Coupled linear parameter varying and flatness-based approach for space re-entry vehicles guidance

Access Full Text

Coupled linear parameter varying and flatness-based approach for space re-entry vehicles guidance

For access to this article, please select a purchase option:

Buy article PDF
£12.50
(plus tax if applicable)
Add to cart
Buy Knowledge Pack
10 articles for £75.00
(plus taxes if applicable)
Add to cart

IET members benefit from discounts to all IET publications and free access to E&T Magazine. If you are an IET member, log in to your account and the discounts will automatically be applied.

Learn more about IET membership 

Recommend Title Publication to library

You must fill out fields marked with: *

Librarian details
Name:*
Email:*
Your details
Name:*
Email:*
Department:*
Why are you recommending this title?
Select reason:
 
 
 
 
 
IET Control Theory & Applications — Recommend this title to your library

Thank you

Your recommendation has been sent to your librarian.

© The Institution of Engineering and Technology
Published

An linear parameter varying guidance method for the hypersonic phase of a space re-entry vehicle is presented. The suggested guidance scheme, relying on flatness approach, is applied to the non-linear model of the European Atmospheric Re-entry Demonstrator. It is shown that the overall guidance scheme achieves robust stability and performance, even in the presence of entry point kinematics dispersions. The design problem is formulated and solved using a finite set of linear matrix inequalities. Finally, Monte Carlo simulation results are presented to demonstrate the effectiveness of the suggested approach.

Inspec keywords: path planning; nonlinear control systems; Monte Carlo methods; linear matrix inequalities; space vehicles; robust control; vehicle dynamics

Other keywords: flatness approach; Monte Carlo simulation; robust stability; European Atmospheric Re-entry Demonstrator; entry point kinematics dispersion; linear matrix inequalities; nonlinear model; linear parameter varying guidance; space reentry vehicle guidance

Subjects: Algebra; Nonlinear control systems; Aerospace industry; Algebra; Stability in control theory; Statistics; Vehicle mechanics; Aerospace control; Control technology and theory (production); Spatial variables control; Monte Carlo methods

References

    1. 1)
      • United States Committee on Extension to the Standard Atmosphere: ‘U.S. standard atmosphere’, National Oceanic and Atmospheric Administration, National Aeronautics and Space Administration, United States Air Force, Washington, D.C., 1976.
    2. 2)
      • Arrington, J.P., Jones, J.J.: `Shuttle performance: lessons learned', Proc. NASA conf., 1983, Hampton, USA, NASA, p. 2283.
    3. 3)
      • R. Murray , J. Hauser , A. Jadbabaie , M. Milam , N. Petit , W. Dunbar , R. Franz , T. Samad , G. Balas . (2003) Online control customization via optimization-based control, Software-enabled control, information technology for dynamical systems.
    4. 4)
      • M. Fliess , J. Lévine , P. Martin , P. Rouchon . A lie-backlund approach to equivalence and flatness of nonlinear systems. IEEE Trans. Autom. Control , 44 , 922 - 937
    5. 5)
      • van Nieuwstadt, M., Murray, R.M.: `Real time trajectory generation for differentially flat systems', Proc. 34th IEEE Control and Decision Conference, 1995, New Orleans, USA, IEEE, p. 4224–4230.
    6. 6)
      • Morio, V., Cazaurang, F., Zolghadri, A.: `On the formal characterization of reduced-order at outputs over an ore algebra', Proc. IEEE Multi conf. Systems and Control, 2008, San Antonio, TX, USA, IEEE, p. 208–214.
    7. 7)
      • Carson, J., Epstein, M., MacMynowski, D., Murray, R.: `Optimal nonlinear guidance with inner-loop feedback for hypersonic re-entry', Proc. 2006 American Control Conference, 2006, USA, AIAA/CIRA, p. 6.
    8. 8)
      • P. Lu . Entry guidance and trajectory control for reusable launch vehicle. AIAA J. Guid., Control and Dyn. , 20 , 143 - 149
    9. 9)
      • Steinbuch, M., Terlouw, J.C., Bosgra, O.H.: `Robustness analysis for real and complex perturbations applied to an electro-mechanical system', Proc. 1991 American Control Conf., 1991, Boston, USA, IEEE, p. 556–561.
    10. 10)
      • Antritter, F., Lévine, J.: `Towards a computer algebraic algorithm for at output determination’. ISSAC'08', Proc. 21st Int. Sym. Symbolic and Algebraic Computation, 2008, New York, NY, USA, ACM, p. 7–14.
    11. 11)
      • Harpold, J.C., Graves, C.A.J.: `Re-entry targeting philosophy and flight results from apollo 10 and 11', Proc. AIAA Eigth Aerospace Sciences Meeting, 1970, New York, USA, N70‐28AIAA, .
    12. 12)
      • Neckel, T., Talbot, C., Petit, N.: `Collocation and inversion for a reentry optimal control problem', Proc. Fifth Int. Conf. Launcher Technology, 2003, Madrid, Spain, ESA.
    13. 13)
      • Smith, R.P.: `Functional control law design using exact non-linear dynamic inversion', Proc. AIAA Guidance, Navigation and Control Conference, 1994, Scottsdale, USA, AIAA, p. 481–489.
    14. 14)
      • M. Fliess , J. Lévine , P. Martin , P. Rouchon . Flatness and defect of non-linear systems: introduction theory and examples. Int. J. Control , 61 , 1327 - 1361
    15. 15)
      • J.T. Betts . (2001) Practical methods for optimal control using nonlinear programming.
    16. 16)
      • J.M. Biannic , P. Apkarian , W.L. Garrard . Parameter-varying control of high performance aircraft. AIAA J. Guid., Control Dyn. , 20 , 225 - 231
    17. 17)
      • V. Hagenmeyer , E. Delaleau . Robustness analysis of exact feedforward linearization based on differential flatness. Automatica , 39 , 1941 - 1946
    18. 18)
      • J. Levine . (2006) On necessary and sufficient conditions for differential flatness.
    19. 19)
      • Pignié, J., Clar, P., Ferreira, E., Bouaziz, L., Caillaud, J.: `Navigation, guidance and control of the atmospheric re-entry demonstrator', Proc. Third ESA Int. Conf. Spacecraft Guidance, Navigation and Control Systems, 1996, Noordwijk, The Netherlands, ESA, p. 149.
    20. 20)
      • F. Zheng , Q.-G. Wang , T. Lee . On the design of multivariable pid controllers via lmi approach. Automatica , 38 , 517 - 526
    21. 21)
      • P. Apkarian , P. Gahinet . A convex characterization of gain-scheduled h∞ controllers. IEEE Trans. Automatic Control , 40 , 853 - 864
    22. 22)
      • F.J. Regan , S.M. Anandakrishnan . (1993) Dynamics of atmospheric re-entry.
    23. 23)
      • K.D. Mease , J. Kremer . Shuttle entry guidance revisited using nonlinear geometric methods. AIAA J. Guid., Control Dyn. , 17 , 1350 - 1356
    24. 24)
      • J. Harpold , C. Graves . Shuttle entry guidance. J. Astronaut. Sci. , 27 , 239 - 268
    25. 25)
      • Zerar, M., Cazaurang, F., Zolghadri, A.: `Robust tracking of nonlinear mimo uncertain at systems', Proc. IEEE Int. Conf. Systems Man and Cybernetics, 2004, The Hague, The Netherlands, ESA, p. 536–541.
    26. 26)
      • P. Rouchon . Necessary condition and genericity of dynamic feedback linearization. J. Math. Syst. Estim. Control , 5 , 345 - 358
    27. 27)
      • N.X. Vinh , A. Busemann , R.D. Culp . (1980) Hypersonic and planetary entry flight mechanics.
    28. 28)
      • Petit, N., Milam, M., Murray, R.: `Inversion based trajectory optimization', Proc. Fifth IFAC Symp. Nonlinear Control Systems Design, 2001, St Petersburg, Russia, IFAC, p. 2767–2774.
    29. 29)
      • P. Gahinet , A. Nemirovskii , A.J. Laub , M. Chilali . (1995) The LMI control toolbox for use with matlab.
    30. 30)
      • M. Fliess , J. Lévine , P. Martin , P. Rouchon . Generalized controller canonical forms for linear and nonlinear dynamics. IEEE Trans. Autom. Control , 35 , 994 - 1001
    31. 31)
      • L.E. Ghaoui , G. Scorletti . Control of rational systems using linear fractional representations and linear matrix inequalities. Automatica , 39 , 1273 - 1284
    32. 32)
      • F. Chaplais , N. Petit . Inversion in indirect optimal control of multivariable systems. ASAIM: Control, Optimisation and Calculus of Variations , 2 , 294 - 317
http://iet.metastore.ingenta.com/content/journals/10.1049/iet-cta.2008.0057
Loading

Related content

content/journals/10.1049/iet-cta.2008.0057
pub_keyword,iet_inspecKeyword,pub_concept
6
6
Loading