Study On Bonding And Testing Techonology Of Thermal Protection System

Hypersonic aircraft has the characteristics of h igh maneuverability and long-range precision strikes,and its role in national security is very important.However,because it needs to fly in the atmosphere at high speed for a long time and faces a severe aerodynamic thermal environment,it needs a therm al protection system to protect the temperature of the equipment very well.Therefore,our paper focuses on the bonding process of materials such as insulation tiles in the thermal protection system.We use comparative test method to analyze the different influences of the diluent,including the thickness of the adhesive layer,the surface state of the base material,as well as the bonding strength.What’s more,we design the bonding curing system,the main of that is the feasibility of the device.Then we verify the function of bounding curing system by the loading device and the conformal loading process test.Besides,the methods for monitoring and performance testing are proposed.Firstly,we design a variety of experiments for different influencing factors,and use tensile and shear test schemes to carry out comparative experiments on different crosslinking agent concentrations,different metal substrates.And whether adding coupling agents is concerned.The adhesive layer thickness and the bonding area are also taken into account.After loads of experiments,we conclude that the bonding strength is higher if the ratio is 100:6;a certain degree of roughness is required;the bonding effect is obvious with the glue layer thickness of 2mm to 0.5mm;the same In the case of the bonding area,the bonding strength is higher when the bonding part is the edge.Then,this paper designs a conformal bonding and curing loading device for the irregularity and diversity of component shapes,which can adapt to the sh ape of the component to uniformly and accurately apply pressure to the thermal insulation panel to ensure the quality of bonding.The test shows that the airbag product deformation can fulfill the basic requirements of filling the cavity.The second conclusion is that the single-sided bonding area ratio under different pressurization conditions should be highly thought of.Finally,according to the characteristics of thermal protection materials,we draw a conclusion that it is useful and important to have non-destructive testing methods and mechanical performance testing methods of thermal protection system bonding quality.Radiographic technology and ultrasonic technology are suitable,and mechanical performance testing can be improved.Good response to the overall performance of the bonding process.From the perspective of design,test,and inspection,the results of bonding strength factors,bonding curing pressure device and bonding strength testing methods obtained in this paper have a certain versatility and can be extended and applied to conventional hypersonic aircraft.The thermal protection component bonding process plan is being designed.