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Digital adaptive control of a winged rocket applicable to abort flight

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Abstract

Since reusable launch vehicles (RLVs) operate in a wide range of flight conditions, the values of the parameters of the dynamic equations are not constant. Therefore, some adaptive control methods for RLVs have been proposed, and digital control systems which are suitable for digital computers. However, the control performance decreases when the nonlinearity strengthens, although linear adaptive control gives an excellent performance when the nonlinearity of the control system can be disregarded. In this article, we apply a digital adaptive feedback linearization control method with time-scale separation to a winged rocket in an abort case. The simulation results show the effectiveness of the control system.

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Abbreviations

δ a , δ e , δ r :

aileron, elevator, and rudder deflection angles, respectively

p, q, r :

rotational rates

α,β :

angle of attack and sideslip angle, respectively

φ, gq :

bank and pitch angles, respectively

L *, M *, N * :

coefficients of rolling, pitching, and yawing moments, respectively

I ij :

moment/product of inertia

V TAS :

true airspeed

References

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Author information

Authors and Affiliations

  1. Department of Control Engineering, Kyushu Institute of Technology, Tobata, Kitakyushu, 804-8550, Japan

    Tomoaki Shimozawa & Shinichi Sagara

Authors
  1. Tomoaki Shimozawa
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  2. Shinichi Sagara
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Corresponding author

Correspondence to Shinichi Sagara.

Additional information

This work was presented in part at the 16th International Symposium on Artificial Life and Robotics, Oita, Japan, January 27–29, 2011

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Cite this article

Shimozawa, T., Sagara, S. Digital adaptive control of a winged rocket applicable to abort flight. Artif Life Robotics 16, 348–351 (2011). https://doi.org/10.1007/s10015-011-0947-3

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  • DOI: https://doi.org/10.1007/s10015-011-0947-3

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