With the requirements of the speed, maneuverability and agility, the structure with large slenderness ratio is widely employed in the design of the modern rocket. The interaction among unsteady aerodynamic load, structural elastic response, as well as flight motion will be more significant. This paper focuses on the aeroelastic effects in the trajectory simulation of a rotary rocket with a large slenderness ratio. A calculation method based on computational fluid dynamics / computational structural dynamics / computational flight mechanics (CFD/CSD/CFM) coupling system is proposed, in which an in-house CFD/CSD strong-coupled program is connected with the six-degree-of-freedom flight mechanics' equations. The CFD/CSD coupling subsystem as well as CFD/CFM coupling subsystem are validated by aeroelastic dynamic stability analysis of AGARD wing and trajectory simulation of a spinning projectile, respectively. Then, the coupling algorithm is performed on a long-range trajectory simulation of an uncontrolled rotary flexible rocket. The unsteady aerodynamic loads, structural deformation, flight motions, as well as the varying thrust direction are obtained and analyzed. Through the Monte Carlo Experiment, the landing points dispersion of the elastic rocket is also calculated and compared with the rigid case. The results show that the aeroelastic effect can decrease the range and reduce the landing accuracy of the rocket. The proposed method can provide technical support for the correction of the firing table and the design of the control system of the rocket.

由于对速度、机动性和敏捷性的要求，大长细比结构在现代火箭的设计中被广泛采用。非定常气动载荷、结构弹性响应以及飞行运动之间的相互作用将更加显着。本文重点研究了大长细比旋转火箭弹道模拟中的气动弹性效应。提出了一种基于计算流体动力学/计算结构动力学/计算飞行力学（CFD/CSD/CFM）耦合系统的计算方法，其中内部CFD/CSD强耦合程序与六度角连接。 - 自由飞行力学方程。CFD/CSD 耦合子系统以及 CFD/CFM 耦合子系统分别通过 AGARD 机翼的气动弹性动态稳定性分析和旋转弹丸的弹道模拟进行验证。然后，对不受控旋转柔性火箭的远程弹道仿真进行耦合算法。获得并分析了非定常气动载荷、结构变形、飞行运动以及变化的推力方向。通过蒙特卡罗实验，还计算了弹性火箭的着陆点离散度，并与刚性情况进行了比较。结果表明，气动弹性效应会减小火箭的射程，降低火箭的着陆精度。