Dynamic Modeling and Analysis of Impact in Space Operation Tasks

For the rigid impact and flexible impact in space operation tasks, impact dynamic models between two objects are established in this paper, laying the model foundation for controlling or suppressing the impact. For the capture task between a grapple shaft and a rigid body, the impact dynamic model is established based on the Zhiying–Qishao model. Moreover, by introducing a friction factor into the original impact model, an improved dynamic model between two rigid bodies is proposed. For the capture task with flexible impact, an impact dynamic model between the grapple shaft and a flexible wire rope is established based on the dynamic model of the flexible wire rope. The ground experiments and simulations are carried out with two objects on an air flow table. The experiment results validate the impact dynamic model proposed in this paper.

Research on Behavior Cause of Limited Space Accident Based on “2-4” Model

In order to prevent accidental casualties in the course of limited space operation, the behavioral safety “2-4” model is used to study the behavioral causes of typical limited space operation accidents. First, the causes of one-time and habitual behavior are studied from the individual level, that is, unsafe action, physical state and safety knowledge, consciousness; then, the research of operational behavior and guiding behavior is studied from the organizational level. Finally, the prevention and control suggestions are put forward to reduce the occurrence of such accidents.

Flow Modelling of Propulsion Nozzles for Nano-Satellites

The development of compact propulsion systems for nano and micro satellites is nowadays a growing research topic. Actually, the availability of low cost materials able to withstand space operation is now becoming widespread technology. This democratization on the access to space was not followed with a corresponding availability of critical propulsion technologies. However, the availability of propulsion systems for this class of satellites will provide them with new possibilities in what relates to mission profiles. In the present work an electrospray will be analysed, in particular the flow in the nozzle. This flow is controlled by a mix of pressure and electrostatic field. A full EHD (electrohydrodynamics) computational model is developed that is integrated in a classic CFD code using user specified functions. The proposed computational model was able to compute the flowfield for the electrospray test case under consideration. A benchmark against experimental results, by comparing spray thruster droplet size, concluded that the numerical model can predict their size within an error of 5%.