Test engine and test method for combustion of double-base system propellant in different overload directions

Abstract

The invention discloses a test engine and a test method for combustion of a double-base system propellant in different overload directions, which successfully eliminate the influence of the overload directions on combustion of the propellant. The test engine comprises a combustion chamber shell body, wherein the combustion chamber shell body is provided with a blasting device, and a large-small dual-circular-step-shaped blasting sealing plug is installed on the blasting device and screwed up by means of a blasting cover; a spray pipe is arranged in the middle of the combustion chamber shell body, and high-strength graphite is installed in a spray pipe base and screwed up by means of a gland so as to prevent the graphite from being sprayed out of a graphite spray throat in a test; and the combustion chamber shell body takes the center of the spray pipe as a symmetry axis, an end surface combustion propellant charge and a fake grain are placed on the two sides, and the purpose of changing the overload directions is achieved through exchanging the positions of the propellant charge and the fake grain. In order to prevent the spray pipe from being blocked and the ignition powder from being thrown out due to combustion of the charge under overload, the celluloid box without residues after combustion is used for fixing the ignition powder, thereby guaranteeing safety and reliabilityof the engine test under overload. The test engine and the test method is suitable for measuring and evaluating propellant charge combustion properties and internal ballistic trajectory performance indifferent overload directions.

Description

technical field [0001] The invention relates to a test engine and a test method for the combustion of double-base propellants in different overload directions, and is applicable to the technical field of evaluation and characterization of solid propellant charge rotating overload combustion characteristics. Background technique [0002] The high precision, high speed, and high penetration capabilities of weapon systems in modern warfare have become the decisive factors for the success or failure of missions. Such as high-speed surface-to-air anti-missile missiles, air-to-air missiles, artillery-launched missiles, etc., will produce greater flight overload and lateral overload during high-acceleration, strong maneuvering flight or sharp turning. The overload environment will affect the charge combustion and internal flow field of the solid rocket motor, leading to an increase in the combustion rate of the propellant, increasing the pressure of the combustion chamber, shorteni...

AI Technical Summary

Problems solved by technology

Studies have shown that the direction of the overload relative to the burning surface has a great influence on the burning speed of the propellant, which in turn affects the burning of the charge, making the internal ballistic performance abnormal

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