31 results about "Internal ballistics" patented technology

The invention discloses a high property solid propellant rocket engine with a laterally arranged nozzle. The high property solid propellant rocket engine with the laterally arranged nozzle comprises a charging combustion chamber, an ignition device and the nozzle, wherein a combustion chamber shell body of the charging combustion chamber is a hollow cylinder. The high property solid propellant rocket engine with the laterally arranged nozzle is characterized in that the nozzle is fixedly mounted at the opening of the outer side of the combustion chamber shell body in a sealed mode, the included angle between the axis of the nozzle and the axis of the cylinder of the combustion chamber shell body is 10-90 degrees. By arranging the nozzle laterally, the requirements for high thrust and high total impulse of the solid propellant rocket engine in a small using structural space are met; by designing a special-shaped nozzle shell body, the problem of sealed mounting of the laterally arranged nozzle is solved; by designing special-shaped nozzle throats, the problem that fuel gas in the charging combustion chamber flows along the wall caused by the nozzle arranged laterally is solved, and ablation and erosion on the position of the sealed mounting structure of the nozzle are substantially improved, the reliability of heat proof, load-carrying capability and connection sealing design on the position of the sealed mounting structure of the nozzle are improved, the integration of the engine work structure and the uniformity of internal ballistic property are guaranteed.

The invention discloses a solid rocket engine erosion combustion rapid parameter identification method, and the method comprises the steps of carrying out an ignition test on a designed standard erosion engine and a standard erosion propellant grain, and obtaining a test pressure intensity curve with erosion pressure intensity peak characteristics; and giving a group of erosion parameters, and substituting the group of erosion parameters into the one-dimensional erosion internal ballistic calculation model to obtain a theoretical pressure intensity curve, and making a curve residual between the test pressure intensity curve and the theoretical pressure intensity curve, and judging whether the curve residual meets the residual requirement or not. And if the requirement is met, outputting the erosion parameter in the erosion inner ballistic calculation as an identification result, and ending the identification calculation; if the curve residual does not meet the requirement, updating anerosion parameter given by iteration through an algorithm, performing inner ballistic calculation again, calculating the curve residual, and judging whether the curve residual meets the requirement ornot; and completing the rapid parameter identification of the erosion combustion after the iteration is ended. The identification method is wide in application, and the erosion parameters of different propellants can be identified.