Simulation test device for firing attitude of rocket

Abstract

The invention belongs to a test device of an engine of a rocket and particularly relates to a simulation test device for firing attitude of the rocket, which has the advantages that when the engine is ignited and started, the rocket moves along a straight line of a ratchet slide rail ballistic simulation mechanism, a rocket pitch angle hydraulic control mechanism controls the rotation angle of a missile body in an emission surface according to the rocket pitch angle change rule, a rocket yaw angle and roll angle control mechanism drives the ratchet slide rail ballistic simulation mechanism and the rocket pitch angle hydraulic control mechanism to rotate along the axis of a vertical plane, and the rotational acceleration, speed and angle are controlled by a rotating flywheel in the rocket yaw angle and roll angle control mechanism. As the three mechanisms control the mechanism to move in the three-dimensional space along three directions, any rocket firing attitude can be simulated according to the design requirement under the condition of simultaneous working of the three mechanisms, and the rocket firing attitude under corresponding combination condition is simulated under the condition of working of only two mechanisms.

Description

Technical field [0001] The invention belongs to a rocket engine test device, in particular to a rocket ignition posture simulation test device. Background technique [0002] During the rocket launch process, the engine gas flow will affect the surrounding launch equipment. This impact mainly includes two aspects: one is that the high temperature and high condensed phase gas flow will cause serious ablation effects on the materials of the launch equipment, and the heat of the launch equipment The protection plan must consider the distribution and range of influence of the gas flow in order to find economical ablation-resistant materials; second, the supersonic gas flow with considerable displacement has a great impact on the launching equipment, and the launching equipment design must consider the structural range that can withstand For the problem of the intensity of the gas flow, the impact center of the gas flow is very high or the center of action of the gas flow deviates far ...

AI Technical Summary

Problems solved by technology

[0008] 1) Only quasi-steady-state research can be carried out, that is, after the design of the engine ignition height and ignition angle is determined before the test, these parameters of the engine remain unchanged during the entire test process, and the dynamic change of the rocket ignition attitude cannot be simulated;

[0009] 2) The adjustment range of engine ignition height and ignition angle is very small, which cannot adapt to the situation of large changes in rocket ignition attitude;

[0011] 4) There is no rocket body in the test device, only an engine with a relatively simple structure, and the influence of the shape of the rocket body on the jet plume field of the engine gas flow is not considered

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