变推力固体火箭发动机喉栓型面的逆向设计

The design of pintle profile directly determines the variation of actual throat area in nozzles, which significantly affects the thrust adjustment of pintle solid rocket motors(SRM). From the perspective of SRM design requirements, this article discussed the reverse design method of pintle profile,and the profile is reverse designed based on the required thrust variation relationship, and the reverse design results were verified through numerical simulation. The control equation system for pintle profile of conical nozzles was derived, then the profile was designed by solving the equation system combined with the relationship between equivalent throat area and the stroke of the pintle. Then an method for determining the relationship between equivalent throat area and the stroke of pintle was proposed, and a complete design process for pintle profile was established. With the objective of linear variation of thrust with the stroke of pintle, two-dimensional axisymmetric steady-state numerical simulation method was used to verify and analyze multiple design cases. The results show that the linearity of thrust with the stroke of pintle is higher than 0.996, and the reverse design of pintle profile can adequately meet the linearity requirements. An empirical formula for the ratio of load of pintle to thrust was proposed, and average deviation of this ratio is within 5%. The reverse design method of pintle profile proposed in this article has a wide range of applicability and can effectively support the advanced design of variable thrust solid rocket motors.