizontal. Finally, an acoustic array was used to measure key frequencies for the main sound sources: motors and propellers. It was found that extraneous noise from the multi-rotor unmanned aircraft system frame vibration and mounting methods was also common. Despite relatively low levels of sound being measured (especially when compared with conventional aircraft and rotorcraft), the increasing numbers of unmanned aircraft systems in urban environments, close to humans and dwellings, suggests that increasing complaints are likely. Thus, further research was suggested, including expanding the range of multi-rotor unmanned aircraft system to be tested, introducing DGPS, improving the mounting for indoor testing, and psychoacoustic analysis of the sound.

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Wang, Ting, Changqing Cao, Xiaodong Zeng, Zhejun Feng, Jingshi Shen, Weiming Li, Bo Wang, Yuedong Zhou, and Xu Yan. "An Aircraft Object Detection Algorithm Based on Small Samples in Optical Remote Sensing Image." Applied Sciences 10, no. 17 (August 20, 2020): 5778. http://dx.doi.org/10.3390/app10175778.

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In recent years, remote sensing technology has developed rapidly, and the ground resolution of spaceborne optical remote sensing images has reached the sub-meter range, providing a new technical means for aircraft object detection. Research on aircraft object detection based on optical remote sensing images is of great significance for military object detection and recognition. However, spaceborne optical remote sensing images are difficult to obtain and costly. Therefore, this paper proposes the aircraft detection algorithm, itcan detect aircraft objects with small samples. Firstly, this paper establishes an aircraft object dataset containing weak and small aircraft objects. Secondly, the detection algorithm has been proposed to detect weak and small aircraft objects. Thirdly, the aircraft detection algorithm has been proposed to detect multiple aircraft objects of varying sizes. There are 13,324 aircraft in the test set. According to the method proposed in this paper, the f1 score can achieve 90.44%. Therefore, the aircraft objects can be detected simply and efficiently by using the method proposed. It can effectively detect aircraft objects and improve early warning capabilities.

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Iwaniuk, Andrzej, and Krzysztof Piwek. "Preliminary design and optimization for fleet to be used in the Small Air Transport system." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 14 (September 13, 2018): 2615–26. http://dx.doi.org/10.1177/0954410018800138.

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Over the last few years, teams from several research centres have been working on the concept of Small Air Transport, filling the niche between a regular surface transport and a scheduled air transport – on the distances over 200 km, utilizing numerous, though low in volume, passengers’ streams – giving regions a chance to improve their communication capabilities. Small Air Transport’s tasks are performed on small aeroplanes, which take up to 19 passengers, with a flight time of up to 4 h and at a reasonable price for a mass recipient. An important feature of the Small Air Transport system is personalization, which is flexible adaptation of the transport process to the customer’s requirements and capabilities. This paper focuses on the selection and optimization of key parameters of aircraft fleet used in Small Air Transport. The research and analysis were based on the parameters of a reference aircraft selected for each individual class of small aircraft. Taking into account the data of currently used aircraft, the calculations were made to obtain the generalized transport costs per passenger kilometre. The generalized transport costs covers both – the total operating costs and value of time of passengers. As a result of minimizing these costs in terms of the variability of the key design factors of aircraft, the parameters of the recommended aircraft, in particular, classes were obtained. It was found that generalized passenger-kilometre costs for recommended Small Air Transport aircraft are only 20–30% higher than for regional aircraft (with the same load factor) and are more advantageous for Small Air Transport aircraft (lower cost) for small local passenger flows. Utilizing Small Air Transport aircraft, the profitability of air transport expands to significantly less intense passenger flows. The analysis allowed defining key design parameters of aircraft fleet in Small Air Transport in the initial phase of a project.

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Poh, Chung-How, and Chung-Kiak Poh. "Isopropanol as Fuel for Small Unmanned Aircraft." Advances in Aerospace Science and Technology 02, no. 03 (2017): 23–30. http://dx.doi.org/10.4236/aast.2017.23003.

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Holmes, Bruce J., Michael H. Durham, and Scott E. Tarry. "Small Aircraft Transportation System Concept and Technologies." Journal of Aircraft 41, no. 1 (January 2004): 26–35. http://dx.doi.org/10.2514/1.3257.

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Prudden, S., A. Fisher, M. Marino, A. Mohamed, S. Watkins, and G. Wild. "Measuring wind with Small Unmanned Aircraft Systems." Journal of Wind Engineering and Industrial Aerodynamics 176 (May 2018): 197–210. http://dx.doi.org/10.1016/j.jweia.2018.03.029.

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McCormack, Edward, and John Stimberis. "Small Unmanned Aircraft Evaluated for Avalanche Control." Transportation Research Record: Journal of the Transportation Research Board 2169, no. 1 (January 2010): 168–73. http://dx.doi.org/10.3141/2169-18.

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McAree, O., J. M. Aitken, and S. M. Veres. "Quantifying situation awareness for small unmanned aircraft." Aeronautical Journal 122, no. 1251 (March 19, 2018): 733–46. http://dx.doi.org/10.1017/aer.2018.14.

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ABSTRACTA novel statistical model is presented to quantify situation awareness in the operation of small civilian Unmanned Aircraft Systems (UAS). Today, the vast majority of small Unmanned Aircraft Systems (UAS) operation takes place under Visual Line of Sight (VLOS) of a human operator, who is wholly responsible for the safety of the flight. As operation begins to move to Beyond Visual Line of Sight (BVLOS), it is likely that this responsibility will become shared between operator and the increasingly autonomous UAS itself. Before we seek to quantify the safety of such a system, it is beneficial to analyse the safety of existing Visual Line of Sight (VLOS) operations to provide a target level of safety. Prior to considering any on-board decision making, it is essential to ensure that the artificial situation awareness system of a UAS in Beyond Visual Line of Sight (BVLOS) is at least as good as awareness of a human operator. The paper provides a probabilistic theory and model for the high-level abstractions of situation awareness to guide future assessment of BVLOS operations.

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Bowen, Brent D., and Frederick D. Hansen. "Implementing A National Small Aircraft Transportation System." Public Works Management & Policy 5, no. 2 (October 2000): 160–69. http://dx.doi.org/10.1177/1087724x0052009.

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Ghommem, Mehdi, Victor M. Calo, and Christian G. Claudel. "Micro-cantilever flow sensor for small aircraft." Journal of Vibration and Control 21, no. 10 (October 2013): 2043–58. http://dx.doi.org/10.1177/1077546313505636.

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Rylander, R., and M. Björkman. "ANNOYANCE BY AIRCRAFT NOISE AROUND SMALL AIRPORTS." Journal of Sound and Vibration 205, no. 4 (August 1997): 533–37. http://dx.doi.org/10.1006/jsvi.1997.1022.

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Adam, John A. "Case study fighter aircraft: Small and agile." IEEE Spectrum 24, no. 5 (1987): 64–66. http://dx.doi.org/10.1109/mspec.1987.6447942.

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Frew, Eric W., and Timothy X. Brown. "Networking Issues for Small Unmanned Aircraft Systems." Journal of Intelligent and Robotic Systems 54, no. 1-3 (July 17, 2008): 21–37. http://dx.doi.org/10.1007/s10846-008-9253-2.

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Pereda Albarrán, M. Y., M. Kreimeier, W. Enders, and E. Stumpf. "Noise evaluation of battery powered small aircraft." CEAS Aeronautical Journal 11, no. 1 (June 27, 2019): 125–35. http://dx.doi.org/10.1007/s13272-019-00404-2.

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Džunda, Milan, Peter Dzurovčin, and Lucia Melníková. "Anti-Collision System for Small Civil Aircraft." Applied Sciences 12, no. 3 (February 4, 2022): 1648. http://dx.doi.org/10.3390/app12031648.

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This paper presents the results of the research in the field of anti-collision systems for small civil aircraft, which are not dependent on secondary radars and satellite navigation systems. The aviation communication network was used to design the anti-collision system. The simulation results manifested that the anti-collision system precision depended on the errors of synchronization of the aviation communication network. The precision of the anti-collision system is also influenced by the errors of the coordinates of individual aviation communication network users, based on which the system identifies its own position. The results of the simulation show that the dispersion of the positioning error σ2∆P by the ACS system varied in the range of 1.94 m2 to 503.23 m2. The simulation results confirm that the designed anti-collision system is operational in establishing its position against other FOs, with the distance from the given FOs being 50.0 km maximum. The main contribution of this paper are derived algorithms for the operation of an anti-collision system for small civil aircraft, in addition to the design of movement trajectory models of five flying objects which operate within the aviation communication network. The advantage of the anti-collision system is that it is independent of satnav systems and secondary radars. A significant advantage is the low cost of this system.

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Guła, Paweł, Dawid Ulma, Krzysztof Żurek, and Rafał Żurawski. "Challenges of turboprop engine installation on small aircraft." Aircraft Engineering and Aerospace Technology 91, no. 7 (July 8, 2019): 938–48. http://dx.doi.org/10.1108/aeat-09-2017-0198.

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Purpose The purpose of this paper is to present the challenges of turbine engine installation on small aircraft. The work was a part of the European Union project Efficient Systems and Propulsion for Small Aircraft, FP7 EU – Activity, 7.1.4. improving cost efficiency. Design/methodology/approach Few of the most interesting issues associated with replacing a piston engine with a turboprop engine were chosen: changes in engine bay cooling, air inlet, exhaust system, nacellès weight and parts reduction, flight tests and performance. The publication presents an approach to: design, assemble and test the small aircraft with a turboprop engine. Findings Replacement of piston engine by turbine was carried out. The full program of ground and flight test small aircraft has been successfully completed. Pros and cons of the new design are described in the paper. Practical implications Currently, aviation gasoline (AVGAS ) is increasingly being replaced by JET-A1 (kerosene-type fuels) or diesel fuel. The change concerns engine replacement and all the necessary additional components on the aircraft. This is consistent with the new directions of development of aviation: clean, green and eco design. Replacing the piston engine with a turbine allows improvement to performance and reduces operation cost. Originality/value The achieved results allow for identifying and highlighting new directions of aviation technology development. A significant added value is to draw attention to the necessity of preparing for future requirements and amendments in regulations for the new class of aircraft: general aviation SET(L) – single engine turboprop.

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Paulson, C. A., A. Sóbester, and J. P. Scanlan. "The rapid development of bespoke small unmanned aircraft." Aeronautical Journal 121, no. 1245 (October 30, 2017): 1683–710. http://dx.doi.org/10.1017/aer.2017.99.

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ABSTRACTThe ability to quickly fabricate small unmanned aircraft system (sUAS) through Additive Manufacturing (AM) methods opens a range of new possibilities for the design and optimisation of these vehicles. In this paper, we propose a design loop that makes use of surrogate modelling and AM to reduce the design and optimisation time of scientific sUAS. AM reduces the time and effort required to fabricate a complete aircraft, allowing for rapid design iterations and flight testing. Co-Kriging surrogate models allow data collected from test flights to correct Kriging models trained with numerically simulated data. The resulting model provides physically accurate and computationally cheap aircraft performance predictions. A global optimiser is used to search this model to find an optimal design for a bespoke aircraft. This paper presents the design loop and a case study which demonstrates its application.

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Lehr, William J. "THE POTENTIAL USE OF SMALL UAS IN SPILL RESPONSE." International Oil Spill Conference Proceedings 2008, no. 1 (May 1, 2008): 431–33. http://dx.doi.org/10.7901/2169-3358-2008-1-431.

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ABSTRACT For the last several decades, the sensors available for remote sensing of oil spills have changed significantly while the platforms for these sensors have remained unaltered. The limitations on these platforms are well known. Satellites are expensive, remote, and inflexible. Fixed-wing aircraft cannot hover easily over the spill site and often fly too fast for good observations. Helicopters are expensive, require specially trained pilots, and can be more hazardous than other alternatives. Unmanned aircraft systems (UAS) provide a potentially new alternative platform for monitoring spill location and clean-up operations. The aircraft (also called unmanned aerial or airborne vehicles) fit into three general categories. Very large aircraft require much or more of the infrastructure of manned aircraft and will probably be deployed only in spills of national significance. Mid-range vehicles have proven their worth monitoring forests fires, emergencies with many similar requirements to oil spills, but still require designated landing and take-off facilities. A rapidly expanding category is the very small UAS that can be field launched and recovered. The range, guidance, and sensor availability of these aircraft have improved considerably from early prototypes. This paper explores the possibility of incorporating particularly these smaller UAS into spill response. Potential roadblocks include weather limitations, operator training, payload restrictions and regulatory restrictions. This last roadblock is presently the most difficult to overcome although re-consideration at the Federal Aviation Administration could modify existing regulations, making use of low-flying unmanned aircraft more plausible. Assuming the necessary regulatory changes, the paper explores typical applications and expected benefits from such system.

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Li, Ziheng. "Prototype of a Solar-powered Fix-winged Unmanned Aerial Vehicle." Journal of Physics: Conference Series 2029, no. 1 (September 1, 2021): 012016. http://dx.doi.org/10.1088/1742-6596/2029/1/012016.

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Abstract The usage of solar power is a plausible and environment-friendly solution to solve the problem of limited duration of operation of current Unmanned Aerial Vehicle (UAVs) in market. Based on the state-of-the-art experiments in integrating solar power into aircraft and the basic theoretical calculations, this study investigates an attempt to construct a remote control solar-panel powered autopilot fixed-wing aircraft with technology accessible for home crafting. The aircraft is designed to recharge itself using sunlight within the duration of its operation and execute certain simple autopilot routes. The success of this model sheds light for further research and investment in making small-scale aircrafts solar-powered.

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Yang, Du Wei, Jian Zhong Zhou, and Jun Chao Dong. "Modeling Study of Aircraft Based on Small Perturbation Equation." Advanced Materials Research 466-467 (February 2012): 1407–12. http://dx.doi.org/10.4028/www.scientific.net/amr.466-467.1407.

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In aircraft flight control law design, the first key is to establish actual aircraft mathematical model, then according to the model of dynamic output information, analysis control law design is appropriate. But in the movement the aircraft is a complex dynamics system, modeling is very complex. This paper firstly carry out comprehensive feasibility analysis, on a plane modeling consideration simplified, secondly, in actual applications verified using the perturbation method of nonlinear equation linearization, establish the plane mathematics model.

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Dolzhenko, N., E. Mailyanova, I. Assilbekova, and Z. Konakbay. "ANALYSIS OF METEOROLOGICAL CONDITIONS SIGNIFICANT FOR SMALL AVIATION AND TRAINING FLIGHTS AT THE AIRFIELD “BALKHASH” FOR PLANNING AND FLIGHT SAFETY PURPOSES." Series of Geology and Technical Sciences 2, no. 446 (April 15, 2021): 62–67. http://dx.doi.org/10.32014/2021.2518-170x.35.

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Cloudiness and range of visibility are the most significant flight conditions for aircraft. The impact of clouds and visibility on the safety of aircraft flights, especially small aircraft, cannot be overestimated. According to the Interstate Air Committee, Kazakhstan ranks second in the number of aviation disasters. The average age of a third of Kazakhstan's small aircraft is more than 30 years. Over the past few years, 14 air accidents have occurred in the Republic of Kazakhstan, 11 of them with small aircraft. In this work, we investigate long-term data on cloudiness and visibility at the most weather-favorable airfield in Balkhash, for the possibility of safe and economical flights of small aircraft and planning training flights.

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Glowacki, Pawel Jan, Leszek Loroch, and Wlodzimierz Balicki. "Operations reliability study of small aircraft powered by piston engines." Aircraft Engineering and Aerospace Technology 92, no. 3 (October 12, 2018): 285–95. http://dx.doi.org/10.1108/aeat-01-2018-0005.

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Purpose Europe has adopted Flight Path 2050 (FP 2050) challenge with an objective of 90 per cent of the travelers being able to reach door-to-door European destinations within 4 hours by 2050. The aim can be achieved by reliable, well-organized small aircraft transport (SAT). Analysis of the currently operating small aircraft operational reliability data will support the development of future aircraft designs as well as reliability and safety requirements necessary for commercial operations. Design/methodology/approach The paper provides results of a statistical analysis of small aircraft current operations based on the reported events contained in the Database named European Coordination Centre for Aviation Incident Reporting Systems database. It presents identified safety indicators and focuses particularly on those related to the aviation technology. Findings It has been found that certain airframe and powerplant systems have the biggest influence on flight safety. Practical implications Multidisciplinary analysis of the operational and aircraft components reliability data will help in a proper preparation of the SAT supporting facilities, a design process of new aircraft and improvements of the existing airframe and powerplant systems. Originality/value Presented results are valuable for further developments of the statistical tools facilitating new product introduction.

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Hospodka, Jakub, Helena Bínová, and Stanislav Pleninger. "Assessment of All-Electric General Aviation Aircraft." Energies 13, no. 23 (November 25, 2020): 6206. http://dx.doi.org/10.3390/en13236206.

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The purpose of this paper is to describe the upcoming changes that will bring the transition from piston engines to all-electric aircrafts. The article focuses on the differences in operation of small general aviation aircrafts. This topic is timely, as the first all-electric aircraft was certified by the European Union Aviation Safety Agency (EASA) in 2019. As there are no data concerning this new type of operation available, the data have been derived from other applicable sources. At first, we compared the energy consumption of the same aircraft with the piston engine, and then afterwards with the retrofitted all-electric variant. Our results focus on the difference in fuel price, which is discussed in the context of electricity price comparison with AVGAS prices. Moreover, we discuss the environmental impacts, especially concerning electricity source mix and emissions produced (we estimate both with and without life-cycle assessment). In the discussion, we compare the results and identify the benefits of an all-electric solution. Furthermore, several operational restrictions of all-electric aircrafts are discussed.

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Li, Peng, Yan Heng Zhang, Han Xu Sun, and Hao Pan. "Design and Aerodynamic Characteristics Study of a Spherical Aircraft." Advanced Materials Research 662 (February 2013): 612–15. http://dx.doi.org/10.4028/www.scientific.net/amr.662.612.

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In order to achieve the goals of small aircraft’s taking off and landing in any posture and the protection of propeller, a new single-propeller spherical aircraft structure was proposed, which had the capacity of flying in the air and walking on the ground simultaneously. An aerodynamic model of the aircraft was built. The aerodynamic characteristics of the spherical aircraft, including the lift and the anti-torque and the generated torque of the flow deflectors under the propeller’s down airflow, are studied in depth by means of CFD numerical simulation method. A reasonable design and installation program is proposed according to the research results.

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Aitmagambetov, Altay Z., Denis I. Yeryomin, Dinara G. Zhaxygulova, and Rimma A. Kaliyeva. "Satellite-based location determination of small aircraft in case of accidents and disasters." SYNCHROINFO JOURNAL 6, no. 5 (2020): 33–37. http://dx.doi.org/10.36724/2664-066x-2020-6-2-33-37.

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From the moment the air/aero/aerial objects appeared the necessity of monitoring for them arose and were solved using different tools, such as radio communications, radio direction finding, radar and others. With the advent of global satellite navigation, the massive introduction of navigation equipment began in almost all areas of human activity and especially in mobile (moving) objects (cars, aircraft, ships, etc.). This allowed aircraft crews to accurately determine their coordinates in real time under any weather conditions. However, the organization of uninterrupted data transmission to ground control centers remained problematic. In this regard, aircraft monitoring systems were primarily installed on military and civil aircraft, while the other categories and types of aircraft were equipped only with communication systems. Thus, currently, there is the lack of navigation devices allowing flight monitoring and communication in small aviation. As a result, in case of emergency landing of small aircraft, it takes a lot of time and effort to find its location, therefore providing emergency assistance to passengers and crew is not possible. This problem can be solved by the system for determining the location of small aircraft using technologies of global navigation satellite systems and mobile satellite communications. This system includes devices for registering the location of the observed object, transmitting data via mobile cellular and satellite communications, processing, storage and displaying of data. The proposed system, by continuously recording and transmitting aircraft location data to the ground control center, helps minimize time and narrow the search area of the aircraft that made an emergency landing.

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Iwaniuk, Andrzej, and Witold Wiśniowski. "Optimization of small aircraft parameters in the initial phase of the project." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 12 (June 28, 2017): 2248–58. http://dx.doi.org/10.1177/0954410017716481.

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Conceptual and preliminary designs of future aircraft have become increasingly complex due to the enlargement of the basic criteria for evaluating emerging solutions. In the past, the basic performance characteristics of an airplane were the only selection criteria. Today, more and more emphasis is placed on factors such as impact on the environment, cost-effectiveness, or comfort of travel. The method for optimization of the key parameters of a small aircraft for use in the initial phase of a project is presented in this paper. It takes into account the requirements of aviation safety imposed by the European Union certification specifications CS-23 and requirements of aircraft competitiveness. Requirements and design assumptions were formulated based on the concept of the Small Air Transport system (SATs). The method is based on the multidisciplinary design optimization and covers the basic areas related to the design of aircraft: aerodynamics, aircraft structure, performance and expected operating costs. The objective function is defined as the value of the direct operating cost per passenger-kilometre. An evolutionary algorithm was applied to solve the optimization problem. As an example of the use of this method, the optimization of design parameters of the two classes of aircraft, 9-seater and 19-seater was carried out. The results were compared with the parameters of aircraft, which are in service. Sensitivity analysis of the objective function with respect to selected parameters of the aircraft was also made. The analysis allowed to select the most important parameters responsible for the operational costs.

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Pan, Weijun, Zhengyuan Wu, and Xiaolei Zhang. "Identification of Aircraft Wake Vortex Based on SVM." Mathematical Problems in Engineering 2020 (May 12, 2020): 1–8. http://dx.doi.org/10.1155/2020/9314164.

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The aircraft wake vortex has important influence on the operation of the airspace utilization ratio. Particularly, the identification of aircraft wake vortex using the pulsed Doppler lidar characteristics provides a new knowledge of wake turbulence separation standards. This paper develops an efficient pattern recognition-based method for identifying the aircraft wake vortex measured with the pulsed Doppler lidar. The proposed method is outlined in two stages. (i) First, a classification model based on support vector machine (SVM) is introduced to extract the radial velocity features in the wind fields by combining the environmental parameters. (ii) Then, grid search and cross-validation based on soft margin SVM with kernel tricks are employed to identify the aircraft wake vortex, using the test dataset. The dataset includes wake vortices of various aircrafts collected at the Chengdu Shuangliu International Airport from Aug 16, 2018, to Oct 10, 2018. The experimental results on dataset show that the proposed method can identify the aircraft wake vortex with only a small loss, which ensures the satisfactory robustness in detection performance.

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Zikmund, Pavel, Lukáš Dubnický, Michaela Horpatzká, Miroslav Macík, and Ivo Jebáček. "Flight Test of Pilot-Aircraft Haptic Feedback System." MATEC Web of Conferences 304 (2019): 06005. http://dx.doi.org/10.1051/matecconf/201930406005.

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This research is focused on an innovative improvement of pilot-aircraft interaction and is targeted on small aircraft. Haptic feedback is performed by actuators mounted on an aircraft's controls. The purpose of the actuators on a control stick and pedals is stall warning and a pilot guiding to safe and economical flight regimes. The feedback system mediates airflow data as angles of attack and sideslip. The paper brings results of a flight test of the proposed system. Qualitative evaluation of the haptic feedback inflight is presented. Benefits of the system are presented on a sideslip during turning. Some recommendations for the haptic pilot-aircraft interaction are stated within the discussion of the flight test results.

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Wang, Yantian, Haifeng Li, Peng Jia, Guo Zhang, Taoyang Wang, and Xiaoyun Hao. "Multi-Scale DenseNets-Based Aircraft Detection from Remote Sensing Images." Sensors 19, no. 23 (November 29, 2019): 5270. http://dx.doi.org/10.3390/s19235270.

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Deep learning-based aircraft detection methods have been increasingly implemented in recent years. However, due to the multi-resolution imaging modes, aircrafts in different images show very wide diversity on size, view and other visual features, which brings great challenges to detection. Although standard deep convolution neural networks (DCNN) can extract rich semantic features, they destroy the bottom-level location information. The features of small targets may also be submerged by redundant top-level features, resulting in poor detection. To address these problems, we proposed a compact multi-scale dense convolutional neural network (MS-DenseNet) for aircraft detection in remote sensing images. Herein, DenseNet was utilized for feature extraction, which enhances the propagation and reuse of the bottom-level high-resolution features. Subsequently, we combined feature pyramid network (FPN) with DenseNet to form a MS-DenseNet for learning multi-scale features, especially features of small objects. Finally, by compressing some of the unnecessary convolution layers of each dense block, we designed three new compact architectures: MS-DenseNet-41, MS-DenseNet-65, and MS-DenseNet-77. Comparative experiments showed that the compact MS-DenseNet-65 obtained a noticeable improvement in detecting small aircrafts and achieved state-of-the-art performance with a recall of 94% and an F1-score of 92.7% and cost less computational time. Furthermore, the experimental results on robustness of UCAS-AOD and RSOD datasets also indicate the good transferability of our method.

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Janovec, Michal, Jozef Čerňan, Filip Škultéty, and Andrej Novák. "Design of Batteries for a Hybrid Propulsion System of a Training Aircraft." Energies 15, no. 1 (December 22, 2021): 49. http://dx.doi.org/10.3390/en15010049.

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In this article, we propose the parameters of a battery that would be suitable for the conceptual design of a small training aircraft. The mass design of the battery is based on the requirements for real training flights performed by students in pilot training. Such a serial hybrid propulsion aircraft could be used in our UNIZA aviation, training and education center for pilot training. Due to socio-political pressures in reducing emissions generated by vehicles, there has also been massive research in the aviation industry in the field of hybrid and electric aircraft propulsion. In the introduction, the article deals with the energy sources used in aircraft propulsion. In hybrid propulsion, a combination of aviation fuel and electricity is used as the energy source. The required total energy must choose a suitable combination of these two energy sources. The biggest drawback of batteries that can be used in hybrid systems is their low energy density. Low energy density means that larger and heavier batteries need to be used to achieve the required performance, which is their main disadvantage. Therefore, it is necessary to find a suitable compromise between the hybrid’s percentage, i.e., the ratio between conventional and electric drive. We applied the hybrid aircraft system’s calculations to the real training flights to determine the necessary parameters of the hybrid aircraft suitable for pilot training. This calculation will help in obtaining an idea of the basic parameters of the hybrid drive and the battery parameters, which are necessary for particular applications in the training aircraft. The performed calculations of the hybrid configuration and, especially, the determination of the battery of the hybrid propulsion parameters provide the basic information necessary for the design of the hybrid system of a small training aircraft. These outputs can be used to determine the parameters of batteries that would be used in hybrid systems. A limiting factor to consider with hybrid aircrafts is that the aircraft must be charged on the ground before the flight, which poses interesting logistical and infrastructure problems at the airport.

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Phillips, W. F., and B. W. Santana. "Aircraft Small-Disturbance Theory with Longitudinal-Lateral Coupling." Journal of Aircraft 39, no. 6 (November 2002): 973–80. http://dx.doi.org/10.2514/2.3050.

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Zhang, Xing, Wei Wang, and Guang Hua Zong. "The Application of Piezoelectric Actuator for Small Aircraft." Advanced Materials Research 998-999 (July 2014): 674–77. http://dx.doi.org/10.4028/www.scientific.net/amr.998-999.674.

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This paper describes the design, construction, and analysis of a new piezoelectric actuator design for small aircrafts in the special requirements of the steering weight. It describes the working principle of piezo actuator, optimizes the piezo chip specification parameters by experimental measurements, put forward the finite element analysis simulation and the experimental testing of piezoelectric actuators’ drive performance. The simulation and experimental results show that the new design meets the design requirements of weight and space control.

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Journal articles on the topic 'Small aircraft'

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