Research On Horizontal Thrust Test System Of Solid Rocket Motor

Focusing on the rapid progress of aerospace industry and aircraft technology,thrust vectoring measurement technology has also become a key research direction of various countries.Engine is the core component of aerospace vehicle power system,accurate measurement of thrust vector of the engine is very important to improve engine life and ensure the safety of using.In order to obtain various performance-related parameters of the thrust vector generated by the rocket engine,it is necessary to carry out rigorous thrust test experiments before the engine is officially used to ensure accuracy of the test results.In addition,as the solid propellant is in the combustion process,the mass and center of mass of the rocket engine will change over time,which will affect the test results.In particular,it affects the test accuracy of the test system in the vertical direction.This feature makes the test accuracy of the thrust vector more challenging.According to the test requirements of the solid rocket motor thrust vector,a solid rocket motor horizontal thrust vector test system is developed in this paper.The performance of the test system is verified by the thrust vector loading device,and the influence of the solid propellant mass/centroid change on the test performance is further explored,which has important research significance for improving the measurement accuracy of the horizontal thrust vector test system.The theoretical mechanics model of the test system is established.Based on the six-dimensional force measurement principle of the piezoelectric dynamometer,the layout of the dynamometer is selected.In this paper,the theoretical mechanical model of the thrust vector test system under the arrangement of the four-point support dynamometer is established,and the force state of each force measurement unit is analyzed mechanically,which laid a theoretical foundation for the follow-up research.The overall structure design of the test system is completed.According to the design difficulties and requirements of the engine thrust vector calibration and simulation device,in order to ensure the high stiffness,high strength and high natural frequency of the test device,the structural design of the three-way force calibration loading device and the vector force simulation loading device are carried out,and the engine model is selected.The software ANSYS is used to simulate the force of the key device structure in the test system.The static and dynamic calibration experiment of the test system is carried out.Through the six-dimensional force calibration loading device,a static calibration experiment was carried out on the four force measuring units that make up the test system.In this paper,a horizontal thrust vector test system is built.Through the three-way calibration experiment,the static performance indicators of the test system are obtained in all directions.Further carried out the deflection simulation loading experiment,the test research of the vector force is truly simulated,and the error analysis and research of the test device are carried out.The three-way natural frequency of the overall test system is obtained through dynamic percussion experiments.Through the experimental results,it can be obtained that the static and dynamic performance of the thrust vector test system meets the test requirements.And the high-precision measurement of the solid rocket motor thrust vector can be achieved.Simulated loading experiments of mass/centroid changes are completed.The engine model is installed on the horizontal thrust vector test system,and the all-directional performance of the test system after the installation of the model is obtained through the three-way calibration experiment,which meets the test requirements.Aiming at the influence of the change in the weight of the solid rocket motor during the working process,a mass/center of mass simulation loading experiment is designed,the test accuracy of the test system is studied,and the error is analyzed and compensated.