Integral air injection device with plurality of obliquely cut and arranged injection pipes and air injection method

Abstract

The invention provides an integral air injection device with a plurality of obliquely cut and arranged injection pipes and an air injection method. The air injection device comprises a injection pipebody, throat liners and blocking caps; the injection pipe body is of a shell structure and comprises a barrel section and the multiple obliquely cut and arranged injection pipes evenly distributed atthe rear end of the barrel section in the circumferential direction; engine gas is exhausted from the obliquely cut and arranged injection pipes, and the synthetic thrust is in the axis direction of the injection pipe body; the throat liners are bonded at inlets of the obliquely cut and arranged injection pipes; and the blocking caps adhere to the tail parts of the throat liners. According to theair injection device and method, an obliquely cut and arranged injection pipe structure is adopted, the engine gas is exhausted from the side faces of the injection pipes, synthetic thrust is in the axis direction of the injection pipe body, and the requirement for axial thrust is met; and meanwhile, high-temperature gas at outlets of the injection pipes cannot damage a rear cabin section, the injection pipe body structure is formed by uniformly arranging the obliquely cut and arranged injection pipes and integrally processing, the thrust eccentricity is less than or equal to 3 ', and the high-precision requirement of axial synthetic thrust is met.

Description

technical field [0001] The invention belongs to the technical field of nozzle structure design of a solid rocket separation engine, and in particular relates to an integral air injection device and an air injection method with a plurality of obliquely cut and inclined nozzles. Background technique [0002] The fairing is an important part of protecting the payload and maintaining the aerodynamic shape of the missile body. When the aircraft gets rid of the interference of the atmospheric environment, the fairing no longer functions and needs to be separated from the aircraft body. The overall axial separation of the fairing is a method currently used. In order to avoid collision with the aft cabin during the separation of the fairing, it is necessary to accelerate the spinner axially to complete the separation from the aft cabin. As the power source for the axial separation of the fairing, the solid rocket separation motor needs to generate axial thrust during operation, and ...

AI Technical Summary

Problems solved by technology

Traditional separation technologies such as explosive bolts or ring-shaped explosive locks have low separation energy and cannot complete the axial separation of fairings well.

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