A free-loading single-chamber double-push solid small rocket structure

Abstract

The invention relates to a free-loading single-chamber double-push solid small rocket structure, comprising an igniter, a connecting tube seat, a first sealing gasket, an ignition powder box, a shell component, a spring piece, a powder column component, a set screw, a stopper Medicine plate, second gasket, nozzle assembly. On the basis of completing the single-chamber double-push function, the present invention completely avoids the problem of possible debonding between the contact interfaces of propellants with different burning rates when the composite propellant is used for casting. At the same time, on the basis of constant charge quantity, the ratio between high and low thrust can be adjusted within a certain range by adjusting the quantity ratio between different burning rates.

Description

technical field [0001] The invention relates to a free-loading single-chamber double-push solid small rocket structure. Background technique [0002] The single-chamber double-propelled solid small rocket can generate at least two different thrust platform segments when the same rocket engine is working, and act on the target to form different speed-time curve combinations to complete the predetermined function. [0003] At present, composite propellants are often used in the design of commonly used single-chamber double-propellant solid rockets. When working, the high-burning rate propellant burns first, generating a larger thrust period, while the low-burning rate propellant has a longer working time and generates a smaller thrust period. Although this design method can effectively solve the design requirements of single-chamber double thrusters, due to the inconsistent shrinkage characteristics of propellants with different burning rates affected by temperature, and ther...

AI Technical Summary

Problems solved by technology

Although this design method can effectively meet the design requirements of single-chamber double-push, due to the inconsistent shrinkage characteristics of propellants with different burning rates affected by temperature, and there is a fixed interface between the two, there is a possibility of grain combination in this design method. The hidden danger of surface debonding

The debonding of the bonding surface will lead to obvious deviations in the working performance of the engine, which is one of the faults that are not allowed to occur during the use of the product

There are many factors that lead to this hidden danger, such as changes in ambient temperature, casting process of grains, and stress release between grains. These cannot be avoided only through ex-factory inspection, and may gradually appear during the actual use of the product.

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