Готові списки джерел за темами / Aerodynamic angle estimation

Добірка наукової літератури з теми "Aerodynamic angle estimation"

Автор: Grafiati

Опубліковано: 14 березня 2023

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Статті в журналах з теми "Aerodynamic angle estimation"

Oh, Gyeongtaek, Jongho Park, Jeongha Park, Hongju Lee, Youdan Kim, Sang-Joon Shin, Jaemyung Ahn, and Sangbum Cho. "Load relief control of launch vehicle using aerodynamic angle estimation." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 8 (March 23, 2017): 1598–605. http://dx.doi.org/10.1177/0954410017699435.

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A nonlinear closed-loop load relief scheme is proposed to reduce the aerodynamic load during the ascent phase of a launch vehicle. The proposed controller is designed based on a back-stepping and sliding-mode control scheme with aerodynamic angle feedback. A hybrid load-relief strategy using the load relief scheme around the period of the maximum dynamic pressure and the traditional minimum-drift scheme during the other period is proposed. An aerodynamic angle estimator is also developed using a Kalman filter for the feedback of the load relief control. Numerical simulation is conducted to demonstrate the performance of the proposed strategy as well as the potential benefits.

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Tang, Wei, and Bi-Feng Song. "Transitional flight equilibrium and performance study for the X-NMRL tail-sitter VTOL MAV." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 8 (August 19, 2018): 3056–77. http://dx.doi.org/10.1177/0954410018794731.

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An investigation on transitional flight equilibrium, performance analysis and parameter impacts is conducted in a conversion corridor, based on the proposed X-NMRL tail-sitter Vertical Takeoff and Landing Micro Air Vehicles (VTOL MAVs). Dependent on a propulsion model, aerodynamic model and physical control model, a nonlinear mathematical transitional model of the vehicle dynamics was constructed with consideration of the velocity, angle of attack, thrust, control surface deflection and pitching angle. The momentum theory and estimation method are applied to simulated propeller slipstream effects on aerodynamics, and an aerodynamic model for all regions of angles of attack and velocities is built. The nonlinear indefinite high-order dynamic model is solved by the improved Newton iteration algorithm. The corridor of the pitching angle or flight-path angle to the velocity reveals that the boundaries are mainly governed by the stalling performance, full throttle thrust and zero thrust, respectively. The performance corridor indicates different performance parameter variations under different conditions of steady climbing, cruising and descending states. Additionally, the performance for a steady transitional strategy can be illustrated to some extent. In terms of the parameter impacts, the increasing max propulsive power, supplied voltage, and decreasing total weight can widen the transitional corridor effectively, and the changes in the aerodynamics will only move the boundaries toward the same direction. These results will benefit transitional vehicle designs and control designs.

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Escobar-Ruiz, Alan G., Omar Lopez-Botello, Luis Reyes-Osorio, Patricia Zambrano-Robledo, Luis Amezquita-Brooks, and Octavio Garcia-Salazar. "Conceptual Design of an Unmanned Fixed-Wing Aerial Vehicle Based on Alternative Energy." International Journal of Aerospace Engineering 2019 (November 14, 2019): 1–13. http://dx.doi.org/10.1155/2019/8104927.

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This paper focuses on the aerodynamics and design of an unmanned aerial vehicle (UAV) based on solar cells as a main power source. The procedure includes three phases: the conceptual design, preliminary design, and a computational fluid dynamics analysis of the vehicle. One of the main disadvantages of an electric UAV is the flight time; in this sense, the challenge is to create an aerodynamic design that can increase the endurance of the UAV. In this research, the flight mission starts with the attempt of the vehicle design to get at the maximum altitude; then, the UAV starts to glide and battery charge recovery is achieved due to the solar cells. A conceptual design is used, and the aerodynamic analysis is focused on a UAV as a gliding vehicle, with the calculations starting with the estimation of weight and aerodynamics and finishing this stage with the best glide angle. In fact, the aerodynamic analysis is obtained for a preliminary design; this step involves the wing, fuselage, and empennage of the UAV. In order to achieve the preliminary design, an estimation of aerodynamic coefficients, along with computational fluid dynamics analysis, is performed.

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Zhang, Jiaming, Qing Li, Nong Cheng, and Bin Liang. "Non-linear flight control for unmanned aerial vehicles using adaptive backstepping based on invariant manifolds." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 227, no. 1 (January 6, 2012): 33–44. http://dx.doi.org/10.1177/0954410011430027.

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A novel adaptive backstepping control scheme based on invariant manifolds for unmanned aerial vehicles in the presence of some uncertainties in the aerodynamic coefficients is presented in this article. This scheme is used for command tracking of the angle of attack, the sideslip angle, and the bank angle of the aircraft. The control law has a modular structure, which consists of a control module and a recently developed non-linear estimator. The estimator is based on invariant manifolds, which allows for prescribed dynamics to be assigned to the estimation error. The adaptive backstepping control law combined with the estimator covers the entire flight envelope and does not require accurate aerodynamic parameters. The stability of the whole closed-loop system is analyzed using the Lyapunov stability theory. The full six-degree-of-freedom non-linear model of a small unmanned aerial vehicle is used to demonstrate the effectiveness of the proposed control law. The numerical simulation result shows that this method can yield satisfying command tracking despite some unknown aerodynamic parameters.

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Korsun, O. N., A. I. Daneko, P. A. Motlich, and M. H. Om. "Estimation of Angles of Attack and Sideslip of Unmanned Aerial Vehicle in the Absence of Aerodynamic Angle Sensors." Mekhatronika, Avtomatizatsiya, Upravlenie 23, no. 5 (May 6, 2022): 274–80. http://dx.doi.org/10.17587/mau.22.274-280.

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A method for estimating aerodynamic angles in the absence of appropriate sensors is proposed, using measurements of three projections of flight speed carried out by the navigation system and the values of the orientation angles. The relevance of the problem being solved is determined by the fact that on unmanned aerial vehicles (UAVs) sensors of aerodynamic angles, that is, angles of attack and slip, are often not installed due to restrictions on dimensions and mass. The proposed method is based on the joint use of mathematical models of aircraft motion, known from flight dynamics, and the theory of parametric identification of dynamic systems. The key factor ensuring the accuracy of the proposed method is the use of very accurate measurements of three UAV velocity projections performed by a satellite navigation system or an inertial navigation system with satellite correction. To account for the influence of wind, parametric identification of three projections of wind speed is provided. Another feature of the method is that instead of the missing aerodynamic angle sensors, it is proposed to use information about the aerodynamic coefficients of the lifting and lateral forces of the UAV. If these coefficients are known with errors, their values are also specified by identification methods. The dimension of the identification problem turns out to be low in the range of small and medium angles of attack when the aerodynamic dependencies are linear. The results of testing the proposed method based on simulation data on the flight test bench of a modern training aircraft for nine different flight modes under conditions of simulating random errors of onboard measurements corresponding to the flight experiment are presented.

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Nowacki, Marcin, and Damian Olejniczak. "Determination of the operational parameters values for Airbus A300-600ST Beluga aircraft on the basis of CFD tests." MATEC Web of Conferences 357 (2022): 02019. http://dx.doi.org/10.1051/matecconf/202235702019.

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The article presents a method for estimating the values of basic operational and aerodynamic parameters of an aircraft. It contains a multistage analysis of CFD test results for the Beluga Airbus A300-600ST model. The first step of the method is to determine the values of aerodynamic parameters such as lift coefficient, drag coefficient, lift force and drag force in specific flight conditions. A comparative analysis of the coefficients of lift and drag force depending on the angle of attack of the aircraft allowed the estimation of the optimal angle of attack of the Airbus A300-600ST Beluga. In the next step, the operational values and the maximum flight ceiling of the aircraft were determined. For this purpose, the results of CFD simulation tests for the optimal angle of attack of the aircraft were used. This article allowed determining the characteristics of the components of aerodynamic force of an airplane depending on the angle of attack, flight altitude and flight speed, determining the optimal angle of attack of the aircraft and calculation of the optimal and maximum flight ceiling values of the Airbus A300-600ST Beluga.

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Morelli, Eugene A. "Real-Time Aerodynamic Parameter Estimation Without Air Flow Angle Measurements." Journal of Aircraft 49, no. 4 (July 2012): 1064–74. http://dx.doi.org/10.2514/1.c031568.

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Chen, D. H., W. H. Wu, J. J. Wang, and Y. Huang. "Investigation on the aerodynamic performance of an ejection seat." Aeronautical Journal 111, no. 1120 (June 2007): 373–80. http://dx.doi.org/10.1017/s0001924000004620.

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Abstract A unique experimental method is used, in combination with numerical calculation and engineering estimation, to study the aerodynamic performance of an ejection seat at M = 0·60, 0·90 and 1·20, angles-of-attack α = 0°~360°, and sideslip angles (β = 0°~–90°. Several basic characteristics of the aerodynamic performance are explored. The normal force of the ejection seat varies in a sinusoidal way and the axial force in a cosinoidal way, with the angle-of-attack. The model is statically unstable longitudinally at most attitude angles and the longitudinal stability could be improved by a stabiliser. These characteristics result from a large low pressure area caused by the leeward separation and the windward high pressure area in the ejection seat flow field, at all α, due to the blunt configuration. A set of engineering calculation formulae is deduced, based on the aerodynamic characteristics of the ejection seat.

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Lerro, Angelo, Manuela Battipede, Piero Gili, and Alberto Brandl. "Aerodynamic angle estimation: comparison between numerical results and operative environment data." CEAS Aeronautical Journal 11, no. 1 (September 4, 2019): 249–62. http://dx.doi.org/10.1007/s13272-019-00417-x.

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Saderla, S., R. Dhayalan, and A. K. Ghosh. "Non-linear aerodynamic modelling of unmanned cropped delta configuration from experimental data." Aeronautical Journal 121, no. 1237 (January 12, 2017): 320–40. http://dx.doi.org/10.1017/aer.2016.124.

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ABSTRACTThe paper presents the aerodynamic characterization of a low-speed unmanned aerial vehicle, with cropped delta planform and rectangular cross section, at and around high angles-of-attack using flight test methods. Since the linear models used for identification from flight data at low and moderate angles of attack become unsuitable for accurate parameter estimation at high angles of attack, a non-linear aerodynamic model has to be considered. Therefore, the Kirchhoff's flow separation model was used to incorporate the non-linearity in the aerodynamic model in terms of flow separation point and stall characteristic parameters. The Maximum Likelihood (ML) and Neural Gauss-Newton (NGN) methods were used to perform the parameter estimation on one set of low angle-of-attack and one set of near-stall flight data. It is evident from the estimates that the NGN method, which does not involve solving equations of motion, performs on a par with the classical ML method. This may be attributed to the reason that NGN method uses a neural network which has been trained by performing point to point mapping of the measured flight data. This feature of NGN method enhances its application over a wider envelope of high angles of attack flight data.

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Більше джерел

Дисертації з теми "Aerodynamic angle estimation"

Jouannet, Christopher. "Model based aircraft design : high angle of attack aerodynamics and weight estimation methods /." Linköping : Dept. of Mechanical Engineering, Linköping University, 2005. http://www.bibl.liu.se/liupubl/disp/disp2005/tek968s.pdf.

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Тези доповідей конференцій з теми "Aerodynamic angle estimation"

McCrink, Matthew, and James W. Gregory. "Aerodynamic Parameter Estimation for Derived Angle-of-Attack Systems." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4061.

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Morelli, Eugene. "Real-Time Aerodynamic Parameter Estimation Without Air Flow Angle Measurements." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-7951.

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Machado, Humberto. "Estimation of Aerodynamic Warming with Non-zero Angle of Attack." In Brazilian Congress of Thermal Sciences and Engineering. ABCM, 2018. http://dx.doi.org/10.26678/abcm.encit2018.cit18-0012.

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Aksu, Arda. "Aerodynamic Parameter Estimation of a Missile Without Wind Angle Measurements." In AIAA Atmospheric Flight Mechanics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2557.

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Brandl, Alberto, Graziano Coppa, and Piero Gili. "Sensitivity Analysis of a Certifiable Synthetic Sensor for Aerodynamic Angle Estimation." In 2020 IEEE 7th International Workshop on Metrology for AeroSpace (MetroAeroSpace). IEEE, 2020. http://dx.doi.org/10.1109/metroaerospace48742.2020.9160045.

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Clark, Christopher J. "A Step Towards an Intelligent Aerodynamic Design Process." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-91637.

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Abstract A new type of section inverse design is presented that offers a 200 times speed up over conventional iterative methods. The method parametrises a blade section in terms of its aerodynamic duty and design style. The duty is defined by the inlet and outlet flow angles, and the Mach and Reynolds numbers at which the blade must operate. The aerodynamic style is represented by a normalised Mach number distribution, parametrised by four control variables. This is found to provide a wide range of desirable loading distributions. For a given style and duty, the method obtains the section geometry and its performance using a radial basis function network. This network is trained, a priori, on a database of designs produced using a conventional inverse design method. The database covers a range of inlet and exit angles for a range of Mach numbers, at each duty aerofoil families are produced varying the four style parameters. During the database production the radial basis function (RBF) network is sequentially refitted and used to accelerate future designs convergence by providing an increasingly better initial guess. Errors in prediction accuracy, of the fully trained system, are calculated by evaluating the obtained geometry and comparing its aerodynamic performance with the intent. The average exit flow angle error was calculated to be 0.074° from the intent. The root-mean-squared error between intent and achieved Mach fraction distributions averaged below 0.0275. The loss prediction featured average errors of 0.012% and hence provides a very accurate method of performance estimation. It is highlighted that not all combinations of aerodynamic duty and design style are compatible. “Infeasible” regions within the design space where the aerodynamic intent is not possible exist. A method is applied to avoid these regions, where section errors are above average, ensuring accurate section generation.

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Figaschewsky, Felix, Arnold Kühhorn, Bernd Beirow, Thomas Giersch, Jens Nipkau, and Ferdinand Meinl. "Simplified Estimation of Aerodynamic Damping for Bladed Rotors: Part 2 — Experimental Validation During Operation." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56458.

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Due to increasing requirements of future engine projects, much effort has been spent on the design of more efficient turbomachinery blades in the recent years. Besides aerodynamic efficiency constraints, these designs need to meet structural criteria ensuring that they are safe and robust with respect to High Cycle Fatigue (HCF). The estimation of the resonant vibration amplitude is done based on the aerodynamic force and the overall damping level. Since, for many applications the contribution of mechanical damping is often rather low compared to the aerodynamic counterpart, the determination of the aerodynamic damping is vital for the estimation of the forced vibration response. This second part is meant to contribute to a simplified computation of the aerodynamic damping during operation by making additional assumptions: The investigated mode family shall not suffer from flutter, has a high reduced frequency and the influence of adjacent blades is negligible. Under these circumstances a simplified approach can be introduced that allows for the computation of the mean value of the aerodynamic damping based on a steady state CFD solution of the regarded stage. It is well known, that the aerodynamic damping of a blade mode family depends on the inter blade phase angle (IBPA) and its direction of propagation, which is not covered by the simplified approach. For higher modes the difference between the minimum and maximum damping is often low and the mean value is a good approximation, whereas for fundamental modes there is often a significant difference. However, it is shown that considering a mistuned vibration response of the rotor, the expected value of the mistuned damping exhibits the mean value of IBPA-dependent aerodynamic damping. CFD simulations of an oscillating airfoil indicate a certain validity range of the simplified approach based on a modified reduced frequency and inlet Mach number, which allows to determine for which industrial applications the approach is most suitable. Finally, this range of validity is verified with experimentally determined overall damping values from strain gauge measurements during operation for 2 different industrial applications, an axial compressor stage of a jet engine and a radial turbine stage of a turbocharger.

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Fujimoto, Keiichiro, and Kozo Fujii. "Compressible Flow Simulations Over Basic Reusable Rocket Configurations." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45427.

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Compressible flow around the basic reusable rocket configurations are numerically simulated by Navier-Stokes computations. The study started with the simulations of Apollo configuration to validate the simulation method by the comparison of the aerodynamic data with NASA’s experiments, and the capability of CFD estimation are discussed. Computed aerodynamic coefficients for the Apollo agreed well with the experiments at subsonic to supersonic flow regime for whole angle of attack range. Then, the effects of the configuration parameters on the aerodynamic characteristics are numerically investigated and clarified in detail. It turns out that the aerodynamic characteristicsismainlyinfluenced by the separating position of the flow, shock wave on the surface and the pressure level behind the body. Large shoulder radius causes the strong Mach number dependency of the aerodynamic characteristics, and large fineness ratio strongly influences to the (CL)max.

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Zheng, Yuqiao, Zhe He, Yongyong Cao, and Chengcheng Zhang. "Optimization of Wind Turbine Blades Considering the Specific Wind." In ASME 2017 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/detc2017-67423.

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When designing a wind turbine blade, the goal is to attain the highest possible power output under specified atmospheric conditions.In this paper,the maximum likelihood estimation method was used to compute the hub height wind speed at 65m mathematical model based on the observation data of He xi Corridor wind at 10m height, taking He xi region of a certain type of 40m blade as an example, based on the Blade Element Momentum Theoty and tip loss, established the blade aerodynamic mathematic model, using the genetic algorithm on the blades. Each section of the chord, twist angle of wind energy utilization coefficient, girder cap layer thickness parameters were optimized, The aerodynamic performance and stress distribution are given out, the results showed that the optimized blade wind energy utilization coefficient is greatly improved and the quality of the blade is significantly reduced. It is suitable for wind the characteristics of the blade design condition performance supper than that of general blade.It provides a theoretical basis for the blade design.

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Hoque, Syed J., and Pramod Kumar. "Theoretical Estimation of Minimum and Maximum Allowable Rotational Speed of Supercritical CO2 Inward Flow Radial Turbine." In ASME 2021 Gas Turbine India Conference. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gtindia2021-76379.

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Abstract Supercritical CO2 inward flow radial turbines necessitate high operating speeds due to the high density of sCO2, especially in sub-MW scale power generation where rotational speeds can be in the range of 50k to 150k rpm. Although designing the turbine at these high rotational speeds is reasonable from the aerodynamic efficiency point of view but generally not practical to operate. A theoretical framework based on 1-D meanline analysis is built to evaluate the minimum and maximum rotational speed limits corresponding to a set of boundary conditions and operating constraints. The results show that minimum allowable speed depends on the inlet velocity triangle (IVT) and is constrained by inlet Mach number, inlet blade height, and inlet flow angle. On the other hand, maximum allowable speed depends on the outlet velocity triangle (OVT) and is constrained by outlet relative Mach number, outlet hub radius, and blade speed. The theoretical models are demonstrated from kilowatt to megawatt power levels, and the results are compared with commercial software and Balje’s Ns-Ds diagram. Although this study is highlighted in the context of supercritical CO2 as the working fluid, in principle, the same models are equally valid for any working fluid.

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