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Relevant bibliographies by topics / Slender Missile

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Academic literature on the topic 'Slender Missile'

Author: Grafiati

Published: 4 June 2021

Last updated: 9 February 2022

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Journal articles on the topic "Slender Missile"

1

Kumar, Priyank. "Rolling Moment of Slender Body at High Incidence for Air to Air Missile Rocket Applications." Defence Science Journal 70, no. 1 (2020): 18–22. http://dx.doi.org/10.14429/dsj.70.13612.

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Measurements of moments were carried out on a slender body having a pointed forebody at lower velocities. The slender body had an ogive nose shape and an overall length to diameter ratio of 16. The angle of incidence was varied from low to moderate angles of attack in the pitch plane. The main objective of the present investigation was to measure the rolling moments on the slender body with and without the control technique. The side force was reduced using a rectangular cross-sectioned ringplaced suitably on the body, however, the slender body was found to experience rolling moments which may

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Wu, Lei, Changchuan Xie, and Chao Yang. "Aeroelastic Stability of a Slender Missile with Constant Thrust." Procedia Engineering 31 (2012): 128–35. http://dx.doi.org/10.1016/j.proeng.2012.01.1002.

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3

Wong, F. C., C. A. Rabbath, N. Hamel, et al. "SHAPE MEMORY ALLOY ACTUATED MICRO-FLOW EFFECTORS FOR VORTEX MANIPULATION." Transactions of the Canadian Society for Mechanical Engineering 31, no. 1 (2007): 19–38. http://dx.doi.org/10.1139/tcsme-2007-0002.

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Smart structures are seen as an enabling technology for designing innovative control actuation systems for future missiles. In this study, the feasibility of employing shape memory alloy (SMA)-actuated micro-flow effectors to control the vortex shedding behaviour that produces side forces on slender body missiles is examined. Supersonic wind tunnel tests were performed on a slender finless missile equipped with static micro-flow effectors on a conical nose to determine suitable configurations that could generate significant side forces. Shape memory alloy actuators for the flow effector were d

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4

Singh, Manak, and V. B. Tawakley. "Non-Slender Missile Geometries of Minimum Ballistic Factor via Calculus of Variations." Defence Science Journal 36, no. 1 (1986): 63–70. http://dx.doi.org/10.14429/dsj.36.5962.

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Tahani, M., M. Masdari, and M. Kazemi. "Aerodynamic performance improvement of a canard control missile." Aircraft Engineering and Aerospace Technology 89, no. 6 (2017): 871–78. http://dx.doi.org/10.1108/aeat-01-2016-0019.

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Purpose This paper aims to analyze the influence of the changings in geometrical parameters on the aerodynamic performance of the control canard projectiles. Design/methodology/approach Because of the mentioned point, the range of projectiles increment has a considerable importance, and the design algorithm of a control canard projectile was first written. Then, were studied the effects of canard geometric parameters such as aspect ratio, taper ratio and deflectable nose on lift to drag coefficient ratio, static margin based on the slender body theory and cross section flow. Findings The code

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BRYSON, ARTHUR E. "Stability Derivatives for a Slender Missile with Application to a Wing-Body-Vertical-Tail Configuration." Journal of Spacecraft and Rockets 40, no. 6 (2003): 1048–59. http://dx.doi.org/10.2514/2.7050.

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Bryson, JR., Arthur E. "Stability Derivatives for a Slender Missile with Application to a Wing-Body-Vertical-Tail Configuration." Journal of Spacecraft and Rockets 40, no. 6 (2003): 1048–59. http://dx.doi.org/10.2514/1.10864.

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Geng, Xi, Zhiwei Shi, and Keming Cheng. "Experimental investigation of roll characteristics of a cruciform-finned slender body." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 4 (2016): 698–712. http://dx.doi.org/10.1177/0954410016641450.

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Next-generation aircraft and missile are required to have extreme maneuverability, which should maintain stability at high angle of attack. However, the unsteady flow field surrounding the air vehicle would affect the aerodynamics loads and induce unwanted nonlinear motions, of which the rolling motions are usually generated. In order to investigate the unsteady rolling characteristics of a cruciform-finned slender body, the free-to-roll and force measurement tests including particle image velocimetry measurement have been conducted comprehensively. Different types of rolling motion, trimming

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Jeans, Tiger L., A. Gordon L. Holloway, George D. Watt, and Andrew G. Gerber. "A Force Estimation Method for Viscous Separated Flow Over Slender Axisymmetric Bodies With Tapered Tails." Journal of Ship Research 54, no. 01 (2010): 53–67. http://dx.doi.org/10.5957/jsr.2010.54.1.53.

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A new impulse method for modeling the normal force distributions along slender axisymmetric bodies with tapered tails is presented. This method is based on a decomposition of the hydrodynamic impulse along the body into an inviscid, profile-dependent component and a viscous, profile-independent component. It is applicable to separated flows up to 30 deg of incidence. Model results for the normal force distributions, total normal force, and total moment on axisymmetric streamlined bodies with tapered tails are compared with computational fluid dynamics (CFD) simulations and experimental data up

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Verhaegen, Anatole, and Rafał Żbikowski. "Aeroservoelastic modelling and control of a slender anti-air missile for active damping of longitudinal bending vibrations." Aerospace Science and Technology 66 (July 2017): 20–27. http://dx.doi.org/10.1016/j.ast.2017.03.001.

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Dissertations / Theses on the topic "Slender Missile"

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Kennaugh, Andrew. "An investigation of the flow around slender bodies at high incidence." Thesis, University of Manchester, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.329329.

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2

Akgul, Mehmet. "Static Aeroelastic Analysis Of A Generic Slender Missile Using A Loosely Coupled Fluid Structure Interaction Method." Master's thesis, METU, 2012. http://etd.lib.metu.edu.tr/upload/12614139/index.pdf.

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In this thesis, a loosely coupled Fluid-Structure Interaction (FSI) analysis method is developed for the solution of steady state missile/rocket aeroelastic problems. FLUENT is used as the Computational Fluid Dynamics (CFD) tool to solve Euler equations whereas ANSYS is used as the Computational Structural Dynamics (CSD) tool to solve linear structural problem. The use of two different solvers requires exchanging data between fluid and structure domains at each iteration step. Kriging interpolation method is employed for the data transfer between non-coincident fluid and structure grids. For m

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Baskut, Erkut. "Development Of A Closely Coupled Approach For Solution Of Static And Dynamic Aeroelastic Problems." Master's thesis, METU, 2010. http://etd.lib.metu.edu.tr/upload/3/12612128/index.pdf.

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In this thesis a fluid-structure coupling procedure which consists of a commercial flow solver, FLUENT, a finite element structural solver, MSC/NASTRAN, and the coupling interface between the two disciplines is developed in order to solve static and dynamic aeroelastic problems. The flow solver relies on inviscid Euler equations with finite volume discretization. In order to perform faster computations, multiple processors are parallelized. Closely coupled approach is used to solve the coupled field aeroelastic problems. For static aeroelastic analysis Euler equations and elastic linear struct

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Saravanan, S. "Experimental Investigation Of The Effect Of Nose Cavity On The Aerothermodynamics Of The Missile Shaped Bodies Flying At Hypersonic Mach Numbers." Thesis, 2007. http://hdl.handle.net/2005/694.

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Hypersonic vehicles are exposed to severe heating loads during their flight in the atmosphere. In order to minimize the heating problem, a variety of cooling techniques are presently available for hypersonic blunt bodies. Introduction of a forward-facing cavity in the nose tip of a blunt body configuration of hypersonic vehicle is one of the most simple and attractive methods of reducing the convective heating rates on such a vehicle. In addition to aerodynamic heating, the overall drag force experienced by vehicles flying at hypersonic speeds is predominate due to formation of strong shock wa

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Books on the topic "Slender Missile"

1

Crouzet, Edward. Slender thread: Origins and history of the Benedictine Mission in Bungay 1657-2007. Downside Abbey Books, 2007.

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Book chapters on the topic "Slender Missile"

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Weinand, K., K. J. Dahlem, R. Höld, D. Stern, B. Sauerwein, and F. Seiler. "Analysis of Jet Thruster Control Effectiveness and the Interaction with Aerodynamic Surfaces for a Slender Cylindrical Missile." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14243-7_47.

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Conference papers on the topic "Slender Missile"

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HEMSCH, M. "Nonlinear applications of slender-body theory to missile aerodynamics." In 12th Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1775.

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2

Xu, Yun, Changchuan Xie, and Chao Yang. "Effect of Thrust on Aeroelastic Stability of a Slender Missile." In 49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference
16th AIAA/ASME/AHS Adaptive Structures Conference
10t. American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-2022.

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3

GATES, ROGER, GERALD WINCHENBACH, JOHN CIPOLLA, and MARK FISCHER. "Aerodynamic test and analysis of a slender generic missile configuration." In 16th Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-3368.

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4

Howerton, Walter, and Wayne Hathaway. "Aerodynamic test and analysis of a slender grooved-body, generic missile configuration." In 19th Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-3498.

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5

Arevalo-Campillos, M. A., S. Tuling, L. Parras, C. del Pino, and L. Dala. "Experimental Study of Very Low Aspect Ratio Wings in Slender Bodies." In ASME 2012 11th Biennial Conference on Engineering Systems Design and Analysis. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/esda2012-82332.

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The dynamics of very low aspect ratio wings (or strakes) vortices in slender bodies are complex due to the interaction of the shed vortex sheet and the body vortex. For missiles at supersonic speeds these interactions are not easily predicted using engineering level tools. To shed some new light onto this problem, an experimental study in a water channel for moderate Reynolds number (Re = 1000) was performed for a 19D body and strake configuration with strakes having a span to body diameter ratio of 1.25. Comparisons to numerical simulations in supersonic flow are also performed. Flow visualis

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6

Birch, Trevor, Jerry Allen, and Floyd Wilcox, Jr. "Force, surface pressure and flowfield measurements on slender missile configurations at supersonic speeds." In 18th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4207.

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Wilcox, F., T. Birch, and J. Allen. "Force, Surface Pressure, and Flowfield Measurements on a Slender Missile Configuration with Square Cross-Section at Supersonic Speeds." In 22nd Applied Aerodynamics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-5451.

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Wang, Yu, Wei Tang, Mao Cui, and Gongping Zhang. "Aeroservoelastic Modeling and Stability Analysis." In ASME 2019 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/detc2019-97773.

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Abstract It is well known that the elasticity has a great impact on the performance of the slender missile. In this paper, the dynamics of the flexible missile is regarded as a combination of the rigid motion and the elastic vibration. To simplify the modeling, we focus on the influence of the rigid motion on the elastic vibration, instead of completely considering the coupling between rigidity and elasticity. Based on certain assumptions, the longitudinal models of the rigid and elastic missile are derived, and the model of a typical three-loop acceleration autopilot is designed in accordance

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9

Rambach, Jean-Mathieu. "Dynamic Motion of RC Beams and One-Way Slabs Impacted by a Missile at Medium Velocity: Models for Spreadsheet Application." In 18th International Conference on Nuclear Engineering. ASMEDC, 2010. http://dx.doi.org/10.1115/icone18-29087.

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This paper deals with the simulation of the motion of a one-span slender rectilinear RC beam or a thin one-way RC rectangular slab when impacted by a missile, within and beyond the elastic domain, up to a maximal displacement equal to the height of the section. The loading is variable in time and in space and the supporting conditions at each extremity are either of simply resting type or of clamping type. The equation of motion for each beam segment is expressed, through finite differences method, by relations between velocity and flexural moment that are decomposed on the basis of the first

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PLATUS, D. "Aeroelastic stability of slender, spinning missiles." In 16th Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-3393.

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