通过将物资舱体内埋于无人机，在抵达目标区域后快速分离投放并展开减速伞，可有效提升空投任务的灵活性与效费比。不同于作战飞机的内埋武器分离，物资舱体与无人机通常紧密配合且质量相当，二者受到分离流场的气动干扰更为严重。在分离过程中，减速伞的充气展开涉及到流场快速变化及与物资舱体、无人机的相互干扰，导致传统基于任意拉格朗日-欧拉（ALE）描述的分析方法难以考虑开伞过程分离流场对无人机与物资舱体分离动力学特性的影响。本文提出基于充气时间法与壁面假设相结合的开伞等效方法，通过与计算流体力学（CFD）耦合六自由度方程（6DOF）方法相结合，构建欧拉描述下多体分离减速伞展开过程的等效，实现了对物资舱体内埋分离-开伞过程的一体化仿真分析，并探究物资舱体分离弹道参数与气动干扰影响规律。分析结果表明，所提出方法能够有效分析减速伞的开伞过程；物资舱体弹道较为稳定，无人机在分离与开伞时则受到俯仰方向的较大干扰；各参数对分离的影响均存在非线性，分离方案需要进一步设计优化。本文工作可为无人机系统及分离方案设计奠定基础。

The supply chamber can be internally carried in the Unmanned Aerial Vehicle （UAV）， and be separated in the target area by deploying a deceleration parachute swiftly. The agility and cost-effectiveness ratio of the airdropping can be improved significantly with this concept. However， the supply chamber is snugly assembled in the internal bay of UAV and has comparable mass with the UAV， which leads to stronger aerodynamic interference in the separation flow field. This is different from the separation of internal weapons from the combat aircraft. During the separation， the inflation and deployment of the deceleration parachute will cause highly unsteady flow fields and aerodynamic interference with the supply chamber and UAV. This makes it difficult for traditional methods based on the Arbitrary Lagrangian-Eulerian （ALE） method to analyze the impact of deployment of the deceleration parachute on the separation dynamic characteristics. In this paper， a parachute deployment equivalent method combining the inflation time method and wall assumption is proposed. By combining with Computational Fluid Dynamics （CFD） coupled with the 6 Degree Of Freedom （6DOF） equation method， an equivalent model of multi body separation accompanied by parachute deployment with Eulerian description is constructed. An integrated simulation analysis of the internal separation with the parachute deployment process for the supply chamber is achieved， and the impact of separation trajectory parameters and aerodynamic interference for the supply chamber is explored.Result shows that the proposed equivalent method can effectively analyze the deployment of the deceleration parachute. The trajectory of the supply chamber is relatively stable， while the UAV is affected by significant pitching interference during separation and parachute deployment. The impact of the analyzed variables on separation dynamics is nonlinear， and it is necessary to optimize the separation scheme further. Works in this paper can be the foundation for the design of UAV systems and separation schemes.