Solid fuel regression rate test device

Abstract

The invention discloses a solid fuel regression rate test device. According to the invention, a combustion chamber with a rectangular recess structure is adopted. An igniter is arranged on the front of an upper cap, and communicates with the combustion chamber. A pressure measurement port is fixed on the middle of the upper cap, and communicates with the combustion chamber. An air inlet pipe is connected to a balancing chamber. An air inlet plate is positioned between the balancing chamber and the combustion chamber. A Laval sprayer nozzle is fixed on the back part of the combustion chamber. A fixing slot is positioned at a central part on the bottom in the combustion chamber. An agent column is placed in the fixing slot, and testing can be carried out. During the operation of the test device, combustion chamber pressure intensity and oxidant flow are both adjustable. Through the changes on the pressure intensity and the flow, a functional relationship between a burning rate and the pressure intensity and the oxidant flow can be obtained, such that test complexity can be effectively reduced. The test device provided by the invention has the advantages of simple structure, low cost, easy processing, and safe and reliable operation. With the test device, the solid fuel regression rate of a hybrid rocket motor can be tested. The test device has low requirements on various propellants. Once a propellant is prepared into a rectangular body, testing can be carried out by using the test device provided by the invention.

Description

technical field [0001] The invention relates to a solid fuel retreat rate testing device, which belongs to the technical field of solid-liquid mixed rocket engines and testing, and is used for testing the retreat rate of solid-liquid mixed rocket engine fuel under different oxidant flow conditions. Background technique [0002] In recent years, the solid-liquid hybrid rocket engine has attracted the attention of researchers because of its safety, reliability, non-toxicity and pollution-free, low cost, multiple starts and adjustable thrust. There is no or only a small amount of oxidant in the solid-liquid rocket engine. The solid fuel grain burns with the liquid or gaseous oxidant flowing through its surface. The retreat rate of the surface of the engine grain is very low, which will affect the combustion efficiency of the engine. Then it affects the performance of the engine, and improving the retreat rate becomes the key to the development of solid-liquid engines. The ener...

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Problems solved by technology

[0007] In order to avoid the deficiencies in the prior art and overcome the difficulty of measuring the rocket engine fuel retreat rate, the present invention proposes a solid fuel retreat rate test device, which adopts a combustion chamber with a rectangular groove structure, and the propellant is made into a rectangular parallelepiped. Test; when the test device is working, the pressure of the combustion chamber and the flow rate of the oxidizer can be adjusted. By changing the pressure and flow rate, the functional relationship between the burning rate and the pressure and flow rate of the oxidant can be obtained, which can effectively reduce the complexity of the test; the device structure is simple and the cost is low. , easy to process, safe and reliable to operate, and can better test the solid-liquid rocket engine solid fuel retreat rate

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