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Numerical Simulation Studies of the Separation Process of Eccentric Tail Cover
ZOU Wenting, ZHENG Jian, ZHANG Menglong
JPRMG ›› 2024, Vol. 44 ›› Issue (3) : 87-95.
PDF(3320 KB)
PDF(3320 KB)
Numerical Simulation Studies of the Separation Process of Eccentric Tail Cover
({{custom_author.role_en}}), {{javascript:window.custom_author_en_index++;}}In order to realize the purpose of the tail cover being side-thrown away from the launch axis during the second ignition of the cold catapult missile, a new type of shroud throwing scheme was proposed: the eccentric tail cover and the nozzle outlet were connected by a sealing plug, and the gas jet was used as the power source to realize the side-throwing separation. Considering the influence of different centroid positions and horizontal lateral winds on the separation process, a three-dimensional tail mask separation model was established, combined with the overlapping dynamic mesh technology, the fluid control equation and the rigid body six-degree-of-freedom motion equation were coupled, and the tail cover separation process was numerically simulated. The variation curve of the motion characteristics of the tail cover when it is impacted by the jet and the interference characteristics of the tail cover on the flow field of the gas jet are obtained. The results show that the scheme can achieve the purpose of lateral throwing of the tail cover away from the emission axis. With the increase of the degree of centroid bias, it is beneficial for the jet state at the axis to be stable first. When the centroid position is greater than one-half radius, the jet has a greater accelerating rotation effect on the tail cover than the translational rotation, which increases the instability of the tail cover during the movement, and the tail cover tends to be close to the axis in the later stage of separation. The horizontal lateral wind is conducive to the tail cover to stay away from the axis, and the trend of moving away from the axis is more obvious with the increase of wind speed.
separation of tail cover / gas jet / centroid offset / sidewind / overlapping grids {{custom_keyword}} /
Table 1 Centroid positional parameter表1 质心位置参数 |
| Case | Reference point | Coordinate | Sidewind speed/(m/s) |
|---|---|---|---|
| 1 | 1 | (-0.25r,0,0) | 0 |
| 2 | 3 | (-0.50r,0,0) | 0 |
| 3 | 5 | (-0.75r,0,0) | 0 |
| 4 | 1 | (-0.25r,0,0) | 15 |
Table 2 Distribution of tail cover landing points表2 尾罩落点分布 |
| Centroid No. | Speed of slidewind/(m/s) | Landing point on the X-axis/m | Distance from launch point/m |
|---|---|---|---|
| 1 | 0 | 3.6 | 3.5 |
| 2 | 0 | 3.27 | 3.83 |
| 3 | 0 | 3.13 | 3.97 |
| 4 | 0 | 3.35 | 3.75 |
| 5 | 0 | 3.56 | 3.54 |
| 6 | 1~8 | 3.12 | 3.98 |
| 7 | 1~15 | 2.43 | 4.67 |
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Some missiles use head cover to protect the internal equipment during the launching process. In order to prevent the head cover from damaging the people or equipment after separation, researchers need to predict the landing position range and take protective measures. This paper designs a separation scheme for a missile head cover separation based on solid propellant gas generator and solid rocket. In this study, we establish a dynamic simulation model of head cover separation and falling procedure. The simulation calculation of the head cover location range considering multiple factors using <em>Monte-Carlo method is developed</em>. And the motional curve of separation bodies and<em> the danger zone of head cover landing location</em> are obtained. The simulation results in this paper will provide technical support for rocket launcher and personnel protection design.
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PDF(3320 KB)
Fig.1 Schematic diagram of tail cover separationFig.2 Tail cover meshing modelFig.3 Overset meshing modelFig.4 Transient characteristics of the flow field in the nozzle at different moments in the pressure building process
Table 1 Centroid positional parameterFig.5 Transient characteristics of the flow field at different moments during the movement of the tail cover in case 1Fig.6 Transient characteristics of the flow field at different moments during the movement of the tail cover in case 2Fig.7 Transient characteristics of the flow field at different moments during the movement of the tail cover in case 3Fig.8 Transient characteristics of the flow field at different moments during the movement of the tail cover in case 4Fig.9 Pressure distribution on the nozzle axis at different momentsFig.10 Rotational characteristics of tail cover centroidFig.11 Translational characteristics of tail cover centroidFig.12 Prediction of the position of the tail cover landing pointTable 2 Distribution of tail cover landing points/
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