Solid rocket ramjet engine gas flow adjusting device

Abstract

The invention discloses a solid rocket ramjet engine gas flow adjusting device. The solid rocket ramjet engine gas flow adjusting device comprises a master controller, a projectile body, a gas generator and a spraying pipe; the spraying pipe comprises a sealing plate and a hollow pipe, an unthreaded hole is formed in the wall of the pipe in the direction vertical to the pipe axis direction, a plunger sliding valve is installed in the unthreaded hole in a sealed manner, and a driving device is arranged on the plunger sliding valve; N through air inlet holes are formed in the sealing plate, theair inlet holes are distributed within the pipe diameter scope, plugging covers capable of sealing and plugging the air inlet holes are arranged in N-1 air inlet holes, and detonation devices capableof detonating the plugging covers are arranged on the plugging covers; and a pressure sensor is installed in a cavity between the pipe outer wall and the projectile body and is electrically connectedwith the master controller, and the master controller is electrically connected with the driving device; and the pressure sensor is electrically connected with the detonation devices. By means of thesolid rocket ramjet engine gas flow adjusting device, a larger flow adjusting scope can be achieved under the non-jamming state and the jamming state of a solid rocket ramjet engine, and the beneficial effects of being low in price, accurate and reliable in work and the like are achieved.

Description

technical field [0001] The invention belongs to rocket engine technology, in particular to a gas flow regulating device for a 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. [0003] 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 the gas generator m...

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.

[0008] To sum up, for the three gas flow adjustment schemes in the prior art, it is difficult to meet the demand for large-scale adjustment of gas flow in the case of a wide range of environmental parameter changes

Moreover, the structure is complicated, the cost is expensive, and the work is unreliable

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