Abstract
The conceptual design parameters and design processes which are used to access the development of the generic stability and control method are identified and discussed in Sect. 4.4. Primarily, design related commonalties and peculiarities for the range of conventional and unconventional aircraft types are considered.
This is a preview of subscription content, log in via an institution.
Buying options
Tax calculation will be finalised at checkout
Purchases are for personal use only
Learn about institutional subscriptionsNotes
- 1.
The axis of abscissa represents the flight Mach number , the axis of the ordinate the ratio of range versus Earth circumference.
- 2.
Figure 4.2 does not imply that the design parameter space is a continuum; in fact, several aircraft configurations and concepts belong into discrete groups (e.g., a wing may inherit either the variable sweep or fixed sweep concept ).
- 3.
The classification scheme relates to the foundations laid for the KBS, see Sect. 2.5.2.
- 4.
An extended version of this Virtual Toolbox can be used for brainstorming sessions, to stimulate creaticity during the configuration definition phase.
- 5.
Second generation SCT projects are the US HSCT (High-Speed Commercial Transport ) and the European ESCT (European Supersonic Commercial Transport ).
- 6.
The time scale allocated obviously needs modification, but the development trends seem to be valid when reviewing the number of current US X-plane research programmes.
- 7.
Much empirical data exists which is not included in low-order codes.
- 8.
During the conceptual design stage, only gross geometric parameters are available and are of relevance.
- 9.
The term CE (Control Effector ) is used throughout this report to describe all types of controls, including aerodynamic controls, thrust vectoring , thrusters or jets, etc.
- 10.
The following lists some of the expressions used alone or in combination to define the term ‘derivative ’: coefficient, parameter , static , dynamic , longitudinal , lateral -directional , aerodynamic, stability , control , cross, damping , aeroelastic, static , dynamic , quasi-static , rotary , translational, equivalent, linear, non-linear, rate, time-dependent, …
- 11.
Primary controls (PC) are: LoCE, DiCE, and LaCE (elevator , elevon , aileron , taileron , rudder , drag rudder , spoiler , canard , body flap , thrustvector, etc.).
- 12.
Secondary controls (SC) are: trailing-edge flaps, leading-edge flaps , air brakes , etc.
- 13.
Configuration settings (CS) are: landing gear position, wing tip deflection angle (XB-70 ), etc.
- 14.
The following theoretical modifications have been introduced: the wing edge square-root singularity , the logarithmic singularity in the case of flap deflection of the vortex distribution, and the Cauchy singularity in the downwash integral .
- 15.
The dynamic analysis is expected to fine-tune the configuration .
- 16.
The method is primarily developed for Airbus Industrie type transonic transport aircraft .
- 17.
The approach is used at Lockheed Martin Skunk Works and it is only an assumption that it is integrated into a multidisciplinary synthesis environment, see Nikolai [180].
- 18.
The approach is primarily developed for fighter type configurations and the High-Speed Commercial Transport (HSCT).
- 19.
The dynamic parameter approach is based on eigenvalues of the aircraft equations of motion , linearised about a specific trimmed or steady-state flight condition .
- 20.
To recall, in classical aircraft design , design for stability and control follows a predefined schedule. First, a c.g. range is pre-defined as an operational requirement. Consequently, the range of stability is given and must be provided by hardware design decisions. With this pre-defined stability scenario, control is evaluated in a second step throughout the flight envelope . In the case of deficient control authority , modifications are unavoidable which in turn effect stability as well. This hardware design coupling of stability and control can not be avoided for unaugmented aircraft types and poses design trade-off constraints on behalf of the designer.
- 21.
The concept of the free-floating canard must be regarded as an exceptional case. The n.p.-position of the aircraft is, however, not influenced by permanent deflection of the canard surface. For more detail see Middel [185].
- 22.
The construction of the sizing diagram for the CEs of a OFWC represents a real challenge. An elevon functions as a LoCE, LaCE and eventually as well as a DiCE. Design aspects like control allocation schemes need to be considered, leading to sizing diagrams which consequently will have lost physical transparency and simplicity.
- 23.
The term RSS implies relaxed stable and indifferent, but as well unstable airframes.
- 24.
Relaxing stability has been traditionally an add-on performance improvement measure for commercial transport aircraft , with little but usually no effect on the overall aircraft layout; for fighters, the implementation of RSS has been dictated by manoeuverability demands.
- 25.
The emulation of a FCS using the simplified control law (ESD-approach) has certain limitations. It is impossible to emulate a FCS representation valid for generic conceptual design . The typical pre-selected feedback variables for conventional aircraft might be misleading for novel aircraft applications. Although the ESD-approach has an overall generic character, the selection of the feedback variables might be case-specific. Follow-on studies have to determine the most suitable choice of feedback variables for the range of aircraft configurations and concepts. The following assumes the classical feedback variables.
- 26.
Although the design of a simplified SAS appears not too difficult, the main challenge, however, arises in off-design conditions.
- 27.
An ad hoc distribution frequently advocated for the TSC is to carry no load on the tail. An alternative is to carry equal but opposite loads on the canard and tail.
- 28.
The coupled static 6-DOF EOM are called trim EOM.
- 29.
Simplicity has highest priority during conceptual design evaluations due to permanent design data shortage and computing time limitations.
- 30.
In case of no interdisciplinary coupling effect of a design parameter at conceptual design level, its investigation can be done with more freedom and accuracy at a more detailed analysis level.
- 31.
ESCT stands for European Supersonic Commercial Transport .
- 32.
The simulator in Toulouse/France is owned by Air France, the simulator in Bristol/United Kingdom is owned by British Airways.
- 33.
The underlying aerodynamic database includes α− and β-sweeps well beyond standard operational limits [233].
- 34.
FBW system incorporating C* law.
- 35.
Design guidelines for the variety of aircraft configurations and concepts are embedded in the KBS, see Sect. 2.5.
- 36.
The calculation methods are discussed in Chap. 5.
- 37.
CEV (Centre d’Essais en Vol) – French Flight Test Centre (Certification Authority—DGAC).
- 38.
On Airbus aircraft , the problem has been resolved with the Attitude-Protection system, which reduces the elevator -pull authority; the system prevents the dangerous exceedance of αmax.
References
Küchemann, D. and Bagley, J.A., “Twenty Years’ Progress in Aerodynamics and the Changing Shape of Aeroplanes,” Interavia, 1966, pp. 487–489.
Försching, H.W., “Grundlagen der Aeroelastik,” First Edition, Springer-Verlag, 1974.
Nickel, K. and Wohlfahrt, M., “Tailless Aircraft – In Theory and Practice,” First Edition, Edward Arnold, Translator E.M. Brown, 1994.
Roskam, J., “Airplane Flight Dynamics and Automatic Flight Controls—Part I,” Third Edition, DARcorporation, 1995.
Goldsmith, H.A., “Stability and Control of Supersonic Aircraft at Low Speeds,” ICAS Paper 64.588, 4th International Council of the Aeronautical Sciences, Paris, France, 24-28 August 1964.
Sim, A.G., “A Correlation Between Flight-Determined Derivatives and Wind-Tunnel Data for the X-24B Research Aircraft,” NASA TM 113084, NASA, August 1997.
Pinsker, W.J.G., “The Lateral Motion of Aircraft, and in Particular of Inertially Slender Configurations,” ARC R.&M. No. 3334, 1963.
McRuer, D., Ashkenas, I., and Graham, D., “Aircraft Dynamics and Automatic Control,” Princeton University Press, 1973.
Lee, H.P., Chang, M., and Kaiser, M.K., “Flight Dynamics and Stability and Control Characteristics of the X-33 Vehicle,” AIAA Paper 98-4410, AIAA Guidance, Navigation, and Control Conference and Exhibit, Boston, MA, 10-12 August 1998.
Nickel, K. and Wohlfahrt, M., “Tailless Aircraft – In Theory and Practice,” Translated by Brown, E.M., Edward Arnold, 1994.
Sim, A.G. and Curry, R.E., “Flight Characteristics of the AD-1 Oblique-Wing Research Aircraft,” NASA TP 2223, NASA, March 1987.
Abzug, M.J. and Larrabee, E.E., “Airplane Stability and Control – A History of the Technologies That Made Aviation Possible,” First Edition, Cambridge Aerospace Series No. 6, Cambridge University Press, 1997.
Miller, J., “The X-Planes X-1 to X-29,” First Edition, Speciality Press, 1983.
Sternfiel, L., “Some Considerations of the Lateral Stability of High-Speed Aircraft,” NACA TN 1282, NASA, 1947.
Hallion, R.P., “Test Pilots: The Frontiersmen of Flight,” Doubleday, 1981.
Ford, D., “Glen Edwards – The Diary of a Bomber Pilot,” First Edition, Smithsonian Institution Press, 1998.
Pape, G.R. and Campbell, J.M., “Northrop Flying Wings – A History of Jack Northrop’s Visionary Aircraft,” First Edition, Schiffer Military, Aviation History, 1995.
Northrop, J.K., “The Development of All-Wing Aircraft,” 35th Wilbur Wright Memorial Lecture, The Royal Aeronautical Society, London, 1947.
Wilson, J.R., “New Blend For An Old Wing Design,” Aerospace America, April 2000, pp. 28–35.
Phillips, E.H., “NASA To Fly Sub-Scale Blended Wing Body,” Aviation Week & Space Technology, 07 February 2000, pp. 48–49.
Rech, J. and Leyman, C.S., “A Case Study By Aerospatiale and British Aerospace on the Concorde,” AIAA Professional Study Series, AIAA, 01 April 2003.
Sachs, G., “Minimum Trimmed Drag and Optimum C.G. Position,” Vol. 15, No. 8, AIAA Journal of Aircraft, August 1978, pp. 456–459.
Cameron, D. and Princen, N., “Control Allocation Challenges and Requirements for the Blended Wing Body,” AIAA Paper 2000-4539, AIAA Guidance, Navigation, and Control Conference and Exhibit, 14-17 August 2000.
Anon., “Concorde Flying Manual – Vol. 1,” ATP. No. E.8021, Serial No. 4, Holder no. 2304, British Airways, January 1986.
Anon., “A300-600ST: Technical Description – Vol. 1 – General Characteristics,” SATIC/TE DN 0268/95-24/3/1995, Satic, 1995.
Jenkins, D.R., “The History of Developing the National Space Transportation System – The Beginning Through STS-50,” Second Edition, Motorbooks Inernational, 1993.
Weightman, G.D., “Vertical Centre of Gravity Flight Issues,” Very Large Transport Aeroplane Conference, Leeuwenhorst Congres, The Netherlands, 13–16 October 1998.
Heidmann, H., “Trimmtank-System zum Erreichen widerstands-optimaler Schwerpunktslagen,” Jahrestagung der DGLR, October 1982.
Anon., “Introduction to Supersonics,” BA/SST/47/A, British Aerospace Airbus, August 1986.
Jenkins, D.R., “B-1 Lancer – The Most Complicated Warplane Ever Developed,” Vol. 2, Military Aircraft Series, McGraw-Hill, 1999.
Moon, H., “Soviet SST – The Technopolitics of the Tupolev-144,” First Edition, Orion Books, 1989.
Ross, J.W. and Rogerson, D.B., “XB-70 Technology Advancements,” A83-1048, Rockwell International Corporation, 1983.
Holloway, R.B., “Introduction of CCV Technology Into Airplane Design,” AGARD CP-147, Vol. 1, October 1973.
Ashkenas, I.L. and Klyde, D.H., “Tailless Aircraft Performance Improvements With Relaxed Static Stability,” NASA CR 181806, NASA, March 1989.
Sanders, K.L., “Simpler Wing Location for a Specified Longitudinal Stability,” Aerospace Engineering, March 1960, pp. 67–72.
Torenbeek, E., “Synthesis of Subsonic Airplane Design,” Delft University Press, Kluwer Academic Publishers, 1990.
Hoey, R.G., “Testing Lifting Bodies at Edwards,” A PAT Projects, Inc. Publication, July 1997.
Erickson, B.A., “Flight Characteristics of the B58 Mach 2 Bomber,” Vol. 66, Nr. 623, Journal of the Royal Aeronautical Society, November 1962, pp. 665–671.
Greff, E., “Aerodynamic Design and Technology Concepts For a New Ultra-High Capacity Aircraft,” ICAS Paper 96-4.6.3, 20th Congress of the International Council of the Aeronautical Sciences, 08-13 September 1996.
Sacco, G., “P.180: Reasons and Evolution of an Unconventional Aerospace Vehicle Design,” The Michigan State University, October 1989.
Wakayama, S. and Kroo, I., “The Challenge and Promise of Blended-Wing-Body Optimization,” AIAA Paper 98-4736, 7th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, St. Louis, MO, 02-04 September 1998.
Morris, S.J. and Tigner, B., “Flight Tests of an Oblique Flying Wing Small Scale Demonstrator,” AIAA Paper 95-3327-CP, Guidance, Navigation, and Control Conference, Baltimore, MD, 07-10 August 1995.
Davies, P.E. and Thornborough, T., “Boeing B-52 Stratofortress,” First Edition, Crowood Aviation Series, The Crowood Press, 1998.
Yaros, S.F., Sexstone, M.G., et al, “Synergistic Airframe-Propulsion Interactions and Integrations,” NASA TM-1998-207644, NASA, March 1998.
Myhra, D., “The Horten Brothers and Their All-Wing Aircraft,” First Edition, Schiffer Military Aviation History, Schiffer Publishing Ltd., 1998.
Grellmann, H.W., “B-2 Aerodynamic Design,” AIAA Paper 90-1802, Aerospace Engineering Conference and Show, Los Angeles, CA, 13-15 February 1990.
Crickmore, P.F., “Lockheed SR-71 – The Secret Missions Exposed,” First Edition, Osprey Aerospace, 1993.
McCarty, C.A., Feather, J.B., et al, “Design and Analysis Issues of Integrated Control Systems for High-Speed Civil Transports,” NASA CR 186022, NASA, May 1992.
Stillwell, W.H., “X-15 – Research Results With A Selected Bibliography,” NASA SP-60, NASA, November 1964.
Robinson, M.R. and Herbst, W.B., “The X-31A and Advanced Highly Maneuverable Aircraft,” ICAS Paper 90-0.4, 17th Congress of the International Council of the Aeronautical Sciences, Stockholm, Sweden, 09-14 September 1990.
Moore, M. and Frei, D., “X-29 Forward Swept Wing Aerodynamic Overview,” AIAA Paper 83-1834, Applied Aerodynamics Conference, Danvers, MA, 13-15 July 1983.
Stollery, J., “Aerodynamics, Past, Present and Future,” The Sydney Goldstein Memorial Lecture, College of Aeronautics, Cranfield University, 1 November 1995.
Prem, H., “Cooperation Know-How in High-Tech Products,” Binational Conference, University Hohenheim, Stuttgart, 16–17 October 1986, in “Forschung und Entwicklung – Technisch-Wissenschaftliche Veröffentlichungen 1956-1987—Ein Rück- und Ausblick,” Jubiläumsausgabe anläßlich des 75. Geburtstag von Dipl.-Ing. Dr.-Ing. E.h. Ludwig Bölkow, MBB, 1987.
Prandtl, L., “Applications of Modern Hydrodynamics to Aeronautics,” NACA TR 116, NASA, 1921.
Busemann, A., “Aerodynamischer Auftrieb bei Überschallgeschwindigkeit,” 5th Volta Congress, Rome, Italy, 30 September-06 October1935, pp. 328–360.
Weissinger, J., “The Lift Distribution of Swept-Back Wings,” NACA TM 1120, NASA, 1942.
Jones, R.T., “Properties of Low-Aspect Ratio Pointed Wings at Speeds Below and Above the Speed of Sound,” NACA Report 835, NACA, 1946.
Multhopp, H., “Methods for Calculating the Lift Distribution of Wings (Subsonic Lifting Surface Theory),” Aeronautical Research Council R&M 2884, 1950.
Küchemann, D., “A Simple Method of Calculating the Span and Chordwise Loading on Straight and Swept Wings Of Any Given Aspect Ratio at Subsonic Speeds,” Aeronautical Research Council R&M 2935, 1952.
Anon., “Design of Body-Wing Junctions for High Subsonic M, for Swept Back Wings and Symmetrical Bodies,” RAE R Aero 2336, 1949.
Hoerner, S.F., “Aerodynamic Drag,” First Edition, Published by the Author, May 1951.
Hoerner, S.F., “Fluid-Dynamic Drag,” Third Edition, Published by the Author, 1965.
Hoerner, S.F. and Borst, H.V., “Fluid-Dynamic Lift,” Second Edition, Published by L.H. Hoerner, April 1985.
Hoak, D.E., Finck, R.D., et al, “USAF Stability and Control Datcom,” Flight Control Division, Air Force Flight Dynamics Laboratory, Wright-Patterson Air Force Base, 1978.
Anon., “Method for Predicting the Pressure Distribution on Swept Wings With Subsonic Attached Flow,” ESDU Transonic Data Memo 6312, 1963.
Schemensky, R.T., “Development of an Empirically Based Computer Program to Predict the Aerodynamic Characteristics of Aircraft – Volume I Empirical Methods,” TR AFFDL-TR-73-144, Air Force Flight Dynamics Laboratory, Wright-Patterson AFB, October 1973.
Vukelich, S.R., “Development Feasibility of Missile Datcom,” AFWAL-TR-81-3130, Air Force Flight Dynamics Laboratory, Wright-Patterson AFB, October 1981.
Falkner, V.M., “The Calculation of Aerodynamic Loading on Surfaces of Any Shape,” ARC R&M 1910, Aeronautical Research Council, National Physical Laboratory, August 1943.
Hess, J.L. and Smith, A.M.O., “Calculation of Nonlifting Potential flow About Arbitrary Three-Dimensional Bodies,” Douglas Report ES40622, Douglas Aircraft Company, 1962.
Adam, Y., “A Hermitian Finite Difference Method for the Solution of Parabolic Equations,” No. 1, Comp. Math. Applications, 1975, pp. 393–406.
Chung, T.J., “Finite Element Analysis in Fluid Dynamics,” First Edition, McGraw-Hill, 1978.
Rizzi, A.W. and Inouye, M., “Time Split Finite Volume Method for Three-Dimensional Blunt-Body Flows,” Vol. 11, No. 11, AIAA Journal, November 1973, pp. 1478–85.
Gottlieb, D. and Orszag, S.A., “Numerical Analysis of Spectral Methods: Theory and Applications,” SIAM, Philadelphia, 1977.
Snyder, J.R., “CFD Needs in Conceptual Design,” AIAA Paper 90-3209, Aircraft Design, Systems and Operations Conference, Dayton, OH, 17-19 September 1990.
Shevell, R.S., “Aerodynamic Bugs: Can CFD Spray Them Away?,” AIAA Paper 85-4067, 3rd Applied Aerodynamics Conference, Colorado Springs, CO, 14-16 October 1985.
Sinclair, J. (Editor in Chief), “BBC English Dictionary,” First Edition, BBC English and HarperCollins Publishers Ltd., 1992.
Blake, W.B., “Prediction of Fighter Aircraft Dynamic Derivatives Using Digital Datcom,” AIAA Paper 85-4070, 3rd Applied Aerodynamics Conference, Colorado Springs, CO, 14-16 October 1985.
Blake, W.B. and Simon, J.M., “Tools for Rapid Analysis of Aircraft and Missile Aerodynamics,” AIAA Paper 98-2793, 16th AIAA Applied Aerodynamics Conference, Albuquerque, NM, 15-18 June 1998.
Razgonyaev, V. and Mason, W.H., “An Evaluation of Aerodynamic Prediction Methods Applied to the XB-70 for Use in High Speed Aircraft Stability and Control System Design,” AIAA Paper 95-0759, 33rd Aerospace Sciences Meeting and Exhibit, Reno, NV, 09-12 January 1995.
Rubbert, P.E. and Tinoco, E.N., “Impact of Computational Methods on Aerospace Vehicle Design,” AIAA Paper 83-2060, August 1983.
Mason, W.H., “Applied Computational Aerodynamics,” Class Notes for AOE 4114, Department of Aerospace and Ocean Engineering, Virginia Polytechnic Institute and State University, 1995.
Nicolai, L.M. and Carty, A., “Role of the Aerodynamicist in a Concurrent Multi-Disciplinary Design Process,” Paper ADP010502, Symposium of the RTO (Research and Technology Organization) Applied Vehicle Technology Panel (AVT), Ottawa, Canada, 18–21 October 1999.
Morris, S.J., “Integrated Aerodynamics and Control System Design for Tailless Aircraft,” AIAA Paper 92-4604, Astrodynamics Conference, Hilton Head Island, SC, 10-12 August 1992.
Morris, S.J., “Integrated Aerodynamic and Control System Design of Oblique Wing Aircraft,” Ph.D. Thesis, SUDAAR #620, Department of Aeronautics and Astronautics, Stanford University, January 1990.
Dorsett, K.M. and Peters, S.E., “Needs Description,” NASA CP 10138, Proceedings of the Non-Linear Aero Prediction Requirements Workshop, NASA, March 1994.
Hancock, G.J., “Dynamic Effects of Controls,” AGARD R-711, March 1983.
Young, A.D., “Introductory Remarks and Review of 1979 Symposium,” AGARD R-711, March 1983.
Ross, A.J. and Thomas, H.H.B.M., “A Survey of Experimental Data on the Aerodynamics of Controls, in the Light of Future Needs,” AGARD CP-262, September 1979.
Sweetman, B., “Northrop B-2 Stealth Bomber – The Complete History, Technology, and Operational Development of the Stealth Bomber,” First Edition, Mil-Tech Series, Motorbooks International, 1992.
Moul, T.M., Fears, S.P., Ross, H.M., and Foster, J.V., “Low-Speed wind-Tunnel Investigation of the Stability and Control Characteristics of a Series of Flying Wings With Sweep Angles of 60°,” NASA TM 4649, NASA, August 1995.
Thomas, H.H.B.M., “The Aerodynamics of Aircraft Control – A General Survey in the Context of Active Control Technology,” AGARD Report R-711, March 1983.
Skow, A.M., “Control of Advanced Fighter Aircraft,” AGARD Report R-711, March 1983.
Bryan, G.H., “Stability in Aviation,” MacMillan, London, 1911.
Nelson, R.C., “Flight Stability and Automatic Control,” Second Edition, WCB/McGraw-Hill, 1998.
Kalviste, J. and Eller, B., “Coupled Static and Dynamic Stability Parameters,” AIAA Paper 89-3362-CP, 16th Atmospheric Flight Mechanics Conference, Boston, MA, 14-16 August 1989.
Ellison, D.E. and Hoak, D.E., “Stability Derivative Estimation at Subsonic Speeds,” Vol. 2, No. 154, Annals of the New York Academy of Sciences, 1968, pp. 367–396.
Thomas, H.H.B.M., “Estimation of Stability Derivatives (State of the Art),” ARC CP No. 664, 1963.
Blakelock, J.H., “Automatic Control of Aircraft and Missiles,” Second Edition, John Wiley, 1991.
Sim, A.G. and Curry, R.E., “Flight-Determined Aerodynamic Derivatives of the AD-1 Oblique-Wing Research Airplane,” NASA TP-2222, NASA, 1984.
Anon., “VLAERO,” Prospectus, Analytical Methods, Inc., Redmond, Washington, October 1996.
Lamar, J.E., “A Vortex Lattice Method for the Mean Camber Shapes of Trimmed Noncoplanar Planforms with Minimum Vortex Drag,” NASA TN D-8090, NASA, 1976.
Carmichael, R., “Public Domain Aeronautical Software - A Collection of Public Domain Software from NASA and USAF for the PC,” Internet, http://pdas.com/, June 1997.
Lamar, J.E. and Herbert, H.E., “Production Version of the Extended NASA-Langley Vortex Lattice FORTRAN Computer Code,” Volume 1, User’s Guide, NASA TM 83303, NASA, April 1982.
Rom, J., Melamed, B., and Almosnino, D., “Comparison of Experimental Results with the Non-Linear Vortex Lattice Method Calculations for Various Wing-Canard Configurations,” ICAS-90-3.3.4, 17th Congress of the International Council of the Aeronautical Sciences, Stockholm, Sweden, 09-14 September 1990.
Anon., “Program VORLAT,” http://cac.psu.edu/~lnl/497/mpi/vorlat.f, with reference to Bertin, J.J. and Smith, M.L., “Aerodynamics for Engineers,” Second Edition, Prentice Hall, 1989.
Anon., “LinAir Pro Users Guide,” Desktop Aeronautics, Inc., 1996.
Gallman, J.W., Kaul, R.W., Chandrasekharan, R.M. and Hinson, M.L., “Optimization of an Advanced Business Jet,” Vol. 34, No. 3, AIAA Journal of Aircraft, May-June 1997.
Buresti, G., Lombardi, G. and Petagna, P., “Wing Pressure Loads in Canard Configurations: A Comparison Between Numerical Results and Experimental Data,” Vol. 96, Issue 957, Aeronautical Journal, August-September 1992, pp. 271-279.
Gaydon, J.H., “Improved Panel Methods for the Calculation of Low-Speed Flows Around High-Lift Configurations,” Ph.D. Thesis, Bristol University, September 1995.
Anon., “3-D Subsonic Aerodynamics Software - Sub3D for Windows – Version 1.0 User’s Guide,” User’s Guide Rev. A, SoftwAeronautics, Inc., 1996.
Albright, A.E., Dixon, C.J., and Hegedus, M.C., “Modification and Validation of Conceptual Design Aerodynamic Prediction Method HASC95 With VTXCHN,” NASA CR-4712, NASA, March 1996.
Miranda, L.R., Elliott, R.D., and Baker, W.M., “A Generalized Vortex Lattice Method for Subsonic and Supersonic Flow Applications,” NASA CR-2865, NASA, December 1977.
Lan, C.E., “Methods of Analysis in The VORSTAB Code (Version 3.1),” The University of Kansas, May 1993.
Margason, R.J., Kjelgaard, S.O., Sellers, W.L., et. al., “Subsonic Panel Methods - A Comparison of Several Production Codes,” AIAA 85-0280, 23rd Aerospace Sciences Meeting, Reno, NV, 14-17 January 1985.
Rubbert, P.E. and Saaris, G.R., “A General Three-Dimensional Potential Flow Method Applied to V/STOL Aerodynamics,” SAE Paper 68004, National Air Transportation Meeting, February 1968.
Petrie, J.A.H., “Development of an Efficient and Versatile Panel Method for Aerodynamic Problems,” Ph.D. Thesis, University of Leeds, March 1979.
Katz, J. and Plotkin, A., “Low-Speed Aerodynamics - From Wing Theory to Panel Methods,” McGraw-Hill, Inc., 1991.
Roberts, A. and Rundle, K., “Computation of Incompressible Flow About Bodies and Thick Wings Using the Spline-Mode System,” BAC (CAD) Report Aero Ma 19, 1972.
Hunt, B. and Semple, W.G., “The BAC (MAD) Program to Solve the 3-D Lifting Subsonic Neumann Problem Using the Plane Panel Method,” Report ARG 97 BAC (MAD), 1973.
Erickson, L.L., “Panel Methods - An Introduction,” NASA-TP-2995, NASA Ames Research Center, 01 December 1990.
Lamar, J.E., “The Use of Linearized-Aerodynamics and Vortex-Flow Methods in Aerospace Vehicle Design (Invited Paper),” AIAA Paper 82-1384, August 1982.
Anon., “AMI - Specialists in Computational Fluid Dynamics Services and Software Products,” Prospectus, Analytical Methods, Inc., Februar 1997.
Hoeijmakers, H.W.M., “Panel Methods for Aerodynamic Analysis and Design,” AGARD Report 783, May 1991.
Petrie, J.A.H., “Development of an Efficient and Versatile Panel Method for Aerodynamic Problems,” Ph.D. Thesis, University of Leeds, March 1979.
Lötstedt, P., “A Three-Dimensional Higher-Order Panel Method for Subsonic Flow Problems - Description and Applications,” SAAB-SCANIA Rep. L-0-1 R100, 1984.
Roggero, F. and Larguier, R., “Aerodynamic Calculation of Complex Three-Dimensional Configurations,” Vol. 30, No. 5, AIAA Journal of Aircraft, Sept.-Oct. 1993.
Baston, A., Lucchesini, M., Manfriani, L., et. al., “Evaluation of Pressure Distributions on an Aircraft by two Different Panel Methods and Comparison with Experimental Measurements,” ICAS-86-1.5.3, 15th Congress of the International Council of the Aeronautical Sciences, London, England, 07-12 September 1986.
Anon., “PMARC_12 - Panel Method Ames Research Center, Version 12,” Internet, http://www.cosmic.uga.edu./abstracts/arc-13362, July 1997.
Anon., “AeroMaster,” http://www.ssmotion.com/aeromstr.htm, July 1997.
Manning, V.M., “A Comparison of the Woodward-Carmichael Code and PAN AIR,” Internet, http://www-leland.stanford.edu/~valman/research/WCMST/WCMST.html, 8 October 1996.
Anon., “USSAERO - Unified Subsonic Supersonic Aerodynamic Analysis Program,” Internet, http://cognac.cosmic.ug…bstracts/lar-11305.html, July 1997.
Mason, W.H. and Rosen, B.S., “The COREL and W12SC3 Computer Programs for Supersonic Wing Design and Analysis,” NASA CR-3676, NASA Langley Research Center, December 1983.
Carmichael, R., “Public Domain Aeronautical Software - A Collection of Public Domain Software from NASA and USAF for the PC,” Internet, http://pdas.com/, June 1997.
Hoeijmakers, H.W.M., “A Panel Method for the Determination of the Aerodynamic Characteristics of Complex Configurations in Linearized Subsonic or Supersonic Flow,” Report NLR TR 80124, 1980.
Maughmer, M., Ozoroski, L., Straussfogel, D., and Long, L., “Validation of Engineering Methods for Predicting Hypersonic Vehicle Control Forces and Moments,” Vol. 16, No. 4, AIAA Journal of Guidance, Control, and Dynamics, July-August 1993.
Siclari, M., Visich, M., Cenko, A., Rosen, B., and Mason, W., “Evaluation of NCOREL, PAN AIR, and W12SC3 for Supersonic Wing Pressures,” Vol. 21, No. 10, AIAA Journal of Aircraft, October 1984, pp. 816–822.
Anon., “Introducing ADAPT,” Version 1.0, Synaps, Inc., 1996.
Lan, C.E., “Applied Airfoil and Wing Theory,” First Edition, Cheng Chung Book Company, 1988.
Pistolesi, E., “Betrachtungen über die gegenseitige Beeinflussung von Tragflügelsystemen,” Collected Presentations of the 1937 Lilienthal-Gesellschaft Meeting, 1937, pp.214-219.
Schlichting, H. and Truckenbrodt, E., “Aerodynamik des Flugzeuges – Erster Band – Grundlagen aus der Strömungsmechanik – Aerodynamik des Tragflügels (Teil I),” Second Edition, Springer, 1967.
Bertin, J.J. and Smith, M.L., “Aerodynamics For Engineers,” Second Edition, Prentice Hall, 1989.
Moran, J., “An Introduction to Theoretical and Computational Aerodynamics,” First Edition, John Wiley & Sons, 1984.
Rakowitz, M.E., “Evaluation of LinAir as a Design Tool for the Lift Distribution of a Three-Surface Aircraft,” M.Sc. Thesis, College of Aeronautics, Cranfield University, September 1997.
Lan, C.E., "A Quasi-Vortex-Lattice Method in Thin Wing Theory,” Vol. 11, No. 9, AIAA Journal of Aircraft, September 1974, pp. 518–527.
Lan, C.E., Emdad, H. et al, “Calculation of High Angle-Of-Attack Aerodynamics of Fighter Configurations,” AIAA Paper 89-2188-CP, 7th Applied Aerodynamics Conference, Seattle, WA, 31 July-02 August 1989.
Lan, C.E., “VORSTAB – A Computer Program For Calculating Lateral-Directional Stability Derivatives With Vortex Flow Effect,” NASA CR 172501, NASA, January 1985.
Lan, C.E., “Methods of Analysis in The VORSTAB Code (Version 3.1),” Department of Aerospace Engineering, The University of Kansas, May 1993.
Obert, E., “Tail Design,” Report No. H-0-93, Issue No. 1, Fokker Aircraft B.V., Lecture Notes to the ECATA Postgraduate Aerospace Vehicle Design Course, 22 March 1992.
Root, L.E., “Dynamic Longitudinal Stability Charts for Design Use,” Vol. 2, No. 3 Journal of Aeronautical Sciences (JAS), May 1935, pp. 101–108.
Silverstein, A., “Towards a Rational Method of Tail-Plane Design,” Journal of the Aeronautical Sciences, 1939.
Root, L.E., “Empennage Design With Single and Multiple Vertical Surfaces,” Vol. 6, No. 9, Journal of the Aeronautical Sciences, July 1939, pp. 353–360.
Morgan, M.B. and Thomas, H.H.B.M., “Control Surface Design in Theory and Practice,” Vol. 49, Issue 416, The Aeronautical Journal, The Royal Aeronautical Society, August 1945, pp. 431–510.
Wimpenny, J.C., “Stability and Control in Aerospace Vehicle Design,” Vol. 58, Journal of the Royal Aeronautical Society, May 1954, pp. 329–360.
Lee, G.H., “The Aeroplane Designer’s Approach to Stability and Control,” AGARD Report 334, April 1961.
Wood, K.D., “Aerospace Vehicle Design – Volume I – Aerospace Vehicle Design,” Eleventh Edition, Johnson Publishing Company, 1963.
Burns, B.R.A., “Design Considerations for the Satisfactory Stability and Control of Military Combat Aeroplanes,” AGARD CP 119, 1972.
Torenbeek, E., “Synthesis of Subsonic Airplane Design,” 6th Printing, Delft University Press, Kluwer Academic Publishers, 1990.
Nicolai, L.M., “Fundamentals of Aerospace Vehicle Design,” Second Edition, METS, Inc., 1984.
Hünecke, K., “Modern Combat Aerospace Vehicle Design,” Second Edition, Airlife Publishing Ltd., 1987.
Whitford, R., “Design for Air Combat,” First Edition, Jane’s Publishing Company Limited, 1987.
Stinton, D., “The Design of the Aeroplane,” BSP Professional Books, 1991.
Raymer, D.P., “Aerospace Vehicle Design: A Conceptual Approach,” Second Edition, AIAA Education Series, AIAA, 1992.
Heinemann, E., “Aerospace Vehicle Design,” First Edition, Aerospace Vehicle Designs Inc., 1997.
Hünecke, K., “Die Technik des modernen Verkehrsflugzeuges,” First Edition, Motorbuchverlag, 1998.
Stinton, D., “The Anatomy of the Aeroplane,” Second Edition, Blackwell Science, 1998.
Anderson, J.D., “Aircraft Performance and Design,” First Edition, WCB/McGraw-Hill, 1999.
Jenkinson, L.R., Simpkin, P., and Rhodes, D., “Civil Jet Aerospace Vehicle Design,” First Edition, Arnold, 1999.
Scholz, D., “Skript zur Vorlesung Flugzeugentwurf,” First Edition, Fachhochschule Hamburg, Fachbereich Fahrzeugtechnik, Sommersemester, 1999.
Howe, D., “Aircraft Conceptual Design Synthesis,” First Edition, Professional Engineering Publishing, October 2000.
Oman, B.H., “Vehicle Design Evaluation Program (VDEP),” NASA CR 145070, NASA, 01 January 1977.
Thorbeck, J., “Ein Beitrag zum Rechnergestützten Entwurf von Verkehrsflugzeugen,” Ph.D. Thesis, Technical University Berlin, 1984.
Alsina, J., “Development of an Aerospace vehicle design Expert System,” Ph.D. Thesis, Cranfield Institute of Technology, College of Aeronautics, October 1987.
Bil, C., “Development and Application of a Computer-Based System for Conceptual Aerospace Vehicle Design,” Ph.D. Thesis, Delft University, Delft University Press, 1988.
Kay, J., Mason, W.H., et al, “Control Authority Issues in Aircraft Conceptual Design: Critical Conditions, Estimation Methodology, Spreadsheet Assessment, Trim and Bibliography,” VPI-Aero-200, Virginia Polytechnic Institute and State University, Department of Aerospace and Ocean Engineering, November 1993.
Heinze, W., “Ein Beitrag zur quantitativen Analyse der technischen und wirtschaftlichen Auslegungsgrenzen verschiedener Flugzeugkonzepte für den Transport großer Nutzlasten,” Ph.D. Thesis, ZLR-Forschungsbericht 94.01, Institut für Flugzeugbau und Leichtbau, Technical University Braunschweig, 1994.
Nunes, J.M.B., “Aerospace Vehicle Design Optimisation – Conceptual Evaluation of a Three-Lifting Surface Turbo-Fan Airliner,” Ph.D. Thesis, College of Aeronautics, Cranfield University, February 1995.
MacMillin, P.E., “Trim, Control, and Performance Effects in Variable-Complexity High-Speed Civil Transport Design,” M.Sc. Thesis, Department of Aerospace and Ocean Engineering, Virginia Polytechnic Institute and State University, May 1996.
Pohl, T., “Improvement and Extension of Tail Sizing Procedures for Preliminary Design Purposes,” M.Eng. Thesis, Department of Aeronautics, Imperial College of Science, June 1997.
Nicolai, L.M. and Carty, A., “Role of the Aerodynamicist in a Concurrent Multi-Disciplinary Design Process,” Paper RTO MP-35, RTO AVT Symposium on 'Aerodynamic Design and Optimization of Flight Vehicles in a Concurrent Multi-Disciplinary Environment', Research and Technology Organization, Applied Vehicle Technology Panel (AVT), Ottawa, Canada, 18–21 October 1999.
Sauvinet, F., “Longitudinal Active Stability: Key Issues for Future Large Transport Aircraft,” ICAS Paper 4101, 22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August-01 September 2000.
Etkin, B., “Transfer Functions: Improvement on Stability Derivatives for Unsteady Flight,” UTIA Report 42, 1958.
Thomas, H.H.B.M., “State of the Art of Estimation of Derivatives,” AGARD Report 339, April 1961.
Etkin, B. and Reid, L.D., “Dynamics of Flight – Stability and Control,” Third Edition, John Wiley & Sons, Inc., 1996.
Middel, J., “Development of a Computer Assisted Toolbox for Aerodynamic Design of Aircraft at Subcritical Conditions with Application to Three-Surface and Canard Aircraft,” Ph.D. Thesis, Delft University Press, 1992.
Hofmann, L.G. and Clement, W.F., “Vehicle Design Considerations for Active Control Application to Subsonic Transport Aircraft,” NASA CR-2408, August 1974.
Jenny, R.B., Krachmalnick, F.M., and LaFavor, S.A., “Air Superiority with Controlled Configured Fighters,” AIAA Paper 71-764, 3rd Aircraft Design and Operations Meeting, Seattle, WA, 12-14 July 1971.
Pasley, L.H. and Kass, G.J., “Improved Airplane Performance Through Advanced Flight Control System Design,” AIAA Paper 70-875, July 1970.
Pasley, L.H., Rohling, W.J., and Wattman, W.J., “Compatibility of Maneuver Load Control and Relaxed Static Stability,” AIAA Paper 73-791, 5th Aircraft Design,Flight Test and Operations Meeting, St. Louis, MO, 06-08 August 1973.
Mueller, L.J., “Pilot and Aircraft Augmentation on the C-5,” Vol. 7, No. 6, AIAA Journal of Aircraft, November-December 1970, pp. 550–553.
Cook, M.V., “Flight Dynamics Principles,” First Edition, Arnold, 1997.
Gibson, J.C. (Handling Qualities Expert, BAe Military) and Chudoba, B., Personal Communication, 6 February 1997.
Gibson, J.C., “The Definition, Understanding and Design of Aircraft Handling Qualities,” Report LR-756, Delft University of Technology, February 1995.
Gibson, J.C., “Development of a Methodology for Excellence in Handling Qualities Design for Fly By Wire Aircraft,” Ph.D. Thesis, Published in Series 03, Control and Simulation 06, Delft University Press, 1999.
Hodgkinson, J., “Aircraft Handling Qualities,” First Edition, Blackwell Science Ltd, 1999.
McRuer, D.T., “Aviation Safety and Pilot Control – Understanding and Preventing Unvavorable Pilot-Vehicle Interactions,” National Research Council, National Academy Press, 1997.
Mavris, D.N., DeLaurentis, D.A., and Soban, D.S., “Probabilistic Assessment of Handling Qualities Characteristics in Preliminary Aerospace Vehicle Design,” AIAA Paper 98-0492, 36th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, 12-15 January 1998.
Graeber, U.P., “Realisation of Relaxed Static Stability on a Commercial Transport,” AGARD Paper CP-384, October 1984.
Anderson, M.R. and Mason, W.H., “An MDO Approach to Control-Configured-Vehicle Design,” AIAA Paper 96-4058, 6th Symposium on Multidisciplinary Analysis and Optimization, Bellevue, WA, 04-06 September 1996.
Beaufrere, H., “Integrated Flight Control System Design for Fighter Aircraft Agility,” AIAA Paper 88-4503, Aircraft Design, Systems and Operations Conference, Atlanta, GA, 07-09 September 1988.
Imlay, F.H., “A Theoretical Study of Lateral Stability with an Automatic Pilot,” NACA Report 693, 1940.
Etkin, B., “Dynamics of Atmospheric Flight,” Second Edition, John Wiley & Sons, Inc., 1972.
Roskam, J., “Airplane Flight Dynamics and Automatic Flight Controls – Part II,” First Edition, DARcorporation (Design, Analysis and Research Corporation), 1995.
Durham, W.C., “Constrained Control Allocation,” Vol. 16, No. 4, AIAA Journal of Guidance, Control, and Dynamics, July-August 1993, pp. 717–725.
Bordignon, K.A. and Durham, W.C., “Null-Space Augmented Solutions to Constrained Control Allocation Problems,” AIAA Paper 95-3209-C, Guidance, Navigation, and Control Conference, Baltimore, MD, 07-10 August 1995.
Durham, W.C. and Bordignon, K.A., “Multiple Control Effector Rate Limiting,” AIAA Paper 95-3208-CP, Guidance, Navigation, and Control Conference, Baltimore, MD, 07-10 August 1995.
Buffington, J.M., “Tailless Aircraft Control Allocation,” AIAA Paper 97-3605, Guidance, Navigation, and Control Conference, New Orleans, LA, 11-13 August 1997.
Page, A.B. and Steinberg, M.L., “A Closed-Loop Comparison of Control Allocation Methods,” AIAA Paper 2000-4538, AIAA Guidance, Navigation, and Control Conference and Exhibit, Denver, CO, 14-17 August 2000.
Ikeda, Y. and Hood, M., “An Application of L1 Optimization to Control Allocation,” AIAA Paper 2000-4566, AIAA Guidance, Navigation, and Control Conference and Exhibit, Denver, CO, 14-17 August 2000.
Goodrich, K.H., Sliwa, S.M., and Lallman, F.J., “A Closed-Form Trim Solution Yielding Minimum Trim Drag for Airplanes With Multiple Longitudinal-Control Effectors,” NASA TP 2907, May 1989.
Kolk, W.R., “Modern Flight Dynamics,” Prentice-Hall, 1961.
Babister, A.W., “Aircraft Stability and Control,” Pergamon Press, 1961.
Woodcock, R.J. and Drake, D.E., “Estimation of Flying Qualities of Piloted Airplanes,” AFFDL-TR-65-218, April 1966.
McLean, D., “Automatic Flight Control Systems,” First Edition, Prentice Hall International Series in Systems and Control Engineering, Prentice Hall International Ltd., 1990.
Stevens, B.L. and Lewis, F.L., “Aircraft Control and Simulation,” First Edition, John Wiley & Sons, Inc., 1992.
Brockhaus, R., “Flugregelung,” First Edition, Springer-Verlag, 1994.
Hancock, G.J., “An Introduction to the Flight Dynamics of Rigid Aeroplanes,” First Edition, Ellis Horwood Series in Mechanical Engineering, Ellis Horwood Limited, 1995.
Russell, J.B., “Performance & Stability of Aircraft,” First Edition, Arnold, 1996.
Schmidt, L.V., “Introduction to Aircraft Flight Dynamics,” First Edition, AIAA Education Series, AIAA, 1998.
Phillips, W.F., “Phugoid Approximation for Conventional Airplanes,” Vol. 37, No. 1, AIAA Journal of Aircraft, January-February 2000, pp. 30–36.
Phillips, W.F., “Improved Closed-Form Approximation for Dutch Roll,” Vol. 37, No. 3, AIAA Journal of Aircraft, May-June 2000, pp. 484.490.
Burdun, I.Y. and Parfentyev, O.M., “Analysis of Aerobatic Flight Safety Using Autonomous Modeling and Simulation,” SAE Paper 2000-01-2100, 2000 Advances In Aviation Safety Conference & Exposition, April 2000.
Burdun, I.Y., “Virtual Test and Evaluation of Air France Concorde Flight No. AF4590,” Preliminary Case Study, Atlanta, 26 July 2000.
Chudoba, B. and Burdun, I.Y, “Virtual Test and Evaluation of Air France Concorde Flight No. AF4590,” Presentation at Fairchild Dornier, Oberpfaffenhofen, 27 July 2000.
Leyman, C.S., “Concorde Flight Mechanics/Aircraft Sizing,” Presentation at the Future Projects Office, British Aerospace Airbus, Filton, 4 February 1997.
Nicholls, K., “Critical Flight Cases for Handling Qualities,” Memorandum B57M/SST/KPN/11890, Future Projects, British Aerospace Airbus, 2 May 1996.
Le Tron, X., “Handling Qualities Requirements,” Memo 822.008/97, AI/LE-D, Airbus Industrie, 25 April 1997.
Bennett, F., Priestly, and Chudoba, B., Personal Communication, Concorde Training Centre, British Aerospace Airbus, Bristol/Filton, United Kingdom, 29 May 1996.
Hammer, J., Cros, T., and Chudoba, B., Personal Communication, Flight Test Division, Airbus Industrie, Toulouse, France, 11 June 1996.
Morton, R.F. and Chudoba, B., Personal Communication, Concorde Simulator, British Aerospace Airbus, Bristol/Filton, United Kingdom, 26 June 1996.
Graeber, U. and Chudoba, B., Personal Communication, College of Aeronautics, Cranfield University, 20–21 August 1996.
Pacull, M., Hugo, F., Druot, T., Irvoas, J., Smith, H., and Chudoba, B., Personal Communication, Aérospatiale Aéronautique Airbus, Toulouse, 10 September 1996.
Green, P., Miller, A., Reid, S., Hyde, L., Smith, H., and Chudoba, B., Personal Communication, Future Projects Office, British Aerospace Airbus, Bristol/Filton, United Kingdom, 19 September 1996.
Leyman, C.S., Hyde, L., Haddrell, A., Nicholls, K., and Chudoba, B., Personal Communication, Future Projects Office, British Aerospace Airbus, Bristol/Filton, United Kingdom, 4 February 1997.
Khaski, E., Irvoas, J., and Chudoba, B., Personal Communication, Aérospatiale Aéronautique Airbus, Toulouse, 11 February 1997.
Morton, C., Britton, D., and Chudoba, B., Personal Communication, Concorde Simulator, British Aerospace Airbus, Bristol/Filton, United Kingdom, 21 February 1997.
Bailey, R., Morton, C., Gaudrey, J., Graeber, U., and Chudoba, B., Personal Communication, Concorde Flight Simulator Session, British Aerospace Airbus, Bristol/Filton, United Kingdom, 27 February 1997.
Green, P., Morton, C., and Chudoba, B., Personal Communication, Concorde Simulator Logic, Concorde Simulator, British Aerospace Airbus, Bristol/Filton, United Kingdom, 6 March 1997.
Perrin, K.M., Reid, J., and Chudoba, B., Personal Communication, Civil Aviation Authority (CAA), Gatwick Airport, United Kingdom, 24 March 1997.
Rauscher, E., Smith, B., Hammer, J., and Chudoba, B., Personal Communication, SATIC-Beluga, Toulouse, 2 April 1997.
Chudoba, B., “Investigation of Inherent Slender-Body Characteristics Using the CONCORDE Simulator,” CoA Report NFP0104, Department of Aerospace Technology, College of Aeronautics, Cranfield University, 27 February 1997.
Chudoba, B., “Stability & Control Aerospace Vehicle Design and Test Condition Matrix,” Technical Report EF-039/96, Daimler-Benz Aerospace Airbus, September 1996.
Regis, Y., “A330/A340 Joint Certification Basis,” AI/EA-A 414.000/89, Issue 4, Airbus Industrie, July 1994.
Anon., “Concorde TSS Standards,” Avion de Transport Supersonique, Supersonic Transport Aircraft, Part 3 - Issue 4 - Flying Qualities, Part 7-3 - Issue 3 - Flying Controls, The Air Registration Board, 1969–1976.
Anon., “Flying Qualities of Piloted Airplanes – Military Specification,” MIL-F-8785C, 1980.
Anon., “Flying Qualities of Piloted Vehicles – Military Standards,” MIL-STD-1797A, 1990.
Author information
Authors and Affiliations
Corresponding author
Rights and permissions
Copyright information
© 2019 Springer Nature Switzerland AG
About this chapter
Cite this chapter
Chudoba, B. (2019). Generic Characterisation of Aircraft—Parameter Reduction Process. In: Stability and Control of Conventional and Unconventional Aerospace Vehicle Configurations. Springer Aerospace Technology. Springer, Cham. https://doi.org/10.1007/978-3-030-16856-8_4
Download citation
DOI: https://doi.org/10.1007/978-3-030-16856-8_4
Published:
Publisher Name: Springer, Cham
Print ISBN: 978-3-030-16855-1
Online ISBN: 978-3-030-16856-8
eBook Packages: EngineeringEngineering (R0)