H. Karami Mazraeshahi; S. A. R Jalali-Chimeh; M. Naderi-Tabrizi
Volume 4, Issue 2 , January 2012, , Pages 35-46
Abstract
In this paper the apparent velocity regulation system has been studied and simulated. The objective of this system is to adjust the missile’s fight velocity with the predetermined value, in specified time steps. In fact the apparent velocity regulation system calculates and changes the thrust of ...
Read More
In this paper the apparent velocity regulation system has been studied and simulated. The objective of this system is to adjust the missile’s fight velocity with the predetermined value, in specified time steps. In fact the apparent velocity regulation system calculates and changes the thrust of the engine (pressure of the combustion chamber) in order to accomplish the desired fight velocity. For this purpose, a dynamic simulation for the propulsion system and also the missile’s flight has been developed. After analyzing the results, it is revealed that using the apparent velocity regulation system; the flight’s range accuracy will be improved dramatically. Comparing two similar missiles, with a same disturbance; one equipped with the apparent velocity regulation system and the other not, revealed that using such a controlling system will keep the accuracy of the target hitting within 200 meters while in the absence of it, the error would be more than 1.5 kilometers
M. Naderi Tabrizi; S. A. R. Jalali Chimeh; H. Karimi
Volume 3, Issue 2 , January 2011, , Pages 31-43
Abstract
In this article the Propellant Utilization system (PU) has been simulated. The objective of this system is to adjust the consumption ratio of the propellants in order to ensure the minimum propellant residuals at engine’s shutdown phase. Using the PU system, the orbital or range and also the payload ...
Read More
In this article the Propellant Utilization system (PU) has been simulated. The objective of this system is to adjust the consumption ratio of the propellants in order to ensure the minimum propellant residuals at engine’s shutdown phase. Using the PU system, the orbital or range and also the payload capabilities of missiles or launch vehicles will be enhanced. In this article, after studying and simulation of the PU system, the necessity of using such system is compared with a missile without the PU system. At the end of this paper it is proven that using PU system on a desired missile has enhanced its range up to 7 percent and has also reduced the propellant residuals up to 25 percent.
