Research On Heating Characteristics Of Thermostatic Chamber Of Rocket Launch Vehicle

Because the reliability of solid rocket is obviously affected by temperature,it is usually required to keep the rocket body warm before flight test,so it cannot be transported directly by ordinary transport vehicle.In this paper,a traction rocket launch test platform is taken as the research object,the air supply system of the thermal insulation bin is designed,and the temperature field and flow field of the rocket storage area in the thermal insulation bin of the launch vehicle are theoretically analyzed by using the research method of numerical simulation and experiment,and then the optimal air supply strategy is explored to achieve the purpose of uniform insulation.By introducing the composition and functions of each part of the mobile rocket launch test platform,the structure design of the thermal insulation bin is emphasized.According to the type and thermal insulation requirements of the test rocket,the multi-layer thermal insulation panel material and structure are selected to ensure the overall tightness of the cabin.After that,the main technology used in the numerical calculation of the temperature field inside the compartment is analyzed in detail,including the calculation of the heat preservation power and the theoretical air supply speed,which paves the way for the study of the temperature field distribution in the rocket storage area of the thermal insulation warehouse.Based on the idea and steps of modeling,the mathematical model and solid domain model of the thermal insulation cabin and air duct of the rocket launch vehicle are established.Then the fluid domain is derived and the appropriate boundary conditions are determined.The grid tool is used to mesh the calculation area.The governing equations are solved according to the theoretical basis of fluid mechanics and simulation method,and the flow characteristics of high temperature air flow in the thermal insulation cabin are analyzed The detailed distribution of temperature field and velocity field on the characteristic section is obtained by numerical simulation.Then the influence of inlet velocity on the temperature distribution in the rocket storage area is studied.Finally,the thermal insulation performance test is carried out under the condition that the upper part of the thermal insulation cabin and the tail cabin door are closed,which is prepared for the next study of the heat transfer analysis of the grain in the thermal insulation cabin.The temperature distribution of solid rocket motor grain under insulation temperature is studied.Based on the physical parameters of the rocket motor section,a model is established.The internal heat transfer process of the rocket motor section in the insulation process is simulated by using the finite element analysis software.The temperature change curve and the temperature distribution of the grain at different positions are obtained temperature time has made accurate judgment and verification.The design and research work of this paper provides a theoretical method for the design of similar thermal insulation cabin and the selection of air supply strategy.