Pub Date : 2007-02-01DOI: 10.1017/S000192400008684X
Riti Singh
{"title":"Elements of Propulsion: Gas Turbines and Rockets – Second edition J.D. Mattingly American Institute of Aeronautics and Astronautics, 1801 Alexander Bell Drive, Suite 500, Reston, VA 20191-4344, USA. 2006. 867pp. Illustrated. $79.95 (AIAA members), $109.95 (non-members). ISBN 1-56347-779-3.","authors":"Riti Singh","doi":"10.1017/S000192400008684X","DOIUrl":"https://doi.org/10.1017/S000192400008684X","url":null,"abstract":"","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2007-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79481505","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2006-06-01DOI: 10.1017/S0001924000086711
Sondipon Adhikari
{"title":"Dynamics of Multibody Systems – Third edition A.A. Shabana Cambridge University Press, The Edinburgh Building, Shaftesbury Road, Cambridge, CB2 2RU, UK. 2005. 374pp, Illustrated. £45. ISBN 0-521-85011-8.","authors":"Sondipon Adhikari","doi":"10.1017/S0001924000086711","DOIUrl":"https://doi.org/10.1017/S0001924000086711","url":null,"abstract":"","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2006-06-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"79907353","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2005-11-01DOI: 10.1017/S0001924000086516
H. Harrison
{"title":"Elements of Continuum Mechanics R.C. Batra American Institute of Aeronautics and Astronautics, 1801 Alexander Bell Drive, Reston, VA 20191, USA. 2005. 325pp. Illustrated. $54.95 (AIAA members); $79.95 (non-members). ISBN 1-56347-699-1.","authors":"H. Harrison","doi":"10.1017/S0001924000086516","DOIUrl":"https://doi.org/10.1017/S0001924000086516","url":null,"abstract":"","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2005-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1017/S0001924000086516","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"57255405","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2003-01-01DOI: 10.1017/S0001924000011805
B. V. van Oudheusden
Abstract The method of matched asymptotic expansions has been applied to analyse the asymptotic structure of the incompressible turbulent attachment-line boundary layer at large Reynolds numbers. Inner and outer solutions were obtained that give the ‘wall-unit’ and ‘velocity-defect’ represention of both the spanwise and chordwise velocity profiles. The predictions from the theory agree with experimental and DNS data in the range of fully developed turbulence.
{"title":"The asymptotic structure of the turbulent attachment-line boundary layer","authors":"B. V. van Oudheusden","doi":"10.1017/S0001924000011805","DOIUrl":"https://doi.org/10.1017/S0001924000011805","url":null,"abstract":"Abstract The method of matched asymptotic expansions has been applied to analyse the asymptotic structure of the incompressible turbulent attachment-line boundary layer at large Reynolds numbers. Inner and outer solutions were obtained that give the ‘wall-unit’ and ‘velocity-defect’ represention of both the spanwise and chordwise velocity profiles. The predictions from the theory agree with experimental and DNS data in the range of fully developed turbulence.","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2003-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"57252916","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2002-05-01DOI: 10.1017/S0001924000013099
J. Ackroyd
The second part of this survey closed a little after the termination of the First World War. By then the utility of the aeroplane as an instrument of warfare had been amply demonstrated. Moreover, something of its future potential in civil use had been indicated by such British achievements as the first transatlantic flight by Alcock and Brown in 1919, albeit in a Vickers Vimy biplane of otherwise limited performance. It was also at this time that the new aerodynamic ideas of Kutta, Zhukovskii and Prandtl reached Britain. All such thinking pointed inevitably to the greater speed, efficiency and economy to be expected of the streamlined monoplane.
{"title":"The United Kingdom's contributions to the development of aeronautics. Part 3. The development of the streamlined monoplane (the 1920s-1 940s)","authors":"J. Ackroyd","doi":"10.1017/S0001924000013099","DOIUrl":"https://doi.org/10.1017/S0001924000013099","url":null,"abstract":"The second part of this survey closed a little after the termination of the First World War. By then the utility of the aeroplane as an instrument of warfare had been amply demonstrated. Moreover, something of its future potential in civil use had been indicated by such British achievements as the first transatlantic flight by Alcock and Brown in 1919, albeit in a Vickers Vimy biplane of otherwise limited performance. It was also at this time that the new aerodynamic ideas of Kutta, Zhukovskii and Prandtl reached Britain. All such thinking pointed inevitably to the greater speed, efficiency and economy to be expected of the streamlined monoplane.","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2002-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1017/S0001924000013099","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"57253020","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2002-05-01DOI: 10.1017/S0001924000013105
K. P. Sinhamahapatr
Abstract This paper presents an algorithm to solve the three-dimensional unsteady Euler equations on unstructured tetrahedral meshes using a dynamic mesh algorithm. The driving algorithm is an upwind biased implicit second order accurate cell-centered finite volume scheme. The spatial discretisation technique involves a naturally dissipative flux-split approach that accounts for the local wave propagation characteristics of the flow and captures shock waves sharply. A continuously differentiable flux limiter has been employed to eliminate the spurious oscillations near shock waves, generally arising in calculations involving upwind biased schemes. The temporal discretisation is also second order accurate and uses a Newton linearisation for unsteady calculations. To calculate time dependent flows a dynamic mesh algorithm has been implemented in which the mesh is moved to conform to the instantaneous position of the body by modelling each edge of each cell by a spring. The paper presents a description of the solver and the grid movement algorithm along with results and comparison that assess their capabilities.
{"title":"Unsteady aerodynamic calculations using three-dimensional Euler equations on unstructured dynamic grids","authors":"K. P. Sinhamahapatr","doi":"10.1017/S0001924000013105","DOIUrl":"https://doi.org/10.1017/S0001924000013105","url":null,"abstract":"Abstract This paper presents an algorithm to solve the three-dimensional unsteady Euler equations on unstructured tetrahedral meshes using a dynamic mesh algorithm. The driving algorithm is an upwind biased implicit second order accurate cell-centered finite volume scheme. The spatial discretisation technique involves a naturally dissipative flux-split approach that accounts for the local wave propagation characteristics of the flow and captures shock waves sharply. A continuously differentiable flux limiter has been employed to eliminate the spurious oscillations near shock waves, generally arising in calculations involving upwind biased schemes. The temporal discretisation is also second order accurate and uses a Newton linearisation for unsteady calculations. To calculate time dependent flows a dynamic mesh algorithm has been implemented in which the mesh is moved to conform to the instantaneous position of the body by modelling each edge of each cell by a spring. The paper presents a description of the solver and the grid movement algorithm along with results and comparison that assess their capabilities.","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2002-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"57253023","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2002-04-01DOI: 10.1017/S0001924000012082
F. Nitzsche, S Liberatore, D. G. Zimcik
In the present investigation, the results obtained during the ground vibration tests of a closed-loop control system conducted on a full-scale fighter to attenuate vertical fin buffeting response using strain actuation are presented. The experimental results are supported by numerical analyses using a finite element aeroelastic model of the structure. Two groups of actuators consisting of piezoelectric elements distributed over the structure were designed to achieve authority over the first and second modes of the vertical fin. The control laws were synthesised using the linear quadratic Gaussian (LQG) method for a time-invariant two-input, two-output (2x2 MIMO) control system. Three different pairs of sensors including strain gauges and accelerometers at different locations were used to close the feedback loop. The results demonstrated that actual reductions of up to 18% in the root-mean-square (RMS) values of the fin dynamic response measured by the strain transducer at the critical point for fatigue at the root were achieved for the second mode under the most severe buffet condition.
{"title":"Theoretical and experimental investigations on an active control system for vertical fin buffeting alleviation using strain actuation","authors":"F. Nitzsche, S Liberatore, D. G. Zimcik","doi":"10.1017/S0001924000012082","DOIUrl":"https://doi.org/10.1017/S0001924000012082","url":null,"abstract":"In the present investigation, the results obtained during the ground vibration tests of a closed-loop control system conducted on a full-scale fighter to attenuate vertical fin buffeting response using strain actuation are presented. The experimental results are supported by numerical analyses using a finite element aeroelastic model of the structure. Two groups of actuators consisting of piezoelectric elements distributed over the structure were designed to achieve authority over the first and second modes of the vertical fin. The control laws were synthesised using the linear quadratic Gaussian (LQG) method for a time-invariant two-input, two-output (2x2 MIMO) control system. Three different pairs of sensors including strain gauges and accelerometers at different locations were used to close the feedback loop. The results demonstrated that actual reductions of up to 18% in the root-mean-square (RMS) values of the fin dynamic response measured by the strain transducer at the critical point for fatigue at the root were achieved for the second mode under the most severe buffet condition.","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2002-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1017/S0001924000012082","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"57253006","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2002-04-01DOI: 10.1017/S0001924000012045
F. Nitzsche
Abstract A continuous frequency domain method with roots on the classic Hill’s determinant analysis is presented to approximate the time-varying characteristics of a linear periodic system. The method is particularly useful to derive a time-invariant equivalent form of the time-varying aeroelastic problem of a rotor blade in forward flight. The proposed technique allows methodology usually employed in fixed wing aircraft to obtain closed-loop control laws be extended to rotary wings. The method is first validated solving Mathieu’s equation. Next, the two-degree-of-freedom (flap bending and torsion) problem of rotating beam subject to unsteady and incompressible aerodynamics in forward flight is solved in the laplace domain. As a demonstration of the proposed method, the transfer functions in the ‘s’ plane between a sudden and uniformly distributed input pressure perturbation applied along the beam and the output response of the two elastic degrees of freedom considered are obtained at a set of local sections.
{"title":"Laplace-domain approximation to the transfer functions of a rotor blade in forward flight","authors":"F. Nitzsche","doi":"10.1017/S0001924000012045","DOIUrl":"https://doi.org/10.1017/S0001924000012045","url":null,"abstract":"Abstract A continuous frequency domain method with roots on the classic Hill’s determinant analysis is presented to approximate the time-varying characteristics of a linear periodic system. The method is particularly useful to derive a time-invariant equivalent form of the time-varying aeroelastic problem of a rotor blade in forward flight. The proposed technique allows methodology usually employed in fixed wing aircraft to obtain closed-loop control laws be extended to rotary wings. The method is first validated solving Mathieu’s equation. Next, the two-degree-of-freedom (flap bending and torsion) problem of rotating beam subject to unsteady and incompressible aerodynamics in forward flight is solved in the laplace domain. As a demonstration of the proposed method, the transfer functions in the ‘s’ plane between a sudden and uniformly distributed input pressure perturbation applied along the beam and the output response of the two elastic degrees of freedom considered are obtained at a set of local sections.","PeriodicalId":50846,"journal":{"name":"Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":1.4,"publicationDate":"2002-04-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://sci-hub-pdf.com/10.1017/S0001924000012045","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"57252974","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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