| 摘要 |
The invention relates to aerospace engineering, in particular to rocket-engine plants, i.e. plants carrying both fuel and oxidant, or therefor plants including a gas turbine driving a compressor or a ducted fan of launch vehicles propulsion systems.In the basis of the invention advanced design of the rocket hybrid stage lays so that to order its structure and work in time at the expense of other relative positioning of elements and their configuration, and also thanks to an optimum choice of optionsThe rocket hybrid stage of this invention is characterized by turbo-pump unit is established on an input of combustion chamber case at the beginning of a gas path with ability of its ordered tap which is generated and liquid components which it move, turbo-pump unit is established on an input part of combustion chamber case at the beginning of a gas path with ability of ordered tap of working gas which is generated by it, and liquid components which are moved by it, to combustion chamber, and also that pressure value in combustion chamber is regulated on its upper border of combustion chamber supporability by, for instance, changing of turbo-pump unit turns in time.The such solution allows to supply high-energy components to combustion chamber with a charge of solid propellant due the purposeful ordered propellant components, for example, liquid oxygen and full as much as possible to use combustion chamber case mechanical properties. |
