Modified trajectory tracking guidance for artillery rocket
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Warsaw University of Technology, Warsaw, Poland
Submission date: 2019-08-09
Final revision date: 2019-09-29
Acceptance date: 2019-10-25
Online publication date: 2020-07-15
Publication date: 2020-07-15
Corresponding author
Mariusz Adam Jacewicz   

Faculty of Power and Aeronautical Engineering, Warsaw University of Technology, Nowowiejska, 00-665, Warsaw, Poland
Journal of Theoretical and Applied Mechanics 2020;58(3):611-622
This paper contributes to a modified guidance scheme based on a trajectory tracking method which is dedicated for an artillery rocket with a finite set of single use solid propellant side thrusters. Frequency modulation of pulses was used to achieve effective firing logic. The proposed control law is applicable in the last phase of flight when the rocket reaches the vertex of the trajectory. A correction engine activation sequence was chosen in such a way that possibility of rocket axial unbalance is minimized due to motors firing. Numerical simulation results indicate that significant dispersion reduction was achieved and the number of activated side rocket thrusters is minimized.
Cao X. B., Xu Y. C., Rui C., Y., Shan Z., Y., 2013, Simulation of trajectory correction for an impulse control mortar projectile with a strapdown laser seeker, Applied Mechanics and Materials, 367, 377-381, DOI:
Gao M., Zhang Y., Yang S., 2015, Firing control optimization of impulse thrusters for trajectory correction projectiles, International Journal of Aerospace Engineering, 2015, 1-11, DOI: 10.1155/2015/781472.
Gupta S.K., Saxena S., Singhal A., Ghosh A.K., 2008, Trajectory correction flight control system using pulsejet on an artillery rocket, Defence Science Journal, 58, 1, DOI: 10.14429/dsj.58.1621.
Jitpraphai T., Burchett B. Costello M., 2001, A comparison of different guidance schemes for a direct fire rocket with a pulse jet control mechanism, AIAA Atmospheric Flight Mechanics Conference and Exhibit, Guidance, Navigation, and Control and Co-located Conferences, DOI: 10.2514/6.2001-4326.
Jitpraphai T., Costello M., 2001, Dispersion reduction of a direct-fire rocket using lateral pulse jets, Journal of Spacecraft and Rockets, 38, 6, 929-936, DOI: 10.2514/2.3765.
Mandić S., 2009, Guidance of ground to ground rockets using flight path steering method, Scientific Technical Review, LIX, 3-4, 3-11, UDK: 623.465.3.
Mccoy R., 2004, Modern Exterior Ballistics: The Launch and Flight Dynamics of Symmetric Projectiles, Schiffer Publishing, Ltd.
Moore F., 1993, State-of-the-art Engineering Aeroprediction Methods with Emphasis on New Semiempirical Techniques for Predicting Nonlinear Aerodynamics on Complete Missile Configurations, Naval Surface Warfare Center, Dahlgren, Virginia.
Pavic M., Pavkovic B., Mandic S., Zivkovic S., Cuk D., 2015, Pulse-frequency modulated guidance laws for a mortar missile with a pulse jet control mechanism, The Aeronautical Journal, 119, 1213, 389-405, DOI: 10.1017/S0001924000010526.
Pavkovic B., 2012a, Enhancing the precision of artillery rockets using pulsejet control systems with active damping, Scientific Technical Review, 62, 2, 10-19, UDK: 621.453/457.001.57:519.637.
Pavkovic B., Pavic M., Cuk D., 2012b, Frequency-modulated pulse-jet control of an artillery rocket, Journal of Spacecraft and Rockets, 49, 2, 286-294, DOI: 10.2514/1.A32133.
Siddiq K.M., Jian C.F., Wen B.Y., 2012, State dependent Riccati equation based roll autopilot for 122mm artillery rocket, International Journal of Aerospace and Mechanical Engineering, 6, 12.
Zipfel P., 2014, Modeling and Simulation of Aerospace Vehicle Dynamics, American Institute of Aeronautics and Astronautics, Inc.
Żugaj M., Głębocki R., 2010, Model of gasodynamic control system for guided bomb, Journal of Theoretical and Applied Mechanics, 48, 1, 27-44.
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