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 agilityand 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 UAVand 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 inflationand deployment of the deceleration parachute will cause highly unsteady flow fieldsand aerodynamic interference with the supply chamberand 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 methodand 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 parametersand 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 separationand 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 systemsand separation schemes.

The rotating disk-shaped vehicle can significantly enhance penetration capabilities in denied environments by imitating stone skipping. Ensuring continuous skipping and reducing impact overload are critical dynamic design objectives. While setup settings are also important for the vehicle’s posture motion and load distribution during skipping, the dynamic aspects of skipping are mostly determined by the starting motion parameters. Therefore, the parameters affecting the dynamic characteristics of the rotating disk-shaped vehicle are strongly coupled, making the mechanisms of their influences remain unclear. This paper proposes a parameterized configuration for the disk-shaped vehicle. Utilizing the arbitrary Lagrange-Euler (ALE) method and penalty function method, a simulation analysis of the rotating disk-shaped vehicle is conducted. The study investigates the coupling relationship between configuration parameters and starting motion parameters and reveals their influence patterns on the vehicle's dynamic characteristics while skipping. The results demonstrate that increasing the edge curvature radius can effectively reduce the overload on the vehicle during skipping. Additionally, a better attitude stability can be achieved by increasing the spin rate. The findings presented in this paper can serve as valuable references for the design of new types of skipping anti-ship weapons, such as a rotating disk-shaped vehicle.

As a crucial weapon in the sea battle, anti-ship missiles generally employ a sea-skimming penetration strategy to reduce the probability of being detected by the target radar, which greatly increases the risk of touching water caused by sensor errors or random sea conditions. To alleviate the large impact load by high-velocity water touching, a novel anti-ship missile body configuration is proposed in this paper, which is inspired by the idea of hydroplaning. A parametric geometry model is first developed to modify the configuration of the anti-ship missile body. Subsequently, a structured arbitrary Lagrange-Eulerian based Fluid-Structure Interaction (FSI) model is established to analyze the kinematics parameters of the missile body during the hydroplaning process. A missile body configuration optimization problem is then formulated to minimize the impact load considering several constraints, e.g., horizontal velocity loss, pitch angle after touching water, and inside capacity for payload. Due to the time-consuming FSI simulation, a Kriging-assisted constrained differential evolution method is utilized to optimize the missile body configuration for reducing the impact load. During the optimization process, radial basis function and Kriging are combined with evolutionary operators to lead the search to the vicinity of the optimum rapidly. The result shows that the proposed missile body configuration can reduce the impact load by 18.8% compared with the ordinary configuration. Additionally, the optimized configuration can further yield a 17.4% impact load decrease subject to all the constraints and avoid structural damage by the high-velocity water touching, which demonstrates the effectiveness and practicability of the proposed anti-ship missile body configuration and corresponding optimization framework for reducing the impact load.