CAJ | 학술논문

某固体火箭发动机滚动球窝喷管运动过程中，其接头内部和阴球、阳球及支撑体在滚动体的接触碰撞作用下，运动及受力、变形状态复杂，无法试验测量，是系统结构设计和功能发挥的关键问题。为解决系统运动性能，模拟热试车试验，采用单方程湍流模型计算喷管内流场，得到系统推力；建立系统刚柔耦合多体动力学模型，计算分析系统及接头内部主要构件的运动规律、接触应力及变形。在预研阶段，以检验系统结构设计和运动性能的合理性，同时为机械类固体火箭发动机推力向量控制系统的研制提供更实用和可行的理论分析方法。
모고체화전발동궤곤동구와분관운동과정중，기접두내부화음구、양구급지탱체재곤동체적접촉팽당작용하，운동급수력、변형상태복잡，무법시험측량，시계통결구설계화공능발휘적관건문제。위해결계통운동성능，모의열시차시험，채용단방정단류모형계산분관내류장，득도계통추력；건립계통강유우합다체동역학모형，계산분석계통급접두내부주요구건적운동규률、접촉응력급변형。재예연계단，이검험계통결구설계화운동성능적합이성，동시위궤계류고체화전발동궤추력향량공제계통적연제제공경실용화가행적이론분석방법。
The motion force,complexity deformation and immeasurability of the mechanism are key problems in the system de-sign and performance requirement,when the ball,concave sphere,convex sphere and supporting body are under the rolling body con-tact impacting,in the rolling ball joint socket nozzle of a certain solid propellant rocket motor. In order to solve the dynamic perform-ance problems of the system,Spalart-Allmaras turbulence model was used in the calculation of nozzle flow field to simulate the igni-tion test and obtain the system thrust. Coupled rigid and flexible multi-body dynamics model was established. Characteristics of mo-tion on the system parts,contact stress and deformation were computed and analyzed. Analysis results verify rationality of system de-sign and kinematic characteristics in the pre-research state. A practical and feasible way for design of solid propellant rocket motor thrust vector control system was provided.