FIELD: missiles.
SUBSTANCE: invention relates to the field of rocket equipment, namely to multi-mode solid propellant rocket engines, and can be used in the development of missiles. Multi-mode solid-propellant rocket engine comprises cylindrical housing, intermediate bottom dividing it into launching and mid flight combustion chambers, solid propellant charges, igniting devices and outlet nozzle. Intermediate bottom is made of semi-spherical perforated shell made of high-strength alloyed steel and having variable thickness increasing from center to outer edge, which is curved towards marching chamber. Intermediate bottom is covered by metal foil and rubber membrane on starting combustion chamber side. In the heat-resistant coating of the start-up combustion chamber there is an annular projection, which during the engine assembly is pressed and clamps the outer edge of the rubber membrane.
EFFECT: invention allows improving operating reliability of rocket engine, as well as improving manufacturability of manufacturing and assembly of such engine.
1 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| MULTI-MODE ROCKET ENGINE | 2019 |
|
RU2715450C1 |
| TWO-MODE SOLID PROPELLANT ROCKET ENGINE | 2008 |
|
RU2390646C1 |
| INTEGRAL ROCKET RAMJET ENGINE (IRRE) | 2006 |
|
RU2325544C2 |
| SEPARATING BOTTOM OF MULTI-IMPULSE SOLID PROPELLANT ROCKET ENGINE | 2018 |
|
RU2704058C1 |
| DUAL-CHAMBER SOLID PROPELLANT ROCKET ENGINE (SPRE) | 2022 |
|
RU2789097C1 |
| DUAL-MODE SOLID-PROPELLANT ROCKET ENGINE | 2017 |
|
RU2687500C1 |
| SOLID-PROPELLANT ROCKET ENGINE | 2010 |
|
RU2422663C1 |
| ROCKET ENGINE OF ROCKET-ASSISTED PROJECTILE | 2016 |
|
RU2620613C1 |
| PYROTECHNIC TRAIN-TYPE IGNITION SYSTEM | 2000 |
|
RU2178093C2 |
| SOLID PROPELLANT ROCKET ENGINE | 1993 |
|
RU2053401C1 |
