Sliding Mode Guidance Law Considering Missile Dynamic Characteristics and Impact Angle Constraints

  • Hui-Bo ZhouEmail author
  • Jun-Hong Song
  • Shen-Min Song
Research Article


In order to improve the precision of guidance for the missile intercepting maneuvering targets, this paper proposes a sliding mode guidance law with impact angle constraints based on the equation of the relative motion of the missile and the target in a 2D plane. Two finite-time convergent guidance laws are proposed based on the nonsingular terminal sliding mode, while, two exponential convergent guidance laws involving dynamic delay are developed through applying the higher-order nonsingular terminal sliding mode. The simulations denote that, in all the four scenarios of the target’s maneuvering, the guidance laws are able to inhibit the chattering phenomenon of the sliding modes effectively; and from an expected aspect angle, the missiles could attack the targets with high precision and fast speed.


Autopilot impact angle nonsingular terminal sliding mode finite-time convergent guidance 


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Copyright information

© Institute of Automation, Chinese Academy of Sciences and Springer-Verlag GmbH Germany, part of Springer Nature 2016

Authors and Affiliations

  1. 1.School of Mathematical SciencesHarbin Normal UniversityHarbinChina
  2. 2.Center for Control Theory and Guidance TechnologyHarbin Institute of TechnologyHarbinChina

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