Simple autopilot design procedure based on a factorization approach

Emerald - Tập 78 Số 5 - Trang 407-414 - 2006
AmirNassirharand1, MohammadHosain Alizadeh2
1Mechanical Engineering Group, Islamic Azad University, Damavand, Iran
2Fara‐Faza Company, Tehran, Iran

Tóm tắt

PurposeThe purpose of this paper is to apply a factorization‐based control system design procedure to design of auto‐pilot systems.Design/methodology/approachThe design approach is based on a previously developed factorization‐based control system design procedure. The design approach requires a stable coprime factorization of the plant, a set of stable coprime factors that are solutions to the Bezout identity, the linear model of a desired response, and the desired frequency range of interest. When all this information is provided, the developed automated software outputs a candidate auto‐pilot whose performance should be verified.FindingsFor a specific class of aerospace vehicles, it is found that the described factorization‐based auto‐pilot design procedure may replace the presently complicated auto‐pilot design procedures. The final design is simpler than other techniques that are based on classical, robust, adaptive, QFT, gain scheduling, or interpolation techniques, and the total required man hours for the design loop is less than the mentioned alternative approaches.Research limitations/implicationsThere are two basic limitations – time variations of plant parameters must not be very large as is the case with the agile aerospace vehicles, and specification of the desired closed‐loop system behavior is not systematic.Practical implicationsThe major outcome of this research is that complicated autopilots of a class of aerospace vehicles may be replaced by simpler systems with competitive performance.Originality/valueThis is the first paper in the area of autopilot design that is based on the application of a simple factorization‐based design procedure.

Từ khóa


Tài liệu tham khảo

Bennani, S., Willemsen, D.M.C. and Scherer, C.W. (1998), “Robust control of linear parametrically varying systems with bounded rates”, AIAA J. of Guidance, Control, and Dynamics, Vol. 21 No. 6, pp. 916‐22.

Benshabat, D.G. and Chait, Y. (1993), “Application of quantitative feedback theory to a class of missiles”, AIAA J. of Guidance, Control, and Dynamics, Vol. 16 No. 1, pp. 47‐52.

Biannica, J‐M. and Apkariana, P. (1999), “Missile autopilot design via a modified LPV synthesis technique”, Aerospace Science and Technology, Vol. 3 No. 3, pp. 153‐60.

Buschek, H. (2003), “Design and flight test of a robust autopilot for the IRIS‐T air‐to‐air missile”, Control Engineering Practice, Vol. 11 No. 5, pp. 551‐8.

Chen, W‐H., Ballance, D.J. and Gawthrop, P.J. (2003), “Optimal control of nonlinear systems: a predictive control approach”, Automatica, Vol. 39 No. 4, pp. 633‐41.

Crawford, L.S., Cheng, V.H.L. and Menon, P.K. (1999), “Synthesis of flight vehicle guidance and control laws using genetic search methods”, Proceedings of AIAA Guidance, Navigation, and Control Conference and Exhibit, Portland, OR, USA, AIAA‐1999‐4153,Vol. 2.

Davison, D.E., Kabamba, P.T. and Meerkov, S.M. (1999), “Limitations of disturbance rejection in feedback systems with finite bandwidth”, IEEE Transactions on Automatic Control, Vol. 44 No. 6, pp. 1132‐44.

Devaud, E., Siguerdidjane, H. and Fonta, S. (2000), “Some control strategies for a high‐angle‐of‐attack missile autopilot”, Control Engineering Practice, Vol. 8 No. 8, pp. 885‐92.

Donha, D.C., Desanj, D.S., Katebi, M.R. and Grimble, M.J. (1998), “H∞ adaptive controllers for auto‐pilot applications”, Int. J. of Adaptive Control and Signal Processing, Vol. 12 No. 8, pp. 623‐48.

Han, D. and Balakrishnan, S.N. (2002), “Adaptive critic‐based neural networks for agile missile”, AIAA J. of Guidance, Control, and Dynamics, Vol. 25 No. 2, pp. 404‐7.

Huang, Y.J. and Way, H.K. (2001), “Placing all closed loop poles of missile attitude control systems in the sliding mode via the root locus technique”, ISA Transactions, Vol. 40 No. 4, pp. 333‐40.

Kabamba, P.T. (1987), “Control of linear systems using generalized sampled‐data hold functions”, IEEE Transactions on Automatic Control, Vol. AC‐32 No. 9, pp. 772‐83.

Kim, S‐H., Kim, Y‐S. and Song, C. (2004), “A robust adaptive nonlinear control approach to missile autopilot design”, Control Engineering Practice, Vol. 12 No. 2, pp. 149‐54.

Leith, D.J., Tsourdos, A., Whiteband, B.A. and Leitheada, W.E. (2001), “Application of velocity‐based gain‐scheduling to lateral auto‐pilot design for an agile missile”, Control Engineering Practice, Vol. 9 No. 10, pp. 1079‐93.

Lin, C‐L. and Hsiao, Y‐H. (2001), “Adaptive feedforward control for disturbance torque rejection in seeker stabilizing loop”, IEEE Transactions on Control Systems Technology, Vol. 9 No. 1, pp. 108‐21.

Lin, C‐L. and Lai, R‐M. (2001), “Parameter design for a guidance and control system using genetic approach”, Aerospace Science and Technology, Vol. 5 No. 6, pp. 425‐34.

Lin, C‐F. and Lee, S‐P. (1984), “Robust missile autopilot design using generalized singular optimal control technique”, Proceedings of AIAA Guidance and Control Conference, Seattle, WA, USA, pp. 124‐32.

Lin, C‐K. and Wang, S‐D. (1998), “A self‐organizing fuzzy control approach for bank‐to‐turn missiles”, Fuzzy Sets and Systems, Vol. 96 No. 3, pp. 281‐306.

Lu, P. (1994), “Nonlinear predictive controllers for continuous systems”, AIAA J. of Guidance, Control, and Dynamics, Vol. 17 No. 3, pp. 553‐60.

McLain, T.W. and Beard, R.W. (1999), “Nonlinear robust missile autopilot design using successive Galerkin approximation”, Proceedings of AIAA Guidance, Navigation, and Control Conference and Exhibit, Portland, OR, USA, AIAA‐1999‐3997.

Nassirharand, A. (1991), “Design of dual‐range linear controllers for nonlinear systems”, ASME Transactions: J. of Dynamic Systems, Measurement, and Control, Vol. 113 No. 4, pp. 590‐6.

Nassirharand, A. (1993), “Factorization approach to control system synthesis”, AIAA Journal of Guidance, Control, and Dynamics, Vol. 16 No. 2, pp. 402‐5.

Nassirharand, A. (2003), “Computation of lucid factors for Bezout identity”, Advances in Engineering Software, Vol. 34 No. 9, pp. 527‐31.

Nassirharand, A. and Karimi, H. (2004), “Controller synthesis methodology for multivariable nonlinear systems with application to aerospace”, ASME Transactions: J. of Dynamic Systems Measurement, and Control, Vol. 126 No. 3, pp. 598‐607.

Nassirharand, A. and Karimi, H. (2005), “Mixture ratio control of liquid propellant engines”, Aircraft Engineering and Aerospace Technology: An International Journal, Vol. 77 No. 3, pp. 230‐42.

Nassirharand, A. and Karimi, H. (2006), “Nonlinear controller synthesis based on inverse describing function technique in the MATLAB environment”, Advances in Engineering Software, corrected proof, available at: www.sciencedirect.com.

Nasirharand, A., Taylor, J.H. and Reid, K.N. (1988), “Controller design for nonlinear systems based on simultaneous stabilization theory and describing function models”, ASME Transactions: J. of Dynamic Systems, Measurement, and Control, Vol. 110 No. 3, pp. 134‐43.

Reichert, R.T. (1992), “Dynamic scheduling of modern‐robust‐control autopilot designs for missiles”, IEEE Control Systems Magazine, Vol. 12 No. 5, pp. 35‐42.

Rodriguez, A.A. and Cloutier, J.R. (1994), “Control of a bank‐to‐turn (BTT) missile with saturating actuators”, Proceedings of the American Control Conference,Vol. 2, pp. 1660‐4.

Schumacher, C. and Khargonekar, P.P. (1998), “Missile autopilot designs using H∞ control with gain scheduling and dynamic inversion”, AIAA J. of Guidance, Control, and Dynamics, Vol. 21 No. 2, pp. 234‐43.

Shamma, J.S. and Cloutier, J.R. (1993), “Gain‐scheduled missile autopilot design using linear parameter varying transformations”, AIAA J. of Guidance, Control, and Dynamics, Vol. 16 No. 2, pp. 256‐63.

Shkolnikov, I.A., Shtessel, Y.B., Lianos, D. and Thies, A.T. (2000), “Robust missile autopilot design via high‐order sliding mode control”, Proceedings of AIAA Guidance, Navigation, and Control Conference and Exhibit, Denver, CO, USA, AIAA‐2000‐3968.

Smith, P.R. (1991), “Aircraft flight control system design concepts”, Measurement and Control, Vol. 24 No. 3, pp. 73‐7.

Stallard, D.V. (1966), “A missile adaptive roll autopilot with a new dither principle”, IEEE Transactions on Automatic Control, Vol. AC‐11 No. 3, pp. 368‐78.

Taylor, J.H. (1983), “A systematic nonlinear controller design approach based on quasilinear models”, Proceedings of American Control Conference, San Francisco, CA, USA, pp. 141‐5.

Taylor, J.H. and Strobel, K.L. (1985), “Nonlinear control system design based on quasilinear system models”, Proceedings of American Control Conference, Boston, MA, USA, pp. 1242‐7.

Tribble, A.C., Lempia, D.L., Miller, S.P. and Collins, R. (2002), “Software safety analysis of a flight guidance system”, Proceedings of AIAA/IEEE Digital Avionics Systems Conference,Vol. 2, pp. 13C11‐13C110.

Tsourdos, A. and White, B.A. (2005), “Adaptive flight control design for nonlinear missile”, Control Engineering Practice, Vol. 13 No. 3, pp. 373‐82.

Tsourdos, A., Hughes, E.J. and White, B.A. (2005), “Fuzzy multi‐objective design for a lateral missile autopilot”, Control Engineering Practice, corrected proof, available: www.sciencedirect.com.

Vidyasagar, M. (1985), Control System Synthesis, MIT Press, Cambridge, MA.

Wise, K.A. and Broy, D.J. (1996), “Agile missile dynamics and control”, Proceedings of AIAA Guidance, Navigation, and Control Conference, San Diego, CA, USA, AIAA‐1996‐3912.

Wise, K.A. and Nguyen, T. (1992), “Optimal disturbance rejection in missile autopilot design using projective controls”, IEEE Control Systems Magazine, Vol. 12 No. 5, pp. 43‐9.

Thông tin
Thông tin xuất bản

Emerald

Tập 78 Số 5

407-414

Thông tin tác giả