RESEARCH ON LOW OVERLOAD EJECTION OF SMALL PROJECTILE BASED ON PROPELLANT GAS

Abstract

With the rapid development of artificial intelligence technology, intelligent projectile is gradually becoming an indispensable weapon in modern high-tech war. Small low-cost intelligent projectile has the advantages of good concealment, strong mobility and high combat efficiency cost ratio [1-2]. The development of intelligent projectile is an important link in the process of carrying out combat tasks, which directly determines whether the aircraft can take off smoothly [3]. Small low-cost intelligent projectile must meet two conditions: (1) have a certain high orbit speed to maintain aircraft stability; (2) In order to meet the demand of low cost, the impact overload borne by the guiding head, communication module and other components of projectile is limited, that is, the launching process of projectile must have low overload characteristics. Scholars from various countries have developed extensive and indepth research on the ejection methods of small projectiles, including high-pressure gas ejection [4], electromagnetic ejection [5], rocket assisted ejection [6], artillery direct launch [7] and ejection launch [8].According to the low overload ejection requirements of a small low cost intelligent projectile, a method was proposed to realise low overload ejection of the small projectile by using propellant gas based on the high-low pressure launching theory. The interior ballistic mathematical model of the projectile ejection was established and the numerical simulation was finished. Based on the simulation result, a low overload ejection device for propellant gas was designed. With this device, an ejection experiment study of the small intelligent projectile was carried out. The test results indicate that while the impact overload of the projectile is less than 60g ， the velocity the projectile leaving the barrel is more than 45m/s. The experimental results show that it is feasible to realize low overload ejection of small projectile by using propellant gas. The simulation results agree well with the test . The mathematical model can describe the projectile ejection process well. The research work provides theoretical and experimental basis for realizing low overload ejection process of small low cost intelligent projectile by using propellant gas.