Solid rocket ramjet engine gas flow adjusting device

Abstract

The invention discloses a fuel gas flow regulating device for a solid rocket ramjet, which comprises a main controller, a projectile body, a gas generator, and a nozzle pipe. The nozzle pipe includes a sealing plate and a hollow pipe body; There is a light hole in the axial direction of the pipe body, and a plunger slide valve is sealed and installed in the light hole, and a driving device is arranged on the plunger slide valve; N through air inlet holes are opened on the sealing plate, and the distribution of the air inlet holes is located at Within the diameter range of the pipe body, there are N-1 air inlet holes with plugging caps that can seal and block the air inlet holes, and a blasting device that can blast the caps is provided on the blocking caps; between the outer wall of the pipe body and the projectile A pressure sensor is installed in the cavity, the pressure sensor is electrically connected to the main controller, the main controller is electrically connected to the driving device; the pressure sensor is electrically connected to the blasting device. The invention enables the solid rocket ramjet to have a larger flow regulation range in both the non-choked state and the blocked state, and has the advantages of low price, precise and reliable operation, and the like.

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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