导弹与航天运载技术
導彈與航天運載技術
도탄여항천운재기술
MISSILES AND SPACE VEHICLES
2015年
1期
13-16
,共4页
助推器%姿态和轨迹%气动特性%动力学模型
助推器%姿態和軌跡%氣動特性%動力學模型
조추기%자태화궤적%기동특성%동역학모형
Booster%Attitude and trajectory%Aerodynamic characteristics%Dynamic model
运载火箭助推器分离后的姿态和轨迹对于助推器着陆区域确定以及回收系统设计十分重要，研究分析助推器姿态和轨迹的关键在于确定助推器分离后的气动特性。由于助推器分离后在稀薄大气环境条件下自由飞行，国外往往通过风洞试验方法来模拟助推器的气动参数。采用一种基于粘性绕流和细长体理论的工程算法来计算助推器分离后飞行的气动参数，并将气动数据用于助推器的飞行动力学模型，分析助推器分离后的姿态和轨迹。仿真结果表明，该仿真模型可以客观反映助推器的飞行特性，为运载火箭助推器回收应用提供一定的技术支持。
運載火箭助推器分離後的姿態和軌跡對于助推器著陸區域確定以及迴收繫統設計十分重要，研究分析助推器姿態和軌跡的關鍵在于確定助推器分離後的氣動特性。由于助推器分離後在稀薄大氣環境條件下自由飛行，國外往往通過風洞試驗方法來模擬助推器的氣動參數。採用一種基于粘性繞流和細長體理論的工程算法來計算助推器分離後飛行的氣動參數，併將氣動數據用于助推器的飛行動力學模型，分析助推器分離後的姿態和軌跡。倣真結果錶明，該倣真模型可以客觀反映助推器的飛行特性，為運載火箭助推器迴收應用提供一定的技術支持。
운재화전조추기분리후적자태화궤적대우조추기착륙구역학정이급회수계통설계십분중요，연구분석조추기자태화궤적적관건재우학정조추기분리후적기동특성。유우조추기분리후재희박대기배경조건하자유비행，국외왕왕통과풍동시험방법래모의조추기적기동삼수。채용일충기우점성요류화세장체이론적공정산법래계산조추기분리후비행적기동삼수，병장기동수거용우조추기적비행동역학모형，분석조추기분리후적자태화궤적。방진결과표명，해방진모형가이객관반영조추기적비행특성，위운재화전조추기회수응용제공일정적기술지지。
The prediction of attitude and trajectory for separated rocket booster is important for determining the landing area and designing the recovery system. And the key point is the aerodynamic characterization for separated booster. Because the fight after separation is un- controlled within rare atmosphere, aerodynamic characterization for booster is usually realized by wind tunnel experiments at abroad. In this paper, an engineering algorithm, which based on the viscous circumferential flow and slender-body theory, is presented for computing the aerodynamic coefficients after separation. And the aerodynamic database is applied in dynamic model of booster to predict its attitude and trajectory. The simulation results prove that the model can accurately reflect the booster flight characteristics and provide some technical support for the application of booster recovery system.
