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The Study on the Performance of Pintle Controlled Thrust Solid Rocket Motor

Author: MiaoHeZhuang
Tutor: WangGe
School: Harbin Engineering University
Course: Aerospace Propulsion Theory and Engineering
Keywords: Solid rocket motor Thrust control Hydrants Interior ballistics calculation Numerical Simulation
CLC: V435
Type: Master's thesis
Year: 2009
Downloads: 34
Quote: 0
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Abstract


The hydrants style solid rocket motor to achieve controllable solid rocket motor , which can be adjusted according to the actual needs of the size of the thrust , and thus improve the performance of the aircraft from different perspectives , So the hydrants Solid rocket engine research has attracted widespread attention . In this paper, the characteristics of hydrants Solid rocket engine work , establish a quasi-steady and unsteady flow field numerical calculation model to carry out a theoretical analysis and numerical simulation , reveal a the hydrants style solid rocket motor flow rule and thrust regulation characteristics , provides a theoretical basis for the the hydrants style solid rocket motor . The paper first theoretically analyzed the hydrants Solid rocket engine works , the paper argues that the hydrants type of solid rocket motors equivalent throat area in the minimum cross-section of the nozzle contour and hydrants type surface into the flow tube area at , as the basis for solid rocket motor of the type of hydrants interior ballistics calculation numerical solution . Then using FLUENT hydrants style solid rocket motor quasi-steady-state flow field and the unsteady flow field numerical model , the interior ballistics check the results of the numerical model . Carried out a large number of numerical calculation reveals the solid rocket motor flow characteristics of the type of hydrants , hydrants configuration , and the match between the law of the relationship between the flow field and thrust nozzle configuration , hydrants position and from the thrust regulation performance and than rushed efficiency point of view to get a better hydrants and nozzle type surface . Finally, the use of dynamic mesh hydrants style solid rocket motor unsteady flow field numerical model , the unsteady numerical simulation study . Analysis of the characteristics of the the thrust adjustment process unsteady flow field , burning rate characteristics of the charge , hydrants factors such as speed of movement of the pressure response of the impact of the law , and to reveal the nature of the physical phenomena of variable thrust transient process flow for experiments The study provides a theoretical basis .

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CLC: > Aviation, aerospace > Aerospace ( Astronauts ) > Propulsion system ( engine, propeller ) > Solid propellant rocket motor
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