This paper mainly focuses on the simulation and experimental study of the reliability of the solid rocket nozzle cover.The test-bed is designed according to the technical requirements in order to provide different sta...This paper mainly focuses on the simulation and experimental study of the reliability of the solid rocket nozzle cover.The test-bed is designed according to the technical requirements in order to provide different stamping rates and tests for different sizes of covers.The gas source,the four valves and the installation container structure are used to realize the stamping.The installation container is a multistage flange stacking structure to achieve the installation of different sizes of plugging covers,and then the opening process of the plugging cover is recorded by the high speed pressure sensor and the automatic control system.The fluid solid coupling method is used to simulate the impact state of plugging cover in the flow field at 10,20,30 and 35 ms,and the maximum pressure at 35 ms is 1.244 MPa.Then the deformation of aluminum alloy plugging cover is observed by stress analysis and display dynamic method.The maximum value of Von Mises Stress of the simulation result is 277.600 MPa.In the experimental test,the performance of the system is tested with a high strength plugging cover.In the opening state of the two large flux control valves,the pressure in the installation container reaches 1.000 MPa at 35 ms.And then we modify the experimental system with the knowledge of aerodynamic theory.Finally,the plugging cover is installed to carry out the experiment,so as to obtain the reliable stamping rate of the plugging cover.Simulations,blind measurements and measurement results provide strong data for reliability of the plugging cover opening,and provide reliable reference data for rocket engine charge structure and nozzle shape optimization.展开更多
文摘This paper mainly focuses on the simulation and experimental study of the reliability of the solid rocket nozzle cover.The test-bed is designed according to the technical requirements in order to provide different stamping rates and tests for different sizes of covers.The gas source,the four valves and the installation container structure are used to realize the stamping.The installation container is a multistage flange stacking structure to achieve the installation of different sizes of plugging covers,and then the opening process of the plugging cover is recorded by the high speed pressure sensor and the automatic control system.The fluid solid coupling method is used to simulate the impact state of plugging cover in the flow field at 10,20,30 and 35 ms,and the maximum pressure at 35 ms is 1.244 MPa.Then the deformation of aluminum alloy plugging cover is observed by stress analysis and display dynamic method.The maximum value of Von Mises Stress of the simulation result is 277.600 MPa.In the experimental test,the performance of the system is tested with a high strength plugging cover.In the opening state of the two large flux control valves,the pressure in the installation container reaches 1.000 MPa at 35 ms.And then we modify the experimental system with the knowledge of aerodynamic theory.Finally,the plugging cover is installed to carry out the experiment,so as to obtain the reliable stamping rate of the plugging cover.Simulations,blind measurements and measurement results provide strong data for reliability of the plugging cover opening,and provide reliable reference data for rocket engine charge structure and nozzle shape optimization.