CAJ | 학술논문

大型整流罩仿真分析与试验预示是国内新一代运载火箭研制过程中的关键技术。采用高精度非线性显式动力学分析方法，对某大型弹性整流罩有无导向孔的2种设计方案分别进行显式动力学分析，比较了2种方案的分离特性及罩内可用包络空间，分析了弹簧顶杆与导向孔等的接触作用对整流罩分离的影响，并结合原型整流罩地面分离试验对仿真结果进行了对比验证。计算结果表明，含导向孔的整流罩分离速度更快，呼吸变形更小，弹簧顶杆与整流罩的接触作用能有效地限制整流罩的呼吸变形。试验结果验证了数值分析结果，这对新一代运载火箭的研制具有一定参考价值。
대형정류조방진분석여시험예시시국내신일대운재화전연제과정중적관건기술。채용고정도비선성현식동역학분석방법，대모대형탄성정류조유무도향공적2충설계방안분별진행현식동역학분석，비교료2충방안적분리특성급조내가용포락공간，분석료탄황정간여도향공등적접촉작용대정류조분리적영향，병결합원형정류조지면분리시험대방진결과진행료대비험증。계산결과표명，함도향공적정류조분리속도경쾌，호흡변형경소，탄황정간여정류조적접촉작용능유효지한제정류조적호흡변형。시험결과험증료수치분석결과，저대신일대운재화전적연제구유일정삼고개치。
Simulation analysis and test prediction for large?scale payload fairing are the key technologies during the development of new generation launch vehicles.In this paper,the separation dynamics of large?scale elastic payload fairings with and without guid?ing holes were studied by comparing the separation parameters and the effective enveloping space using the high?fidelity nonlinear explicit dynamic method.Then,the influence of the contact between spring component and guiding holes on the fairing separation was analyzed.Finally,the numerical results were compared and validated by the prototype ground test of the fairing separation.Results in?dicate that the rotational velocity is larger and the breathing deformation is smaller for the payload fairing with guiding holes.Moreo?ver, the contact between the spring component and payload fairing could restrict the breathing deformation of payload fairing.Test re?sults verify the numerical results,which provide a reference for the development of new generation launch vehicles.