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Method for calculating pressure of small combustion chamber of double-combustion-chamber solid rocket engine

A solid rocket, dual-combustion chamber technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve problems such as no similar mature algorithms, and achieve the effect of speeding up the development progress and facilitating parameter adjustment

Active Publication Date: 2020-04-24
XIAN MODERN CHEM RES INST
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Problems solved by technology

[0004] From the technical information currently retrieved, no similar mature algorithm has been seen to estimate the pressure of the small combustion chamber

Method used

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  • Method for calculating pressure of small combustion chamber of double-combustion-chamber solid rocket engine
  • Method for calculating pressure of small combustion chamber of double-combustion-chamber solid rocket engine
  • Method for calculating pressure of small combustion chamber of double-combustion-chamber solid rocket engine

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Embodiment Construction

[0031] The specific embodiment of the present invention will be further described in detail below in conjunction with the accompanying drawings and Table 1.

[0032] Table 1 Pressure sampling data of large combustion chamber

[0033]

[0034]

[0035] see figure 1 , the method for calculating the pressure of the small combustor of the dual-combustion chamber solid rocket motor includes the following steps:

[0036] (1) First collect the large combustion chamber pressure data of a certain double combustion chamber solid rocket motor, Table 1 test data (sampling frequency is 1kHz);

[0037] (2) Import the data file, the initial pressure P of the small combustion chamber S 0 is 0.1MPa, and the propellant performance data is total temperature 2800K, gas specific heat ratio 1.22, gas molecular weight 224.6J / (kg·K);

[0038] (3) The initial pressure P of the small combustion chamber S 0 is 0.1MPa assigned to the pressure Ps of the small combustion chamber, and the pressure...

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Abstract

The invention belongs to the field of solid rocket engine combustion chamber pressure intensity calculation, and relates to a method for calculating double-combustion-chamber solid rocket engine smallcombustion chamber pressure intensity. The method comprises the steps that firstly, collecting the pressure of a large combustion chamber; initializing small combustion chamber pressure data Ps0; determining that the small combustion chamber is in an inflated or deflated state by comparing the pressure Pb of the large combustion chamber with the pressure Ps of the small combustion chamber; calculating the gas variation of the small combustion chamber according to a flow formula, and finally determining the pressure of the small combustion chamber; and repeating the calculation process until the pressure intensity data of the large combustion chamber is completely read. The influence of a throttling hole and the gunpowder performance on the pressure intensity in the small combustion chamber can be comprehensively considered, parameter adjustment by designers is facilitated, and the product development progress is accelerated.

Description

technical field [0001] The invention belongs to the field of solid rocket motors and relates to a method for calculating the pressure of a small combustion chamber in a double combustion chamber solid rocket motor. Background technique [0002] The dual-chamber solid rocket motor is used in the field of weapon ejection power. It mainly includes two combustion chambers, one large and one small, wherein the small combustion chamber is located inside the large combustion chamber. The working principle is that the gunpowder burns in the large combustion chamber to produce high-temperature and high-pressure gas, part of the gas is discharged through the nozzle of the large combustion chamber, and the other part of the gas flows into the small combustion chamber through the orifice to increase the pressure of the small combustion chamber. When the pressure of the chamber is higher than that of the large combustion chamber, the gas starts to flow out of the small combustion chambe...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F02K9/34
CPCF02K9/34F02K9/96
Inventor 邢鹏涛王中李瑞锋李宏岩朱佳佳孙志刚舒慧明许云志古呈辉马宇
Owner XIAN MODERN CHEM RES INST
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