Typical Wing Research Articles

Novel Wing Box Design

Composite materials offer the possibility to tailor a structure to have the desired stiffness distribution. Current aircraft design is yet to fully utilise and exploit these capabilities to improve an aircraft’s performance. In this study, a typical wing box structure is optimised with the aim of achieving a set of target aeroelastic parameters, while minimizing the mass. Focus is given to the model parameterisation to reduce the number of optimisation variables. A number of design variables will be considered and conclusions are drawn based on performance gains. Keywords: Optimisation, Aeroelasticity, Composites, NURBS.

A high-efficiency aerothermoelastic analysis method

In this paper, a high-efficiency aerothermoelastic analysis method based on unified hypersonic lifting surface theory is established. The method adopts a two-way coupling form that couples the structure, aerodynamic force, and aerodynamic thermo and heat conduction. The aerodynamic force is first calculated based on unified hypersonic lifting surface theory, and then the Eckert reference temperature method is used to solve the temperature field, where the transient heat conduction is solved using Fourier’s law, and the modal method is used for the aeroelastic correction. Finally, flutter is analyzed based on the p-k method. The aerothermoelastic behavior of a typical hypersonic low-aspect ratio wing is then analyzed, and the results indicate the following: (1) the combined effects of the aerodynamic load and thermal load both deform the wing, which would increase if the flexibility, size, and flight time of the hypersonic aircraft increase; (2) the effect of heat accumulation should be noted, and therefore, the trajectory parameters should be considered in the design of hypersonic flight vehicles to avoid hazardous conditions, such as flutter.

Performance Evaluation of a Solar Adsorption Refrigeration System with a Wing Type Compound Parabolic Concentrator

Simulation study of a solar adsorption refrigeration system using a wing type compound parabolic concentrator (CPC) is presented. The system consists of the wing type collector set at optimum angles, adsorption bed, a condenser and a refrigerator. The wing type collector captures the solar energy efficiently in the morning and afternoon and provides the effective temperature for a longer period of time compared to that achieved by a linear collector. The objectives of the study were to evaluate the system behavior, the effect of wing length, and to compare the performance of the systems with wing type and linear CPCs. A detailed dynamic simulation model was developed based on mass and energy balance equations. The simulation results show that the system performance with wing type CPC increases by up to 6% in the summer and up to 2% in the winter, compared to the performance with a linear CPC having same collector length. The ice production also increases up to 13% in the summer with the wing type CPC. This shows that the wing type CPC is helpful to increase the performance of the system compared to the linear CPC with the same collector length and without the need for tracking.

3A1-X05 トンボを規範としたはばたき飛翔ロボット : 翼形状が推進力に及ぼす影響(バイオミメティクス・バイオメカトロニクス)

This paper describes effects of the wings for flapping-wing robots on thrust forces. A dragon-fly inspired robot with four wings driven by four-bar link mechanisms was developed. Four types of wings that have various sizes and shapes were prepared for the robot and the thrust forces generated by the wings were measured using a balance. The time-averaged thrust was calculated from the balance of moments. Experimental results show that 20% decrease in wing size causes 40% decrease in thrust force, if the wings have the same shape. Thrust of the wings that have similar shape to dragonfly's wings is 1.2 times larger than that of rectangular wings.

20602 地面効果内にある翼型の動特性に関する研究

Stability of wing moving near ground wall is very complex because of ground effect. We investigate dynamic characteristics of wings in ground effect with pitching motion by wind tunnel experiments. As a result, in the case of lift force type, conditions that Venturi effect does not occur are required for the sake of stable flight near ground. In the case of down force type, when positions of center of pressure are located forward, dynamic down force occurs strongly than static down force, however, certain type of wing leads unstable down force. Wing that center of pressure is located forward and down force is produced stably, is required.

Comparative Study on Viscous and Inviscid Analysis of Partial Cavitating Flow for Low Noise Propeller Design

선박용 프로펠러가 수중에서 빠른 속도로 회전할 때, 날개 표면의 국부적인 압력이 낮아짐에 따라 불가피하게 여러 형태의 공동이 발생한다. 이러한 공동현상은 근본적으로 날개 단면의 기하학적 형상 특성과 수동력학적 운용조건에 의해 결정되며, 결과적으로 선박 프로펠러에서 유기되는 수중방사소음은 공동의 발생특성과 직결된다고 할 수 있다. 따라서 저소음 프로펠러 설계를 위해서는 날개 단면의 형상에 따라 발생하는 공동과 그에 따른 소음특성을 이론 및 실험을 통해 정량적으로 평가할 수 있어야 한다. 본 연구에서는 저소음 프로펠러의 설계단계에서부터 적용이 가능한 부분공동성능 해석법 개발 및 날개단면 형상정보 도출을 목표로 선박용 프로펠러 날개 단면에서 발생하는 부분공동 다상 유동의 비점성 수치해석을 수행하였다. 또한 점성해석 상용프로그램인 FLUENT에서 제공하는 난류 및 공동 모델 조합에 따른 결과를 살펴보았으며, 점성 및 비점성 해석 결과를 비교, 평가 하였다. When a ship propeller having wing type sections rotates at high speed underwater, local pressure on the blade decreases and various types of the cavitation inevitably occur where the local pressure falls below the vapor pressure. Fundamentally characteristics of the cavitation are determined by the shapes of the blade section and their operating conditions. Underwater noise radiated from a ship propeller is directly connected to the occurrence of the cavitation. In order to design low noise propeller, it is preferentially demanded to figure out key features: how the cavity is generated, developed and collapsed and how the effect of viscosity works in the process. In this study, we first perform inviscid analysis of the partial cavity generated on two dimensional hydrofoil. Secondly, viscous analysis using FLUENT with different turbulence and cavitation models are presented. Results from both approaches are also compared and estimated.

Aerodynamic Characteristics of the Ventilated Design for Flapping Wing Micro Air Vehicle

Inspired by superior flight performance of natural flight masters like birds and insects and based on the ventilating flaps that can be opened and closed by the changing air pressure around the wing, a new flapping wing type has been proposed. It is known that the net lift force generated by a solid wing in a flapping cycle is nearly zero. However, for the case of the ventilated wing, results for the net lift force are positive which is due to the effect created by the “ventilation” in reducing negative lift force during the upstroke. The presence of moving flaps can serve as the variable in which, through careful control of the areas, a correlation with the decrease in negative lift can be generated. The corresponding aerodynamic characteristics have been investigated numerically by using different flapping frequencies and forward flight speeds.

Electrospun Nanopaper and its Applications to Microsystems

A new method of preparing Nylon-66 nanopaper using electrospun nonwoven nanofiber and fiber fusing is presented. The fusing temperature for Nylon-66 nanofiber was found to be 190°C. Both carbon and glass fiber reinforced nanopapers were prepared. The unreinforced Nylon-66 nanopaper of areal density 4.5 g/m2 had a modulus and strength of 681 MPa and 92.8 MPa, respectively, while the unfused nanopaper had 430 MPa and 59.3 MPa, respectively. This increase was attributed to fusing of randomly oriented fibers. Several types of insect wings, namely FlyTech dragonfly and Deadalus flight system wings, were fabricated and tested for their flyability. Vibration test was conducted to measure the wing stiffness by matching the measured first natural frequency to the stiffness.

Signal Processing Pushes the Aerospace Envelope [Special Reports

Large, stealthy birds of prey aren't usually associated with the world of signal processing, except perhaps for some owls living near Cambridge, United Kingdom. Owls were renowned for their nearly silent flying ability long before people ever took to the skies. Now, researchers at the University of Cambridge in the United Kingdom are carefully examining the owl's wing structure in an effort to better understand its ability to mitigate noise. The engineers hope to apply the insights they obtain to the design of various types of aircraft wings.

Ergonomic Evaluation of Aircraft Wing Recovering Tasks in General Aviation Maintenance

General aviation (GA) maintenance ergonomics has been a largely understudied area. It is known that risks for musculoskeletal disorders (MSD) occur in other types of maintenance. This paper presents an approach to ergonomic evaluations in a GA maintenance workshop for tasks of recovering aircraft wings. First, a high-level analysis and resulting job/task hierarchy were completed. The task hierarchy suggested that the recovering tasks for three different types of aircraft wings present different musculoskeletal risks to maintainers. Next, ergonomic screening tools were used to evaluate the work performed on each wing type. Finally, based on the screening, more detailed ergonomic analyses were performed. Results indicated that risks to the low back as well as hands and wrists are present in these tasks with risks largely dependent on task duration. Evaluation tools used and suggestions for further research in this work domain are discussed.

Flutter Characteristics of a Morphing Flight Vehicle with Varying Inboard and Outboard Folding Angles

Morphing aircraft capable of varying their wing form can operate efficiently at various flight conditions. However, radical morphing of the aircraft leads to increased structural complexities, resulting in occurrence of dynamic instabilities such as flutter, which can lead to catastrophic events. Therefore, it is of utmost importance to investigate and understand the changes in flutter characteristics of morphing wings, to ensure uncompromised safety and maximum reliability. In this paper, a study on the flutter characteristics of the folding wing type morphing concept is conducted, to examine the effect of changes in folding angles on the flutter speed and flutter frequency. The subsonic aerodynamic theory Doublet Lattice Method (DLM) and p-k method are used, to perform the flutter analysis in MSC.NASTRAN. The present baseline flutter characteristics correspond well with the results from previous study. Furthermore, enhancement of the flutter characteristics of an aluminum folding wing is proposed, by varying the outboard wing folding angle independently of the inboard wing folding angle. It is clearly found that the flutter characteristics are strongly influenced by changes in the inboard/outboard folding angles, and significant improvement in the flutter characteristics of a folding wing can be achieved, by varying its outboard wing folding angle.

Diversity of waterbird in mangrove forest at Sabar Miokre, Supiori Island, Papua

Abstract. Indrianto AP, Budiharjo A, Sugiyarto. 2013. Diversity of waterbird in mangrove forest at sabar miokre village supiori island Papua. Bonorowo Wetlands 3: 50-54. The diversity of waterbirds of an area is affected by habitat conditions. Supiori Island is a large forest area, and along its coastline is covered by mangrove forest vegetation. Supiori Island, located on the north of Papua island and directly adjacent to the Pacific Ocean, has a dense mangrove ecosystem. The purpose of this research was to know the diversity and relationship of waterbirds in Sabar Miokre harbor area, Koiryakam (Koryakam) Village, Supiori District, Papua. The study was conducted in the mangrove forest. The location of many waterbirds determines the observation station; there are four observation posts. The observation is done between 06.00-09.00 am and 03.00-6.00 pm. Species identification involves beak form, short-term beak, wing types, foot shape, and claw form. The observation of waterbirds is done by sampling method, which records all species of waterbirds found in the observation post. Numerical taxonomy determines the relationship. The results showed five species: Phalacrocorax melanoleucos, Egretta sacra, Clytoceyx rex, Egretta alba, and Limosa limosa. The closest relationship was found between E. sacra and E. alba with a 64.28% similarity index, whereas the farthest relationship was found in P. melanoleucos and L. limosa with a similarity index of 21.42%.

The analysis of the flying wing in morphing concept

The combination between the flying wing morphing concept and the use of modern command and control system offers exponential advantages having a leverage effect in the economy and research. The flying wing architecture has the advantage of low cost against efficiency, the morphing of this concept defining the new characteristic frontiers and aerodynamic performances which derive immediately. On designing an unmanned aerial vehicle for a various range of missions, its lifting surface needs to display optimal geometrical features, so that the UAV may maintain the induced drag and the moment coefficient at reasonable levels. The command and control of the lifting surfaces in morphing concept offer characteristics and in-flight performances at a superior level. The limits of the system depend on the reliability of the execution elements and the grade of accuracy for the control laws which are implemented in the calculation module. The paper aims at presenting an analysis regarding the robotic air systems of flying wing type through the aerodynamic analysis and with the help of specific software instruments. The performances and flight qualities depend directly on the geometry of the lifting surface of the aerial vehicle.

RNAI INDUCED WING MODIFICATION IN LEON MUTANT <I>DROSOPHILA</I>: A DEVELOPMENTAL ANALYSIS

The precision of growth of an animal is meticulously regulated by extrinsic and intrinsic factors, with focus on maintenance of organismal homeostasis. The clue to change in physiology or metabolism of an organism, at times can be derived from the changes in phenotypes. In the Drosophila melanogaster model system, GAL 4-overexpressed RNAi driver males (Mini-White Marker), targeted against specific genes, when crossed with Leon mutant (19-2/TM6B) females, yield progeny of different wing types. Different RNAi lines expressing the phenotypes in a gradient of sodden, mid to normal; explains the varying severity of the wing phenotypes. The comparison of flies co-expressed RNAi and Leon mutant with wild type or Leon mutant females; show changes in wing phenotype; in terms of wing venation, Anterior Cortical Vein (ACV) position, Posterior Cortical Vein (PCV) position, bristles on the wing margins and the inter-segmental distance. There is a distinct evidence of both rescue and deterioration phenotype observed at various levels, with the varying levels of RNAi expression in sodden, mid and normal type. A correlational study of these modified wing phenotypes to the physiological and metabolic functionalities; reveals the expression of most of these genes targeted by RNAi, mainly in the brain, heart, thoracic-abdominal ganglion, salivary gland, ovary and testis. Therefore, it can be hypothesized that the Leon mutant can be correlated with the RNAi.

Optimal Flutter Suppression of Nonlinear Typical Wing Section Using Time-Domain Finite Elements Method

AbstractIn this paper, the optimal time-domain finite element method is applied to the flutter suppression of a nonlinear two-dimensional typical wing section. The aeroelastic governing equations are based on the inclusion of stiffness nonlinearity in pitching motion and on the quasi-steady aerodynamics. The flutter suppression problem is formulated as a general optimization problem with equality constraints that are functions of state variables. Using the variational approach, the optimality conditions are derived and the resulting equations are discretized in time-domain. Then, by setting out the discrete equations, a set of nonlinear algebraic equations is generated, and through the Newton–Raphson method, the optimum answer is attained. The numerical results are presented in which the performance of the nonlinear optimal control system designed by the time-domain finite element technique for nonlinear aeroelastic wing sections is illustrated.

Generation of a New Three Dimension Autonomous Chaotic Attractor and its Four Wing Type

In this paper, a new three-dimension (3D) autonomous chaotic system with a nonlinear term in the form of a hyperbolic sine (or cosine) function is reported. Some interesting and complex attractors are obtained. Basic dynamical properties of the new chaotic system are demonstrated in terms of Lyapunov exponents, Poincare mapping, fractal dimension and continuous spectrum. Meanwhile, for further enhancing the complexity of the topological structure of the new chaotic attractors, the attractors are changed from two-wing to four-wing through making axis doubly polarized, theoretically analyzed and numerically simulated. The obtained results clearly show that the chaotic system deserves further detailed investigation.

Synthesis of In-Flight Strains Using Flight Parameters for a Fighter Aircraft

This paper describes the methodology for synthesis of structural strains during flight using recorded flight parameters of a fighter aircraft. This technique can be applied to regenerate data in the event of data loss due to faults in transmission or recording or due to faulty strain gauges. In such a case, flight parameters recorded during the flight can be employed to synthesize the strain response at the structural locations for which the data loss is observed. Artificial neural networks are used in this study to model and synthesize structural strain response using a prescribed set of flight parameters. The approach is demonstrated through the examples of typical wing root and fin root fittings of a fighter aircraft. The neural network model is developed using available data of an instrumented aircraft. The results provide not only the proof-of-concept but also indicate the acceptable efficacy of the model in terms of the accuracy of predictions. Accuracy of predictions is used to identify a more suitable set of flight parameters for efficient implementation of this model. Predicted strain responses for a number of flights are shown to be within 7% of the measured data for the entire flight duration.

RNAi Induced Wing Modification in Leon Mutant Drosophila Females: Exploring the Tissue Specificity and Physiological Interference

The precision of growth of an animal is meticulously regulated by extrinsic and intrinsic factors, with focus on maintenance of organismal homeostasis. The clue to change in physiology or metabolism of an organism, at times, can be derived from the changes in phenotypes. In the Drosophila melanogaster model system, GAL 4-overexpressed RNAi driver males (Mini-White Marker), targeted against specific genes, when crossed with Leon mutant (19-2/TM6B) females, yield progeny of different wing types. Different RNAi lines expressing the phenotypes in a gradient of sodden, mid to normal, explains the varying severity of the wing phenotypes. The comparison of flies co-expressed RNAi and Leon mutant with wild type or Leon mutant females, show changes in wing phenotype; in terms of wing venation, anterior cortical vein (acv) position, posterior cortical vein (pcv) position, bristles on the wing margins and the intersegmental distance. There is a distinct evidence of both rescue and deterioration phenotype observed at various levels, with the varying levels of RNAi expression in sodden, mid and normal type. A correlational study of these modified wing phenotypes to the physiological and metabolic functionalities, reveals the expression of most of these genes targeted by RNAi, mainly in the brain, heart, thoracic-abdominal ganglion, salivary gland, ovary and testis. Therefore, it can be hypothesized that the Leon mutant can be correlated with the RNAi.

Gender Relations and Division of Labour among Prison Officers in Swedish Male Prisons

In Sweden, female prison officers are a long-established fact. Today women make up about 38% of the prison officer work-force. However, the distribution of sexes in the organization is quite uneven between different types of prison wings and units, and at the in-group level there is an informal gendered division of labour going on. The article deals with how a gendered division of labour comes about as a result of socially established motives and notions among prison officers, as well as prisoners, about men's and women's different qualities in performing different types of work tasks. It is based on data from a minor interview study (from 2006), and a 3-year multi-strategic research project containing qualitative case-studies and a nationwide survey (from 2007–2009). The article concludes that a great number of female officers contribute to a more prominent position for the rehabilitative side of prison work. However, the on-going gendered division of labour in and between wings and units is also one important factor behind sub-cultural differentiation and variations in work practices in the prison organization. A more balanced distribution of the sexes would stimulate rehabilitative work and a more unified view of the occupational role throughout the whole organization.

QTW 무인항공기의 종축 비행동역학에 관한 연구

본 논문에서는 고정익항공기와 회전익 항공기의 장점을 결합시킨 신개념 복합형 무인항공기인 QTW(Quad Tilt Wing)의 종축 동특성을 연구한 결과를 기술하였다. 설계된 QTW 무인항공기는 Tandem Wing 형상을 가지며 각 주익의 끝단에는 프로펠러를 구동하는 모터를 장착하였다. 비행역학적 분석을 위해 모멘텀 이론을 이용해 추력을 계산하였으며, 틸트 각도에 따른 프로펠러의 Slip stream에 의한 양력과 항력을 고려한 비선형 모델링을 구축하였다. 또한 트림분석을 통해 설계된 비행체가 적절한 비행속도 대비 틸팅각을 가짐을 보여주었으며, 각 트림 점에서의 성분별 힘을 분석하였다. 각 비행 모드의 선형모델 고유치 분석하여 동적 특성을 분석하였으며 고정익모드로 전환됨에 따라 안정한 부분으로 극점이 이동함을 확인하였다. A Quad Tilt Wing UAV is a new concept hybrid UAV having the advantages of both fixed-wing and rotary-wing aircraft. This paper presents longitudinal flight dynamic characteristics of a Quad Tilt Wing UAV. The designed Quad Tilt Wing UAV is a configuration of a tandem wing type aircraft with an actuating motor and propeller mounted at each wing. Momentum theory is used to calculate the thrust, and nonlinear modeling is performed considering lift and drag generated by slip stream effect of propellers. Also, Force and moment variation at each tilting angle is considered. Static trim on longitudinal axis is analyzed via numerical simulation. Componentwise force contribution was analyzed at each trim mode. Dynamic characteristics were evaluated through eigenvalue analysis for a linear model at each flight mode. It is verified that longitudinal dynamic characteristics are changing from unstable to stable state by continuous transition of dominant poles.