The Simulation And Analysis Of The Rocket Fairing Separation Process

With the development and progress of the aerospace industry, the geometry of therocket fairing is also growing and the method which is called the folio and flat separatedway would replace the method called flip-hinge to become the main developmentdirection for fairing separation techniques. The size increasing and the change ofseparation method cause the reduction of stiffness in the fairing, as well as the fierceelastic deformation of the separation process, and fairing is becoming more complex,which increased the risk of collision between effective load and arrow for payloadfairing.Currently, flexible multi-body dynamics and related theories is still not perfectenough to prepare detail calculation and description of elastic deformations in fairingseparation process; fairing separation test requires large canister vacuum and a series ofhigh-tech experiments to simulate space environment, but currently we do not have acomplete testing facility; the ground test can simulate fairing separation process in somedegree, but there are confounding factors such as air and gravity.In summary, the development for fairing urgent needs a method with the use of anew technology, focusing on the simulation and analysis in the elastic deformation ofthe separation process, but the existing research work on elastic deformation of fairingis not sufficient. Focusing on this situation, this article uses the finite element methodand software including ANSYS/LS-DYNA to simulation separation process for fairing,focusing on the impact caused by elastic deformation.Firstly, this article introduce the structure and operation of fairing, established theparameters such as dimensions, materials, structures used in the analysis, fitting airbagsseparation force to determine process load positions and loading action time for solvingprocess, which well prepared for the research work.Secondly, based on the kinetic theory of elasticity and flexibility, with the use offinite element method, analysis the static and dynamic characteristics happened in theprocess which rocket fairing is flying. The aerodynamic loads are equal to static loads inevery direction, with the analysis of strain and stress; modal analysis and loads ofsinusoidal vibration response analysis are taking into account for fairing to determine itsdynamics.Thirdly, based on flexible multi-body dynamics and fluid-solid coupling theory,this article conduct the separation process of fairing in a ground simulation environmentby comparison with the ground test data, check and improve the simulation model.Three conditions of the deformation and movement of the fairing are taken into account,which determines the effective load safety envelope, focusing on the separation of air resistance of the fairing.Finally, based on flexible multi-body dynamics theory, this article carry out asimulation for fairing separation process under a vacuum environment, which indicatedthe fairing’s working performance. Analysis elastic deformation and movement offairing, discussion have been draw attention to the relevant factors which determine thesafety envelope and payload rocket body safe overload.