FIELD: rocket technology.
SUBSTANCE: The invention relates to rocket technology and is intended for use in rockets. A dual-mode solid propellant rocket engine, containing a starting and sustainer combustion chambers, a diaphragm with peripheral holes with a cross section in the form of ring sectors, a membrane and a nozzle, according to the invention, grooves are made in the membrane from the side of the starting combustion chamber in the area of the side and inner surfaces of the gas ducts with grooves with a membrane thickness under grooves, decreasing towards the axis of the starting chamber, and the thickness of the membrane under the grooves at the inner surface of the gas ducts is 0.2…0.8 of the membrane thickness at the outer surface of the gas ducts.
EFFECT: invention provides increased reliability of operation of a dual-mode solid propellant rocket engine with a high-energy fuel charge.
1 cl, 1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| DUAL-MODE SOLID-PROPELLANT ROCKET ENGINE | 2017 |
|
RU2687500C1 |
| MISSILE BODY OF A ROCKET PROJECTILE | 2022 |
|
RU2791165C1 |
| MULTI-MODE SOLID-PROPELLANT ROCKET ENGINE | 2019 |
|
RU2715453C1 |
| TWO-MODE SOLID PROPELLANT ROCKET ENGINE | 2008 |
|
RU2390646C1 |
| MULTI-MODE ROCKET ENGINE | 2019 |
|
RU2715450C1 |
| DOUBLE-DUTY SOLID PROPELLANT ROCKET ENGINE | 2008 |
|
RU2379539C1 |
| METHOD OF OPERATION OF DUAL-MODE JET ENGINE | 2016 |
|
RU2670287C1 |
| DUAL-CHAMBER SOLID PROPELLANT ROCKET ENGINE (SPRE) | 2022 |
|
RU2789097C1 |
| SEPARATING BOTTOM OF MULTI-IMPULSE SOLID PROPELLANT ROCKET ENGINE | 2018 |
|
RU2704058C1 |
| DUAL-MODE POWER PLANT | 2010 |
|
RU2445492C1 |
