Vacuum-thrust-vector measurement system capable of adjusting rocket-motor swinging direction in real time

Abstract

The invention discloses a vacuum-thrust-vector measurement system capable of adjusting the rocket-motor swinging direction in real time. The vacuum-thrust-vector measurement system comprises a rocket-motor installing platform, six one-direction force measurement and movement control assemblies, a base, a measurement and control cable and a computer measurement and control system. The one-direction force measurement and movement control assemblies are composed of lower hinging boxes, lower spherical hinges, servo motors, cylinders, lead-screw ejector rod mechanisms, force measurement sensors, upper spherical hinges and upper hinging boxes. The lead-screw ejector rod mechanisms are composed of lead screws and ejector rods. The servo motors are controlled by the computer measurement and control system to rotate, and rotating movement of the servo motors is converted into linear movement of the ejector rods through the lead screws to further drive the rocket-motor installing platform to move. One-direction force measured by the six force measurement sensors is synthesized through the computer measurement and control system to obtain the thrust vector of a rocket motor. The servo motors are vacuum motors, the force measurement sensors are of open structures, and swinging control and thrust-vector measurement can be carried out in a vacuum.

Description

technical field [0001] The invention relates to a rocket engine thrust vector measurement system, in particular to a vacuum thrust vector measurement system capable of real-time adjustment of the rocking direction of the rocket engine, belonging to the technical field of thrust measurement. Background technique [0002] Ideally, the thrust line of the rocket engine coincides with the central axis of the engine, but in fact, due to the limitation of machining accuracy, the geometric asymmetry of the engine, or the asymmetric flow of high-temperature and high-pressure gas through the nozzle and the ablation of the nozzle throat The resulting deformation causes the thrust action line of the engine to deviate from the central axis of the engine, resulting in thrust eccentricity. When the rocket is in flight, in addition to the thrust of the rocket engine, it is also affected by atmospheric resistance and environmental wind speed, which will cause the attitude of the rocket to ch...

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Problems solved by technology

[0002] Ideally, the thrust line of the rocket engine coincides with the central axis of the engine, but in fact, due to the limitation of machining accuracy, the geometric asymmetry of the engine, or the asymmetric flow of high-temperature and high-pressure gas through the nozzle and the ablation of the nozzle throat The resulting deformation causes the thrust action line of the engine to deviate from the central axis of the engine, resulting in thrust eccentricity

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