The artilleries have been the part of many armies over the long history and have evolved over the time into a complex system to have better accuracy, ease of use, and most importantly having a larger range. Use of base bleed unit is one of the widely used methods to enhance the range of the shell, which primarily reduces the base drag of the shell by injecting hot gases in the rear end Gany (1991); Zhang and Zheng (2018). To enhance the range further, it requires to propel the shell further by mean of an active propulsion during the flight. The solid rockets have been used for this propose. A solid fuel ramjet (SFRJ) due to its certain advantages over a solid rocket, is another promising way to provide propulsion to an artillery shell. Being an air-breathing engine, ramjet has higher Isp (> 4000 N s/kg) compared to that of a solid rocket (∼2500 N s/kg) and therefore provides much higher overall impulse to the shell for the same mass of propellant. In spite of advantages of a ramjet over a rocket engine, it has not been incorporated in artillery shell till date. A Norwegian company ‘NAMMO’ unveiled a prototype of a 155 mm-ramjet propelled artillery shell recently. The viability of use of a ramjet for this application had been in question primarily because, it is quite challenging to realize a ramjet engine in the given geometrical constraints set by the gun used to propel the shell, and yet maximize its performance to obtain an overall improvement in the range. The primary objective of this work was to explore the possibility of using ramjet to propel an artillery shell and estimate the possible enhancement in range. As first step towards the intended objectives, a MATLAB-Simulink based trajectory simulation was developed to estimate the trajectory of a ramjet propelled artillery shell. As, the thrust produced by a ramjet depends on the altitude of its operation, it requires to analyze its propulsive performance at each altitude to obtain the accurate trajectory of the shell. The methodology followed for the same has been presented in the thesis. The overall length of the shell is restricted by the fixed length of the combustion chamber of the gun. One of the challenges involved for a ramjet to be used in current application is to have high combustion efficiency with restricted secondary combustor length. This problem was addressed by two ways. One, the efforts were made to develop aluminized, Hydroxyl-terminated polybutadiene (HTPB) based fuel-rich propellants to have high burn rates, low residue and reduced residence time. As suggested in literature (Chittilapilly et al., 1990; Zhongqin et al., 1986), another way explored to improve the combustion efficiency was the use of multiple annular primary nozzles to enhance the mixing of air-fuel rich gases in secondary chamber. The various fuel-rich propellants were developed with the flake like aluminium (Al), referred as ‘Pyral’, to have high burn rates as suggested by Verma and Ramakrishna (2013). Following the work by Gaurav and Ramakrishna (2016); Gaurav and Ramakrishna, the use of polytetrafluoroethylene (PTFE) and Viton were explored to increase the reactivity of Al. The use of Iron oxide (IO) embedded ammonium perchlorate (AP) (Gaurav et al., 2013) and KP as an oxidizer were studied experimentally to examine their effect on the ballistic properties of the propellant. The fuel-rich propellant with 34.3 % AP, 0.7 % IO, 40.5 % Al, 4.5 % Viton and 25 % HTPB based binder was identified as a suitable candidate among the propellants developed for the current application, due to its high burn rates and pressure index r¤ = 0.92P 0.47, observed residue lower than 3 %, and high specific impulse density, Isp−den. The experiments to study the performance of a ramjet in terms of the combustion efficiency, ηc, were carried out. The ramjet setup in dual-combustor configuration having secondary combustor of L/D ratio of 1.8 was developed. The primary nozzle with six annularly symmetrically placed orifice was used to inject the fuel-rich gases into the airstream at an angle of 45 °to enhance the mixing. The ramjet with the identified fuel-rich propellant F3A was observed to provide an average combustion efficiency of 91.5 % The possible enhancement in range of an artillery shell by use of a ramjet was estimated using the trajectory simulation software developed. Considering the inputs from the experiments, the various trajectories of a ramjet propelled artillery shell having different design conditions in terms of thrust and A/F ratio at sea level were obtained. It was found that the ramjet producing a thrust of 1.6 times of the drag at sea level, with initial A/F ratio of 10 increases the range of the shell to around 89.7 km, which is a significant enhancement in range considering the current range of 24 km without a ramjet assistance.