Thematische Bibliographien / Flying-wing aircraft

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Auswahl der wissenschaftlichen Literatur zum Thema „Flying-wing aircraft“

Autor: Grafiati

Veröffentlicht am 4. Juni 2021

Zuletzt aktualisiert am 18. Februar 2022

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Zeitschriftenartikel zum Thema "Flying-wing aircraft"

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.

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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.

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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.

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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.

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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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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.

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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.

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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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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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Dissertationen zum Thema "Flying-wing aircraft"

Huang, Haidong. „Optimal design of a flying-wing aircraft inner wing structure configuration“. Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7439.

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Flying-wing aircraft are considered to have great advantages and potentials in aerodynamic performance and weight saving. However, they also have many challenges in design. One of the biggest challenges is the structural design of the inner wing (fuselage). Unlike the conventional fuselage of a tube configuration, the flying-wing aircraft inner wing cross section is limited to a noncircular shape, which is not structurally efficient to resist the internal pressure load. In order to solve this problem, a number of configurations have been proposed by other designers such as Multi Bubble Fuselage (MBF), Vaulted Ribbed Shell (VLRS), Flat Ribbed Shell (FRS), Vaulted Shell Honeycomb Core (VLHC), Flat Sandwich Shell Honeycomb Core (FLHC), Y Braced Box Fuselage and the modified fuselage designed with Y brace replaced by vaulted shell configurations. However all these configurations still inevitably have structural weight penalty compared with optimal tube fuselage layout. This current study intends to focus on finding an optimal configuration with minimum structural weight penalty for a flying-wing concept in a preliminary design stage. A new possible inner wing configuration, in terms of aerodynamic shape and structural layout, was proposed by the author, and it might be referred as ‘Wave-Section Configuration’. The methodologies of how to obtain a structurally efficient curvature of the shape, as well as how to conduct the initial sizing were incorporated. A theoretical analysis of load transmission indicated that the Wave-Section Configuration is feasible, and this was further proved as being practical by FE analysis. Moreover, initial FE analysis and comparison of the Wave-Section Configuration with two other typical configurations, Multi Bubble Fuselage and Conventional Wing, suggested that the Wave-Section Configuration is an optimal design in terms of weight saving. However, due to limitations of the author’s research area, influences on aerodynamic performances have not yet been taken into account.

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Saeed, Tariq Issam. „Conceptual design for a laminar-flying-wing aircraft“. Thesis, University of Cambridge, 2012. https://www.repository.cam.ac.uk/handle/1810/243926.

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The laminar-flying-wing aircraft appears to be an attractive long-term prospect for reducing the environmental impact of commercial aviation. In assessing its potential, a relatively straightforward initial step is the conceptual design of a version with restricted sweep angle. Such a design is the topic of this thesis. In addition to boundary layer laminarisation (utilising distributed suction) and limited sweep, a standing-height passenger cabin and subcritical aerofoil flow are imposed as requirements. Subject to these constraints, this research aims to: provide insight into the parameters affecting practical laminar-flow-control suction power requirements; identify a viable basic design specification; and, on the basis of this, an assessment of the fuel efficiency through a detailed conceptual design study. It is shown that there is a minimum power requirement independent of the suction system design, associated with the stagnation pressure loss in the boundary layer. This requirement increases with aerofoil section thickness, but depends only weakly on Mach number and (for a thick, lightly-loaded laminar flying wing) lift coefficient. Deviation from the optimal suction distribution, due to a practical chamber-based architecture, is found to have very little effect on the overall suction coefficient. In the spanwise direction, through suitable choice of chamber depth, the pressure drop due to frictional and inertial effects may be rendered negligible. Finally, it is found that the pressure drop from the aerofoil surface to the pump collector ducts determines the power penalty; suggesting there is little benefit in trying to maintain an optimal suction distribution through increased subsurface-chamber complexity. For representative parameter values, the minimum power associated with boundary-layer losses alone contributes some 80% - 90% of the total power requirement. To identify the viable basic design specification, a high-level exploration of the laminar-flying-wing design space is performed, with an emphasis above all on aerodynamic efficiency. The characteristics of the design are assessed as a function of three parameters: thickness-to-chord ratio, wingspan, and unit Reynolds number. A feasible specification, with 20% thickness-to-chord, 80 m span and a unit Reynolds number of 8 x 10[superscript 6] m[superscript -1], is identified; it corresponds to a 187 tonne aircraft which cruises at Mach 0.67 and altitude 22,500 ft, with lift coefficient 0.14. The benefit of laminarisation is manifested in a high lift-to-drag ratio, but the wing loading is low, and the structural efficiency and gust response are thus likely to be relatively poor. On the basis of this specification, a detailed conceptual design is undertaken. A 220-passenger laminar-flying-wing concept, propelled by three turboprop engines, with a cruise range of 9000 km is developed. The estimated fuel burn is 13.9 g/pax.km. For comparison, a conventional aircraft, propelled by four turboprop engines, with a high-mounted, unswept, wing is designed for the same mission specification and propulsion characteristics, and is shown to have a fuel burn of 15.0 g/pax.km. Despite significant aerodynamic efficiency gains, the fuel burn of the laminar flying wing is only marginally better as it suffers from a poor cruise engine efficiency, due to extreme differences between takeoff and cruising requirements, and is much heavier. The laminar flying wing proposed in this thesis falls short of the performance improvements expected of the concept, and is not worth the development effort. It is therefore proposed that research efforts either be focussed on improving the engine efficiency, or switching to a low aspect ratio, high sweep, design configuration.

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Miao, Zhisong. „Aircraft engine performance and integration in a flying wing aircraft conceptual design“. Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7249.

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The increasing demand of more economical and environmentally friendly aero engines leads to the proposal of a new concept – geared turbofan. In this thesis, the characteristics of this kind of engine and relevant considerations of integration on a flying wing aircraft were studied. The studies can be divided into four levels: GTF-11 engine modelling and performance simulation; aircraft performance calculation; nacelle design and aerodynamic performance evaluation; preliminary engine installation. Firstly, a geared concept engine model was constructed using TURBOMATCH software. Based on parametric analysis and SFC target, the main cycle parameters were selected. Then, the maximum take-off thrust was verified and corrected from 195.56kN to 212kN to meet the requirements of take-off field length and second segment climb. Besides, the engine performance at offdesign points was simulated for aircraft performance calculation. Secondly, an aircraft performance model was developed and the performance of FW-11 was calculated on the basis of GTF-11 simulation results. Then, the effect of GTF-11 characteristics performance on aircraft performance was evaluated. A comparison between GTF-11 and conventional turbofan, RB211- 524B4, indicated that the aircraft can achieve a 13.1% improvement in fuel efficiency by using the new concept engine. Thirdly, a nacelle was designed for GTF-11 based on NACA 1-series and empirical methods while the nacelle dimensions of conventional turbofan RB211-525B4 were obtained by measure approach. Then, the installation thrust losses caused by nacelle drags of the two engines were evaluated using ESDU 81024a. The results showed that the nacelle drags account for about 4.08% and 3.09% of net thrust for GTF-11 and RB211-525B4, respectively. Finally, the considerations of engine installation on a flying wing aircraft were discussed and a preliminary disposition of GTF-11 on FW-11 was presented.

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Zhu, Yan. „Longitudinal control laws design for a flying wing aircraft“. Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7423.

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This research is concerned with the flight dynamic, pitch flight control and flying qualities assessment for the reference BWB aircraft. It aims to develop the longitudinal control laws which could satisfy the flying and handing qualities over the whole flight envelope with added consideration of centre of gravity (CG) variation. In order to achieve this goal, both the longitudinal stability augmentation system (SAS) and autopilot control laws are studied in this thesis. Using the pole placement method, two sets of local Linear-Time-Invariant (LTI) SAS controllers are designed from the viewpoints of flying and handing qualities assessment and wind disturbance checking. The global gain schedule is developed with the scheduling variable of dynamic pressure to transfer gains smoothly between these two trim points. In addition, the poles movement of short period mode with the varying CG position are analysed, and some approaches of control system design to address the problem of reduced stability induced by CG variation are discussed as well. To achieve the command control for the aircraft, outer loop autopilot both pitch attitude hold and altitude hold are implemented by using the root locus method. By the existing criteria in MIL-F-8785C specifications being employed to assess the augmented aircraft response, the SAS linear controller with automatic changing gains effectively improve the stability characteristic for the reference BWB aircraft over the whole envelope. Hence, the augmented aircraft equals to a good characteristic controlled object for the outer loop or command path design, which guarantee the satisfactory performance of command control for the BWB aircraft. The flight control law for the longitudinal was completed with the SAS controller and autopilot design. In particular, the SAS was achieved with Level 1 flying and handing qualities, meanwhile the autopilot system was applied to obtain a satisfactory pitch attitude and altitude tracking performance.

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Ikeda, Toshihiro, und toshi ikeda@gmail com. „Aerodynamic Analysis of a Blended-Wing-Body Aircraft Configuration“. RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070122.163030.

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In recent years unconventional aircraft configurations, such as Blended-Wing-Body (BWB) aircraft, are being investigated and researched with the aim to develop more efficient aircraft configurations, in particular for very large transport aircraft that are more efficient and environmentally-friendly. The BWB configuration designates an alternative aircraft configuration where the wing and fuselage are integrated which results essentially in a hybrid flying wing shape. The first example of a BWB design was researched at the Loughead Company in the United States of America in 1917. The Junkers G. 38, the largest land plane in the world at the time, was produced in 1929 for Luft Hansa (present day; Lufthansa). Since 1939 Northrop Aircraft Inc. (USA), currently Northrop Grumman Corporation and the Horten brothers (Germany) investigated and developed BWB aircraft for military purposes. At present, the major aircraft industries and several universities has been researching the BWB concept aircraft for civil and military activities, although the BWB design concept has not been adapted for civil transport yet. The B-2 Spirit, (produced by the Northrop Corporation) has been used in military service since the late 1980s. The BWB design seems to show greater potential for very large passenger transport aircraft. A NASA BWB research team found an 800 passenger BWB concept consumed 27 percent less fuel per passenger per flight operation than an equivalent conventional configuration (Leiebeck 2005). The purpose of this research is to assess the aerodynamic efficiency of a BWB aircraft with respect to a conventional configuration, and to identify design issues that determine the effectiveness of BWB performance as a function of aircraft payload capacity. The approach was undertaken to develop a new conceptual design of a BWB aircraft using Computational Aided Design (CAD) tools and Computational Fluid Dynamics (CFD) software. An existing high-capacity aircraft, the Airbus A380 Contents RMIT University, Australia was modelled, and its aerodynamic characteristics assessed using CFD to enable comparison with the BWB design. The BWB design had to be compatible with airports that took conventional aircraft, meaning a wingspan of not more than 80 meters for what the International Civil Aviation Organisation (ICAO) regulation calls class 7 airports (Amano 2001). From the literature review, five contentions were addressed; i. Is a BWB aircraft design more aerodynamically efficient than a conventional aircraft configuration? ii. How does the BWB compare overall with a conventional design configuration? iii. What is the trade-off between conventional designs and a BWB arrangement? iv. What mission requirements, such as payload and endurance, will a BWB design concept become attractive for? v. What are the practical issues associated with the BWB design that need to be addressed? In an aircraft multidisciplinary design environment, there are two major branches of engineering science; CFD analysis and structural analysis; which is required to commence producing an aircraft. In this research, conceptual BWB designs and CFD simulations were iterated to evaluate the aerodynamic performance of an optimal BWB design, and a theoretical calculation of structural analysis was done based on the CFD results. The following hypothesis was prompted; A BWB configuration has superior in flight performance due to a higher Lift-to-Drag (L/D) ratio, and could improve upon existing conventional aircraft, in the areas of noise emission, fuel consumption and Direct Operation Cost (DOC) on service. However, a BWB configuration needs to employ a new structural system for passenger safety procedures, such as passenger ingress/egress. The research confirmed that the BWB configuration achieves higher aerodynamic performance with an achievement of the current airport compatibility issue. The beneficial results of the BWB design were that the parasite drag was decreased and the spanwise body as a whole can generate lift. In a BWB design environment, several advanced computational techniques were required to compute a CFD simulation with the CAD model using pre-processing and CFD software.

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de, Castro Helena V. „Flying and handling qualities of a fly-by-wire blended-wing-body civil transport aircraft“. Thesis, Cranfield University, 2003. http://hdl.handle.net/1826/119.

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The blended-wing-body (BWB) configuration appears as a promising contender for the next generation of large transport aircraft. The idea of blending the wing with the fuselage and eliminating the tail is not new, it has long been known that tailless aircraft can suffer from stability and control problems that must be addressed early in the design. This thesis is concerned with identifying and then evaluating the flight dynamics, stability, flight controls and handling qualities of a generic BWB large transport aircraft concept. Longitudinal and lateral-directional static and dynamic stability analysis using aerodynamic data representative of different BWB configurations enabled a better understanding of the BWB aircraft characteristics and identification of the mechanisms that influence its behaviour. The static stability studies revealed that there is limited control power both for the longitudinal and lateral-directional motion. The solution for the longitudinal problem is to limit the static margins to small values around the neutral point, and even to use negative static margins. However, for the directional control problem the solution is to investigate alternative ways of generating directional control power. Additional investigation uncovered dynamic instability due to the low and negative longitudinal and directional static stability. Furthermore, adverse roll and yaw responses were found to aileron inputs. The implementation of a pitch rate command/attitude hold flight control system (FCS) improved the longitudinal basic BWB characteristics to satisfactory levels, or Level 1, flying and handling qualities (FHQ). Although the lateral-directional command and stability FCS also improved the BWB flying and handling qualities it was demonstrated that Level 1 was not achieved for all flight conditions due to limited directional control power. The possibility to use the conventional FHQs criteria and requirements for FCS design and FHQs assessment on BWB configurations was also investigated. Hence, a limited set of simulation trials were undertaken using an augmented BWB configuration. The longitudinal Bandwidth/Phase delay/Gibson dropback criteria, as suggested by the military standards, together with the Generic Control Anticipation Parameter (GCAP) proved possible to use to assess flying and handling qualities of BWB aircraft. For the lateral-directional motion the MIL-F-8785C criteria were used. Although it is possible to assess the FHQ of BWB configuartions using these criteria, more research is recommended specifically on the lateral-directional FHQs criteria and requirements of highly augmented large transport aircraft.

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Xu, Rongxin. „Optimal design of a composite wing structure for a flying-wing aircraft subject to multi-constraint“. Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7290.

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This thesis presents a research project and results of design and optimization of a composite wing structure for a large aircraft in flying wing configuration. The design process started from conceptual design and preliminary design, which includes initial sizing and stressing followed by numerical modelling and analysis of the wing structure. The research was then focused on the minimum weight optimization of the /composite wing structure /subject to multiple design /constraints. The modelling, analysis and optimization process has been performed by using the NASTRAN code. The methodology and technique not only make the modelling in high accuracy, but also keep the whole process within one commercial package for practical application. The example aircraft, called FW-11, is a 250-seat commercial airliner of flying wing configuration designed through our MSc students Group Design Project (GDP) in Cranfield University. Started from conceptual design in the GDP, a high-aspect-ratio and large sweepback angle flying wing configuration has been adopted. During the GDP, the author was responsible for the structural layout design and material selection. Composite material has been chosen as the preferable material for both the inner and outer wing components. Based on the derivation of structural design data in the conceptual phase, the author continued with the preliminary design of the outer wing airframe and then focused on the optimization of the composite wing structure. Cont/d.

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Wang, Xiaoyang. „Aircraft fuel system prognostics and health management“. Thesis, Cranfield University, 2012. http://dspace.lib.cranfield.ac.uk/handle/1826/7214.

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This thesis contains the specific description of Group Design Project (GDP) and Individual Research Project (IRP) that are undertaken by the author and form part of the degree of Master of Science. The target of GDP is to develop a novel and unique commercial flying wing aircraft titled FW-11. FW-11 is a three-year collaborative civil aircraft project between Aviation Industry Corporation of China (AVIC) and Cranfield University. According to the market analysis result conducted by the author, 250 seats capacity and 7500 nautical miles were chosen as the design targets. The IRP is the further study of GDP, which is to enhance the competitive capability by deploying prognostics and health management (PHM) technology to the fuel system of FW-11. As a novel and brand-new technology, PHM enables the real-time transformation of system status data into alert and maintenance information during all ground or flight operating phases to improve the aircraft reliability and operating costs. Aircraft fuel system has a great impact on flight safety. Therefore, the development of fuel system PHM concept is necessary. This thesis began with an investigation of PHM, then a safety and reliability analysis of fuel system was conducted by using FHA, FMEA and FTA. According to these analyses, fuel temperature diagnosis and prognosis were chosen as a case study to improve the reliability and safety of FW-11. The PHM architecture of fuel temperature had been established. A fuel temperature prediction model was also introduced in this thesis.

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Plumley, Ryan W. „Conceptual Assessment of an Oblique Flying Wing Aircraft Including Control and Trim Characteristics“. Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/31417.

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A method was developed to assist with the understanding of a unique configuration and investigate some of its stability and control attributes. Oblique wing aircraft concepts are a design option that is well understood, but has yet to be used in a production aircraft. Risk involved in choosing such a design can be averted through additional knowledge early in the concept evaluation phase. Analysis tools commonly used in early conceptual level analysis were evaluated for applicability to a non-standard aircraft design such as an oblique flying wing. Many tools used in early analyses make assumptions that are incompatible with the slewed wing configuration of the vehicle. Using a simplified set of tools, an investigation of a unique configuration was done as well as showing that the aircraft could be trimmed at given conditions. Wave drag was investigated to determine benefits for an oblique flying wing. This form of drag was reduced by the distribution of volume afforded by the slewing of the aircraftâ s wing. Once a reasonable concept was developed, aerodynamic conditions were investigated for static stability of the aircraft. Longitudinal and lateral trim were established simultaneously due to its asymmetric nature.
Master of Science

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Mardanpour, Pezhman. „Effects of engine placement and morphing on nonlinear aeroelastic behavior of flying wing aircraft“. Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50268.

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Effects of engine placement on flutter characteristics of a very flexible high-aspect-ratio wing are investigated using the code NATASHA (Nonlinear Aeroelastic Trim And Stability of HALE Aircraft). The analysis was validated against published results for divergence and flutter of swept wings and found to be in excellent agreement with the experimental results of the classical wing of Goland. Moreover, modal frequencies and damping obtained for the Goland wing were found in excellent agreement with published results based on a new continuum-based unsteady aerodynamic formulation. Gravity for this class of wings plays an important role in flutter characteristics. In the absence of aerodynamic and gravitational forces and without an engine, the kinetic energy of the first two modes are calculated. Maximum and minimum flutter speed locations coincide with the area of minimum and maximum kinetic energy of the second bending and torsion modes. Time-dependent dynamic behavior of a turboshaft engine (JetCat SP5) is simulated with a transient engine model and the nonlinear aeroelastic response of the wing to the engine's time-dependent thrust and dynamic excitation is presented. Below the flutter speed, at the wing tip and behind the elastic axis, the impulse engine excitation leads to a stable limit cycle oscillation; and for the ramp kind of excitation, beyond the flutter speed, at 75% span, behind the elastic axis, it produces chaotic oscillation of the wing. Both the excitations above the flutter speed are stabilized, on the inboard portion of the wing. Effects of engine placement and sweep on flutter characteristics of a backswept flying wing resembling the Horten IV are explored using NATASHA. This aircraft exhibits a non-oscillatory yawing instability, expected in aircraft with neither a vertical tail nor yaw control. More important, however, is the presence of a low frequency “body-freedom flutter” mode. The aircraft center of gravity was held fixed during the study, which allowed aircraft controls to trim similarly for each engine location, and minimized flutter speed variations along the inboard span. Maximum flutter speed occurred for engine placement just outboard of 60% span with engine center of gravity forward of the elastic axis. The body-freedom flutter mode was largely unaffected by the engine placement except for cases in which the engine is placed at the wing tip and near the elastic axis. In the absence of engines, aerodynamics, and gravity, a region of minimum kinetic energy density for the first symmetric free-free bending mode is also near the 60% span. A possible relationship between the favorable flutter characteristics obtained by placing the engines at that point and the region of minimum kinetic energy is briefly explored. Effects of multiple engine placement on a similar type of aircraft are studied. The results showed that multiple engine placement increases flutter speed particularly when the engines are placed in the outboard portion of the wing (60% to 70% span), forward of the elastic axis, while the lift to drag ratio is affected negligibly. The behavior of the sub- and supercritical eigenvalues is studied for two cases of engine placement. NATASHA captures a hump body-freedom flutter with low frequency for the clean wing case, which disappears as the engines are placed on the wings. In neither case is there any apparent coalescence between the unstable modes. NATASHA captures other non-oscillatory unstable roots with very small amplitude, apparently originating with flight dynamics. For the clean-wing case, in the absence of aerodynamic and gravitational forces, the regions of minimum kinetic energy density for the first and third bending modes are located around 60% span. For the second mode, this kinetic energy density has local minima around the 20% and 80% span. The regions of minimum kinetic energy of these modes are in agreement with calculations that show a noticeable increase in flutter speed at these regions if engines are placed forward of the elastic axis. High Altitude, Long Endurance (HALE) aircraft can achieve sustained, uninterrupted flight time if they use solar power. Wing morphing of solar powered HALE aircraft can significantly increase solar energy absorbency. An example of the kind of morphing considered in this thesis requires the wings to fold so as to orient a solar panel to be hit more directly by the sun's rays at specific times of the day. In this study solar powered HALE flying wing aircraft are modeled with three beams with lockable hinge connections. Such aircraft are shown to be capable of morphing passively, following the sun by means of aerodynamic forces and engine thrusts. The analysis underlying NATASHA was extended to include the ability to simulate morphing of the aircraft into a “Z” configuration. Because of the “long endurance” feature of HALE aircraft, such morphing needs to be done without relying on actuators and at as near zero energy cost as possible. The emphasis of this study is to substantially demonstrate the processes required to passively morph a flying wing into a Z-shaped configuration and back again.

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Mehr Quellen

Bücher zum Thema "Flying-wing aircraft"

Jack Northrop and the flying wing: The story behind the stealth bomber. New York: Paragon House, 1988.

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Coleman, Ted. Jack Northrop and the Flying Wing: The story behind the Stealth bomber. New York: Paragon House, 1988.

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NASA advanced design program: Design and analysis of a radio-controlled flying wing aircraft. [Worcester, Mass.]: Worcester Polytechnic Institute, 1993.

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Biewener, Andrew A., und Shelia N. Patek, Hrsg. Movement in Air. Oxford University Press, 2018. http://dx.doi.org/10.1093/oso/9780198743156.003.0006.

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Aerial flight involves the same fluid mechanical principles as aquatic locomotion. However, the 800-fold lower density of air compared with water has marked consequences on the mechanisms of aerial locomotion. We examine the forces acting on a flying animal in which these fluid forces can be calculated. We then consider how basic features of the wings and body affect flight forces. Building on this understanding, we examine the power requirements associated with flight as a function of flight speed, based on conventional aerodynamics (i.e. steady airflow past non-oscillating wings, which applies to most engineered aircraft). Gliding flight is explained by steady-state theory and is discussed in this context. However, because flying animals must flap their wings to support weight and overcome drag, non-steady aerodynamic effects come into play. These non-steady aerodynamic effects are revealed by tracking the flow over a moving wing or by the use of robotic models.

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Buchteile zum Thema "Flying-wing aircraft"

Mardanpour, Pezhman, und Dewey H. Hodges. „Passive Morphing of Solar Powered Flying Wing Aircraft“. In Fluid-Structure-Sound Interactions and Control, 351–56. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-40371-2_50.

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Strüber, H., und M. Hepperle. „Aerodynamic Optimisation of a Flying Wing Transport Aircraft“. In New Results in Numerical and Experimental Fluid Mechanics V, 69–76. Berlin, Heidelberg: Springer Berlin Heidelberg, 2006. http://dx.doi.org/10.1007/978-3-540-33287-9_9.

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Wang, Yanxiong, Xiaoping Zhu, Zhou Zhou und Zhuang Shao. „Landing Control System Design for a Flying-Wing Aircraft Based on ADRC“. In Intelligent Robotics and Applications, 340–51. Cham: Springer International Publishing, 2014. http://dx.doi.org/10.1007/978-3-319-13966-1_34.

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Sissingh, G. „Flying Qualities“. In Göttinger Monograph N: German Research and Development on Rotary-Wing Aircraft (1939–1945), 135–73. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2015. http://dx.doi.org/10.2514/5.9781624102738.0135.0174.

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„From Tube and Wing to Flying Wing“. In Advanced Aircraft Design, 121–55. Oxford, UK: John Wiley & Sons, Ltd, 2013. http://dx.doi.org/10.1002/9781118568101.ch5.

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Zenowicz, Kamil, und Wojciech Skarka. „Verification of Flutter Method for the Purposes of Building a Very Flexible Wing Generative Model“. In Advances in Transdisciplinary Engineering. IOS Press, 2020. http://dx.doi.org/10.3233/atde200097.

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First step of aircraft design is calculation of initial parameters, based on assumptions determining flight parameters which designed aircraft should meet. During these calculations, it is possible to pre-detect structure instability called a flutter. These calculations are made based on the geometric parameters assumed in the first conceptual drawings of the flying vehicle. Assumed masses and speeds allow for preliminary analysis of forces acting on the structure. The next step is to determine the displacements and deformations occurring in the structure of the aircraft in different phases of flight and under different conditions. The article presents all the stages of wing analysis for a proposed stratospheric drone with a highly flexible wing structure. This analysis, after integration with CAD software, will allow for the preparation of a comprehensive generative model. The basic assumptions of the designed aircraft are: flight altitude, wings area, very extended or unlimited flight time, approximate flight speed, climbing time, hull parameters, rudder size and placement, wing profile and mass of the structure. These assumptions made it possible to carry out a preliminary analysis of loads, wing pressure distribution, lift force and total resistance force. The goal of the research is to develop a methodology of preliminary flutter analysis which can be easily integrated in the form of calculation backgound for generative model. This methodology has been developed to determine displacements, structure stability and critical vibration frequencies. CAD software after integration with constantly optimizing calculation software will allow the generation of optimal shape and structure rigidity for given initial assumptions.

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„Flying Qualities“. In Flight Testing Of Fixed-Wing Aircraft, 359–63. Reston ,VA: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/5.9781600861840.0359.0363.

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Konferenzberichte zum Thema "Flying-wing aircraft"

Ma, Chao, und Lixin Wang. „Flying-Wing Aircraft Control Allocation“. In 47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-55.

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Rustagi, Vishvendra, Mangal Kothari und Anindya Chatterjee. „Gyroscopic Stabilization of Flying Wing Aircraft“. In 2018 AIAA Atmospheric Flight Mechanics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0530.

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Sineglazov, V. M., und D. P. Karabetsky. „Flying wing design for solar rechargeable aircraft“. In 2013 IEEE 2nd International Conference Actual Problems of Unmanned Air Vehicles Developments (APUAVD). IEEE, 2013. http://dx.doi.org/10.1109/apuavd.2013.6705281.

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Liang, Jianjian, Qing Fei, Bo Wang und Qingbo Geng. „Tailsitter VTOL flying wing aircraft attitude control“. In 2016 31st Youth Academic Annual Conference of Chinese Association of Automation (YAC). IEEE, 2016. http://dx.doi.org/10.1109/yac.2016.7804934.

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Saeed, Tariq, William Graham, Holger Babinsky, J. Eastwood, Cesare Hall, Jerome Jarrett, M. Lone und Keith Seffen. „Conceptual Design for a Laminar Flying Wing Aircraft“. In 27th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-3616.

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Saeed, Tariq, und William Graham. „Conceptual Design for a Laminar-Flying-Wing Aircraft“. In 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-868.

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Xu, Mingxing, Xiaoping Zhu, Zhou Zhou und Bo Zhang. „Flight control system design for a flying-wing aircraft“. In TENCON 2013 - 2013 IEEE Region 10 Conference. IEEE, 2013. http://dx.doi.org/10.1109/tencon.2013.6718805.

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Ferrell, Peter, Brendan Smith, Brandon Stark und YangQuan Chen. „Dynamic flight modeling of a multi-mode flying wing quadrotor aircraft“. In 2013 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2013. http://dx.doi.org/10.1109/icuas.2013.6564714.

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Shin, Hyo-Sang, Antonis F. Antoniadis und Antonios Tsourdos. „Parametric study on efficient formation flying for a blended-wing UAV“. In 2017 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2017. http://dx.doi.org/10.1109/icuas.2017.7991453.

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Huang, Chenyu, und Shaojie Zhang. „A prescribed performance adaptive optimal control scheme for flying-wing aircraft“. In 2020 International Conference on Unmanned Aircraft Systems (ICUAS). IEEE, 2020. http://dx.doi.org/10.1109/icuas48674.2020.9213966.

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Berichte der Organisationen zum Thema "Flying-wing aircraft"

Staab, Janet E., Margaret A. Kolka und Bruce S. Cadarette. Metabolic Rate and Heat Stress Associated With Flying Military Rotary-Wing Aircraft. Fort Belvoir, VA: Defense Technical Information Center, Juni 1998. http://dx.doi.org/10.21236/ada345641.

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Miller, Dorothy, John Wallin und R. C. Wooten. Environmental Assessment Use of Golden Triangle Regional Airport by 14th Flying Training Wing Aircraft. Fort Belvoir, VA: Defense Technical Information Center, März 2004. http://dx.doi.org/10.21236/ada609295.

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