FIELD: weapons.
SUBSTANCE: invention relates to missilery and can be used to stabilise missile trajectory by spinning it about lengthwise axis and with the help of aerodynamic fins. Missile spinning device comprises housing spigot interacting with appropriate helical groove on tubular guide inner surface. Proposed device comprises also a rod arranged in the tubular guide to interact with its inner surface. Aforesaid rod is aligned with the missile and fixed on its rear end face with the help of explosive link furnished with control device. Aforesaid explosive link can represent an explosive bolt.
EFFECT: simplified missile design, lower weight smaller crosswise sizes of fins.
2 cl, 4 dwg
Title | Year | Author | Number |
---|---|---|---|
SALVO LAUNCHING COMPLEX | 1998 |
|
RU2126945C1 |
JET PROJECTILE | 2002 |
|
RU2220399C1 |
ANTIAIRCRAFT GUIDED MISSILE | 2007 |
|
RU2341762C1 |
SUPERSONIC SPINNING MISSILE | 2010 |
|
RU2442101C1 |
SHIP-BORNE MISSILE STORAGE AND LAUNCHING PACK | 1999 |
|
RU2156941C1 |
SHIPBORNE CONTAINER FOR ROCKET STORAGE AND LAUNCH | 2000 |
|
RU2194235C2 |
MISSILE | 2000 |
|
RU2167384C1 |
TRANSPORT-LAUNCHING MODULE | 2003 |
|
RU2245503C1 |
STABILIZING DEVICE OF AIRCRAFT WINGED MISSILE | 2006 |
|
RU2315261C2 |
FLIGHT METHOD OF ROLLING MISSILE | 2014 |
|
RU2544447C1 |
Authors
Dates
2009-09-20—Published
2008-03-25—Filed