System and method for detecting launching force thermal environment of carrier rocket

Abstract

The invention discloses a system and method for detecting a launching force thermal environment of a carrier rocket. The system comprises a plurality of force-thermal environment combination detectionunits capable of simultaneously measuring pressure, temperature, heat flow, acceleration and strain, wherein the force-thermal environment combination detection units are correspondingly arranged ata center position of a boosting rocket engine combustion gas stream core region boundary, in a launching platform tabletop combustion gas stream diffusion zone, on a core-stage rocket engine combustion gas stream core region boundary, on the core-grade flow guide hole wall, on the boosting flow guide hole wall, on a flow guide cone and in a flow guide groove. According to the system, the arrangement position and arrangement number of array sensors can be greatly reduced, and the on-site construction workload and the protection workload are reduced; and meanwhile, the sound vibration coupling damage of combustion gas stream strong noise to electrical components of a detection sensor and a front-end amplifier is reduced.

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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