A non-congested solid rocket ramjet gas flow regulating device

Abstract

The invention discloses a non-jammed solid rocket ramjet gas flow adjusting device. The non-jammed solid rocket ramjet gas flow adjusting device comprises a gas generator. The side, close to the gas generator, of a fuel cavity is connected with an afterburning chamber. A partition plate for separating the afterburning chamber from the fuel cavity is arranged between the afterburning chamber and the fuel cavity. The partition plate is provided with N through gas inlet holes. Blocking covers which can seal and block the gas inlet holes are arranged in the N-1 gas inlet holes, and the blocking covers are provided with blasting devices which can blast the blocking covers. The afterburning chamber is internally provided with a pressure sensor, and the pressure sensor is electrically connected with the blasting device. N is larger than 1 and is a positive integer. According to the non-jammed solid rocket ramjet gas flow adjusting device, the blocking covers with detonating cords are adoptedas a changing device for gas flow between the gas generator and the afterburning chamber, and the blocking covers are low in price and accurate and reliable in work. Meanwhile, by means of the designof a cowling, gas entering the afterburning chamber from the gas generator and air can be evenly mixed, and the burning efficiency is improved.

Description

technical field [0001] The invention belongs to the field of rocket engines, and in particular relates to a gas flow regulating device for a non-choked solid rocket ramjet engine. Background technique [0002] With the continuous improvement of aircraft engine requirements and the development of aircraft technology, solid rocket ramjet has become the development direction due to its advantages such as high specific impulse, small size, light weight, compact structure, and low cost. In order to meet the diversification requirements of mobile attack and combat missions, the flight speed range of the missile is correspondingly widened. The design speed range of supersonic over-the-horizon air-to-air missiles is generally 2Ma to 4Ma, and even required to reach 2Ma to 5Ma. When the altitude is constant, the mass flow rate of the captured air in the intake duct changes greatly due to the speed change. In order to ensure the good performance of the engine, the rich gas flow of th...

AI Technical Summary

Problems solved by technology

However, the range of self-regulation is limited, and the self-regulation method often cannot meet the requirements when the range of missile flight speed is correspondingly widened and the range of flight altitude becomes wider.

Images