FIELD: defense technology.
SUBSTANCE: multistaged air-defense missile comprises at least two stages with at least one liquid propellant rocket engine at lower stage (LPRE). Fuel and oxidant tanks are connected to LPRE. Controlled aerodynamic rudders and wings are installed on upper stage and at least one solid propellant rocket engine. Solid propellant boosters with solid propellant rocket engines are connected to lower stage parallel to its axis. Each LPRE comprises combustion chamber with system of regenerative cooling, turbopump set and gas generator. Turbopump set comprises oxidant and fuel pumps and main and startup turbine. Gas generator is installed coaxially with turbopump set. Outlet of fuel pump is connected to inlet of regenerative cooling system and to inlet of gas generator, outlet of oxidant pump is connected to the second inlet of gas generator, outlets of gas generator and system of regenerative cooling are connected to cylindrical portion of combustion chamber.
EFFECT: improved technical characteristics of rocket in wide range of flight modes at various height.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| AIR-DEFENSE MISSILE | 2008 |
|
RU2380650C1 |
| MULTISTAGED CRUISE MISSILE | 2008 |
|
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|
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|
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| LIQUID-PROPELLANT ENGINE (VERSIONS) | 2012 |
|
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| ANTI-AIRCRAFT MISSILE AND LIQUID-PROPELLANT ROCKET | 2012 |
|
RU2496090C1 |
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|
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|
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| MULTISTAGE CARRIER ROCKET, LIQUID-PROPELLANT ROCKET ENGINE, TURBO PUMP UNIT AND BANK NOZZLE UNIT | 2011 |
|
RU2464208C1 |
| ANTIAIRCRAFT MISSILE | 2012 |
|
RU2477446C1 |
