Split type axial force bearing structure
A load-bearing structure and axial force technology, applied in the fairing field, can solve problems such as affecting the separation direction of the fairing, difficult assembly, and the rocket body is vulnerable to impact, so as to avoid multi-process processing and tolerance accumulation, and improve product economy and reliability, the effect of reducing instability
Pending Publication Date: 2021-08-13
东方空间技术(山东)有限公司
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Problems solved by technology
However, the explosive bolts of the traditional fairing are arranged inside the fairing, which is not easy to install, the assembly is difficult, and the impact of the explosion is relatively large, which affects the separation direction of the fairing, and the arrow body inside the fairing is easily affected by the impact
Method used
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Embodiment Construction
[0020] Embodiments of the technical solutions of the present invention will be described in detail below in conjunction with the accompanying drawings. The following examples are only used to illustrate the technical solutions of the present invention more clearly, and therefore are only examples, rather than limiting the protection scope of the present invention.
[0021] Such as figure 1 , figure 2 with image 3 As shown, this embodiment provides a split axial force bearing structure for connecting the fairing 1 and the adapter ring 2, including twelve bolt boxes 3 and twelve connecting pieces 4, twelve bolt boxes 3 are evenly distributed in the circumferential direction on the outer periphery of the adapter ring 2, and twelve connecting pieces 4 are evenly distributed in the circumferential direction on the outer periphery of the fairing 1, and the bolt boxes 3 and the connecting pieces 4 are connected in one-to-one correspondence.
[0022] Specifically, the bolt box 3 ...
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The invention relates to a split type axial force bearing structure which is used for connecting a fairing and an adapter ring and comprises a plurality of bolt boxes. The bolt boxes are evenly distributed on the periphery of the adapter ring in the circumferential direction. The side, away from the adapter ring, of each bolt box is open, a first plate body is arranged in the direction, close to the fairing, of each bolt box, an explosive bolt is installed on each first plate body, a detonating cord is connected to each explosive bolt, and the end, away from the corresponding explosive bolt, of each detonating cord penetrates through the adapter ring. A plurality of connecting pieces are arranged at the side, close to the adapter ring, of the fairing, the multiple connecting pieces correspond to the multiple bolt boxes in a one-to-one manner, and the ends, exposed out of the first plate bodies, of the explosive bolts are connected with the corresponding connecting pieces. According to the split type axial force bearing structure, a mounting mode that the explosive bolts are externally arranged is adopted, so that the impact on the fairing and a rocket body at the separation moment can be reduced while the explosive bolts are conveniently mounted.
Description
technical field [0001] The invention relates to the technical field of fairings, in particular to a split axial force bearing structure. Background technique [0002] The role of the rocket fairing is to protect the rocket when it passes through the atmosphere. When leaving the atmosphere, the fairing needs to be separated from the rocket. The existing separation methods of the fairing include integral forward separation, two-lobed spin separation and peace Toss to separate. [0003] In the traditional integral forward separation method, the fairing is connected to the instrument cabin through an adapter ring, and the fairing and the adapter ring are connected by explosive bolts. The connecting ring is separated, and the fairing can be thrown forward and separated as a whole. However, the explosive bolts of the traditional fairing are arranged inside the fairing, which is inconvenient to install, difficult to assemble, and the impact of the explosion is relatively large, w...
Claims
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IPC IPC(8): F42B15/38
CPCF42B15/38
Inventor 赵伟伟布向伟侯世远谷泽林宋文峰吴昊
Owner 东方空间技术(山东)有限公司