Design Of Individual Penetration Projectile

In order to meet the demands of the new form of war and improve the weapon system,a penetration rocket that can be carried and used by individual soldier and mounted on unmanned combat platforms was designed in this paper.The equipment is light in weight and small,which can be used for striking living targets in civil fortifications,light armored vehicles,and buildings.To meet the low load requirement during launching,the projectile was designed as a trajectory scheme in which the projectile ignited by the engine and accelerated in the air after ejected at certain muzzle velocity and then flying at the maximum speed.The ballistic coefficient of ammunition was analyzed and calculated in comparsion with the external ballistic parameters of similar projectiles.The key parameter of the firing angle was calculated by Materlab software.2.3° was selected as firing angle for the external ballistic scheme.The penetration warhead was also designed for miniaturization to meet relevant requirements.According to the existing research theory,the warhead shape optimized.The double cone shape was designed.For the limitation of the warhead diameter at 40 mm,the double cone angle is selected to be 110° and 15°,respectively.Due to the complexity of warhead penetration into steel plates,the penetration capability of the warhead is assessed by using energy consumption theory according to practical experience.Through theoretical calculation,the projectile penetration into sandbags is more than 1,300 mm,for a brick wall,it is 600 mm,for concrete,it is 391 mm,and for homogeneous military steel plates,it is more than 15 mm.Therefore,the warhead design scheme meets the design requirements.For ensuring the penetration speed of ammunition and the requirement of ammunition miniaturization,the appropriate shape for loading the ammunition was chosen according to its characteristic for existing propellor engine for individual soldiers.According to the limitation of the size of the engine,the important parameter of the engine,that is nozzle area,was selected after setting the size and mass of the ammunition.The design scheme with a throat diameter of 8 mm was selected through simulation by Materlab.The balance pressure of the engine is 13 MPa,the total impulse is 324 N ? s,the thrust is 981 N,and the working time is 0.33 s.It can be seen that the solid rocket motor has low pressure and large thrust,which meets the design requirements.The mechanical characteristic of the engine components was analyzed by the 3D design software and the strength of each part is checked.The results show that the strength design of each part is reasonable.The projectile needs a higher stable reserve in order to ensure the flight stability of the projectile.The tail wing is designed specifically and its maximum outer diameter is set as 40 mm in the folded state.The three-dimensional design software is used to simulate and assemble the projectile.The center of mass and pressure of the projectile were calculated according to the aerodynamic principles.The stable reserve is more than 20%,which meets the design requirements.After the design of the projectile’s exterior trajectory and the subsystems,a weapon with a strong ability to penetrate multiple targets has been completed,which is suitable for individual use and capable of being used by multiple unmanned platforms.