| 摘要 |
rocket engines. SUBSTANCE: cruise pulsejet engine has combustion chamber unit, each provided with propellant injectors and de Laval nozzle. Engine is designed for operation on hypergolic propellant. Combustion chamber unit capable of withstanding pressures up to 1000 atm is made in form of common structure consisting of two plates forming combustion chambers with nozzles and connected through heat-resistant gasket by bolt joints. Combustion chamber unit can accumulate excess heat. Ball-shaped combustion chambers accommodate propellant delivery injectors. Injectors are coupled with electronic injection sets installed on upper plate of unit. De Laval nozzles of each chamber are arranged in lower plate. Two opposite chambers have tangential nozzles making it possible to adjust position of engine. Are of inner surface of combustion chamber is 500 times greater than area of nozzle critical section. EFFECT: enlarged operating capabilities. 2 cl, 2 dwg |
