A launch vehicle takeoff force thermal environment detection system and method

Abstract

A launch vehicle take-off force thermal environment detection system and method, comprising a plurality of combined force and heat environment detection units capable of simultaneously measuring pressure, temperature, heat flow, acceleration, and strain, respectively arranged in the boundary of the core region of the gas flow of the booster rocket engine. The center position, in the gas flow diffusion area of ​​the launch platform table, on the boundary of the core area of ​​the core stage rocket engine gas flow, on the core stage guide hole wall, on the boost guide flow hole wall, on the guide cone, and in the guide groove. The invention can greatly reduce the arrangement position and number of array sensors, simplify the on-site construction workload and protection workload, and at the same time reduce the sound-vibration coupling damage of the detection sensor and the electrical components of the front-end amplifier caused by the strong noise of the gas flow.

Description

technical field [0001] The invention relates to a system and method for detecting the thermal environment of a launch vehicle's take-off force, and belongs to the technical field of launch vehicles. Background technique [0002] The thermal environment of the launch vehicle determines the safety of the launch vehicle. It is also the basis for the design of the comprehensive protection system of the rocket system and its subsystems, and the basis for the application of new technologies in the launch engineering of the launch vehicle. The detection of the thermal environment of the launch vehicle is a direct means to obtain the impact characteristics of the launch gas flow and the ablation environment of the launch vehicle. The gas flow impact characteristics and ablation environment data obtained from the launch force thermal environment test of the launch vehicle directly support the structural strength design and thermal The protection design is also the direct basis for t...

AI Technical Summary

Problems solved by technology

[0004] Under the condition of further adding the structural strain and acceleration response parameter detection requirements of the gas flow impact condition, the array detection method introduced in the patent "a carrier rocket launch gas flow field monitoring system" (ZL201210373253.4) is used to obtain a huge amount of parameter data. The detection workload is also huge, the detection signal interference or serial is serious, and the detection cost and detection complexity are greatly increased

[0005] In addition, the take-off force and thermal environment of the launch vehicle is very complex and very harsh. In the detection practice, there are often problems that the gas flow burns out the sensor, cable, and preamplifier, causing the detection data to be distorted or not detected directly. It is also necessary to propose specific detection and protection methods Improve the reliability and effectiveness of data detection methods

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