Статті в журналах з теми "Integrated Wing Design"
Щоб переглянути інші типи публікацій з цієї теми, перейдіть за посиланням: Integrated Wing Design.
Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями
Ознайомтеся з топ-50 статей у журналах для дослідження на тему "Integrated Wing Design".
Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.
Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.
Переглядайте статті в журналах для різних дисциплін та оформлюйте правильно вашу бібліографію.
1
Rais-Rohani, M., R. T. Haftka, B. Grossman, and E. R. Unger. "Integrated aerodynamic-structural-control wing design." Computing Systems in Engineering 3, no. 6 (December 1992): 639–50. http://dx.doi.org/10.1016/0956-0521(92)90015-b.
Повний текст джерела
2
Oleinikov, Alexander Ivanovich. "Integrated Design of Wing Panel Manufacture Processes." Key Engineering Materials 554-557 (June 2013): 2175–86. http://dx.doi.org/10.4028/www.scientific.net/kem.554-557.2175.
Повний текст джерелаАнотація:
ALEXANDER IVANOVICH OLEINIKOV Aircraft Engineering Faculty, Komsomolsk-on-Amur State Technical University Lenina prospect 27, 681013 Komsomolsk-on-Amur, Russian Federation a.i.oleinikov@mail.ru Keywords: forming, creep, age, transversely isotropic, kind of the stress state effect, wing panel, inverse problem, reverse engineering, computer-aided process design system. Abstract. Problems of inelastic straining of three-dimensional bodies with large displacements and turns are considered. In addition to the sought fields, surface forces and boundary displacements, original size and shape have also to be determined from specified residual displacements in these problems. Currently, forming of light metals poses tremendous challenges due to their low ductility at room temperature and their unusual deformation characteristics at hot-cold work: strong asymmetry between tensile and compressive behavior, and a very pronounced anisotropy. We proposed the constitutive models of steady-state creep of initially transverse isotropy structural materials the kind of the stress state has influence [1]. The forming process considered includes two stages: active stage of elastoviscoplastic straining of the blank in the die tooling and passive stage of unloading of the blank withdrawn from the die tooling. The final stress-strain state at the active stage is the initial state for the passive stage. Unloading is considered as purely elastic straining, with no increments of inelastic strains. The active stage, in turn, also includes two steps. At the first step, the frontal faces of the “cold” blank are pressed to the working surfaces of the die tooling, which results in elastoplastic straining of the blank. The second step includes the processes of stress relaxation and creep strain in the blank fixed in this die tooling during a given time at an elevated ageing temperature. Computer modeling of these forming processes involves the use of the finite element method for consecutive solutions of three-dimensional quasi-static problems of elastoplastic straining, relaxation, and unloading, and also determining boundary conditions from given residual displacements [2] . The paper gives basics of the developed computer-aided system of design, modeling, and electronic simulation targeting the processes of manufacture of wing integral panels. System application data resulting from computation of 3D-involute of a CAD-based panel model, determination of working surfaces of die tooling, three-dimensional analysis of stresses, and simulation of panel shaping under diverse thermo-mechanical and speed conditions are demonstrated. Modeling of forming of wing panels of the SSJ-100 aircraft are considered [2,3]. The modeling results can be used to calculate the die tooling, determine the panel processibility, and control panel rejection in the course of forming [3]. References [1] A.I. Oleinikov, Models for the steady-state creep of transversely isotropic materials with different tension and compression characteristics, J. Ind. Appl. Math. 5 (2011) 406-409. [2] B.D. Annin, A.I. Oleinikov and K.S. Bormotin, Modeling of forming of wing panels of the SSJ-100 aircraft, J. Appl. Mech. Physics 51 (2010) 579-589. [3] A.I. Oleinikov, A.I. Pekarsh, Integrated Design of Integral Panel Manufacture Processes. Dalnauka, Vladivostok, 2010.
3
Grossman, B., Z. Gurdal, G. J. Strauch, W. M. Eppard, and R. T. Haftka. "Integrated aerodynamic/structural design of a sailplane wing." Journal of Aircraft 25, no. 9 (September 1988): 855–60. http://dx.doi.org/10.2514/3.45670.
Повний текст джерела
4
Grossman, B., R. T. Haftka, P. J. Kao, D. M. Polen, M. Rais-Rohani, and J. Sobieszczanski-Sobieski. "Integrated aerodynamic-structural design of a transport wing." Journal of Aircraft 27, no. 12 (December 1990): 1050–56. http://dx.doi.org/10.2514/3.45980.
Повний текст джерела
5
SALISTEAN, ADRIAN, DOINA TOMA, IONELA BADEA, and MIHAELA JOMIR. "Design of a small-scale UAV textile wing fluid-structure numerical modelling." Industria Textila 72, no. 04 (September 1, 2021): 449–53. http://dx.doi.org/10.35530/it.072.04.1844.
Повний текст джерелаАнотація:
This paper depicts the early phase in the research development for an integrated UAV (Unmanned Aerial Vehicle)support system tailored for emergency response actions and remote sensing. The support system is envisioned as an integrated Unmanned Aerial System (UAS) system that consists of one or more ultralight multifunctional aerial units with a configuration that can be adapted to the nature of the intervention: monitoring, mapping, observation, logistics etc. These aerial units comprise of para-motor type UAVs that use textile paraglider wings of a special design. The overall development and theoretical design aspects that are involved in this research is subject of change been part of an ongoing research study. Starting from wing airfoil and material selection, a design phase is under development for a single sail paraglider wing that can meet the operational demands for the envisioned system. The wing is designed mainly to have an easy handling, predictable deployment at all times and good aerodynamic characteristics. The paper tackles in particular the stretch effect on the wing and the influence on these aerodynamic characteristics as well as means of minimizing the adverse effects.
6
Patil, Ankur S., and Emily J. Arnold. "Sensor-Driven Preliminary Wing Ground Plane Sizing Approach and Applications." International Journal of Aerospace Engineering 2018 (July 2, 2018): 1–15. http://dx.doi.org/10.1155/2018/6378635.
Повний текст джерелаАнотація:
Structurally integrated antenna arrays provide synergies allowing the integration of large apertures onto airborne platforms. However, the surrounding airframe can greatly impact the performance of the antenna array. This paper presents a sensor-driven preliminary wing ground plane sizing approach to provide insight into the implications of design decisions on payload performance. The improvement of a wing-integrated antenna array that utilizes the wing as a ground plane motivated this study. Relationships for wing span, wing chord, and thickness are derived from extensive parametric electromagnetic simulations based on optimum antenna performance. It is expected that these equations would be used after an initial wing-loading design point has been selected to provide the designer guidance into how various wing parameters might affect the integrated antenna performance.
7
Maute, K., and G. W. Reich. "Integrated Multidisciplinary Topology Optimization Approach to Adaptive Wing Design." Journal of Aircraft 43, no. 1 (January 2006): 253–63. http://dx.doi.org/10.2514/1.12802.
Повний текст джерела
8
Botez, R. M., M. J. Tchatchueng Kammegne, and L. T. Grigorie. "Design, numerical simulation and experimental testing of a controlled electrical actuation system in a real aircraft morphing wing model." Aeronautical Journal 119, no. 1219 (September 2015): 1047–72. http://dx.doi.org/10.1017/s0001924000011131.
Повний текст джерелаАнотація:
AbstractThe paper focuses on the modelling, simulation and control of an electrical miniature actuator integrated in the actuation mechanism of a new morphing wing application. The morphed wing is a portion of an existing regional aircraft wing, its interior consisting of spars, stringers, and ribs, and having a structural rigidity similar to the rigidity of a real aircraft. The upper surface of the wing is a flexible skin, made of composite materials, and optimised in order to fulfill the morphing wing project requirements. In addition, a controllable rigid aileron is attached on the wing. The established architecture of the actuation mechanism uses four similar miniature actuators fixed inside the wing and actuating directly the flexible upper surface of the wing. The actuator was designed in-house, as there is no actuator on the market that could fit directly inside our morphing wing model. It consists of a brushless direct current (BLDC) motor with a gearbox and a screw for pushing and pulling the flexible upper surface of the wing. The electrical motor and the screw are coupled through a gearing system. Before proceeding with the modelling, the actuator is tested experimentally (stand alone configuration) to ensure that the entire range of the requirements (rated or nominal torque, nominal current, nominal speed, static force, size) would be fulfilled. In order to validate the theoretical, simulation and standalone configuration experimental studies, a bench testing and a wind-tunnel testing of four similar actuators integrated on the real morphing wing model are performed.
9
Zhang, Gong Ping, Zhi Zhong Liao, Chao Yang Duan, and Peng Ju Wang. "Optimal Design of Configuration Change Program for Tactical Missile with Morphing Wings." Applied Mechanics and Materials 101-102 (September 2011): 410–13. http://dx.doi.org/10.4028/www.scientific.net/amm.101-102.410.
Повний текст джерелаАнотація:
The flight Performance of missile can be improved by adaptive morphing wing serving as main lift surface. A novel compounded morphing missile, a complicated nonlinear and non-analytical multivariable constrained optimization problem, is modeled to design adaptive program of the wing geometry versus flight states. Based on reformed optimal algorithms such as Monte Carlo and Particle Swarm Optimization (PSO), a set of integrated approach is developed to optimize the shape change program of wings by interactively reading and writing data files from missile DATCOM. The simulation results show that the proposed algorithms can be used to obtain an optimal missile configuration over large flight envelope, characterized by maximal lift-to-drag ratio and a required normal overload.
10
de Mattos, Bento Silva, Paulo Jiniche Komatsu, and Jesuíno Takachi Tomita. "Optimal wingtip device design for transport airplane." Aircraft Engineering and Aerospace Technology 90, no. 5 (July 2, 2018): 743–63. http://dx.doi.org/10.1108/aeat-07-2015-0183.
Повний текст джерелаАнотація:
Purpose The present work aims to analyze the feasibility of wingtip device incorporation into transport airplane configurations considering many aspects such as performance, cost and environmental impact. A design framework encompassing optimization for wing-body configurations with and without winglets is described and application examples are presented and discussed. Design/methodology/approach modeFrontier, an object-oriented optimization design framework, was used to perform optimization tasks of configurations with wingtip devices. A full potential code with viscous effects correction was used to calculate the aerodynamic characteristics of the fuselage–wing–winglet configuration. MATLAB® was also used to perform some computations and was easily integrated into the modeFrontier frameworks. CFD analyses of transport airplanes configurations were also performed with Fluent and CFD++ codes. Findings Winglet provides considerable aerodynamic benefits regarding similar wings without winglets. Drag coefficient reduction in the order of 15 drag counts was achieved in the cruise condition. Winglet also provides a small boost in the clean-wing maximum lift coefficient. In addition, less fuel burn means fewer emissions and contributes toward preserving the environment. Practical implications More efficient transport airplanes, presenting considerable lower fuel burn. Social implications Among other contributions, wingtip devices reduce fuel burn, engine emissions and contribute to a longer engine lifespan, reducing direct operating costs. This way, they are in tune with a greener world. Originality/value The paper provides valuable wind-tunnel data of several winglet configurations, an impact of the incorporation of winglets on airplane design diagram and a direct comparison of two optimizations, one performed with winglets in the configuration and the other without winglets. These simulations showed that their Pareto fronts are clearly apart from each other, with the one from the configuration with winglets placed well above the other without winglets. The present simulations indicate that there are always aerodynamic benefits present regardless the skeptical statements of some engineers. that a well-designed wing does not need any winglet.
11
Conn, A. T., S. C. Burgess, and C. S. Ling. "Design of a parallel crank-rocker flapping mechanism for insect-inspired micro air vehicles." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 221, no. 10 (September 30, 2007): 1211–22. http://dx.doi.org/10.1243/09544062jmes517.
Повний текст джерелаАнотація:
In the current paper, a novel micro air vehicle (MAV) flapping mechanism for replicating insect wing kinematics is presented. Insects flap their wings in a complex motion that enables them to generate several unsteady aerodynamic mechanisms, which are extremely beneficial for lift production. A flapping wing MAV that can reproduce these aerodynamic mechanisms in a controlled manner is likely to outperform alternative flight platforms such as rotary wing MAVs. A biomimetic design approach was undertaken to develop a novel flapping mechanism, the parallel crank-rocker (PCR). Unlike several existing flapping mechanisms (which are compared using an original classification method), the PCR mechanism has an integrated flapping and pitching output motion which is not constrained. This allows the wing angle of attack, a key kinematic parameter, to be adjusted and enables the MAV to enact manoeuvres and have flight stability. Testing of a near-MAV scale PCR prototype using a high-speed camera showed that the flapping angle and adjustable angle of attack both closely matched predicted values, proving the mechanism can replicate insect wing kinematics. A mean lift force of 3.35 g was measured with the prototype in a hovering orientation and flapping at 7.15 Hz.
12
Tong, L., and H. Ji. "Multi-body dynamic modelling and flight control for an asymmetric variable sweep morphing UAV." Aeronautical Journal 118, no. 1204 (June 2014): 683–706. http://dx.doi.org/10.1017/s000192400000943x.
Повний текст джерелаАнотація:
AbstractIn this paper, the multi-body dynamic model of an asymmetric variable sweep wing morphing UAV is built based on Kane’s method. This model describes the UAV’s transient behaviour during morphing process and the dynamic characteristic of the variable sweep wings. An integrated design of trajectory tracking control via constrained backstepping method is presented then. The idea of aircraft roll control through asymmetric wing sweep angle changes rather than traditional aileron is explored and used in the fight control design. The control of variable sweep wings is designed as well based on the presented dynamic model. Command filters are used in the backstepping design procedure to accommodate magnitude, rate and bandwidth constraints on virtual states and actuator signals. Stability of the closed-loop system can be proved in the sense of Lyapunov. Simulation of tracking a desired trajectory which contains two manoeuvres demonstrates the feasibility of the proposed protocol and the morphing wing roll controller.
13
Dimino, Ignazio, Giovanni Andreutti, Frédéric Moens, Federico Fonte, Rosario Pecora, and Antonio Concilio. "Integrated Design of a Morphing Winglet for Active Load Control and Alleviation of Turboprop Regional Aircraft." Applied Sciences 11, no. 5 (March 9, 2021): 2439. http://dx.doi.org/10.3390/app11052439.
Повний текст джерелаАнотація:
Aircraft winglets are well-established devices that improve aircraft fuel efficiency by enabling a higher lift over drag ratios and lower induced drag. Retrofitting winglets to existing aircraft also increases aircraft payload/range by the same order of the fuel burn savings, although the additional loads and moments imparted to the wing may impact structural interfaces, adding more weight to the wing. Winglet installation on aircraft wing influences numerous design parameters and requires a proper balance between aerodynamics and weight efficiency. Advanced dynamic aeroelastic analyses of the wing/winglet structure are also crucial for this assessment. Within the scope of the Clean Sky 2 REG IADP Airgreen 2 project, targeting novel technologies for next-generation regional aircraft, this paper deals with the integrated design of a full-scale morphing winglet for the purpose of improving aircraft aerodynamic efficiency in off-design flight conditions, lowering wing-bending moments due to maneuvers and increasing aircraft flight stability through morphing technology. A fault-tolerant morphing winglet architecture, based on two independent and asynchronous control surfaces with variable camber and differential settings, is presented. The system is designed to face different flight situations by a proper action on the movable control tabs. The potential for reducing wing and winglet loads by means of the winglet control surfaces is numerically assessed, along with the expected aerodynamic performance and the actuation systems’ integration in the winglet surface geometry. Such a device was designed by CIRA for regional aircraft installation, whereas the aerodynamic benefits and performance were estimated by ONERA on the natural laminar flow wing. An active load controller was developed by PoliMI and UniNA performed aeroelastic trade-offs and flutter calculations due to the coupling of winglet movable harmonics and aircraft wing bending and torsion.
14
Zink, P. Scott, Daniella E. Raveh, and Dimitri N. Mavris. "Integrated Trim and Structural Design Process for Active Aeroelastic Wing Technology." Journal of Aircraft 40, no. 3 (May 2003): 523–31. http://dx.doi.org/10.2514/2.3126.
Повний текст джерела
15
GU, Xiaojun, Kaike YANG, Manqiao WU, Yahui ZHANG, Jihong ZHU, and Weihong ZHANG. "Integrated optimization design of smart morphing wing for accurate shape control." Chinese Journal of Aeronautics 34, no. 1 (January 2021): 135–47. http://dx.doi.org/10.1016/j.cja.2020.08.048.
Повний текст джерела
16
Won, Daehan, Jeonghwan Oh, Woosung Kang, Songgeun Eom, Dongjin Lee, Doyoon Kim, and Sanghyuck Han. "Flight Scenario Trajectory Design of Fixed Wing and Rotary Wing UAV for Integrated Navigation Performance Analysis." Journal of the Korean Society for Aviation and Aeronautics 30, no. 1 (March 2022): 38–43. http://dx.doi.org/10.12985/ksaa.2022.30.1.038.
Повний текст джерела
17
Mainini, Laura, and Paolo Maggiore. "Multidisciplinary Integrated Framework for the Optimal Design of a Jet Aircraft Wing." International Journal of Aerospace Engineering 2012 (2012): 1–9. http://dx.doi.org/10.1155/2012/750642.
Повний текст джерелаАнотація:
The preliminary design of a jet aircraft wing, through the use of an integrated multidisciplinary design environment, is presented in this paper. A framework for parametric studies of wing structures has been developed on the basis of a multilevel distributed analysis architecture with a “hybrid strategy” process that is able to perform deterministic optimizations and tradeoff studies simultaneously. The particular feature of the proposed multilevel optimization architecture is that it can use different set of variables, defined expressly for each level, in a multi-level scheme using “low fidelity” and “high fidelity” models, as well as surrogate models. The prototype of the design environment has been developed using both commercial codes and in-house tools and it can be implemented in a geographically distributed and heterogeneous IT context.
18
Huang, Xianghua, Xiaochun Zhao, and Jiaqin Huang. "A simplified model for predicting the propeller-wing interaction." Aircraft Engineering and Aerospace Technology 90, no. 1 (January 2, 2018): 196–201. http://dx.doi.org/10.1108/aeat-06-2016-0102.
Повний текст джерелаАнотація:
Purpose The traditional numerical methods to predict the interaction between the wing and propeller are too complex and time-consuming for computation to a certain extent. Therefore, they are not applicable for a real-time integrated turboprop aircraft model. This paper aims to present a simplified model capable of high-precision and real-time computing. Design/methodology/approach A wing model based on the lifting line theory coupled with a propeller model based on the strip theory is used to predict the propeller-wing interaction. To meet the requirement of real-time computing, a novel decoupling parameter is presented to replace lifting line model (LLM) applied for wings with a simplified fitting model (FM). Findings The comparison between the LLM and the simplified FM demonstrates that the results of the FM have a good agreement with the results of the LLM, which means that the simplified FM has the advantages of both high-accuracy and real-time computation. Practical implications After simplification, the propeller-wing interaction model is suitable for a real-time integrated turboprop aircraft model. Originality/value A novel decoupling parameter is presented to replace LLM applied for wings with a simplified FM, which has the advantages of both high-accuracy and real-time computation.
19
Wu, Da Wei, Dongdong Su, and Jian Li. "Aircraft Wing Deflection Measurement Based on PLC Control System Design." Advanced Materials Research 655-657 (January 2013): 868–71. http://dx.doi.org/10.4028/www.scientific.net/amr.655-657.868.
Повний текст джерелаАнотація:
With the domestic aircraft to continuously improve the level of production, digitalization and automation of airplane ground test adjustment technology is transforming it into a requirement, flight test technology will move towards digitization, Integrated ,and commom direction of development. Automation of aircraft wing deflection measurement platform through the development of PLC control system experiment and pc with experimental realization of the process control and real-time monitoring, Established a complete set of data acquisition channel, Promote the development of aircraft wing deflection angle of automated measurement technology.
20
Beiter, Benjamin C., Yohan Sequeira, Adam Tyler, Trinity Blackman, and Rolf Müller. "Optimization approach to designing a bioinspired bat robot for flight and sonar integration." Journal of the Acoustical Society of America 152, no. 4 (October 2022): A70. http://dx.doi.org/10.1121/10.0015577.
Повний текст джерелаАнотація:
In addition to remarkable acoustic sensing and navigation abilities, bats are highly agile and capable fliers, achieving flight efficiency that exceeds that of not only the rest of the animal kingdom, but of all robots as well. We seek to design a robot inspired by the biological capabilites of bats to achieve artificial flapping flight integrated with an acoustic sensing ability. Coupled with the kinematic and dynamic data collection array, we define a process for optimizing the design of bat wings for efficient flight. We identify fitness functions such as flap speed and air subtended throughout a wing cycle and then optimize the size and shape of a wing to achieve desired setpoints of the fitness functions. An inverse kinematics design process can then be used to create a single degree of freedom cyclic mechanism that will achieve the desired wing flap and fold functions. By setting fitness function objectives for both engineering design requirements (weight, lift, aerodynamics) and biologically inspired goals (wing flexibility, similarity to bat flight, responsiveness to echolocation). With this we can procedurally design a bat robot based on updating understandings of bat flight and navigation, leading to a streamlined production process when combined with rapid manufacturing.
21
Wang, Yiwei, Xianghua Huang, and Jiaqin Huang. "Real-time integrated turboprop take-off model under propeller-wing interaction." Aircraft Engineering and Aerospace Technology 91, no. 7 (July 8, 2019): 917–26. http://dx.doi.org/10.1108/aeat-02-2017-0066.
Повний текст джерелаАнотація:
Purpose The purpose of the paper is to build a real-time integrated turboprop take-off model which fully takes the interaction between diverse parts of aircraft into consideration. Turboprops have the advantage of short take-off distance derived from propeller-wing interaction. Traditional turboprop take-off model is inappropriate because interactions between diverse parts of aircrafts are not fully considered or longer calculation time is required. To make full use of the advantage of short take-off distance, a real-time integrated take-off model is needed for analysing flight performance and developing an integrated propeller-engine-aircraft control system. Design/methodology/approach A new integrated three-degree-of-freedom take-off model is developed, which takes a modified propeller model, a wing model and the predominant propeller-wing interaction into account. The propeller model, based on strip theory, overcomes the shortage that the strip theory does not work if the angle of propeller axis and inflow velocity is non-zero. The wing model uses the lifting line method. The proposed propeller-wing interaction model simplifies the complex propeller-wing flow field. Simulations of ATR42 take-off model are conducted in the following three modes: propeller-wing interaction is ignored; influence of propeller on wing is considered only; and propeller-wing interaction is considered. Findings Comparison of take-off distances and flight parameters shows that propeller-wing interaction has a vital impact on take-off distance and flight parameters of turboprops. Practical implications The real-time integrated take-off model provides time-history flight parameters, which plays an important role in an integrated propeller-engine-aircraft control system to analyse and improve flight performance. Originality/value The real-time integrated take-off model is more precise because propeller-wing interaction is considered. Each calculation step costs less than 20 ms, which meets real-time calculation requirements. The modified propeller model overcomes the shortage of strip theory.
22
Velicki, A., and P. Thrash. "Blended wing body structural concept development." Aeronautical Journal 114, no. 1158 (August 2010): 513–19. http://dx.doi.org/10.1017/s0001924000004000.
Повний текст джерелаАнотація:
Abstract A lightweight robust airframe design is one of the key technological advancements necessary for the successful launch of a blended wing body aircraft. The non-circular pressure cabin dictates that substantial improvements beyond current state-of-the-art aluminium and composite structures is needed, and that improvements of this magnitude will require radically new airframe design and manufacturing practices. Such an approach is described in this paper. It is a highly integrated structural concept that is tailored and optimised to fully exploit the orthotropic nature and unique processing advantages inherent in dry carbon fibres, while also employing stitching to enable a unique damage-arrest design approach.
23
Paradies, Rolf, and Paolo Ciresa. "Active wing design with integrated flight control using piezoelectric macro fiber composites." Smart Materials and Structures 18, no. 3 (February 3, 2009): 035010. http://dx.doi.org/10.1088/0964-1726/18/3/035010.
Повний текст джерела
24
Ünlüsoy, Levent, and Yavuz Yaman. "Aeroelastic behaviour of UAV wings due to morphing." Aircraft Engineering and Aerospace Technology 89, no. 1 (January 3, 2017): 30–38. http://dx.doi.org/10.1108/aeat-12-2014-0217.
Повний текст джерелаАнотація:
Purpose The purpose of this paper is to analyse the effects of morphing on the aeroelastic behaviour of unmanned aerial vehicle (UAV) wings to make an emphasis on the required aeroelastic tailoring starting from the conceptual design of the morphing mechanisms. Design/methodology/approach In this study, flutter and divergence characteristics of a fully morphing wing design were discussed to show the dilapidating effect of morphing on the related parameters. The morphing wings were intended to achieve a high efficiency at different flight phases; thus, various morphing concepts were integrated into a UAV wing structure. Although it is considered beneficial to have the morphing capabilities to avoid the failure due to a possible wear out in flutter and divergence parameters; it is necessary to include the aeroelastic analyses at the early design phases. This study utilizes a combination of a reduced order structural model and Theodorsen unsteady aerodynamic model as primary analyses tools for flutter and divergence. The analyses were conducted by using an in-house developed pk-algorithm coupled with a commercial finite element analysis (FEA) tool. This approach yielded a fast solution capacity because of the state-space form used. Findings Analyses conducted showed that transition between take-off, climb, cruise and loiter phases yield a change in the flutter and divergence speeds as high as 138 and 305 per cent, respectively. Practical implications The research showed that an extensive aeroelastic investigation was required for morphing wing designs to achieve a failure safe design. Originality/value The research intends to highlight the possible deteriorating effects on structural design of morphing UAV wings by focusing on the aeroelastic characteristics. In addition to that, fundamental morphing concepts are compared in terms of the order of magnitude of their deteriorating effects.
25
Collins, S. W., B. W. Westra, J. C. Lin, G. S. Jones, and C. H. Zeune. "Wind tunnel testing of powered lift, all-wing STOL model." Aeronautical Journal 113, no. 1140 (February 2009): 129–37. http://dx.doi.org/10.1017/s0001924000002840.
Повний текст джерелаАнотація:
Abstract Short take-off and landing (STOL) systems can offer significant capabilities to warfighters and, for civil operators thriving on maximising efficiencies they can improve airspace use while containing noise within airport environments. In order to provide data for next generation systems, a wind tunnel test of an all-wing cruise efficient, short take-off and landing (CE STOL) configuration was conducted in the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) 14ft by 22ft Subsonic Wind Tunnel. The test’s purpose was to mature the aerodynamic aspects of an integrated powered lift system within an advanced mobility configuration capable of CE STOL. The full-span model made use of steady flap blowing and a lifting centerbody to achieve high lift coefficients. The test occurred during April through June of 2007 and included objectives for advancing the state-of-the-art of powered lift testing through gathering force and moment data, on-body pressure data, and off-body flow field measurements during automatically controlled blowing conditions. Data were obtained for variations in model configuration, angles of attack and sideslip, blowing coefficient, and height above ground. The database produced by this effort is being used to advance design techniques and computational tools for developing systems with integrated powered lift technologies.
26
Lane, P., G. Throneberry, I. Fernandez, M. Hassanalian, R. Vasconcellos, and A. Abdelkefi. "Towards Bio-Inspiration, Development, and Manufacturing of a Flapping-Wing Micro Air Vehicle." Drones 4, no. 3 (July 25, 2020): 39. http://dx.doi.org/10.3390/drones4030039.
Повний текст джерелаАнотація:
Throughout the last decade, there has been an increased demand for intricate flapping-wing drones with different capabilities than larger drones. The design of flapping-wing drones is focused on endurance and stability, as these are two of the main challenges of these systems. Researchers have recently been turning towards bioinspiration as a way to enhance aerodynamic performance. In this work, the propulsion system of a flapping-wing micro air vehicle is investigated to identify the limitations and drawbacks of specific designs. Each system has a tandem wing configuration inspired by a dragonfly, with wing shapes inspired by a bumblebee. For the design of this flapping-wing, a sizing process is carried out. A number of actuation mechanisms are considered, and two different mechanisms are designed and integrated into a flapping-wing system and compared to one another. The second system is tested using a thrust stand to investigate the impact of wing configurations on aerodynamic force production and the trend of force production from varying flapping frequency. Results present the optimal wing configuration of those tested and that an angle of attack of two degrees yields the greatest force production. A tethered flight test is conducted to examine the stability and aerodynamic capabilities of the drone, and challenges of flapping-wing systems and solutions that can lead to successful flight are presented. Key challenges to the successful design of these systems are weight management, force production, and stability and control.
27
Jiang, Shan, Yong Hu, Qiang Li, Long Ma, Yang Wang, Xiaoqin Zhou, and Qiang Liu. "Design and analysis of an innovative flapping wing micro aerial vehicle with a figure eight wingtip trajectory." Mechanical Sciences 12, no. 1 (June 2, 2021): 603–13. http://dx.doi.org/10.5194/ms-12-603-2021.
Повний текст джерелаАнотація:
Abstract. A multi-mode flapping wing micro air vehicle (FWMAV) that uses a figure eight wingtip motion trajectory with wing flapping, rotation, and swing motion is presented in this paper. The flapping wing vehicle achieves three active degrees of freedom (DOF) wing movements only with one driving micromotor which has a good balance in the mechanism design (that is inspired by natural fliers) and total weight. Owing to these characteristics being integrated into the simple mechanism design, the aerodynamic force is improved. The aerodynamic performance of the thrust force is improved by 64.3 % compared to one that could only flap up and down with one active DOF under the condition of routine flapping frequency.
28
Гребеников, А. Г., та Д. Ю. Жиряков. "АНАЛІЗ СИЛ ФУНКЦІОНУВАННЯ ВІД’ЄМНОЇ ЧАСТИНИ КРИЛА ЛІТАКА ТРАНСПОРТНОЇ КАТЕГОРІЇ". Open Information and Computer Integrated Technologies, № 89 (23 березня 2021): 4–20. http://dx.doi.org/10.32620/oikit.2020.89.01.
Повний текст джерелаАнотація:
Each experimental design department has experience in determining design and operational loads for a given type of aircraft. The reliability of the data on the loading of a particular structural element determines the success of the aircraft being created. This is often confidential information. Much work has been investigated to improve the fatigue life of wing structural elements. With the development of integrated design methods, aircraft structure design can be performed in the shortest time, and with high technical excellence. In most cases, the fatigue life of wing elements is determined from the nominal stresses in the element. For a longitudinal structure set, it is customary to perform fatigue calculations directly using normal stresses in the element. For a more detailed specification of the fatigue life, it is necessary to have a general and local stress-strain state of a given structure. A feature of the work is to analyze the spectrum of loads acting on the wing console during a typical flight. The influence of high-lift devises (slats, flaps) on the shear forces and torque moment of the wing was analyzed. It has been shown that with the extensions high-lift devices, there is a significant increase in torque. These articles will make it possible to obtain the stress distribution of the detachable part of the wing under all operating modes. This, in turn, leads to a more thorough prediction of fatigue life. Since some operating loads can significantly change the distribution of the stress-strain state in the design element, and in turn change the fatigue life. The structural elements of the wing, in particular the attachment points for the high-lift devices, operate in a complex-stressed state. This complicates the process of predicting the fatigue life of these elements. To obtain a competitive aircraft, it is necessary to develop new methods of wing design with widespread use of integrated systems. This will contribute to obtaining a more optimal and perfect wing design
29
Khan, S., T. L. Grigorie, R. M. Botez, M. Mamou, and Y. Mébarki. "Novel morphing wing actuator control-based Particle Swarm Optimisation." Aeronautical Journal 124, no. 1271 (September 26, 2019): 55–75. http://dx.doi.org/10.1017/aer.2019.114.
Повний текст джерелаАнотація:
AbstractThe paper presents the design and experimental testing of the control system used in a new morphing wing application with a full-scaled portion of a real wing. The morphing actuation system uses four similar miniature brushless DC (BLDC) motors placed inside the wing, which execute a direct actuation of the flexible upper surface of the wing made from composite materials. The control system of each actuator uses three control loops (current, speed and position) characterised by five control gains. To tune the control gains, the Particle Swarm Optimisation (PSO) method is used. The application of the PSO method supposed the development of a MATLAB/Simulink® software model for the controlled actuator, which worked together with a software sub-routine implementing the PSO algorithm to find the best values for the five control gains that minimise the cost function. Once the best values of the control gains are established, the software model of the controlled actuator is numerically simulated in order to evaluate the quality of the obtained control system. Finally, the designed control system is experimentally validated in bench tests and wind-tunnel tests for all four miniature actuators integrated in the morphing wing experimental model. The wind-tunnel testing treats the system as a whole and includes, besides the evaluation of the controlled actuation system, the testing of the integrated morphing wing experimental model and the evaluation of the aerodynamic benefits brought by the morphing technology on this project. From this last perspective, the airflow on the morphing upper surface of the experimental model is monitored by using various techniques based on pressure data collection with Kulite pressure sensors or on infrared thermography camera visualisations.
30
Anuar, Kaspul, Warman Fatra, and Mustafa Akbar. "Tricopter Vehicle Frame Structure Design Integrated as Platform of Fixed Wing Atha Mapper 2150." Journal of Ocean, Mechanical and Aerospace -science and engineering- (JOMAse) 64, no. 2 (July 30, 2020): 68–72. http://dx.doi.org/10.36842/jomase.v64i2.218.
Повний текст джерелаАнотація:
To upgrade aerial vehicle of Atha Mapper 2150 capable of vertical take-off and landing capability, it needs to be integrated to the tricopter vehicle. In this study the tricopter frame structure was designed based on the Atha Mapper 2150 fixed wing vehicle. This study began with a calculation process to determine the dimensions of the tricopter.. Next, the process of building four tricopter concept designs with variations of the shape of the frame and the cross section of the arm. The four concept designs are selected using a decision matrix. Based on the values in decision matrix table, the design concept I (Y configuration and rectangular arm cross section) was the best design, because it has the highest weighting value. The selected design was then simulated for its structural strength in Ansys software by giving a load of thrust to the three arms of the tricopter frame. In the middle of frame is given a boundary condition in the form of hinges. From the static simulation results of the tricopter frame structure, the maximum stress value was 54,126 MPa, which occurred on the M3 arm. The greatest total deformation also occurred in the M3 arm with a value of 10,335 mm. The safety factor value of tricopter frame structure was 8.77. This shows the tricopter frame structure with the main material in the form of carbon fiber, acrylic and PLA meets the required safety criteria.
31
Rajagopal, S., and R. Ganguli. "Conceptual design of UAV using Kriging based multi-objective genetic algorithm." Aeronautical Journal 112, no. 1137 (November 2008): 653–62. http://dx.doi.org/10.1017/s0001924000002621.
Повний текст джерелаАнотація:
Abstract This paper highlights unmanned aerial vehicle (UAV) conceptual design using the multi-objective genetic algorithm (MOGA). The design problem is formulated as a multidisciplinary design optimisation (MDO) problem by coupling aerodynamic and structural analysis. The UAV considered in this paper is a low speed, long endurance aircraft. The optimisation problem uses endurance maximization and wing weight minimisation as dual objective functions. In this multi-objective optimisation, aspect ratio, wing loading, taper ratio, thickness-to-chord ratio, loiter velocity and loiter altitude are considered as design variables with stall speed, maximum speed and rate of climb as constraints. The MDO system integrates the aircraft design code, RDS and an empirical relation for objective function evaluation. In this study, the optimisation problem is solved in two approaches. In the first approach, the RDS code is directly integrated in the optimisation loop. In the second approach, Kriging model is employed. The second approach is fast and efficient as the meta-model reduces the time of computation. A relatively new multi-objective evolutionary algorithm named NSGA-II (non-dominated sorting genetic algorithm) is used to capture the full Pareto front for the dual objective problem. As a result of optimisation using multi-objective genetic algorithm, several non-dominated solutions indicating number of useful Pareto optimal designs is identified.
32
Liu, Hao, Sridhar Ravi, Dmitry Kolomenskiy, and Hiroto Tanaka. "Biomechanics and biomimetics in insect-inspired flight systems." Philosophical Transactions of the Royal Society B: Biological Sciences 371, no. 1704 (September 26, 2016): 20150390. http://dx.doi.org/10.1098/rstb.2015.0390.
Повний текст джерелаАнотація:
Insect- and bird-size drones—micro air vehicles (MAV) that can perform autonomous flight in natural and man-made environments are now an active and well-integrated research area. MAVs normally operate at a low speed in a Reynolds number regime of 10 4 –10 5 or lower, in which most flying animals of insects, birds and bats fly, and encounter unconventional challenges in generating sufficient aerodynamic forces to stay airborne and in controlling flight autonomy to achieve complex manoeuvres. Flying insects that power and control flight by flapping wings are capable of sophisticated aerodynamic force production and precise, agile manoeuvring, through an integrated system consisting of wings to generate aerodynamic force, muscles to move the wings and a control system to modulate power output from the muscles. In this article, we give a selective review on the state of the art of biomechanics in bioinspired flight systems in terms of flapping and flexible wing aerodynamics, flight dynamics and stability, passive and active mechanisms in stabilization and control, as well as flapping flight in unsteady environments. We further highlight recent advances in biomimetics of flapping-wing MAVs with a specific focus on insect-inspired wing design and fabrication, as well as sensing systems. This article is part of the themed issue ‘Moving in a moving medium: new perspectives on flight’.
33
Jupp, J. "Wing aerodynamics and the science of compromise." Aeronautical Journal 105, no. 1053 (November 2001): 633–41. http://dx.doi.org/10.1017/s0001924000012653.
Повний текст джерелаАнотація:
Abstract From Lanchester to the A380; from the era of the great pioneers to the integrated engineering teams and sophisticated analyses required to develop todays airliner. The ‘art’ of Aerodynamics has progressed a long, long way in the intervening century, but even with todays computational power it is still relevant to understand the basics and the early theories as developed by Lanchester and his contemporaries. In this lecture, the relevance of some of that early work and the compromises that must be made in optimising a modern wing design will be presented. These will include optimisation of spanwise loading, including trimming effects and winglets, and high and low speed aerodynamic and structural interactions, with examples drawn from the author's career in helping to develop the wings for the HS146 (now the RJX) and the Airbus family. With the exponentially increasing computer power available over the last 30 years, the ‘art of compromise’ has progressively become the ‘science of optimisation’ and the lecture closes with a brief reference to techniques used to optimise current wing designs for the Airbus family.
34
Saggu, J. S., and J. P. Fielding. "An integrated CADCAM method for the design and construction of aircraft wing components." Computers in Industry 12, no. 2 (May 1989): 123–30. http://dx.doi.org/10.1016/0166-3615(89)90054-7.
Повний текст джерела
35
SON, Hoesoo, Kazuo YATABE, Atsushi NAKAYAMA, and Goro OBINATA. "Integrated Design of Airframe and Stabilizing Controller in Wing-in-Ground Effect Aircraft." Transactions of the Japan Society of Mechanical Engineers Series C 65, no. 637 (1999): 3592–98. http://dx.doi.org/10.1299/kikaic.65.3592.
Повний текст джерела
36
Liou, M. F., H. Kim, B. Lee, and M. S. Liou. "Aerodynamic design of integrated propulsion–airframe configuration of a hybrid wing body aircraft." Shock Waves 29, no. 8 (November 2019): 1043–64. http://dx.doi.org/10.1007/s00193-019-00933-z.
Повний текст джерела
37
Şahin, Harun Levent, and Yavuz Yaman. "Synthesis, Analysis, and Design of a Novel Mechanism for the Trailing Edge of a Morphing Wing." Aerospace 5, no. 4 (December 11, 2018): 127. http://dx.doi.org/10.3390/aerospace5040127.
Повний текст джерелаАнотація:
In the design and analysis of morphing wings, several sciences need to be integrated. This article tries to answer the question, “What is the most appropriate actuation mechanism to morph the wing profile?” by introducing the synthesis, analysis, and design of a novel scissor-structural mechanism (SSM) for the trailing edge of a morphing wing. The SSM, which is deployable, is created via a combination of various scissor-like elements (SLEs). In order to provide mobility requirements, a four-bar linkage (FBL) is assembled with the proposed SSM. The SSM is designed with a novel kinematic synthesis concept, so it follows the airfoil camber with minimum design error. In this concept, assuming a fully-compliant wing skin, various types of SLEs are assembled together, and emergent SSM provide the desired airfoil geometries. In order to provide the required aerodynamic efficiency of newly-created airfoil geometries and obtain pressure distribution over the airfoil, two-dimensional (2D) aerodynamic analyses have been conducted. The analyses show similar aerodynamic behavior with the desired NACA airfoils. By assigning the approximate link masses and mass centers, the dynamic force analysis of the mechanism has also been performed, and the required torque to drive the newly-developed SSM is estimated as feasible.
38
MARX, WILLIAM J., DIMITRI N. MAVRIS, and DANIEL P. SCHRAGE. "A knowledge-based system integrated with numerical analysis tools for aircraft life-cycle design." Artificial Intelligence for Engineering Design, Analysis and Manufacturing 12, no. 3 (June 1998): 211–29. http://dx.doi.org/10.1017/s0890060498123016.
Повний текст джерелаАнотація:
An integrated design and manufacturing approach allows economic decisions to be made that reflect an entire system design as a whole. To achieve this objective, we have developed and utilized integrated cost and engineering models within a focused design perspective. A framework for the integrated design of an aircraft system with a combined performance and economic perspective is described in this article. This framework is based on the concept of Design Justification using a Design-for-Economics approach. We have developed a knowledge-based system that can be used to evaluate aircraft structural concept material and process selections. The framework consists of the knowledge-based system, integrated with numerical analysis tools including an aircraft performance/sizing code and a life-cycle cost analysis code. Production cost estimates are applied for evaluation of process trades at the subcomponent level of design. Life-cycle cost estimates are used for evaluation of process trades at the system level. Results of a case study are presented for several advanced wing structural concepts for a future supersonic commercial transport aircraft. Cost versus performance studies indicate that a high-speed civil transport aircraft with a hybrid wing structural concept, though more expensive to manufacture than some homogeneous concepts, can have lower direct operating costs due to a lower take-off gross weight and less mission fuel required.
39
Chudoba, B., G. Coleman, H. Smith, and M. V. Cook. "Generic stability and control for aerospace flight vehicle conceptual design." Aeronautical Journal 112, no. 1132 (June 2008): 293–306. http://dx.doi.org/10.1017/s000192400000227x.
Повний текст джерелаАнотація:
Abstract The recent period has been filled with exceptionally interesting developments and advances, resulting in high-performance conventional and non-conventional manned and unmanned aircraft. Although those vehicles seem to comply well with specific mission performance requirements, one is still confronted with an apparent weakness to reliably stabilise and control throughout the flight envelope. Since the provision of satisfactory stability and control characteristics invariably compromises flight performance, it becomes essential to identify and integrate performance-optimal stability and control design solutions early during the flight vehicle definition phase. In particular, the conceptual design of integrated control effectors for advanced aircraft is far from being trivial. Never before have we been presented with such tremendous wealth of specialised data and information suitable for detail design of controls. In contrast, never before has it been necessary to approach any one of the primary design disciplines still as entirely ad hoc and inconsistent as in the case of designing controls during the conceptual design phase. This need initiated the development of a configuration independent (generic) stability and control methodology capable of sizing primary control effectors of fixed wing subsonic to hypersonic designs of conventional and unconventional, symmetric and asymmetric configuration layouts. This paper summarises the methodology concept and demonstrates its versatility and validity by analyzing selected stability and control characteristics of the Northrop YB-49 flying wing.
40
Baucke, Jan, Stefan Steeger, and Ralf Keimer. "Manufacturing, Assembly and Integration of a Large Scale Composite Wing Wind Tunnel Model and the Design and Implementation of an associated Measurement System." IOP Conference Series: Materials Science and Engineering 1226, no. 1 (February 1, 2022): 012052. http://dx.doi.org/10.1088/1757-899x/1226/1/012052.
Повний текст джерелаАнотація:
Abstract Building a wind tunnel model with an innovative aerodynamic design including a laminar airfoil concept and morphing parts requires a suitable manufacturing and assembly plan to transfer the virtual model to concrete reality. The contribution of the INVENT GmbH within the GRETEL consortium is the manufacturing of the main structural components of the Wing and the integration of the Wind Tunnel Model. To realize such a precise projection, the main approach is to implement a high overall accuracy of the later model by realizing a low percentage of geometry deviation already on piece part level. Beginning with a material dedicated tool design concerning cure cycle parameters and induced strain effects, for aspects of geometrical manufacturing accuracy, also suitable inspection techniques, regarding the verification of structural requirements and material conditions are implemented in the integration process at specified steps. A further part of the integration process of the GRETEL Wind Tunnel Model is the installation of application-related measurement equipment. The Institute of Composite Structures and Adaptive Systems of the German Aerospace Center (DLR) is responsible for the design and realization of such a project customized measurement concept. For the measurement of the pressure distribution along the profile contour with various angles of attack and wing configurations during the testing, the wing is equipped with several pressure taps. Further, the measurement equipment spectrum covers also the registration of acceleration forces and mechanical loads of the inner wing structure components. This concept creates a holistic picture of the coherences between aerodynamical and mechanical dimensions for each tested configuration. The implementation of all aforementioned aspects into the large-scale model is elucidated and discussed in the light of morphing parts of the model being delivered by another project. The integrated equipment is described and the impact of the integration into the design and assembly of the overall model is illustrated.
41
Dillinger, Johannes K. S., Yasser M. Meddaikar, Jannis Lübker, Manuel Pusch, and Thiemo Kier. "Design and Optimization of an Aeroservoelastic Wind Tunnel Model." Fluids 5, no. 1 (March 17, 2020): 35. http://dx.doi.org/10.3390/fluids5010035.
Повний текст джерелаАнотація:
Through the combination of passive and active load alleviation techniques, this paper presents the design, optimization, manufacturing, and update of a flexible composite wind tunnel model. In a first step, starting from the specification of an adequate wing and trailing edge flap geometry, passive, static aeroelastic stiffness optimizations for various objective functions have been performed. The second optimization step comprised a discretization of the continuous stiffness distributions, resulting in manufacturable stacking sequences. In order to determine which of the objective functions investigated in the passive structural optimization most efficiently complemented the projected active control schemes, the condensed modal finite element models were integrated in an aeroelastic model, involving a dedicated gust load alleviation controller. The most promising design was selected for manufacturing. The finite element representation could be updated to conform to the measured eigenfrequencies, based on the dynamic identification of the model. Eventually, a wind tunnel test campaign was conducted in November 2018 and results have been examined in separate reports.
42
Grebenikov, Oleksandr, Andrii Humennyi, Oleksandr Dveirin, Oleksandr Soboliev, and Lilia Buival. "Devising a concept of integrated design and modeling of aircraft." Eastern-European Journal of Enterprise Technologies 5, no. 1(113) (October 31, 2021): 15–23. http://dx.doi.org/10.15587/1729-4061.2021.240108.
Повний текст джерелаАнотація:
The analysis of aircraft design methods reported here has revealed that building a competitive aircraft necessitates devising a scientifically based concept of integrated aircraft design employing CAD/CAM/CAE/PLM software suites. A generalized concept of integrated design and three-dimensional computer modeling of aircraft involving the CAD/CAM/CAE/PLM systems has been developed. Based on the proposed concept, the principles of integrated design of aircraft were devised. The features of designing the training and training-combat aircraft, transport-category aircraft, light civilian aircraft have been described. A method for determining the take-off weight, design parameters, and formation of the general appearance of aircraft has been improved. The method is intended to form the appearance of the aircraft at the stages of preliminary design, the purpose of which is reduced to determining the permissible version of the aircraft project. The project must meet the predefined requirements and restrictions in the selected aircraft scheme and the assigned set of parameters that characterize its airframe and power plant. A method of parametric modeling of aircraft has been improved, which includes the stages of creating a master geometry of the aircraft and a model of space distribution. Parametric models of master geometry and models of space distribution, training and training-combat aircraft, transport-category aircraft, light civilian aircraft have been constructed. Methods of integrated design of aircraft main units have been devised and theoretically substantiated. Parametric models of master geometry of the wing for a training aircraft, the wings, appendage, and fuselage of a light civilian aircraft were built, taking into consideration the design features of aircraft units of various categories
43
Abbasi, S. H., A. Mahmood, and Abdul Khaliq. "Bioinspired Feathered Flapping Wing UAV Design for Operation in Gusty Environment." Journal of Robotics 2021 (September 11, 2021): 1–14. http://dx.doi.org/10.1155/2021/8923599.
Повний текст джерелаАнотація:
The flight of unmanned aerial vehicles (UAVs) has numerous associated challenges. Small size is the major reason of their sensitivity towards turbulence restraining them from stable flight. Turbulence alleviation strategies of birds have been explored in recent past in detail to sort out this issue. Besides using primary and secondary feathers, birds also utilize covert feathers deflection to mitigate turbulence. Motivated from covert feathers of birds, this paper presents biologically inspired gust mitigation system (GMS) for a flapping wing UAV (FUAV). GMS consists of electromechanical (EM) covert feathers that sense the incoming gust and mitigate it through deflection of these feathers. A multibody model of gust-mitigating FUAV is developed appending models of the subsystems including rigid body, propulsion system, flapping mechanism, and GMS-installed wings using bond graph modeling approach. FUAV without GMS and FUAV with the proposed GMS integrated in it are simulated in the presence of vertical gust, and results’ comparison proves the efficacy of the proposed design. Furthermore, agreement between experimental results and present results validates the accuracy of the proposed design and developed model.
44
Grigorie, T. L., A. V. Popov, R. M. Botez, M. Mamou, and Y. Mébarki. "On–off and proportional–integral controller for a morphing wing. Part 1: Actuation mechanism and control design." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 226, no. 2 (November 21, 2011): 131–45. http://dx.doi.org/10.1177/0954410011408226.
Повний текст джерелаАнотація:
The main objective of this research work is the development of an actuation control concept for a new morphing actuation mechanism made of smart materials, which is built from a shape memory alloy (SMA). Two lines of smart actuators were incorporated to a rectangular wing to modify the upper wing surface, made of a flexible skin, with the intention to move the laminar-to-turbulent transition point closer to the wing trailing edge. After a brief introduction of the morphing wing system architecture and requirements, the actuation lines' design and instrumentation are presented. The integrated controller controls the SMA actuators via an electrical current supply, so that the transducer position can be used to eliminate the deviation between the required values for vertical displacements (corresponding to the optimized airfoils) and their physical values. The final configuration of the integrated controller is a combination of a bi-positional (on–off) controller and a PI (proportional–integral) controller, due to the two heating and cooling phases of the SMA wires' interconnection. This controller must behave like a switch between the cooling and the heating phases, situations where the output current is 0 A, or is controlled by a PI type law. The PI controller for the heating phase is optimally tuned using integral and surface minimum error criteria (Ziegler–Nichols). The controller is numerically tested on the linear identified system in terms of time response, Bode diagram, amplitude and phase stability margins, and root-locus.
45
Zhou, Wenya, Zongyu Zhang, Xiaoming Wang, Weiliang Lv, and Xinhan Hu. "Structure-Actuator Integrated Design of Piezo-Actuated Composite Plate Wing for Active Shape Control." Journal of Aerospace Engineering 34, no. 6 (November 2021): 04021070. http://dx.doi.org/10.1061/(asce)as.1943-5525.0001322.
Повний текст джерела
46
He, Cheng, Yuhong Jia, Dongli Ma, and Gang Chen. "Integrated Optimization Approach for Aerodynamic, Structural, and Embedded Antenna Design of Joined-Wing SensorCraft." IEEE Access 8 (2020): 138999–9012. http://dx.doi.org/10.1109/access.2020.3012714.
Повний текст джерела
47
Iannuzzelli, R. J., J. M. Pitarresi, and V. Prakash. "Solder Joint Reliability Prediction by the Integrated Matrix Creep Method." Journal of Electronic Packaging 118, no. 2 (June 1, 1996): 55–61. http://dx.doi.org/10.1115/1.2792132.
Повний текст джерелаАнотація:
The integrated matrix creep method for predicting the fatigue life of solder joints is presented. The application of the matrix creep life prediction method to a variety of solder joint/load combinations with a comparison to measured reliability data is presented as a validation of this technique. For a leadless chip carrier, the strain distribution in the solder is studied both through modeling and laser Moire interferometry. Finally, using this methodology as a design tool, the fatigue life simulation of a gull wing leaded package is presented in which various design parameters are modified and their effect on the fatigue life determined.
48
Bourchak, M., R. M. Ajaj, E. I. Saavedra Flores, M. Khalid, and K. A. Juhany. "Optimum design of a PID controller for the adaptive torsion wing." Aeronautical Journal 119, no. 1217 (July 2015): 871–89. http://dx.doi.org/10.1017/s0001924000010964.
Повний текст джерелаАнотація:
AbstractThis paper presents the optimum design of a PID controller for the Adaptive Torsion Wing (ATW) using the genetic algorithm (GA) optimiser. The ATW is a thin-wall, two-spar wingbox whose torsional stiffness can be adjusted by translating the spar webs in the chordwise direction inward and towards each. The reduction in torsional stiffness allows external aerodynamic loads to deform the wing and maintain its shape. The ATW is integrated within the wing of a representative UAV to replace conventional ailerons and provide roll control. The ATW is modelled as a two-dimensional equivalent aerofoil using bending and torsion shape functions to express the equations of motion in terms of the twist angle and plunge displacement at the wingtip. The full equations of motion for the ATW equivalent aerofoil were derived using Lagrangian mechanics. The aerodynamic lift and moment acting on the aerofoil were modelled using Theodorsen’s unsteady aerodynamic theory. The equations of motion are then linearised around an equilibrium position and the GA is employed to design a PID controller for the linearised system to minimise the actuation power require. Finally, the sizing and selection of a suitable actuator is performed.
49
Phan, Hoang Vu, Quang-Tri Truong, and Hoon-Cheol Park. "Implementation of initial passive stability in insect-mimicking flapping-wing micro air vehicle." International Journal of Intelligent Unmanned Systems 3, no. 1 (February 9, 2015): 18–38. http://dx.doi.org/10.1108/ijius-12-2014-0010.
Повний текст джерелаАнотація:
Purpose – The purpose of this paper is to demonstrate the uncontrolled vertical takeoff of an insect-mimicking flapping-wing micro air vehicle (FW-MAV) of 12.5 cm wing span with a body weight of 7.36 g after installing batteries and power control. Design/methodology/approach – The forces were measured using a load cell and estimated by the unsteady blade element theory (UBET), which is based on full three-dimensional wing kinematics. In addition, the mean aerodynamic force center (AC) was determined based on the UBET calculations using the measured wing kinematics. Findings – The wing flapping frequency can reach to 43 Hz at the flapping angle of 150°. By flapping wings at a frequency of 34 Hz, the FW-MAV can produce enough thrust to over its own weight. For this condition, the difference between the estimated and average measured vertical forces was about 7.3 percent with respect to the estimated force. All parts for the FW-MAV were integrated such that the distance between the mean AC and the center of gravity is close to zero. In this manner, pitching moment generation was prevented to facilitate stable vertical takeoff. An uncontrolled takeoff test successfully demonstrated that the FW-MAV possesses initial pitching stability for takeoff. Originality/value – This work has successfully demonstrated an insect-mimicking flapping-wing MAV that can stably takeoff with initial stability.
50
Weigel, Perez, Martin Schüller, André Gratias, Mathias Lipowski, Theo ter Meer, and Michiel Bardet. "Design of a synthetic jet actuator for flow separation control." CEAS Aeronautical Journal 11, no. 4 (October 21, 2020): 813–21. http://dx.doi.org/10.1007/s13272-020-00479-2.
Повний текст джерелаАнотація:
Abstract This paper describes the development of a piezo-electric synthetic jet actuator (SJA) of the AFLoNext project. Active flow—loads and noise control on next generation wing (AFLoNext) is a project within European Union’s 7th Framework Program. One of the main project goals is the application of active flow control (AFC) techniques, such as SJAs and pulsed jet actuators (PJAs) in two different application scenarios to evaluate the potential benefit for retrofit of current aircraft and also for future aircraft designs. This paper is focusing on the SJAs. For large-scale wind tunnel testing, an actuator panel with 84 SJAs including the drive electronics system was designed and pre-tested in a laboratory environment. The performance exceeds 100 m/s with outlet nozzles of 2.5 mm diameter and a span wise clearance of 10 mm. A second actuator design was prepared for the application on the outer wing region and was investigated in a harsh environmental test campaign. Two span wise rows of five actuators were integrated in a panel with 10 × 0.5 mm2 slotted outlet nozzles. With this design also velocities exceeding 100 m/s were measured. The actuators withstand different harsh environmental conditions including extreme temperature, rain, mechanical vibration and shock. With the results of the project, a technology readiness level (TRL) evaluation will conclude the maturity of the technology. Depending on the final test and evaluation results, achievement of TRL4 is expected.