| In the process of designing a container-type vertical hot launching system that using both rudder and deflector,the interaction between the structure and the gas flow has a great influence on distribution of gas flow.Unreasonable device design can lead to improper distribution of gas flow force and thermal load on the launching device,and thus increases the erosion effect on the system structure,which is not conducive to improving the structural compatibility of the system.There are few studies on the structural compatibility of the launching system with gas rudder vector control device around the world,so this article focus on the container-type vertical hot launching system and its gas flow field characteristics and structural compatibility in the launch process,and analyze the mutual influence between the two.The research results are in good agreement with the experiments.It is of great significance to the engineering research of the container-type vertical hot launching system and to reducing or preventing the backward-ejecting flow phenomenon during the launching.The main research content is as follows:1.Based on the establishment and adjustment of the numerical model and the verification of the scaled tests,the jet is divided into three zones according to the gas flow field characteristics of the container-type vertical hot launching system: 1)gas flow from the engine nozzle inlet to the gas engine rudder downstream,which is affected by the flow field around the gas nozzle and forms a complex rudder peripheral flow field;2)gas flow from the gas engine rudder downstream to the flow deflector,where the mainstream structure of gas has gradually developed into a special “X” shape and hits the deflector;3)the gas flow affected by the interaction between the rudder and the deflector flows back from the upper guide surface of the deflector to the launching box,which is developed into the rewinding backflow and the backward-ejecting flow.The phenomena and the characteristics of the flow field in the various zones,and its impact on the system structure are discussed.2.Two calculation models for rudders in container-type vertical hot launching devices were established.The study on the formation and propagation of the initial shock wave before opening the cover and the thermal environment inside the launching box shows that the impact pressure on the wall and the bottom of the launch box is less affected by the rudder,but its temperature increases around 16% with rudder.The study on the mechanism of the change of the structure of the gas flow field after the cover was opened shows that its shape was gradually changed to the "X" shape by the influence of the rudder,and the high temperature and high pressure region on the deflector was also the "X" type.Compared with the structure without rudder,the maximum pressure value is reduced by 20%,and the shock on the guide surface under the adjacent box is weakened.The study on the phenomenon of backflow of the gas flow after opening the cover shows that the effect of the backflow on the pressure of the launching device is small.However,the maximum value of the wall temperature of the launching box and the temperature of the missile base increased by 171.09%and 125.44% respectively.3.Analyzed the air-solid two-phase flow field of solid aluminum-containing propellant and combustion-produced gas containing solid particles of alumina under the interaction of the rudder and the deflector,and its erosion and deposition effects on deflector.The results show that the addition of the rudder has a great influence on the flow field of the gas-solid two-phase flow,which not only aggravates the erosion of the deflector by the particles,but also increases the impact on the wall of the launching box.The maximum pressure and the maximum temperature of the launching box are increased by approximately 10% and211.30%.Similarly,the changes in pressure and temperature at the base of the missile are basically the same as those in the wall of the launcher.4.The different flow field effects of plane deflector and arc deflector were studied.The study on the effect of the gas flow discharge shows that the angle of the gas flow that flows vertically downwards is equal to the angle of the plane deflector everywhere,and the angle between the flow and the circular arc guide surface is not equal in any place.The stagnation point of the circular arc guide surface can be used as the boundary which divides the guide surface into upper and lower parts,and the arc-shaped deflector accelerates the downward flow of the gas flow while the wallop is lower than that of the planar deflector.At the same time,the upward flow of the gas flow is inhibited and the impact is sustained compares with the flat deflector.The analysis of the gas flow back-injection phenomenon shows that the average value of the temperature at the base of the inclined plane deflector model and the average value of the pressure increase by about 8%,and the maximum temperature and the maximum pressure of the wall of the launching box increase by about 17% and 19%.Therefore,the arc deflector is more suitable for vertical double-loaded launch.5.A calculation model for the different distances between the nozzle outlet and the deflector(the gas flow impact height)was established,and the impact of the gas stream impact height was analyzed.The calculation model of the variable parameters of different missile-box gaps was established,and the state of the model was analyzed before and after the opening of the rear cover.Taking the distance from the outlet of the nozzle to the deflector and the missile-box gaps as two variables,and the average temperature of the missile base and the maximum temperature of the wall of the launch box as the target evaluation indicators,two sets of response surfaces are obtained by fitting.The results show that the thermal impact of the ejector is positively correlated with the height of the nozzle from the guiding surface and the gap between the shells.The thermal impact of the jet on wall surface of the launcher is negative correlated with the height of the nozzle from the guiding surface but positive correlation with missile box clearance.7.By adding a bottom baffle ring,the gas flow in the gap of the launch box is changed,thereby improving the thermal environment of the missile box clearance,including the flow field characteristics of the space where the airfoil is located.The addition of a baffle ring reduces the impact of the gas flow on the walls of the launch box,but it also has an adverse effect,which intensifies the impact on the missile base.By changing the inner diameter and height of the baffle ring,the impact on the ground was optimized and analyzed.It was concluded that the impact of the height of the baffle ring on the missile base was less than the impact of the inner diameter of the baffle ring,and the impact of the baffle ring height on the wall surface of the launch box was greater than the impact of the inner diameter of the baffle ring.The baffle ring satisfies the requirements for the compatibility of the wall surface of the launch box and the missile base. |
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