Abstract
In the present study, the microspacecraft bulkhead was reduced to the double honeycomb panel, and the projectile oblique hypervelocity impact on the double honeycomb panel was simulated. The distribution of the debris cloud and the damage of a honeycomb sandwich panel were investigated when the incident angles were set to be 60°, 45°, and 30°. The results showed that as incident angle decreased, the distribution of debris cloud was increased gradually, while the maximum perforation size of the rear face sheet was firstly increased with the decrease of the incident angle and then decreased. On the other hand, the damage area and the damage degree of the front face sheet of the second honeycomb panel layer were increased with the decrease of the incident angle. Finally, the critical angle of front and rear face sheets of the honeycomb sandwich panel was obtained under oblique hypervelocity impact.
Highlights
A large amount of the space debris has been accumulated as the increase of the human space activities within the scope of the near-earth space, which posed a serious threat to the safe operation of the spacecraft in orbit [1, 2]
As for the spacecraft bulkhead, the honeycomb sandwich panel will be firstly suffered the impact of the space debris [5, 6]
In view of the space debris impact on both sides of the spacecraft bulkhead, the spacecraft was simplified to the structure of double honeycomb sandwich panel, which used to study the breaking condition of the projectile and the damage of the honeycomb sandwich panel under the oblique impact
Summary
A large amount of the space debris has been accumulated as the increase of the human space activities within the scope of the near-earth space, which posed a serious threat to the safe operation of the spacecraft in orbit [1, 2]. The space debris can penetrate honeycomb sandwich panel with an average speed of 10 km/s in the earth orbit [1, 3]. As for the spacecraft bulkhead, the honeycomb sandwich panel will be firstly suffered the impact of the space debris [5, 6]. One side of the spacecraft bulkhead will be penetrated; the inside the equipment and the other side of the bulkhead can be damaged due to the high speed and the large kinetic energy of the space debris. In view of the space debris impact on both sides of the spacecraft bulkhead, the spacecraft was simplified to the structure of double honeycomb sandwich panel, which used to study the breaking condition of the projectile and the damage of the honeycomb sandwich panel under the oblique impact. The critical incident angle of the single honeycomb sandwich panel is calculated in this paper
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