Facing the increasingly crowded orbital space and the gradually increasing space threats, more attention needs to be paid to spacecraft safety in space. In order to address the problem of non-cooperative spacecraft's approach interference to our spacecraft, the process of non-cooperative spacecraft's approach to our spacecraft by using Hohmann transfer is given by Satellite Tool Kit (STK) software, and the whole process of spacecraft's abnormal orbital maneuvering to approach our spacecraft is identified and judged by the method based on long short-term memory (LSTM) network. The simulation verifies that the LSTM network achieves good results.
As space becomes increasingly crowded and the orbital space environment gradually deteriorates, countries have gradually begun to pay attention to the in-orbit security of spacecraft. The timely and accurate sensing of space threats can effectively guarantee the in-orbit safety of our spacecraft. The orbital phase prediction for space targets is an important problem in the field of space situational awareness. In this paper, we propose a PSO-LSTM-based orbital prediction method for space targets, which has an accuracy rate of over 88.7% for different phases of orbital prediction.
Abstract Designing a pressure relief structure is an essential method to mitigate the intensity of the cookoff process in the fuze. In order to investigate the influence of the venting structure on the fast cook-off response characteristics of the fuze, a fast cook-off test with and without pressure relief structures was designed for typical naval gun ammunition fuses, and a universal cook-off model (UCM) suitable for fast cook-off was developed for simulation to obtain the response characteristics of fuzes under different conditions. The results indicate that the fuze with sealed structure undergoes deflagration reactions, while the fuze with a vented structure undergoes burning reactions. The venting structure significantly reduces the reaction intensity of the fuze but has a minor effect on response time. The ignition position is located in the central area at the bottom of the fuze, with the ignition temperature of JHX-1 approximately 483K, and the RDX component dominates the ignition process. The developed UCM model can accurately predict the impact of internal pressure variations on the reaction process within the fuze, the internal pressure of the fuze booster explosive decreases by 24.32% when the venting structure is flushed open, which effectively slowing down the chemical reaction process and reducing the reaction intensity. Additionally, there is minimal melting in the ignition area, and resulting in minimal impact on the fuze response characteristics.
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