91results about How to "Good heat protection" 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 provides a special-shaped fuel tank for an aircraft. The special-shaped fuel tank comprises a plate-shaped component, an annular cabin, a first end frame and a second end frame and is characterized in that the annular cabin is provided with a first accommodating cavity used for accommodating an engine, the structure of the first accommodating cavity is matched with the shape of the engine, the plate-shaped component is fixedly arranged on the annular cabin along the length direction of the annular cabin to form a combined part, and the shape of combined part is matched with the shape of the aircraft; the first end frame is fixedly arranged at one ends of the plate-shaped component and the annular cabin, the second end frame is fixedly arranged at the other ends of the plate-shaped component and the annular cabin, the first end frame, the second end frame, the plate-shaped component and the annular cabin jointly form a second accommodating cavity in an enclosed manner, andthe second accommodating cavity is used for accommodating fuel. By the special-shaped fuel tank, the technical problems that a cylindrical fuel tank in the prior art is low in fuel capacity and poorin adaptability are solved.