Ballistic performance calculation method in thrust termination pressure relief process of solid rocket engine

A technology of solid rockets and calculation methods, applied in calculation, computer-aided design, complex mathematical operations, etc.

Pending Publication Date: 2021-02-26
CHINA ACAD OF LAUNCH VEHICLE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The technical solution of the present invention: the present invention combines the characteristics of the engine thrust termination reverse nozzle profile, according to the aerodynamic parameter relationship and the flow conservation equation, and ba...

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  • Ballistic performance calculation method in thrust termination pressure relief process of solid rocket engine
  • Ballistic performance calculation method in thrust termination pressure relief process of solid rocket engine
  • Ballistic performance calculation method in thrust termination pressure relief process of solid rocket engine

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Embodiment Construction

[0080] In order to make the object, technical solution and advantages of the present invention clearer, the embodiments disclosed in the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0081] Such as figure 1 , in this embodiment, the method for calculating the ballistic performance of the solid rocket motor during the end of the depressurization process includes:

[0082] Step 101, establishing a physical model of the solid engine including the thrust termination of the anti-nozzle.

[0083] In this example, if figure 2 , a physical model of a solid engine with thrust termination of the anti-nozzle, including: the combustion chamber, the main nozzle, the anti-nozzle and the thrust termination device. Among them, the angle between the anti-nozzle pipe and the direction of the engine axis is α; the outlet of the anti-nozzle pipe is in the form of a straight section with a bevel angle of α+θ, and the angle between t...

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Abstract

The invention discloses a ballistic performance calculation method in a thrust termination pressure relief process of a solid rocket engine. The ballistic performance calculation method comprises thefollowing steps: establishing a solid engine physical model containing reverse spray pipe thrust termination; according to the solid engine physical model containing reverse spraying pipe thrust termination, solving and obtaining resultant thrust generated by the engine under given pressure intensity; and according to an engine gas generation and exhaust conservation equation, adopting a Runge-Kutta method to determine the pressure intensity of an engine combustion chamber and the change condition of the resultant thrust generated by the engine along with time. According to the method, the characteristics of the molded surface of the thrust termination reverse spraying pipe of the engine are combined, the ballistic performance in the thrust termination pressure relief process of the solidrocket engine is calculated according to the pneumatic parameter relation and the flow conservation equation, and the contradiction problem between the calculation precision and the complexity in theprior art is solved.

Description

technical field [0001] The invention belongs to the technical field of solid rocket motors, and in particular relates to a method for calculating the ballistic performance of a solid rocket motor in the process of thrust termination and pressure relief. Background technique [0002] The solid rocket motor has the advantages of simple structure, convenient use and maintenance, and is the most widely used power device in the field of tactical weapons. According to the energy management requirements of the overall use of missile weapons, it is necessary to use the anti-nozzle pressure relief device to achieve engine thrust termination in specific cases. After the engine thrust termination mechanism is opened, the change process of the internal ballistic performance of the engine has an important impact on the overall separation design of the missile, and is an important parameter in the overall design process. [0003] For the calculation of the internal ballistic performance ...

Claims

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Application Information

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IPC IPC(8): G06F30/28G06F17/13G06F17/11G06F119/14G06F119/08G06F113/08
CPCG06F30/28G06F17/11G06F17/13G06F2119/14G06F2119/08G06F2113/08
Inventor 李新田司世才赵君伟孙兴蔡强李冬谢鹏年秦华海扈明王林朱江赵晓宁许诺王雪坤李延成蒲晓航黄慧慧常浩
Owner CHINA ACAD OF LAUNCH VEHICLE TECH
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