A Rapid Gun Firing Correction Algorithm Using Discrete Time Transfer Matrix Method
Khalil, M., Rui, X., Hendy, H. (2015). A Rapid Gun Firing Correction Algorithm Using Discrete Time Transfer Matrix Method. EKB Journal Management System, 16(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015), 1-13. doi: 10.21608/asat.2015.23008
Mostafa Khalil; Xiaoting Rui; Hossam Hendy. "A Rapid Gun Firing Correction Algorithm Using Discrete Time Transfer Matrix Method". EKB Journal Management System, 16, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015, 2015, 1-13. doi: 10.21608/asat.2015.23008
Khalil, M., Rui, X., Hendy, H. (2015). 'A Rapid Gun Firing Correction Algorithm Using Discrete Time Transfer Matrix Method', EKB Journal Management System, 16(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015), pp. 1-13. doi: 10.21608/asat.2015.23008
Khalil, M., Rui, X., Hendy, H. A Rapid Gun Firing Correction Algorithm Using Discrete Time Transfer Matrix Method. EKB Journal Management System, 2015; 16(AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015): 1-13. doi: 10.21608/asat.2015.23008

A Rapid Gun Firing Correction Algorithm Using Discrete Time Transfer Matrix Method

International Conference on Aerospace Sciences and Aviation Technology
Article 69, Volume 16, AEROSPACE SCIENCES & AVIATION TECHNOLOGY, ASAT - 16 – May 26 - 28, 2015, May 2015, Page 1-13  XML PDF (346.09 K)
Document Type: Original Article
DOI: 10.21608/asat.2015.23008
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Authors
Mostafa Khalil1; Xiaoting Rui2; Hossam Hendy1
1Egyptian Armed Forces, Egypt.
2Professor, Institute of Launch Dynamics, Nanjing University of Science and Technology.
Abstract
To improve the next shot hit accuracy, a firing angle correction algorithm will be developed using the distance error computed between the impact and target coordinates to determine the launch azimuth and quadrant elevation angles for artillery projectiles. This correction method will be developed using the discrete time transfer matrix method of the projectile modified point mass model DTTMM-4DOF to improve correction method performance. To validate the proposed algorithm, a spin-stabilized 155mm-HE projectile flight trajectory will be used, assuming that wind magnitude and direction with the down range are changing as function of projectile altitude.
Keywords
Firing correction; Un-guided projectile; 4-DOF; Discrete Time Transfer Matrix; 105mm-HE; 155mm M107
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