摘要
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。
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.
出处
《导弹与航天运载技术》
北大核心
2015年第1期13-16,共4页
Missiles and Space Vehicles
关键词
助推器
姿态和轨迹
气动特性
动力学模型
Booster
Attitude and trajectory
Aerodynamic characteristics
D3haamic model
