Device and method for testing flow velocity of composite solid propellant slurry

A solid propellant and testing device technology, which is applied in the characterization of the propellant slurry flow rate and the device field of the propellant slurry flow rate, can solve problems such as low test accuracy, eliminate potential safety hazards, facilitate sample injection and sample cleaning, Accurate data collection

Active Publication Date: 2019-08-02
XIAN AEROSPACE CHEM PROPULTION PLANT
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0009] In order to overcome the deficiency of low testing accuracy existing in the prior art, the present invention proposes a composite solid propellant slurry flow velocity testing device and testing method

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  • Device and method for testing flow velocity of composite solid propellant slurry

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Embodiment Construction

[0041] This embodiment is a propellant slurry flow rate testing device under pressurized conditions, including a pressure generator 1, a pressure transmitter 3, a heat preservation jacket 6, three viscosity cups 7, a viscosity cup bracket 9, an electronic balance 10, Constant temperature water bath box 11 and computer 12, wherein:

[0042] The three viscosity cups 7 are respectively the first viscosity cup, the second viscosity cup and the third viscosity cup; the first viscosity cup, the second viscosity cup and the third viscosity cup are all placed on the viscosity cup support 9 . There are three thermal insulation jackets 6, which are respectively set on the shells of the viscosity cups to form the first thermal insulation jacket of the viscosity cup, the second thermal insulation jacket of the viscosity cup and the third thermal insulation jacket of the viscosity cup. There is a distance of 1 mm between the inner surface of each of the thermal insulation jackets and the ...

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Abstract

The invention discloses a device and a method for testing the flow velocity of composite solid propellant slurry. The shells of three viscosity cups are respectively sleeved with a heat preservation jacket. A pressure output pipeline provides pressure for each viscosity cup. A pressure transmitter and a precise pressure reducing valve are mounted on the pressure output pipeline. The signal outputend of the pressure transmitter is connected with the signal input end of the computer through a data line. The signal output end of the electronic balance is connected with the signal input end of the computer through a data line. A periodic test method is adopted to sequentially obtain the flow velocity of the propellant slurry in each sampling period until the average value of the mass of the obtained propellant slurry in the period is less than 1g/min. Pressurizing curing production process conditions are reproduced, multiple models of pressurizing pouring processes of the medium-energy solid rocket engine are simulated, the change trend of the slurry along with curing reaction flowability is detected by applying the slurry flow velocity experiment model, and the high-solid-content high-viscosity slurry flow velocity and the accurate pressure curing time are given.

Description

technical field [0001] The invention relates to the field of testing the flow performance of composite solid propellant slurry, in particular to a device for testing the flow rate of propellant slurry with a solid content ≥ 85% and a viscosity ≥ 2000 Pa·s under pressurized conditions and a method for testing the flow rate of propellant slurry Characterization method. Background technique [0002] The pressurized solidification process of the composite propellant refers to the process in which the propellant slurry continues to apply a constant pressure after the pouring process and remains until the propellant column is completely solidified. After curing, the loading pressure is released at a constant rate, the purpose of which is to eliminate the stress and strain produced by the propellant grain during manufacture and improve the quality and reliability of the engine charge. At present, the pressure curing process test has been completed on the counterfeit drug engine, a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N11/02
CPCG01N11/02
Inventor 乔晓林李佳佳边雷侯媛郭琪赵悦杨丰赵慧王少岩
Owner XIAN AEROSPACE CHEM PROPULTION PLANT
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