Study On Burning Law Of Single Chamber Dual Thrust Of Grain For Solid Rocket Motor

Single chamber dual thrust solid rocket motor is a propulsion system for rockets and missiles.Compared with dual chamber dual thrust solid rocket motor,the single chamber dual thrust solid rocket motor has the advantages of compact structure,light weight and high efficiency and so on,which let the structural performance,flight performance and use performance of the missile has significantly improved.So that the single chamber dual thrust grain has been widely used in rockets and missiles.In this paper,the burning law of slotted shape-end burning of single chamber dual thrust grain and annular-end burning single chamber dual thrust grain were analyzed and studied.The study of the burning law is by the method of geometry topology and method of mathematics analytic formula,by using UG software to draw 3D model,and to make numerical calculation by using MATLAB programming software.By doing these,summarize the burning law.The main tasks are as follows:Firstly,the impact of the disappeared order of the surface of launch stage was studied for the burning law of slotted shape-end burning of single chamber dual thrust grain.By adjusting the initial grain size to change the loss of key order and then burning surface disappear below.By using the method of mathematics analytic formula,the burning areas were derived,and the burning law of slotted shape-end burning of single chamber dual thrust grain was analyzed and summarized.The results show that,when other conditions are constant,the slotted top of launch stage disappears firstly and then the inner arc surface disappears,finally,the slotted end arc surface and the slotted side surface disappear at the same time,the burning law is better than other cases.Burning of continuous sail class is similar to constant.Secondly,the impact of the annular end surface area is coated of launch stage was studied for the burning law of annular-end burning single chamber dual thrust grain.By using the method of mathematics analytic formula,the burning area were derived,and the burning law of annular-end burning single chamber dual thrust grain was analyzed and summarized.The results show that,when other conditions are constant,the annular end surface of launch stage grain is half coated,the burning law is better than other cases.Burning of continuous sail class is similar to constant.Thirdly,the interior ballistic of the Single chamber dual thrust grain solid rocket motor was studied.The interior ballistic curve is calculated by using the program,which provides the basis for the strength checking of the motor and the calculation of the outer ballistic of the rocket and missile.Fourth,the characteristics of three kinds of single chamber dual thrust grain are compared and analyzed,by taking the Patriot PAC-3 engine as an example.The results show that when other conditions are constant,the performance of annular-end burning single chamber dual thrust grain is better than the other two grains.