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1
Hong, Wei Jiang, und Dong Li Ma. „Influence of Control Coupling Effect on Landing Performance of Flying Wing Aircraft“. Applied Mechanics and Materials 829 (März 2016): 110–17. http://dx.doi.org/10.4028/www.scientific.net/amm.829.110.
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As flying wing aircraft has no tail and adopts blended-wing-body design, most of flying wing aircrafts are directional unstable. Pitching moment couples seriously with rolling and yawing moment when control surfaces are deflected, bringing insecurity to landing stage. Numerical simulation method and semi-empirical equation estimate method were combined to obtain a high aspect ratio flying wing aircraft’s aerodynamic coefficients. Modeling and simulation of landing stage were established by MATLAB/Simulink. The control coupling effect on lift and drag characteristics and anti-crosswind landing capability was studied. The calculation results show that when the high aspect ratio flying wing aircraft was falling into the deceleration phase, appropriate to increase the opening angle of split drag rudder can reduce the trimming pitching moment deflection of pitch flap, thereby reduce the loss of lift caused by the deflection of pitch flaps. Flying wing aircraft can be rounded out successfully by using the pitch flap gently and steady. Both side-slip method and crabbed method can be applied to the landing of high aspect ratio flying wing aircraft in crosswind, the flying wing aircraft’s anti-crosswind landing capability was weakened by the control coupling effect of split drag rudder and elevon. Sideslip method was recommended in the crosswind landing of flying wing aircraft after calculation and analysis.
2
Pan, Yalin, und Jun Huang. „Influences of airfoil profile on lateral-directional stability of aircraft with flying wing layout“. Aircraft Engineering and Aerospace Technology 91, Nr. 7 (08.07.2019): 1011–17. http://dx.doi.org/10.1108/aeat-04-2018-0119.
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Purpose The purpose of this study is to analyze influence of airfoil profile on lateral-directional flying quality of flying wing aircraft. The lateral-directional stability is always insufficient for aircraft with the layout due to the absence of vertical stabilizer. A flying wing aircraft with double-swept wing is used as research object in the paper. Design/methodology/approach The 3D model is established for the aircraft with flying wing layout, and parametric modeling is carried out for airfoil mean camber line of the aircraft to analyze lateral-directional stability of the aircraft with different camber line parameters. To increase computational efficiency, vortex lattice method is adopted to calculate aerodynamic coefficients and aerodynamic derivatives of the aircraft. Findings It is found from the research results that roll mode and spiral mode have a little effect on lateral-directional stability of the aircraft but Dutch roll mode is the critical factor affecting flying quality level of such aircraft. Even though changes of airfoil mean line parameters can greatly change assessment parameters of aircraft lateral-directional flying quality, that is kind of change cannot have a fundamental impact on level of flying quality of the aircraft. In case flat shape parameters are determined, the airfoil profile has a limited impact on Dutch roll mode. Originality/value Influences of airfoil profile on lateral-directional flying quality of aircraft with double-swept flying wing layout are revealed in the thesis and some important rules and characteristics are also summarized to lay a theoretical basis for design of airfoil and flight control system of aircraft with the layout.
3
Srinivas, G., und Srinivasa Rao Potti. „Computational Analysis of Fighter Aircraft Wing under Mach Number 0.7 for Small Sweep Angles“. Applied Mechanics and Materials 592-594 (Juli 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.
4
Yang, Xu, Xiao Yi Jin und Xiao Lei Zhou. „Bionic Flapping Wing Flying Robot Flight Mechanism and the Key Technologies“. Applied Mechanics and Materials 494-495 (Februar 2014): 1046–49. http://dx.doi.org/10.4028/www.scientific.net/amm.494-495.1046.
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The flapping wing flying robot is an imitation of a bird or insect like a new type of flying robots, the paper briefly outlines the current domestic and international research in the field of flapping wing flight mechanism of the progress made flapping wing flying robot design. On this basis, the current course of the study were discussed key technical issues, combined with the current research, flapping wing aircraft for the future development prospects.
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Hou, Yu, und Fang Wang. „CPG-Based Movement Control for Bionic Flapping-Wing Mechanism“. Applied Mechanics and Materials 226-228 (November 2012): 844–49. http://dx.doi.org/10.4028/www.scientific.net/amm.226-228.844.
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Flapping-wing flying is a kind of rhythmic movement with symmetry of time and space essentially, and this movement is generated and controlled by Central Pattern Generator (CPG). A 2-DOF flapping mechanism was designed according to the flapping-wing flying principle of insects, and the flapping-wing flying CPG model was constructed by nonlinear oscillators. The system responses were studied, and the influences of the model parameters to the system characteristics were analyzed. Through the engineering simulation of flapping-wing flying control model, the first modal vibration of the system was selected, and the different flying modes of bionic aircraft were realized by adjusting system parameters. This kind of bionic control strategy promoted the movement and control ability of flapping-wing flying, and provided a new method to the generation and control of flapping-wing rhythmic movement.
6
Saeed, T. I., und W. R. Graham. „Design Study for a Laminar-Flying-Wing Aircraft“. Journal of Aircraft 52, Nr. 5 (September 2015): 1373–85. http://dx.doi.org/10.2514/1.c032862.
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7
Liu, Yu, und Xinhua Wang. „Research on obstacle avoidance technology of fixed wing formation based on improved artificial potential field method with stereo vision“. MATEC Web of Conferences 336 (2021): 07007. http://dx.doi.org/10.1051/matecconf/202133607007.
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To solve the problem that distributed fixed wing formation cannot know all the other aircraft states through the ground station and may collide, the improved artificial potential field method based on binocular stereo vision was proposed. This method makes the fixed wing aircraft not need to obtain the position information of other fixed wing aircraft from the ground station, but only need the binocular stereo vision module to obtain the relative position and relative speed information of other fixed wing aircraft. These two parameters are used to improve the traditional artificial potential field method to meet the requirements of distributed fixed wing formation flight. The experimental results show that the improved artificial potential field method improves the safety and reliability of distributed fixed wing formation flying.
8
Jin, Xiao Yi, Ning Lu, Bing Zhang und Jing Ping Yan. „Flexible Wedge-Effect for Insect Flying and Fishtail-Effect for Fish Swimming“. Advanced Materials Research 136 (Oktober 2010): 242–46. http://dx.doi.org/10.4028/www.scientific.net/amr.136.242.
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In this paper, we regard insects wing as a flexible wing and use the flexible wedge-effect to explain the reason for the creation of high lift when insects flying. We disclose the fact that the flexible wedge-effect for insects flying and the fishtail effect for fish swimming have the same core—the force needed for creature movement comes from the flexibility and rhythmic locomotion. The most important bionic meaning of this kind of explanation is that it will be the developmental trend for the driving mode of the future bionics flapping aircraft that the wing is exerted some simple rhythmic locomotion in the state of the self-adaptability distortion. The easier the bionic motion simulation is, the more stable it can be realized. The bionics flapping aircraft research team of the Southeastern University has designed and made a prototype of the bionics flapping aircraft with flexible wing and successfully finished several outdoor test-flies.
9
Zhang, Ning. „Research on Command Allocation Method for Flying Wing Aircraft“. IOP Conference Series: Materials Science and Engineering 887 (10.07.2020): 012020. http://dx.doi.org/10.1088/1757-899x/887/1/012020.
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10
Mardanpour, Pezhman, und Dewey H. Hodges. „Passive morphing of flying wing aircraft: Z-shaped configuration“. Journal of Fluids and Structures 44 (Januar 2014): 17–30. http://dx.doi.org/10.1016/j.jfluidstructs.2013.09.020.
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11
Pan, Yalin, und Jun Huang. „Research on lateral-directional stability augmentation system of flying wing aircraft based on reliability model“. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, Nr. 11 (26.12.2018): 4214–21. http://dx.doi.org/10.1177/0954410018817449.
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Poor lateral-directional stability is a great risk to the design of flying wing aircraft due to the absence of vertical stabilizer. In order to improve the lateral-directional flying quality of this configuration aircraft, eigenstructure assignment technique by state feedback is adopted to design the stability augmentation system. The influence of eigenstructure on energy consumption of the control system is analyzed by citing energy consumption index in this paper. In addition, a reliability model is established to measure the reliability of the control system under uncertain factors. In order to assign eigenvalues and eigenvectors to obtain the control law of the system, a nested optimization model based on coupling degree, energy consumption and reliability is proposed. The outer optimization is used to optimize the eigenstructure, and inner optimization is used to compute the reliability of the control system in optimization process. A flying wing aircraft is used as a basis for the design of the stability augmentation system through the suggested optimization strategy. The optimization results demonstrate the validity of the method, and the lateral-directional flying quality of the aircraft has been improved greatly.
12
Liang, Li, und Sun Qin. „Structural Optimization Research of Composite Aircraft Based on Different Wing Stiffness Constraints“. Advanced Materials Research 466-467 (Februar 2012): 282–86. http://dx.doi.org/10.4028/www.scientific.net/amr.466-467.282.
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Wing stiffness, mainly including bending stiffness and torsion stiffness, is very important in aircraft structure design. In order to research the relation between wing stiffness and optimization results, this paper makes optimization analysis to a composite T-tail configuration and a composite flying wing configuration based on different wing stiffness constraints, and some valuable conclusions are achieved.
13
Portapas, Vilius, und Alastair Cooke. „SIMULATED PILOT-IN-THE-LOOP TESTING OF HANDLING QUALITIES OF THE FLEXIBLE WING AIRCRAFT“. Aviation 24, Nr. 1 (19.03.2020): 1–9. http://dx.doi.org/10.3846/aviation.2020.12175.
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This article aims to indicate the differences between rigid and flexible wing aircraft flying (FQ) and handling (HQ) qualities. The Simulation Framework for Flexible Aircraft was used to provide a generic cockpit environment and a piloted mathematical model of a bare airframe generic high aspect ratio wing aircraft (GA) model. Three highly qualified test pilots participated in the piloted simulation trials campaign and flew the GA model with both rigid and flexible wing configurations. The results showed a negligible difference for the longitudinal HQs between rigid and flexible wing aircraft. However, significant changes were indicated for the lateral/directional HQs of the flexible wing aircraft. A wing ratcheting phenomenon manifested itself during the roll mode tests, the spiral mode exhibited neutral stability and the Dutch roll mode shape changed from a horizontal to a vertical ellipse. The slalom task flight tests, performed to assess the FQs of the aircraft, revealed the degradation of both the longitudinal and lateral/directional FQs.
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KUPRIKOV, Mikhail Yu, Lev N. RABINSKIY und Nikita M. KUPRIKOV. „Moment-inertial representation of the Square-cube law in aircraft industry“. INCAS BULLETIN 11, S (01.08.2019): 163–64. http://dx.doi.org/10.13111/2066-8201.2019.11.s.16.
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Flight distance depends on the dimension of the aircraft, but the designers stand against an insurmountable barrier caused by the dimension of the aircraft. In the process of analysis, alternative variants of the moment-inertial layout of fuel, engines, and commercial loads and their influence on the aircraft mass change are considered. A comparative analysis of the characteristics of the moment-inertial layouts of the main aircraft of the normal aerodynamic configuration and the aircraft made according to the flying wing scheme obtained as a result of a numerical experiment showed a clear advantage in the moment-inertia characteristics of the aircraft made according to the “Flying Wing” scheme. A number of unconditional advantages in the moment-inertial shape were revealed, such as more rational placement of the target load, fuel tanks and engines, which ensured a gain in aircraft mass up to 7-8%, only due to the rational moment-inertial layout. The moment of inertia of the aircraft depends to a fifth degree on the change in the linear type size of the aircraft.
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Wang, Lin Lin, und Ge Gao. „Stability Features of the Saucer-Shaped Blend-Wing-Body Aircraft“. Advanced Materials Research 712-715 (Juni 2013): 1307–11. http://dx.doi.org/10.4028/www.scientific.net/amr.712-715.1307.
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The saucer-shaped aircraft is a novel aircraft adopting blend-wing-body configuration. The linear perturbation theory based on the classic flight dynamics was used to analyze the longitudinal, lateral and directional flight qualities of the saucer-shaped aircraft under low speed conditions. The flight qualities were given. Meanwhile the aerodynamic characteristics of the saucer-shaped aircraft, the conventional aircraft and the flying wing aircraft were also contrasted to discuss their similarities and differences. The results show that the saucer-shaped aircraft has stable longitudinal mode, rollover mode and Dutch roll mode. The spiral mode is unstable. The saucer-shaped aircraft exhibits superior flight qualities and excellent comprehensive performances.
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Rodríguez-Cortés, H., und A. Arias-Montaño. „Robust geometric sizing of a small flying wing planform based on evolutionary algorithms“. Aeronautical Journal 116, Nr. 1176 (Februar 2012): 175–88. http://dx.doi.org/10.1017/s0001924000006680.
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Abstract In this paper a geometric sizing method for a small electric powered flying wing is proposed. The geometric sizing method aims to reduce the effects of variations in the power plant characteristics on endurance. This results in a single-objective design optimisation problem where the sensitivity to power plant characteristics of the endurance equation is minimised, constrained to Reynolds number, wing load, wing taper ratio, aircraft size and wing sweep angle. As a result, geometric characteristics of the flying wing such as span, tip chord and root chord are obtained. Flying wing aerodynamic characteristics are obtained by means of an inviscid fluid flow analysis program of the type low-order panel methods, known as CMARC. The optimisation problem involves a non convex function so that it is necessary to rely on heuristic programming methods. In particular an Evolutionary Algorithm based on differential evolution is considered.
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JAISWAL, Roli, Om PRAKASH und Sudhir Kumar CHATURVEDI. „A Preliminary Study of Parameter Estimation for Fixed Wing Aircraft and High Endurability Parafoil Aerial Vehicle“. INCAS BULLETIN 12, Nr. 4 (04.12.2020): 95–109. http://dx.doi.org/10.13111/2066-8201.2020.12.4.9.
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High Endurability Aerial vehicle includes Airship, Powered parafoil aerial vehicle (PPAV). These flying aerial vehicles have excellent endurance and durability. Nowadays, research in lighter than air technology is pacing up fast. In the past years, the design and development of high endurable flying vehicle has grown due to their application in monitoring of floods/ drought, aerial photography, transportation, surveillance in terrain prone areas, reconnaissance missions etc. System Identification is a mathematical tool applied to develop mathematical model of any physical system based on measured data. Research on System Identification of these types of vehicles is on latest trends. Dynamic modelling of these types of vehicles is more complex than fixed wing aircraft. A detail Literature review in system Identification of PPAV and fixed wing aircraft is presented aiming to provide a source of information for researchers to make vehicle fully autonomous from manual controls. Various system Identification Techniques to estimate parameters of flying aerial vehicles are discussed. Longitudinal stability derivatives of fixed wing Hansa-3 aircraft and PPAV are compared. The methodology used in this study to estimate the longitudinal stability derivatives is ML Method. The results obtained in form of stability derivatives of Hansa-3 aircraft and Powered parafoil aerial vehicle are presented in tabular form. This study will give insight of identification techniques used to estimate parameters.
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Rabbey, M. Fazlay, Anik Mahmood Rumi, Farhan Hasan Nuri, Hafez M. Monerujjaman und M. Mehedi Hassan. „Structural Deformation and Stress Analysis of Aircraft Wing by Finite Element Method“. Advanced Materials Research 906 (April 2014): 318–22. http://dx.doi.org/10.4028/www.scientific.net/amr.906.318.
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Wing of an aircraft is lift producing component. It makes aircraft airborne by generating lift>weight. The wing must take the full aircraft weight during flying. So, it is very sophisticated task for designing a wing by keeping consideration of every design parameters simultaneously. This paper contains analysis of structural properties of wing by using finite element method. For well-organized design all the variables must be considered from the beginning of the design phase. The design phases for aircraft are: conceptual, preliminary and detail design. Until the preliminary design phase the aircraft structure is not considered. During these phases the material of the wing should be selected in such a way so that it can perform efficiently with less unexpected phenomena (drag) for which responsible properties are displacement, stress etc. Currently the most focusing area for the aero-elastic investigation is to design wing with good aerodynamic shape which will associated with less dragging structural behavior. It helps to reduce SFC (Specific Fuel Consumption) and so the cost. The analysis on that has done through Computational means as well as simulation technique to develop knowledge about the variation of aircraft wing structural properties.
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Izadpanahi, Ehsan, Siavash Rastkar und Pezhman Mardanpour. „Constructal Design of Flying Wing Aircraft: Curved and Swept Configurations“. AIAA Journal 57, Nr. 12 (Dezember 2019): 5527–42. http://dx.doi.org/10.2514/1.j058315.
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Peng, Cheng, Xin Min Wang und Chuang Qiu. „Research on Control Augmentation System for a Flying Wing Aircraft“. Advanced Materials Research 1049-1050 (Oktober 2014): 953–56. http://dx.doi.org/10.4028/www.scientific.net/amr.1049-1050.953.
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Requirements of the longitudinal control augmentation system are presented through studying the 25thChina Civil Aviation Regulations and C* flight quality evaluation criterion; The C* control augmentation scheme commonly used in modern large airliners is adopted to design the control augmentation system due to the stability and handling problems for the flying wing aircraft; The particle swarm optimization algorithm is proposed due to the parameter-scheduling difficulties in the designed control augmentation system. Numerical simulation shows that the designed C* control augmentation scheme is feasible.
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Saeed, T. I., W. R. Graham und C. A. Hall. „Boundary-Layer Suction System Design for Laminar-Flying-Wing Aircraft“. Journal of Aircraft 48, Nr. 4 (Juli 2011): 1368–79. http://dx.doi.org/10.2514/1.c031283.
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22
Wang, Yankui, Xiangxi Tang und Tao Li. „Lateral Stability and Control of a Flying Wing Configuration Aircraft“. Journal of Physics: Conference Series 1509 (April 2020): 012022. http://dx.doi.org/10.1088/1742-6596/1509/1/012022.
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23
Campos, Luís M. B. C., und Joaquim M. G. Marques. „On the Handling Qualities of Two Flying Wing Aircraft Configurations“. Aerospace 8, Nr. 3 (16.03.2021): 77. http://dx.doi.org/10.3390/aerospace8030077.
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The coupling of the longitudinal and lateral stability modes of an aeroplane is considered in two cases: (i) weak coupling, when the changes in the frequency and damping of the phugoid, short period, dutch roll, and helical modes are small, i.e., the square of the deviation is negligible compared to the square of the uncoupled value; (ii) strong coupling, when the coupled values may differ significantly from the uncoupled values. This allows a comparison of three values for the frequency and damping of each mode: (i) exact, i.e., fully coupled; (ii) with the approximation of weak coupling; (iii) with the assumption of decoupling. The comparison of these three values allows an assessment of the importance of coupling effects. The method is applied to two flying wing designs, concerning all modes in a total of eighteen flight conditions. It turns out that lateral-longitudinal coupling is small in all cases, and thus classical handling qualities criteria can be applied. The handling qualities are considered for all modes, namely the phugoid, short period, dutch roll, spiral, and roll modes. Additional focus is given to the pitch axis, considering the control anticipation parameter (CAP). The latter relates to the two kinds of manouever points, where damping vanishes, that are calculated for minimum speed, take-off, and initial and final cruise conditions. The conclusion compares two flying wings designs (the “long narrow” and “short wide” fuselage concepts) not only from the point of view of flight stability, but also from other viewpoints.
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Mohammed, Tariq O., Naser M. Elkhmri und Hamza AboBakr. „Analysis and Simulation of UAV Aircraft Flight Dynamics“. Advanced Materials Research 915-916 (April 2014): 7–11. http://dx.doi.org/10.4028/www.scientific.net/amr.915-916.7.
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The objective of the present work is to evaluate the static and dynamic stability of the Flying Wing Unmanned Aircraft Vehicle (UAV) model using the Tornado software. The longitudinal and the lateral-directional aerodynamics were studied using the model with incompressible flow, asymmetric, conditions. The stability coefficients were calculated and give proof that the aircraft is statically stable. Using the stability coefficients, the longitudinal and lateral-directional equations of motion were written to evaluate the dynamic stability of the vehicle. Good flying qualities were obtained, rating in Level 1 for the Cooper and Harper scale.
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Kaparos, Pavlos, Charalampos Papadopoulos und Kyros Yakinthos. „Conceptual design methodology of a box wing aircraft: A novel commercial airliner“. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, Nr. 14 (24.08.2018): 2651–62. http://dx.doi.org/10.1177/0954410018795815.
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In this work, the development of a conceptual design methodology of an innovative aircraft configuration, known as box wing, is presented. A box wing aircraft is based on a continuous-surface nonplanar wing formation with no wing-tips. The A320 medium range conventional cantilever wing aircraft is used as both the reference aircraft and the main competitor of the box wing aircraft. Based on the A320 characteristics and dimensions, a complete aerodynamic analysis of the box wing configuration is made by means of layout design and computational fluid dynamics studies, highlighting the aerodynamic and operating advantages of the box wing configuration compared to the A320 aircraft. The aspect ratio and the Oswald factor of a box wing aircraft differ significantly from the corresponding ones of A320 and provide increased aerodynamic performance. The increased aerodynamic performance leads by consequence, to lower fuel consumption, thus allowing longer range for the same payload or greater payload for the same range, contributing to the efforts for greener environment. In this work, the design methodology begins by estimating the critical initial design parameters, such as aspect ratio, dihedral angle, sweep angle, and taper ratio, which are continuously refined via an iterative process based on a conceptual design study. Various flying scenarios are studied using computational fluid dynamics and analytical calculations, in order to compare the performance of the box wing and the conventional A320, having always the same mission and payload conditions. The conceptual results show that the novel box wing configuration has considerable aerodynamic performance advantages compared to the conventional A320 aircraft.
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Xie, Jiang, Zhi Chun Yang und Shi Jun Guo. „Trim Optimizations of an Adaptive Tailless Aircraft with Composite Wing“. Advanced Materials Research 213 (Februar 2011): 334–38. http://dx.doi.org/10.4028/www.scientific.net/amr.213.334.
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This paper investigates aeroelastic tailoring and optimal trailing edge control surface deflection to minimize induced drag for a HALE UAV flying wing configuration. The analysis process is conducted on the Finite Element(FE) model of a composite slender wing. Genetic Algorithm(GA) is employed to aeroelastically tailor the wing by setting the composite ply orientation. The study examined conformal and traditional flaps and explored two optimization formulations to minimize drag. The impacts of the conformal control surface are recognized as required deflection saving which can be translated to drag reduction. The results also show that the control demands for the optimal trim can be further reduced if the wing is properly tailored.
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Pan, Yalin, Jun Huang, Feng Li und Chuxiong Yan. „Aerodynamic robust optimization of flying wing aircraft based on interval method“. Aircraft Engineering and Aerospace Technology 89, Nr. 3 (02.05.2017): 491–97. http://dx.doi.org/10.1108/aeat-09-2016-0145.
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Purpose The purpose of this paper is to propose a robust optimization strategy to deal with the aerodynamic optimization issue, which does not need a large sum of information on the uncertainty of input parameters. Design/methodology/approach Interval numbers were adopted to describe the uncertain input, which only requires bounds and does not necessarily need probability distributions. Based on the method, model outputs were also regarded as intervals. To identify a better solution, an order relation was used to rank interval numbers. Findings Based on intervals analysis method, the uncertain optimization problem was transformed into nested optimization. The outer optimization was used to optimize the design vector, and inner optimization was used to compute the interval of model outputs. A flying wing aircraft was used as a basis for uncertainty optimization through the suggested optimization strategy, and optimization results demonstrated the validity of the method. Originality/value In aircraft conceptual design, the uncertain information of design parameters are often insufficient. Interval number programming method used for uncertainty analysis is effective for aerodynamic robust optimization for aircraft conceptual design.
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Rojewski, Adam, und Jarosław Bartoszewicz. „Numerical Investigation of Endplates Influence on the Wing in Ground Effect Lift Force“. Journal of KONES 26, Nr. 4 (01.12.2019): 205–10. http://dx.doi.org/10.2478/kones-2019-0109.
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AbstractThe article presents a comparison of the wing in ground effect magnitude of conceptual WIG craft model main characteristics for a wing with and without endplates which are also known as winglets in regular aircraft. In article, the author describes WIG effect with and WIG craft, which operates on low altitude, smaller than the length of wing chord, mostly above the water reservoir. WIG effect phenomenon is simple. The first aircraft needs to fly at adequate altitude, with a smaller distance between lower airfoil surface and ground static pressure rises, leading to rising of lift force. The main advantage of the wing in ground effect craft on regular aircraft is a much higher lift to drag ratio, also this phenomenon provides to drop in specific fuel consumption of aircraft and allows flying with heavier cargo due to higher lift force. Characteristics present in the article were designated from simulations, which were conducted in Ansys Fluent software. Results obtained for a wing with endplate in numerical analysis shows the superiority of this approach. Endplates provide to increase WIG effect by a decrease in induced drag through the move out vertices from the wing tips, which are made by differential pressure above and under the wing. As winglets in regular aircraft, endplates provide to save fuel. WIG craft does not need airports so it could be a cheap alternative for modern aircraft.
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Rizzo, E., und A. Frediani. „A model for solar powered aircraft preliminary design“. Aeronautical Journal 112, Nr. 1128 (Februar 2008): 57–78. http://dx.doi.org/10.1017/s0001924000002001.
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Abstract Solar powered aircraft are becoming more and more interesting for future long endurance missions at high altitudes, because they could provide Earth monitoring, telecommunications, etc. without any atmospheric pollution and, hopefully in the near future, with competitive costs compared with satellites. The research activities carried out till now have been mainly focused on flying wings or conventional aircraft configurations, with a great emphasis on the technological aspects. The present paper aims to define a mathematical model for solar powered aircraft preliminary design, valid independently of the aerodynamic configuration. A preliminary analysis is carried out in order to simulate Helios and the results are compared with those available from the flights of this aircraft. The proposed mathematical model is used also to compare four different aircraft configurations, namely: a flying wing, a conventional aircraft, a twin boom aircraft and a biplane aircraft. The results obtained are discussed in the paper and an optimum aircraft is analysed.
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HOSSAIN, Aynul, Wei WANG und Hailong YUE. „Design and analysis of a linear servo-actuated variable-span morphing wing“. INCAS BULLETIN 12, Nr. 4 (04.12.2020): 71–82. http://dx.doi.org/10.13111/2066-8201.2020.12.4.7.
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Morphing aircraft are multi-role aircraft that change their external shape substantially to adapt to a changing mission environment during flight. Current interest in morphing vehicles has been increased by advances in smart technologies such as materials, sensors and actuators. These advances have led to a series of breakthroughs in a wide variety of disciplines that, when fully realized for aircraft applications, have the potential to produce large improvements in aircraft safety, affordability, and environmental compatibility. Morphing wing designs include rotating, sliding and inflating based on shape change mechanisms. The current trend in technology development shows that there is lots to improve with regards to aircraft size, flying range and flight performance envelope. There should be a balance between shape change and the penalties in cost, complexity and weight. Final performance of the morphing aircraft depends heavily on how such balances in design, manufacture and morphing mechanism can be achieved. This paper was an attempt to design and perform a further analysis of an efficient variable span wing for aircraft and fixed wing UAVs.
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Watkins, A., M. Thompson, M. Shortis, R. Segal, M. Abdulrahim und J. Sheridan. „An overview of experiments on the dynamic sensitivity of MAVs to turbulence“. Aeronautical Journal 114, Nr. 1158 (August 2010): 485–92. http://dx.doi.org/10.1017/s0001924000003973.
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Abstract Aspects of the turbulent wind environment Micro Air Vehicles (MAVs) experience when flying outdoors were replicated in a large wind tunnel. An overview of the facility, instrumentation and initial flight tests is given. Piloting inputs and aircraft accelerations were recorded on fixed and rotary wing MAVs and for some tests, measurements of the approach flow (u,v,w sampled at 1,250Hz at four laterally disposed upstream locations) were made. The piloting aim was to hold straight and level flight in the 12m wide × 4m high × ~50m long test section, while flying in a range of turbulent conditions. The Cooper-Harper rating system showed that a rotary craft was less sensitive to the effects of turbulence compared to the fixed wing craft and that while the fixed wing aircraft was relatively easy to fly in smooth air, it became extremely difficult to fly under high turbulence conditions. The rotary craft, while more difficult to fly per. se., did not become significantly harder to fly in relatively high turbulence levels. However the rotary craft had a higher mass and MOI than the fixed wing craft and further work is planned to understand the effects of these differences.
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Durmus, Seyhun. „Theoretical model proposal on direct calculation of wetted area and maximum lift-to-drag ratio“. Aircraft Engineering and Aerospace Technology 93, Nr. 6 (09.07.2021): 1097–103. http://dx.doi.org/10.1108/aeat-02-2021-0038.
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Purpose As measuring flight performance by experimental methods requires a lot of effort and cost, theoretical models can bring new perspectives to aircraft design. This paper aims to propose a model on the direct calculation of wetted area and L/Dmax. Design/methodology/approach Model is based on idea that the wetted area is proportional to aircraft gross weight to the power of 2/3 (Wg2/3). Aerodynamic underpinning of this method is based on the square–cube law and the claim that parasitic drag is related to the Swet/Swing. The equation proposed by Raymer was used to find the L/Dmax estimate based on the calculated wetted area. The accuracy of the theoretical approach was measured by comparing the L/Dmax values found in the reference literature and the L/Dmax values predicted by the theoretical approach. Findings Proposed theoretical L/Dmax estimate matches with the actual L/Dmax data in different types of aircraft. Among the conventional tube-wing design, only the sailplanes have a very low Swet/Swing. The Swet/Swing of flying wings, blended wing bodies (BWBs) and large delta wings are lower than conventional tube-wing design. Lower relative wetted area (Swet/Swing) is the key design criterion in high L/Dmax targeted designs. Originality/value The proposed model could be used in wing sizing according to the targeted L/Dmax value in aircraft design. The approach can be used to estimate the effect of varying gross weight on L/Dmax. In addition, the model contributes to the L/Dmax estimation of unusual designs, such as variable-sweep wing, large delta wings, flying wings and BWBs. This study is valuable in that it reveals that L/Dmax value can be predicted only with aspect ratio, gross weight (Wg) and wing area (Swing) data.
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Zhang, Ning, Lixin Wang und Feng Li. „Research on multi-task command allocation method for flying wing aircraft“. IOP Conference Series: Materials Science and Engineering 892 (04.08.2020): 012039. http://dx.doi.org/10.1088/1757-899x/892/1/012039.
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Bourdin, P., A. Gatto und M. I. Friswell. „Performing co-ordinated turns with articulated wing-tips as multi-axis control effectors“. Aeronautical Journal 114, Nr. 1151 (Januar 2010): 35–47. http://dx.doi.org/10.1017/s0001924000003511.
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Abstract This paper investigates a novel method for the control of aircraft. The concept consists of articulated split wing-tips, independently actuated and mounted on a baseline flying wing. The general philosophy behind the concept was that adequate control of a flying wing about its three axes could be obtained through local modifications of the dihedral angle at the wing-tips, thus providing an alternative to conventional control effectors such as elevons and drag rudders. Preliminary computations with a vortex lattice model and subsequent wind tunnel tests and Navier-Stokes computations demonstrate the viability of the concept for co-ordinated turns, with individual and/or combined wing-tip deflections producing multi-axis, coupled control moments. The multi-axis nature of the generated moments tends to over-actuate the flight control system, leading to some redundancy, which could be exploited to optimise secondary objective functions such as drag or bending moment.
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Syamsuar, Sayuti. „Simulasi dan Verifikasi Prestasi Terbang Model Remote Control Flying Boat Saat Hidroplaning“. WARTA ARDHIA 42, Nr. 1 (23.09.2017): 1. http://dx.doi.org/10.25104/wa.v42i1.294.1-6.
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Pesawat Wing In Surface Effect A2B tipe B konfigurasi Lippisch mempunyai hambatan air yang cukup besar dibandingkan tenaga mesin saat hydroplaning. Makalah ini berisikan bagian dari analisis dalam perancangan untuk mengetahui karakteristik aerodinamika dan hidrodinamika dari remote control model jenis Flying Boat pada fase hydroplaning. Pada awalnya, dilakukan pemotretan 3D terhadap pesawat model Flying Boat menggunakan kamera laser untuk menghasilkan solid drawing pada program CATIA. Model 3D dianalisis dengan menggunakan piranti lunak CFx pada program AnSys. Planform sayap, memiliki dihedral dan menggunakan airfoil jenis NACA 23012. Karakteristik aerodinamika dan hidrodinamika untuk model 3 D dipresentasikan pada posisi sudut alpha =00. Sedangkan kecepatan yang digunakan adalah 0 sampai25 knots. Untuk memverifikasi data hasil simulasi, digunakan data uji terbang pesawat udara tanpa awak Alap-alap yang mempunyai T/W rasio yang sama, yaitu sudut pitch, kecepatan arah sumbu Z pada sumbu benda, ketinggian dan kecepatan. Gaya angkat aerodimaka arah sumbu Z pada simulasi RC model Flying Boat sebanding dengan gaya angkat aerodinamika arah sumbu Z pada UAV Alap-alap saat take off.
[The Hydroplaning Flight Performance Simulation and Verfication of a Flying Boat Remote Control Model] The Wing in Surface Effect Aircraft A2B type B with Lippisch configuration has higher hydrodynamics drag compared to engine powered aircraft during hydroplaning. This paper explains parts of analysis in aircraft design to identify the aerodynamics and hydrodynamics characteristics of flying boat remote control model during hydroplaning phase. At first, flying boat model was three dimensional photographed using laser camera in order to produce solid drawing for CATIA program. The three dimensional model, later, analyzed by using CFx software in AnSys program. The wing planform has dihedral angle while the airfoil used is NACA 23012. The aerodynamics and hydrodynamics characteristics of this three-dimensional model is represented for alpha =00. Whilst the speed used in simulation was 0 to 25 knots. In verifying the data of the simulation results, the Unmanned Aerial Vehicle UAV Alap-alap flight test data was used in which it has the same T/W ratio for the pitch angle, acceleration in Z body axis, altitude, and speed. The aerodynamics lift in Z axis of flying boat model during simulation is proportional to the aerodynamics lift in Z axis of UAV Alap-alap during take-off.
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Keidel, Dominic, Giulio Molinari und Paolo Ermanni. „Aero-structural optimization and analysis of a camber-morphing flying wing: Structural and wind tunnel testing“. Journal of Intelligent Material Systems and Structures 30, Nr. 6 (18.02.2019): 908–23. http://dx.doi.org/10.1177/1045389x19828501.
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This article presents the design, optimization and performance assessment of a novel structure-actuation morphing concept for a flying wing, enabling the flight control for straight flight and around the pitch and roll axes. The applied camber-morphing concept utilizes an optimized selectively compliant internal structure, combined with electromechanical actuators to achieve a trailing edge deflection. These deflections lead to variations of the local and global lift, permitting to control the flight of the aircraft. The aero-structural behaviour of the wing is analysed using a coupled three-dimensional aerodynamic and structural simulation tool. An optimization of the planform, aerodynamic shape, internal structure and actuation parameters is performed to attain a longitudinally stable and aerodynamically efficient flying wing. The drag increment caused by morphing is minimized through the numerical optimization, resulting in high aerodynamic efficiency across a range of flight speeds. The stiffness and morphing capabilities of the manufactured wing are characterized experimentally and are compared with the numerical predictions, and the aerodynamic and aeroelastic behaviour of the wing is investigated through wind tunnel tests. The test results indicate the ability of the flying wing to achieve sufficient variations in lift, roll and pitch to control the flight completely through camber morphing.
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Xu, Hao, Jinglong Han, Haiwei Yun und Xiaomao Chen. „Calculation of the Hinge Moments of a Folding Wing Aircraft during the Flight-Folding Process“. International Journal of Aerospace Engineering 2019 (03.09.2019): 1–11. http://dx.doi.org/10.1155/2019/9362629.
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A folding wing morphing aircraft should complete the folding and unfolding process of its wings while in flight. Calculating the hinge moments during the morphing process is a critical aspect of a folding wing design. Most previous studies on this problem have adopted steady-state or quasi-steady-state methods, which do not simulate the free-flying morphing process. In this study, we construct an aeroelastic flight simulation platform based on the secondary development of ADAMS software to simulate the flight-folding process of a folding wing aircraft. A flexible multibody dynamic model of the folding wing structure is established in ADAMS using modal neutral files, and the doublet lattice method is developed to generate aerodynamic influence coefficient matrices that are suitable for the flight-folding process. The user subroutine is utilized, aerodynamic loading is realized in ADAMS, and an aeroelastic flight simulation platform of a folding wing aircraft is built. On the basis of this platform, the flight-folding process of the aircraft is simulated, the hinge moments of the folding wings are calculated, and the influences of the folding rate and the aircraft’s center of gravity (c.g.) position on the results are investigated. Results show that the steady-state method is applicable to the slow folding process. For the fast folding process, the steady-state simulation errors of the hinge moments are substantially large, and a transient method is required to simulate the flight-folding process. In addition, the c.g. position considerably affects the hinge moments during the folding process. Given that the c.g. position moves aft, the maximum hinge moments of the inner and outer wings constantly increase.
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Yao, Junkai, Haibo He, Danjie Zhou, Zhiwei Shi und Hai Du. „Effects of Plasma Actuator Discharge on Lift-Enhancement and Flow Patterns of Flying Wing Aircraft“. Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, Nr. 5 (Oktober 2018): 963–69. http://dx.doi.org/10.1051/jnwpu/20183650963.
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The nanosecond pulsed plasma discharge actuator is used on a flying wing aircraft. At the angles of attack rang from -4° to 28°, the impact of plasma actuator arrangement position and discharge frequency on lift-enhancement effect is tested. Oil flow visualization is used to investigate the surface flow pattern varies with angles of attack for the plasma actuator turned on and off. The result indicates that lift-enhancement can be achieved through the actuator discharges at large angles of attack on flying wing aircraft. The arrangement position and discharge frequency both have a significant impact on lift-enhancement effect. The actuator which arranged at the leading edge of the aircraft could get the best lift-enhancement effect. There exists an optimal discharge frequency, flow separation under this frequency can be effectively suppressed, which results the best lift-enhancement effect. The flow visualization test shows that the control mechanisms of the plasma actuator are to inject energy to the shear layer, thus increased the vortex strength. The vortices strengthen the mixing of the outer high-speed fluid with inner low-speed fluid, which effectively restrains the separation.
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Cook, M. V., und H. V. de Castro. „The longitudinal flying qualities of a blended-wing-body civil transport aircraft“. Aeronautical Journal 108, Nr. 1080 (Februar 2004): 75–84. http://dx.doi.org/10.1017/s0001924000005029.
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Abstract This paper describes an evaluation of the longitudinal flying qualities of a generic blended-wing-body (BWB) transport aircraft at low speed flight conditions. Aerodynamic data was obtained from several sources and integrated into the equations of motion of a typical BWB configuration in order to provide a reasonable basis for flying qualities assessment. The control requirements to trim are enumerated for a representative range of cg position and static margin over the typical range of approach speeds for both stable and unstable configurations. The linear dynamic characteristics of the unaugmented airframe are also described for the same range of stability margin. Subsequent work describes the development of a rate command-attitude hold command and stability augmentation system configured to comply with representative modern handling criteria. Finally, the flight dynamics of the augmented aircraft are described after refinement of the control law by means of piloted simulation in a fixed base flight simulator.
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Nasir, Rizal E. M., und Wahyu Kuntjoro. „Longitudinal Flight Stability Augmentation of a Small Blended Wing-Body Aircraft with Canard as Control Surface“. Applied Mechanics and Materials 393 (September 2013): 329–37. http://dx.doi.org/10.4028/www.scientific.net/amm.393.329.
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Transient response of an aircraft in longitudinal motion has two modes of oscillatory motion short period mode and phugoid modes and failure to achieve satisfactory level would mean poor flying and handling qualities leading to unnecessary pilot workload. This study proposes a stability augmentation system (SAS) in longitudinal flying modes for steady and level flight at all airspeeds and altitudes within Baseline-II E-2 BWBs operational flight envelope (OFE). The main controlling component of this stability augmentation system is a set of canard, a control surface located in front of the wing. It must be able to compensate Baseline-II E-2 BWB poor transient responses damping ratios so that good flying quality can be achieved. Observation from the transient responses of the unaugmented system signify high-frequency short-period oscillations with almost constant low damping ratio at an altitude, and low-frequency phugoid oscillation with varying damping ratio depending on airspeed. A conclusive behaviour of natural frequencies and damping ratios against dynamic pressure leads to the understanding on how dynamic pressure influences the flying qualities. Derivation of dynamic equations in terms of dynamic pressures enables one to design and device a feedback system to compensate poor flying qualities of the original unaugmented aircraft with conclusive relationship between important parameters and dynamic pressure are put in the overall dynamic equation. Two feedback gain systems, pitch attitude and pitch rate gains are scheduled based on dynamic pressure values and are combined into the aircraft longitudinal SAS. The proposed SAS has proven to be the suitable candidate for Baseline-II E-2 BWB as it is able to ensure Level 1 flying qualities, longitudinally.
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Dinh, Bao Anh, Hieu Khanh Ngo und Van Nhu Nguyen. „An efficient low-speed airfoil design optimization process using multi-fidelity analysis for UAV flying wing“. Science and Technology Development Journal 19, Nr. 3 (30.09.2016): 43–52. http://dx.doi.org/10.32508/stdj.v19i3.519.
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This paper proposes an efficient low-speed airfoil selection and design optimization process using multi-fidelity analysis for a long endurance Unmanned Aerial Vehicle (UAV) flying wing. The developed process includes the low speed airfoil database construction, airfoil selection and design optimization steps based on the given design requirements. The multi-fidelity analysis solvers including the panel method and computational fluid dynamics (CFD) are presented to analyze the low speed airfoil aerodynamic characteristics accurately and perform inverse airfoil design optimization effectively without any noticeable turnaround time in the early aircraft design stage. The unconventional flying wing UAV design shows poor reaction in longitudinal stability. However, It has low parasite drag, long endurance, and better performance. The multi-fidelity analysis solvers are validated for the E387 and CAL2463m airfoil compared to the wind tunnel test data. Then, 29 low speed airfoils for flying wing UAV are constructed by using the multi-fidelity solvers. The weighting score method is used to select the appropriate airfoil for the given design requirements. The selected airfoil is used as a baseline for the inverse airfoil design optimization step to refine and obtain the optimal airfoil configuration. The implementation of proposed method is applied for the real flying-wing UAV airfoil design case to demonstrate the effectiveness and feasibility of the proposed method.
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Mardanpour, Pezhman, Dewey H. Hodges, Ryan Neuhart und Nathan Graybeal. „Engine Placement Effect on Nonlinear Trim and Stability of Flying Wing Aircraft“. Journal of Aircraft 50, Nr. 6 (November 2013): 1716–25. http://dx.doi.org/10.2514/1.c031955.
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Li, Ming, Junqiang Bai, Li Li, Xiaoxuan Meng, Qian Liu und Bao Chen. „A gradient-based aero-stealth optimization design method for flying wing aircraft“. Aerospace Science and Technology 92 (September 2019): 156–69. http://dx.doi.org/10.1016/j.ast.2019.05.067.
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Gavrilovic, Nikola, Murat Bronz, Jean-Marc Moschetta und Emmanuel Benard. „Bioinspired wind field estimation—part 1: Angle of attack measurements through surface pressure distribution“. International Journal of Micro Air Vehicles 10, Nr. 3 (September 2018): 273–84. http://dx.doi.org/10.1177/1756829318794172.
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One of the major challenges of Mini-Unmanned Aerial Vehicle flight is the unsteady interaction with turbulent environment while flying in lower levels of atmospheric boundary layer. Following inspiration from nature we expose a new system for angle of attack estimation based on pressure measurements on the wing. Such an equipment can be used for real-time estimation of the angle of attack during flight or even further building of wind velocity vector with additional equipment. Those information can find purpose in control and stabilization of the aircraft due to inequalities seen by the wing or even for various soaring strategies that rely on active control for energy extraction. In that purpose, flying wing aircraft has been used with totally four span-wise locations for local angle of attack estimation. In-flight angle of attack estimation from differential pressure measurements on the wing has been compared with magnetic sensor with wind vane. The results have shown that pressure ports give more reliable estimation of angle of attack when compared to values given by wind vane attached to a specially designed air-boom. Difference in local angle of attack at four span-wise locations has confirmed spatial variation of turbulence in low altitude flight. Moreover, theoretical law of energy dissipation for wind components described by Kaimal spectrum has shown acceptable match with estimated ones.
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Mardanpour, Pezhman, und Dewey H. Hodges. „On the Importance of Nonlinear Aeroelasticity and Energy Efficiency in Design of Flying Wing Aircraft“. Advances in Aerospace Engineering 2015 (18.01.2015): 1–11. http://dx.doi.org/10.1155/2015/613962.
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Energy efficiency plays important role in aeroelastic design of flying wing aircraft and may be attained by use of lightweight structures as well as solar energy. NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE Aircraft) is a newly developed computer program which uses a nonlinear composite beam theory that eliminates the difficulties in aeroelastic simulations of flexible high-aspect-ratio wings which undergoes large deformation, as well as the singularities due to finite rotations. NATASHA has shown that proper engine placement could significantly increase the aeroelastic flight envelope which typically leads to more flexible and lighter aircraft. The areas of minimum kinetic energy for the lower frequency modes are in accordance with the zones with maximum flutter speed and have the potential to save computational effort. Another aspect of energy efficiency for High Altitude, Long Endurance (HALE) drones stems from needing to minimize energy consumption because of limitations on the source of energy, that is, solar power. NATASHA is capable of simulating the aeroelastic passive morphing maneuver (i.e., morphing without relying on actuators) and at as near zero energy cost as possible of the aircraft so as the solar panels installed on the wing are in maximum exposure to sun during different time of the day.
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Boller, Christian, Chen Mig Kuo und Ning Qin. „Biologically Inspired Shape Changing Aerodynamic Profiles and their Effect on Flight Performance of Future Aircraft“. Advances in Science and Technology 56 (September 2008): 534–44. http://dx.doi.org/10.4028/www.scientific.net/ast.56.534.
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Flying has been inspired by biology since the very early days of aviation. Although aircraft look to be established with regard to their structural design today, active materials have again triggered as to what degree aerodynamic profiles could become more adaptive with regard to their shape and achieving enhanced flight performance. Demonstrating the shortcomings of wing adaptiveness on manned aircraft size is time consuming and costly. This can however be overcome by performing these demonstrations on aircraft at much smaller scale. Aircraft at this scale are micro aerial vehicles (MAV) which have spans far less than a metre and a weight of no more than a few hundred grams. To enhance manoeuvrability and stability birds and insects use actuation principles along their wings such as changing wing thickness or stiffness, or actuating individual flaps with their feathers. Similar effects will be shown for an MAV’s wing thickness and stiffness change regarding flight stability and manoeuvrability and how this can be realised using active materials. It will be explained how a variable V-tail and a vector thrust propulsion system can be realised on an MAV and the resulting effect on flight performance. Results from real flight tests will be included and conclusions will be based on the consequences regarding larger sized aircraft.
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Sadovnychiy, S., A. Ryzhenko und A. Betin. „Flight control system damage simulation using freely flying models“. Aeronautical Journal 109, Nr. 1091 (Januar 2005): 45–50. http://dx.doi.org/10.1017/s000192400000052x.
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Abstract This article deals with a damage simulation of flight control systems during a flight. As a subject of flight tests the model of a classic aerodynamic aircraft scheme is considered. This aircraft has highly swept wings a moderate wing elongation and all-moving horizontal tail surfaces. The diagrams of flight parameters from flight tests of the freely flying models with loss of a control surface in flight are given. The investigation results for the failures leading to a sharp drop in the stiffness of the control units in the pitch channel are given. The damage investigation in horizontal flight and in complex manoeuvres is given.
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Suroso, Indreswari, und Erwhin Irmawan. „Analysis Of Aerial Photography With Drone Type Fixed Wing In Kotabaru, Lampung“. Journal of Applied Geospatial Information 2, Nr. 1 (04.05.2018): 102–7. http://dx.doi.org/10.30871/jagi.v2i1.738.
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In the world of photography is very closely related to the unmanned aerial vehicle called drones. Drones mounted camera so that the plane is pilot controlled from the mainland. Photography results were seen by the pilot after the drone aircraft landed. Drones are unmanned drones that are controlled remotely. Unmanned Aerial Vehicle (UAV), is a flying machine that operates with remote control by the pilot. Methode for this research are preparation assembly of drone, planning altitude flying, testing on ground, camera of calibration, air capture, result of aerial photos and analysis of result aerial photos. There are two types of drones, multicopter and fixed wing. Fixed wing has an airplane like shape with a wing system. Fixed wing use bettery 4000 mAh . Fixed wing drone in this research used mapping in This drone has a load ability of 1 kg and operational time is used approximately 30 minutes for an areas 20 to 50 hectares with a height of 100 m to 200 m and payload 1 kg above ground level. The aerial photographs in Kotabaru produce excellent aerial photographs that can help mapping the local government in the Kotabaru region.
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Tarnowski, Andrzej. „Morphing wing with skin discontinuity – kinematic concept“. Aircraft Engineering and Aerospace Technology 89, Nr. 4 (03.07.2017): 535–46. http://dx.doi.org/10.1108/aeat-11-2016-0208.
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Purpose This paper aims to describe the concept of morphing tailless aircraft with discontinuous skin and its preliminary kinematic solution. Project assumptions, next steps and expected results are briefly presented. Design/methodology/approach Multidisciplinary numerical optimization will be used to determine control allocation for wing segments rotation. Wing demonstrator will be fabricated and tested in wind tunnel. Results will be used in construction of flying model and design of its control system. Flight data of morphing demonstrator and reference aircraft will result in comparative analysis of both technologies. Findings Proposed design combines advantages of wing morphing without complications of wing’s structure elastic deformation. Better performance, stability and maneuverability is expected due to wing’s construction which is entirely composed of unconnected wing segments. Independent control of each segment allows for free modeling of spanwise lift force distribution. Originality/value Nonlinear multipoint distribution of wing twist as the only mechanism for control and flight performance optimization has never been studied or constructed. Planned wind tunnel investigation of such complex aerodynamic structure has not been previously published and will be an original contribution to the development of aviation and in particular to the aerodynamics of wing with discontinuous skin.
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Ji, Chang-ho, Chong-sup Kim und Byoung-Soo Kim. „A Hybrid Incremental Nonlinear Dynamic Inversion Control for Improving Flying Qualities of Asymmetric Store Configuration Aircraft“. Aerospace 8, Nr. 5 (02.05.2021): 126. http://dx.doi.org/10.3390/aerospace8050126.
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Highly maneuverability fighter aircrafts are equipped with various weapons for successful air-to-air and air-to-ground missions. The aircraft has abrupt transient response due to ejection force generated when store of one wing is launched and the movement of lateral center-of-gravity (YCG) changing by the mass distribution of both wings after launched. Under maintaining 1 g level flight with manual trim system in the asymmetric store configuration, the aircraft causes unexpected roll motion for the pure longitudinal maneuver because the change of AoA and airspeed changes the amount of trim for level flight of the aircraft. For this reason, the pilot should continuously use the roll control stick input to maintain level flight. This characteristic increases the pilot’s workload and adversely affects the flying qualities of the aircraft, which is a major cause of deteriorating mission efficiency for combat maneuver. In this paper, we propose a hybrid control that combines model- and sensor-based Incremental Nonlinear Dynamic Inversion (INDI) control based mathematical model of the supersonic advanced trainer to minimize the transient response of the aircraft when the store is launched and to effectively reduce the unexpected roll motion that occurs for the pure longitudinal maneuvering in the asymmetric store configuration. As a result of the frequency- and time-domain evaluation, the proposed control method can effectively reduce the transient response for store launch and minimize unexpected roll motion for the pure longitudinal maneuver. Therefore, this control method can effectively improve flying qualities and mission efficiency by reducing the pilot’s workload in the operation of the asymmetric store configuration.