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Pulse-frequency modulated guidance laws for a mortar missile with a pulse jet control mechanism

Published online by Cambridge University Press:  27 January 2016

M. Pavic ,
B. Pavkovic ,
S. Mandic ,
S. Zivkovic  and
D. Cuk
B. Pavkovic
Affiliation:
Military Technical Institute, Belgrade, Serbia
S. Mandic
Affiliation:
Military Technical Institute, Belgrade, Serbia
S. Zivkovic
Affiliation:
Military Technical Institute, Belgrade, Serbia
D. Cuk
Affiliation:
Faculty of Mechanical Engineering Belgrade, Serbia
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Abstract

The impact point dispersion of mortar missiles can be drastically reduced with a control ring of lateral pulse jets located around the centre of gravity and a homing head to measure or to derive estimates of appropriate missile-target states, e.g. the line-of-sight rates. A simulation model including a missile as a six-degree-of-freedom vehicle, a jet pulse flight control system, and a relative missile-to-target motion was used for the comparison of four guidance laws i.e. proportional navigation guidance, augmented proportional navigation, augmented proportional navigation with rendezvous, and adaptive sliding-mode guidance. This paper focuses on the efficiency of pulse jet control on miss distance, and thus makes the assumption that sensor measurements and the guidance states required to apply each of the guidance laws are perfectly known. Proportional navigation and the adaptive sliding mode guidance exhibit a large miss distance due to limited control authority. Augmented proportional navigation is slightly better than augmented proportional navigation with rendezvous for the same design parameters and they both give small miss distances with limited control authority, but they both require a free gyro. A proper selection of the design parameters — the number of pulse jets and the magnitude of the individual pulse jet thrust for a particular dispersion of flight parameters and the instant of the guidance start — is required to achieve optimum dispersion reduction. The minimum intensity of the individual pulse jet impulse required for the ‘pin point’ accuracy (the circular error probable smaller than 1m) of the mortar missile was determined for all presented guidance laws considering dispersion from the nominal trajectory.

Type
Research Article
Information
The Aeronautical Journal , Volume 119 , Issue 1213 , March 2015 , pp. 389 - 405
Copyright
Copyright © Royal Aeronautical Society 2015

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References

1.Jitpraphai, T., Burchett, B. and Costello, M. A comparison of different guidance scheme for a direct fire rocket with a pulse jet control mechanism, 2002, Rept ARL-CR-493, Army Research Laboratory, Aberdeen Proving Ground.CrossRefGoogle Scholar
2.Jitpraphai, T. and Costello, M.Dispersion reduction of a direct fre rocket using lateral pulse jets, J Spacecraft and Rockets, 2001, 38, (6), pp 929–936.CrossRefGoogle Scholar
3.Gupta, S.K., Saxena, S., Singhal, A. and Ghosh, A.K.Trajectory correction flight control system using pulse jet on artillery rocket, Def Sc J, 2008, 58, (1), pp 15–33.CrossRefGoogle Scholar
4.Pavkovic, B., Pavic, M. and Cuk, D.Frequency-modulated pulse-jet control of an artillery rocket, J Spacecraft and Rockets, 2012, 49, (2), pp 286–294.CrossRefGoogle Scholar
5.Fresconi, F.Guidance and control of a projectile with reduced sensor and actuator requirements, J Guidance, Control and Dynamics, 2011, 34, (6), pp 1757–1766.CrossRefGoogle Scholar
6.Glebocki, R., and Vogt, R.Guidance system of smart mortar missile, The Arch Mech Eng, 2007, 54, (1), pp 47–63.Google Scholar
7.Rogers, J. and Costello, M.Design of a roll-stabilized mortar projectile with reciprocating canards, J Guidance, Control and Dynamics, 2010, 33, (4), pp 1026–1034.Google Scholar
8.Regan, F.J.Aeroballistics of a terminally corrected spinning projectile (TCSP), J Spacecraft, 1975, 12, (12), pp 733–738.Google Scholar
9.Cuk, D.Trajectory correction of gyroscopic stabilized projectile using proportional navigation, Military Tech Courier, 2010, 58, (1), pp 13–32.Google Scholar
10.Zarchan, P.Tactical and strategic missile guidance, Third Edition, Prog in Astronautics and Aeronautics, 176, 1997, Chaps 2, 6, 8, AIAA, Washington, DC, USA.Google Scholar
11.Ben-Asher, J.Z. and Yaesh, I.Advances in missile guidance theory, Prog in Astronautics and Aeronautics, 1998, 180, pp 25–88, AIAA, Reston, VA, USA.Google Scholar
12.Zhou, D., Chundi, M. and Wenli, X.Adaptive sliding-mode guidance of a homing missile, J Guidance, Control and Dynamics, 1999, 22, (4), pp 589–594.CrossRefGoogle Scholar
13.Etkin, B. and Reid, L.D.Dynamics of Flight Stability and Control, Third edition, 1996, Chap 4, John Wiley and Sons, New York, USA.Google Scholar