Interstage section pneumatic conformal solid rocket and separation method

Abstract

The invention discloses an interstage section pneumatic conformal solid rocket and a separation method. The interstage section pneumatic conformal solid rocket comprises a plurality of solid power devices, the adjacent solid power devices are connected through interstage sections, the solid power devices and the interstage sections are in the shape of a rocket outer body, conformal devices are arranged on the surface of the rocket outer body, and the conformal device comprises a pneumatic resultant force difference generating device, a connection unlocking device and at least two columnar surfaces; the connection unlocking device is used for realizing connection and separation between the columnar surface and the rocket outer body; the first control surface and the second control surface of the pneumatic resultant force difference generating device enable pneumatic resultant force difference to be generated between the two ends of the columnar surface, and the connection unlocking device separates connection between the columnar surface and the rocket outer body in the state that the pneumatic resultant force difference exists at the ends of the columnar surface. After the rocket flies to the maximum dynamic pressure point, the pneumatic resultant force difference generating device and the connection unlocking device are used for controlling the separation action of the columnar surface and the rocket outer body, and the influence of the structure of the rocket outer body on the transport capacity is reduced to the minimum.

Description

technical field [0001] The invention relates to the technical field of material palletizing and separation, in particular to an interstage aerodynamic shape-conserving solid rocket and a separation method. Background technique [0002] The shape of the solid rocket is formed by connecting the solid power of each stage with the interstage section. At present, the selection of sub-stage power systems of large and medium-sized solid launch vehicles is developing in the direction of racking and combination, which often makes the diameter of the lower-stage engine and fairing larger than that of the upper-stage engine, and the rocket presents a "cavity" shape . [0003] The shape of the rocket presents a "cavity". In the transonic section, the pulsating pressure is very strong starting from the inverted cone section of the fairing. Through wind tunnel test measurements, the external noise intensity reaches 160-170dB. This increases the load on the surface of the rocket body; th...

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Problems solved by technology

[0005] The object of the present invention is to provide a solid rocket with aerodynamic shape conforming to the interstage section and a separation method, so as to solve the technical problems of strong transonic pulsating pressure in the "concave" shape rocket in the prior art and increase the aerodynamic resistance of the rocket shape

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