FIELD: weapons.
SUBSTANCE: invention concerns missile technology, particularly multistage missile construction. Two-stage guided missile includes separable march stage, launching engine with stabiliser unit, and separation device. To improve missile reliability, simplify land controls and prevent launching engine fall outside the zone of enemy troops, weight ratio of march stage and launching engine without fuel should be defined. Invention claims dependency for defining the indicated ratio.
EFFECT: improved missile reliability, simplified land controls and prevented fall of launching engine outside the zone of enemy troops.
2 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| RADIO-CONTROLLED ANTI-AIRCRAFT MISSILE | 2001 |
|
RU2184343C1 |
| ROLLING CRUISE MISSILE | 2014 |
|
RU2544446C1 |
| SUPERSONIC AIRCRAFT AND METHOD FOR FLIGHT THEREOF | 2015 |
|
RU2619361C2 |
| SUPERSONIC MISSILE | 2017 |
|
RU2686567C2 |
| METHOD FOR FIRING OF GUIDED MISSILE WITH SEPARATING STAGES AND MISSILE COMPLEX FOR ITS REALIZATION | 1998 |
|
RU2148777C1 |
| FLIGHT METHOD OF ROLLING MISSILE | 2014 |
|
RU2544447C1 |
| COUNTERAIR MISSILE | 2009 |
|
RU2439476C2 |
| METHOD FOR LAUNCHING OF TWO-STAGE GUIDED MISSILE FROM AIR CARRIER | 2006 |
|
RU2321825C2 |
| CRUISE MISSILE WITH CLOSED TYPE FOLDING VARIABLE-SWEEP WINGS | 2019 |
|
RU2737816C1 |
| RADIO-CONTROLLED MISSILE | 2003 |
|
RU2255297C1 |
