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A Fast Parameter Identification Method for Erosion Combustion of Solid Rocket Motor

A technology for parameter identification and solid rockets, which is applied to rocket motor devices, machines/engines, mechanical equipment, etc., can solve problems such as the lack of low-cost parameter identification methods, and achieve the effects of wide applicability, simple and easy-to-understand methods, and cost reduction.

Active Publication Date: 2022-04-05
NORTHWESTERN POLYTECHNICAL UNIV +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At present, there is still a lack of general, low-cost, fast and accurate parameter identification methods for erosion and combustion

Method used

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  • A Fast Parameter Identification Method for Erosion Combustion of Solid Rocket Motor
  • A Fast Parameter Identification Method for Erosion Combustion of Solid Rocket Motor
  • A Fast Parameter Identification Method for Erosion Combustion of Solid Rocket Motor

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Embodiment Construction

[0045] This embodiment is a fast parameter identification method for erosive combustion of a solid rocket motor.

[0046] The rapid parameter identification method for erosion and combustion of solid rocket motors in this embodiment is to obtain test pressure data with erosion pressure peaks by manufacturing and designing a standard erosion test engine and a standard erosion propellant grain, and conducting a ground ignition test with the two. Finally, the parameter identification is carried out on the pressure data, and the unknown parameters in the propellant velocity erosion formula are obtained.

[0047] 1) Manufacture of standard propellant grains

[0048] The standard propellant grain designed for the erosion test is a cylindrical tubular charge with small meat thickness and full-surface burning or a cylindrical tubular charge with both ends coated on the inner and outer surfaces. Before the test starts, ensure that the basic burning rate given by the propellant manufac...

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Abstract

The invention discloses a fast parameter identification method for erosion and combustion of a solid rocket motor. By performing an ignition test on a designed standard erosion engine and a standard erosion propellant grain, a test pressure curve with erosion pressure peak characteristics is obtained. Given a set of erosion parameters, the theoretical pressure curve is obtained by substituting this set of erosion parameters into the one-dimensional erosion internal ballistic calculation model. The test pressure curve and the theoretical pressure curve are used as the curve residual to judge whether the curve residual meets the residual requirement. If the requirements are met, the erosion parameters in the erosion inner ballistic calculation are output as the identification result and the identification calculation ends. If the curve residual does not meet the requirements, the given erosion parameters are updated and iterated through the algorithm, and the internal ballistic calculation is performed again to calculate the curve residual to judge whether the curve residual meets the requirements; the rapid parameter identification of erosion combustion is completed when the iteration is terminated. The identification method is widely applicable, and the identification of erosion parameters can be realized for different propellants.

Description

technical field [0001] The invention relates to the field of aerospace propulsion technology, in particular to a fast parameter identification method for erosion and combustion of solid rocket motors. Background technique [0002] The working process of the solid rocket motor test ignition is very complicated, including the ignition and combustion of the charge, the two-phase flow, the expansion and acceleration of the airflow, and the ejection process. During the work process, the propellant combustion is often unstable, Negative effects of problems such as erosive combustion, nozzle ablation, etc. Solid rocket motors often use side-burning grains, such as tube, star, wheel, and wing column; The ratio of the cross-sectional area of ​​the pipe throat is relatively small, which leads to the unavoidable erosion and combustion in the early stage of engine operation. The characteristics of the solid rocket motor erosion combustion reaction on the internal ballistic curve are m...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/15F02K9/96
Inventor 惠卫华于城博鲍福廷刘旸贺剑郑翔
Owner NORTHWESTERN POLYTECHNICAL UNIV