Monte-Carlo Based Lateral Thruster Parameters Optimization for 122 mm Rocket
- 79 Downloads
One of the current tendencies is to equip the unguided munition designed for ballistic shooting with low cost, solid propellant lateral thrusters based, actuators to achieve the controlled flight functionality and reduce the collateral damage. The basic technical challenge connected with this type of pulsed control system is that each from the thrusters could be used only once which results in projectile low control authority. The thruster parameters have crucial impact on the achieved hit accuracy. The main goal of this article was to investigate and understand the influence of control force magnitude on the guidance process using six-degree-of-freedom numerical simulation. 122 mm artillery rocket controlled with the aim of 30 solid propellant thrusters mounted before center of mass was chosen as a test object. Single channel control was considered. The impact point prediction algorithm based on point mass model was developed and implemented into a Matlab software. Using Monte-Carlo simulations the optimum lateral thruster force amplitude was obtained for shots at low elevation angle. The numerical experiments showed that with the proposed method the circular error probable of the projectile might be reduced 10 times when compared to unguided case.
KeywordsMonte-Carlo Lateral thruster Impact point prediction guidance
This work was supported by The National Centre for Research and Development (NCBiR) under project DOB-BIO8/10/01/2016 “Projectiles control system technology development”.
- 1.Pavković, B., Pavić, M., Ćuk, D.: Enhancing the precision of artillery rockets using pulsejet control systems with active damping. Sci. Tech. Rev. 62(2), 10–19 (2012)Google Scholar
- 4.Guo, Q.-W., Song, W.-D., Gao, M., Fang, D.: Advanced guidance law design for trajectory-corrected rockets with canards under single channel control. Eng. Lett. 24(4), 469–477 (2016)Google Scholar
- 7.Drescher, T., Nielson, J.: Rocket trajectory correction using strap-on GPS guided thrusters. In: IEEE 1998 Position Location and Navigation Symposium (Cat. No. 98CH36153), Palm Springs (1998)Google Scholar
- 8.Jitpraphai, T., Burchett, B., Costello, M.: A comparison of different guidance schemes for a direct fire rocket with a pulse jet control mechanism. In: AIAA Atmospheric Flight Mechanics Conference and Exhibit, Guidance, Navigation, and Control and Co-located Conferences (2001)Google Scholar
- 10.Gross, M., Costello, M., Fresconi, F.: Impact point model predictive control of a spin-stabilized projectile with instability protection. In: AIAA Atmospheric Flight Mechanics (AFM) Conference, Boston (2013)Google Scholar
- 11.Gagnon, E., Lauzon, M.: Course correction fuze concept analysis for in-service 155 mm spin-stabilized gunnery projectiles. In: AIAA Guidance, Navigation and Control Conference and Exhibit, Honolulu (2008)Google Scholar
- 13.Krasnov, N.F.: Rocket Aerodynamics (NASA Technical Translation). National Aeronautics and Space Administration (1971)Google Scholar
- 14.Department of Defense: MIL-HDBK-762 Design of Aerodynamically Stabilized Free Rockets. United States Department of Defense (1990)Google Scholar
- 15.National Aeronautics and Space Administration: U.S. Standard Atmosphere 1976, Washington, D.C. (1976)Google Scholar
- 21.Zhang, Y., Gao, M., Yang, S., Fang, D.: Optimization of trajectory correction scheme for guided mortar projectiles. Int. J. Aerosp. Eng. 2015, 1–14 (2015)Google Scholar
- 22.Park, W., Yun, J., Ryoo, C.-K., Kim, Y.: Guidance law for a modern munition. In: International Conference on Control, Automation and Systems 2010, Gyeonggi-do (2010)Google Scholar