Wing Body Research Articles

Maximizing Lift-to-Drag and Thrust-to-Drag Ratios for Trimmed Hypersonic Vehicles

Ways to maximize the lift-to-drag () and the thrust-to-drag () ratios of hypersonic vehicles are computed using the reduced-order model Michigan-AFRL Scramjet in Vehicle (MASIV). The 84 geometries considered are variations of a generic X-43 for seven chord lengths and three span lengths of the two horizontal stabilizers, and four engine widths. For all cases the vehicle is trimmed for cruise at Mach 8. Computed for each geometry were , angle of attack, deflection angle of the horizontal stabilizer, specific impulse, and engine equivalence ratio. It was found that the “lifting body” design (with small horizontal stabilizers) has a larger than a wing–body design. Large horizontal stabilizers may not be desirable at hypersonic speeds because, while they reduce the angle of attack and reduce the wave drag, the added length of leading edges increases viscous drag. In addition, the optimum acceleration history was computed that minimizes the fuel required for an ascent, for different geometries. Selecting a large dynamic pressure trajectory was found to significantly minimize the fuel required. The scope of the work is limited to aerodynamics, and it does not consider either vehicle stability or control.

Inverse Design Method for Low-Boom Supersonic Transport with Lift Constraint

The low-boom inverse design method is of great interest for the preliminary design of supersonic transport (SST), owing to its good capability of reducing sonic boom at low computational cost. However, the main challenge is how to prescribe an attainable target. This paper proposes an inverse design method using a new target-generation strategy to address this challenge. Unlike existing methods such as the Jones–Seebass–George–Darden method and the mixed-fidelity inverse design method [the Li–Shields–Geiselhart (LSG) method], the proposed method directly parameterizes the near-field overpressure distribution of a reference configuration and minimizes the ground perceived level in decibels (PLdB) predicted by solving the augmented Burgers equation to obtain an optimal target distribution, subject to cruise lift and volume constraints. The proposed method is demonstrated by the Japan Aerospace Exploration Agency (JAXA) Wing Body case, which shows that it mitigates sonic boom under lift constraint and achieves a reduction of 2.07 PLdB more than the LSG method. The proposed method is applied to the low-boom design of a large SST configuration called NPU-T7104, which is close in size to the Tupolev Tu-144; results show that aerodynamic performance is maintained while shock wave coalescence is effectively prevented, and ground-boom intensity is dramatically reduced.

Compact, Consumer Off the Shelf Remotely Piloted Aircraft Systems (COTS-RPAS) in Observing Haliastur indus, the Kali, or Brahminy Kites

The paper demonstrates how small, compact consumer off the shelf remotely piloted aircraft systems (COTS-RPAS) with zoom capability is an effective remote sensing platform in observing Brahminy Kites due to its non-intimidating nature, which arguably minimizes disturbance of the kites. The paper through this remote sensing platform was able to document some key play, cooperative fishing, behaviors of the raptors as well as draft a distribution map of sightings within the raptors range utilizing the compact -COTS-RPAS in tandem with Geographic Information Systems. Use of COTS-RPAS opens a new window or point of view (POV) to avian observational and behavioral studies especially because we are now given horizontal near orthogonal and orthogonal views of the avian species while in flight. Most documentation of birds in flight typically show the underwing and underbody parts but now with the aid of COTS-RPAS we see the upper wing and upper body while in flight

Compact, Consumer Off the Shelf Remotely Piloted Aircraft Systems (COTS-RPAS) in Observing Haliastur indus, the Kali, or Brahminy Kites

The paper demonstrates how small, compact consumer off the shelf remotely piloted aircraft systems (COTS-RPAS) with zoom capability is an effective remote sensing platform in observing Brahminy Kites due to its non-intimidating nature, which arguably minimizes disturbance of the kites. The paper through this remote sensing platform was able to document some play, cooperative fishing, behaviors of the raptors as well as a distribution map of sightings within the raptors range utilizing the compact UAS in tandem with Geographic Information Systems. Use of COTS-RPAS opens a new window to avian observational and behavioral studies especially because we are now given horizontal near orthogonal and orthogonal views of the avian species while in flight. Most documentation of birds in flight typically show the underwing and underbody parts but now with the aid of COTS-RPAS we see the upper wing and upper body while in flight.

Chromosome-level genome of the bean bug Megacopta cribraria in native range, provides insights into adaptation and pest management

Megacopta cribraria, a bean pest causing tremendous economic losses in Asia, was discovered in North America in 2009. Although M. cribraria has become the focus of research on biological invasion and pest management, the lack of genomic resources limits in-depth studies. Here, we report the first chromosome-level genome of M. cribraria using Illumina, PacBio, and Hi-C data. The assembled genome size was 699.65 Mb, with a contig N50 of 1.43 Mb and a scaffold N50 of 109.27 Mb. >97.51 % of bases were successfully anchored to six chromosomes. Through genome annotation, a total of 13,308 coding genes were predicted, 96.3 % of which were successfully accessed function. Expanded gene families were involved in proteolysis, protein metabolism and nitrogen metabolism reflected the underlying genome basis for host adaptation during evolution. Transcriptome analysis revealed different gene expression patterns in antenna, mouthpart, head, leg, wing, and carcass body of the adult M. cribraria, respectively. Moreover, the expression profiles of the odorant receptor genes indicated the potential target genes for pest control. The high-quality chromosome-level genome will benefit further research on the adaptation, evolution, and population genetics of the M. cribraria that will assist in the pest management and tracking the biological invasion routes.

Cyphomyia mexicana sp. nov., a new species of soldier fly (Diptera: Stratiomyidae) in Mexican amber

ABSTRACT A new soldier fly (Diptera: Stratiomyidae) in Mexican amber is described as Cyphomyia mexicana sp. nov. Diagnostic features of the new fossil include a tapering antennal flagellum, with the last three flagellomeres nearly cylindrical in shape, the terminal flagellomere appearing as an arista-like style, the presence of three transverse light bands fused on the posterior portion of the scutum, and the scutellum entirely covered by short and appressed setae. While the new fossil species has the typical wing venation and body shape found in extant Neotropical species of Cyphomyia, the body, wing colour and setal pattern on the thorax and abdomen resembles that of a group of species containing C. wiedemanni Gerstaecker, 1857. The fossil cannot be assigned to any extant or extinct species of Cyphomyia, due to its unique antennae. This is the first fossil species of Cyphomyia in amber and the fourth fossil species of Stratiomyidae from Mexican amber. Cyphomyia rohweri, the only other fossil species assigned to the genus, is more similar to undescribed stratiomyids from Florissan beds, which are not Cyphomyia, so, in this paper, we place C. rohweri as incertae sedis in the Clitellariinae. https://zoobank.org:act:FD826123-076E-45E6-9827-915EB1B8F628

Integration of the athena vortex lattice aerodynamic analysis software into the multivariate design synthesis of a blended wing body aircraft

This paper describes the process of integrating the Athena Vortex Lattice aerodynamics solver into a conceptual design environment for the multivariate design synthesis and optimisation of a Blended Wing Body (BWB) Aircraft. The work is derived from a PhD study, by one of the authors, which developed a design methodology for the conceptual design synthesis, analysis and optimisation of a BWB aircraft. This research was driven by the desire to utilise proven aerodynamic solvers, written in legacy codes, in modern computational design environments in order to improve the accuracy and fidelity in the design of novel aircraft configurations. The Athena Vortex Lattice code is a legacy code written in the FORTRAN programming language and developed at the Massachusetts Institute of Technology by Mark Drela while the multivariate conceptual design synthesis and optimisation was implemented in JAVA object oriented programming tool. The result from this study is the successful integration of the AVL software into the JAVA programming environment for the multivariate design synthesis optimisation of the BWB without loss of accuracy. The successful integration of these codes permit a more accurate design synthesis, analysis and optimisation of the novel aircraft configuration in the absence of a tailor-made and realistic empirical aerodynamic analysis model for the BWB Aircraft. Additionally, this research enables the automation of the design process and the accomplishment of the multivariate optimisation.

Design, Computational Aerodynamic, Aerostructural, and Control Stability Investigations of VTOL-Configured Hybrid Blended Wing Body-Based Unmanned Aerial Vehicle for Intruder Inspections

Unmanned aerial vehicles (UAVs) are gaining in popularity and sophistication in today’s modern world. UAVs are now available in a wide range of configurations. A UAV’s many applications include aerial photography and videography and target tracking. The upward-pointing propellers of some modern fixed-wing UAVs make it possible for them to take off and land vertically. Surveillance and intruder inspections are two areas where the blended wing body (BWB) configuration shines. This is because its weight is spread uniformly throughout the body, its radar signal is weaker than that of alternative configurations, and there is a relatively small amount of interference with its movement. With common design factors in mind, like vertical takeoff and landing, aerodynamic drag, and fundamental wing stability, the optimal BWB plan form for surveillance is designed. CATIA is used to finish the conceptual design of the BWB-based UAV. A fluid-structure interaction (FSI) study is carried out after the model has been examined in ANSYS Fluent. The UAV’s responsiveness is improved through simulation in the MATLAB environment after a proportional-integral-derivative-type altitude controller was developed. The results demonstrate that providing the UAV with an altitude instruction enhances its performance. Given the flexibility of the suggested BWB UAV’s design, we have decided to limit its maximum forward speed to 75 m/s and its maximum rate of vertical ascension to 50 m/s. Rapid BWB UAVs like the one seen here are quite helpful in dangerous situations.

"Biology of the invasive shell lerp psyllid, Spondyliaspis cf. plicatuloides (Froggatt) (Hemiptera: Aphalaridae)"

Spondyliaspis cf. plicatuloides (Froggatt) (Hemiptera: Aphalaridae) is native to Australia but was first detected outside its native range in 2014, in South Africa. It feeds on eucalypt species and thus has the potential to become a pest in commercial Eucalyptus plantations. Information on the basic biology of this insect, which is important for the development of surveillance and management strategies, is lacking. To investigate the life cycle and general biology of S. plicatuloides, the psyllid was reared under controlled glasshouse conditions on potted red-flowering gum, Corymbia ficifolia. The egg incubation period, number of nymphal instars and their developmental time, adult fecundity, adult longevity and duration of the life cycle were determined. The major diagnostic features used to differentiate the five nymphal instars were the number of antennal segments, wing pad development and body length. Females reached reproductive maturity 2.3 ± 0.47 (mean ± SD) days after eclosion and laid 16.2 ± 3.9 (mean ± SD) eggs on average. Reproduction was sexual. The first nymphal instar took 10.7 ± 1.2 (mean ± SD) days to hatch from the egg. The nymphal instars completed their development in 22.6 ± 1.4 (mean ± SD) days under the brown scalloped shelters they secrete. The insect's total life cycle lasted 37.37 ± 1.17 (mean ± SD) days from egg to adult death. Males and females lifespan is also reported. The study provides the first information on the basic biology of S. cf. plicatuloides that will be useful for future studies on surveillance and management strategies.

Evaluation of flyover auralisations of today's and future long-range aircraft concepts

The European research project ARTEM (Aircraft noise Reduction Technologies and related Environmental iMpact) develops innovative aircraft noise reduction technologies such as advanced engine fan lining, metamaterials and low-noise high-lift systems applied to a vehicle with enhanced shielding of the engine noise, namely, a blended wing body. Using aircraft flyover auralisation in laboratory listening experiments, such future technologies can be evaluated with respect to human sound perception. To assess the reliability of such perception-based evaluations, the simulation chain should be validated with existing aircraft flyovers. This contribution presents a systematic and rigorous hierarchical validation of auralisations of current jet aircraft using field recordings. Uncertainty in the source modelling is considered by using two different prediction tools for partial sound sources. In addition to comparing computed noise indicators, a psychoacoustic validation is done in laboratory listening experiments with a 3D loudspeaker array. The validation comprises three levels: (i) direct comparison of auralisations with recordings to study the identifiability of auralisations, (ii) ranking of auralisations and recordings regarding plausibility, and (iii) subjective annoyance ratings to test whether auralisations and recordings differ with respect to noise effects. Further, first results on the comparison of a future concept with a current aircraft are presented.

Flyover noise evaluation of low-noise technologies applied to a blended wing body aircraft

In the frame of the European research project ARTEM (Aircraft noise Reduction Technologies and related Environmental iMpact), new aircraft architectures and alternative propulsion systems, e.g. Blended Wing Body (BWB) and geared turbofan engine concept, are investigated, as well as innovative noise reduction technologies such as metamaterials and low noise high-lift device systems. A noise impact assessment has been performed on a long-haul BWB concept developed by Roma Tre University, using the System Noise Prediction Tools of ONERA (CARMEN) and DLR (PANAM). First, shielding effects on the main noise sources are discussed, through installation effects hemi-spheres at chosen frequencies around the aircraft. Based on the shielding assessment, detailed take-off and landing procedures are simulated for several aircraft configurations. Two motorisations of the BWB are evaluated (BPR 8 and BPR 12), provided by RWTH Aachen. Finally, the most promising low noise technologies developed in the frame of ARTEM are applied, and their impact on noise levels on the ground is discussed. It can be demonstrated how the specific aircraft configuration, the engine type and the additional low-noise technology result in a significant overall noise reduction. A joint conference paper presents flyover auralisations based on these noise emission calculations.

Thrust Vectoring Control of a Novel Tilt-Rotor UAV Based on Backstepping Sliding Model Method.

In this paper, a control method of a novel tilt-rotor UAV with a blended wing body layout is studied. The novel UAV is capable of vertical take-off and landing and has strong stealth capabilities that can be applied to carrier-borne reconnaissance aircraft. However, the high aspect ratio of blended wing body UAVs leads to a wingtip or oar-tip touchdown problem when adopting the conventional position-attitude control (CPAC) scheme with a large crosswind disturbance. Moreover, when the UAV is subject to interference during reconnaissance, aerial photography, and landing missions, the conventional scheme cannot provide both attitude stability and track accuracy. First, a direct thrust vectoring control (DTVC) scheme is proposed. The control authority of the rotor tilt mechanism was added to enable the decoupling of the attitude and trajectory and to improve the response rate and response bandwidth of the flight trajectory. Second, considering the problems of strong couplings and parameter uncertainties and the nonlinear features and mismatched perturbations that are inevitable in the tilt-rotor, we designed a robust UAV controller based on the backstepping sliding mode control method and determined the stability of the control system through the Lyapunov function. Finally, in the case of crosswire interference during vertical takeoff and landing and the aerial photography missions of the UAV, the numerical simulation of the CPAC scheme and the DTVC scheme was carried out, respectively, and the Monte Carlo random test method was introduced to conduct the statistical test of the landing accuracy. The simulation results show that the DTVC scheme improves the landing accuracy and speed compared to the CAPC scheme and decouples the position control loop from the attitude control loop, finally enabling the UAV to complete the flight control in the VTOL phase.

A Modification to the Enhanced Correction Factor Technique for the Subsonic Wing–Body Interference Model

In this work, the enhanced correction factor technique (ECFT) is modified for a subsonic wing–body interference model, which can consider the forces on both the lifting boxes and the body elements of an idealized airplane, termed the advanced ECFT method. A passenger aircraft model is chosen as the simulation model, and the longitudinal static aeroelasticity at the transonic situation for two-degree freedom, including the α (angle of attack) degree and ϕ (angle of horizontal tail) degree, is simulated in this paper. The corresponding CFD results are used to correct the aerodynamic influence coefficients (AIC) matrix, which is then simulated by MSC.NASTRAN. The pressure distribution results of different aircraft components received by the advanced ECFT method indicate that it is suitable for the subsonic wing–body interference model. Compared with the uncorrected linear method and the diagonal corrected method, it is generally more consistent with the CFD/CSD coupling method, not only for the lifting boxes, but also for the body elements. In addition, the aerodynamic derivative results also show good agreement with the flight test data, which solidly verifies the advance ECFT method.

Relationships between environmental stressors and Cliff Swallow (Petrochelidon pyrrhonota) feather coloration and colony size

Cliff Swallows (Petrochelidon pyrrhonota) are aerial insectivores that experience mortality from vehicle collisions because they often nest and hunt under bridges and road culverts. Individual traits that may convey social information, such as body condition, or feather reflectance, may be associated with better coping around cars and other environmental stressors. Cliff swallow colony size may also be affected by environmental stressors. Our objective is to determine if proximity to roads and water level near the colony were related to wing length, body condition, colony size, and feather coloration in Cliff Swallows. We will do this by taking feather samples and measuring reflectance, and taking other body condition measurements, in addition to measuring colonies’ proximity to roads and level of water near the colonies’ locations.

Research on Rigid–Elastic Coupling Flight Dynamics of Hybrid Wing Body Based on a Multidiscipline Co-Simulation

Due to the special aerodynamic layout and mass distribution, the natural frequency differences between the hybrid wing body (HWB)’s rigid-body motion modes and the fuselage structure elastic modes are smaller compared to conventional aircraft, resulting in the disappearance of the decoupling relationship between the HWB’s rigid-body motion and the elastic motion of the airframe structure. For the above reason, the traditional analysis approach based on the rigid-body assumption is no longer applicable when analyzing the flight dynamics of an HWB aircraft, and a shift must be made to an analysis method that takes into account aeroelastic effects. Therefore, in this paper, a time-domain co-simulation program combining the computational fluid dynamics (CFD) method with computational structure dynamics (CSD) and rigid-body dynamics (RBD) is developed to investigate the effect of a rigid–elastic coupling effect on the flight dynamics of the HWB and this co-simulation method is more advantageous in the calculation of unsteady aerodynamics compared to existing methods of rigid–elastic coupling dynamics analysis. By means of the co-simulation technology, this paper completed a series of simulations, based on which the influence of rigid–elastic coupling effect on the short-period dynamic characteristics of aircraft was studied.

A Fast Aerodynamic Model for Aircraft Multidisciplinary Design and Optimization Process

A multidisciplinary design analysis and optimization process is developed at ONERA for the design of tube and wing and blended wing–body aircraft configurations. This process is composed of different disciplinary modules (geometry, propulsion, aerodynamics, structure, handling qualities and flight mission), and the overall process considers different fidelity levels for these modules at each step of the design process. This article describes the low-fidelity aerodynamic module used during the preliminary design optimization process. Analytical formulations retained for lift and drag components are presented in the first part. Then, the performances estimated by the aerodynamic module on some reference configurations are compared with both numerical and experimental data, showing a quite good agreement for both tube and wing and blended wing–body configurations not only for global performance but also for individual drag components.

Investigation of Improvement Design on Aileron Surface Flow State of High Lift Configuration in BWB

The aileron is one of the most important tools for adjusting the roll attitude of the aircraft, but the surface flow state of the aileron is likely to be affected by high-lift devices. In this paper, by using computational fluid dynamics (CFD) simulations and wind tunnel tests, the Krueger flap effects on the surface flow state of ailerons in a typical blended wing body civil aircraft were investigated. In order to increase the lift, deflecting the Krueger flap makes the flow separation occur on the aileron surface of BWB civil aircraft. This way of the surface stall that the flow separation in the aileron zone first appears at the wing tip rather than at the wing root is unreasonable for civil aircraft. For the above problem, a sensitivity analysis of the design parameters of the Krueger flaps was carried out. The results indicate that the angle of the outboard Krueger flap mainly affects the flow separation of the ailerons. Its length affects the pitch moment tremendously, while its width slot affects the pitch moment slightly. Finally, the design principles of the BWB Krueger flap for the improvement aileron surface flow state were proposed, and the redesign of the BWB high lift configuration significantly improved the flow state of the aileron zone at a minimal cost of aerodynamic characteristics without losing the existing great aerodynamic performance.

Study of Modeling and Optimal Take-Off Scheme for a Novel Tilt-Rotor UAV.

The optimal trajectory planning for a novel tilt-rotor unmanned aerial vehicle (UAV) in different take-off schemes was studied. A novel tilt-rotor UAV that possesses characteristics of both tilt-rotors and a blended wing body is introduced. The aerodynamic modeling of the rotor based on blade element momentum theory (BEMT) is established. An analytical method for determining the taking-off envelope of tilt angle versus airspeed is presented. A novel takeoff-tilting scheme, namely tilting take-off (TTO), is developed, and its optimal trajectory is designed based on the direct collocation method. Parameters such as the rotor thrust, tilt angle of rotor and angle of attack are chosen as control variables, and the forward velocity, vertical velocity and altitude are selected as state variables. The time and the energy consumption are considered in the performance optimization indexes. The optimal trajectories of the TTO scheme and other conventional schemes including vertical take-off (VTO) and short take-off (STO) are compared and analyzed. Simulation results indicate that the TTO scheme consumes 47 percent less time and 75 percent less energy than the VTO scheme. Moreover, with minor differences in time and energy consumption compared to the STO scheme, but without the need for sliding distance, TTO is the optimal take-off scheme to satisfy the flight constraints of a novel tilt-rotor UAV.

Aeropropulsive assessment of engine installation at cruise for UHBPR turbofan with body force fan modelling

The overall propulsive performance of an aircraft with podded nacelles depends on the interaction occurring between the wing body and the propulsor. With the tight installation required for Ultra-High Bypass Ratio (UHBPR) turbofans, the engine and airframe flows are more coupled, resulting in a mutual interference that can affect the working condition of the turbomachinery and the wing flow. In the paper, we employ a fully coupled fan stage model based on a body force method to evaluate the performance of an ultra-high bypass ratio turbofan in a nominal and closely-coupled installation position, along the cruise phase of a long-haul flight at Mach number 0.85. By comparing the results obtained with a standard powered-on representation based on one-dimensional static boundary conditions, we assess the effect of the engine/airframe coupling on the aerodynamics and propulsive forces. The major differences occur on the discharge flow, on the internal fan nozzle duct and on the jet/wing interaction, due to the nonuniform fan stage outlet status in the body force simulations. The net vehicle force deviates from 1% to 1.6%, according to the position and the cruise phase. The sensitivity of the propulsive forces to the change of installation position, instead, is in general consistent for the two methods. The discrepancy can be much larger if the 1D boundary conditions are not corrected for true engine operating points arising under installation, exceeding 8% in the tighter assembly for the net vehicle force.

물까치(Cyanopica cyanus)의 형태학적 측정에 의한 성 판별

Most sexually monomorphic species, including the family Corvidae, are visually indistinguishing in field investigations. We investigated intersexaul morphological differences of the Azure-winged magpie (Cyanopica cyanus). We caught 86 adults (67 males, 14 females, and 5 unidentified), measured their morphological characteristics (head-bill length, bill length, maximum and minimum wing length, tarsus length, body length, tail length, and weight), and collected blood samples. Sex was determined by PCR amplification using the previously used P2/P8 (Griffiths et al. 1998) primers. Statistical analysis was used to compare morphological differences between sexes. Males were longer in body length and maximum wing length, and discriminant function analysis using the two variables showed the sex was distinguished with an accuracy of 71.7%. We discussed the significance of the two variables in the monomorphic Azure-winged magpies.