FIELD: astronautics.
SUBSTANCE: group of inventions relates to missile, rocket stage, its launch system and method of delivery. Missile comprises at least one motor unit. This unit includes rotary rocket engine. It is made with possibility of rotation between transport position and deployment position. At that it is possible to change external geometry of rocket at movement of rocket engine into deployment position. There is a disposable mechanism of deployment by means of a spring for movement of the rocket engine from a transport position into deployment position at release of the mechanism of deployment. In order to release mechanism of deployment release mechanism is provided. Missile launching system includes carrier aircraft defining the outer dimension border and the above rocket, in which rocket engine in transport position is placed inside the outer dimension border.
EFFECT: technical result is higher reliability of device and efficiency of method.
22 cl, 8 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| CARRIER ROCKET | 2011 |
|
RU2482030C2 |
| AIRCRAFT MISSILE COMPLEX | 2005 |
|
RU2309090C2 |
| METHOD OF INJECTION OF PAYLOAD INTO NEAR-EARTH SPACE BY MEANS OF AIRCRAFT ROCKET SPACE COMPLEX AND AIRCRAFT ROCKET SPACE COMPLEX FOR REALIZATION OF THIS METHOD | 2005 |
|
RU2265558C1 |
| METHOD OF INJECTION OF OBJECTS INTO NEAR-EARTH ORBIT AND RECOVERABLE AERO-SPACE ROCKET AIRCRAFT-CARRIER FOR REALIZATION OF THIS METHOD (AERO-SPACE SYSTEM NUR-SAID SYSTEM) | 2001 |
|
RU2232700C2 |
| SPACE ROCKET SYSTEM AND METHOD FOR RENDERING SERVICES IN LAUNCHING SPACE VEHICLES USING SPACE ROCKET SYSTEM | 2001 |
|
RU2179941C1 |
| RECOVERABLE ROCKET POD | 1993 |
|
RU2053168C1 |
| PAYLOAD LAUNCHING AND TRANSPORTATION SYSTEM | 1999 |
|
RU2233772C2 |
| RECOVERABLE LAUNCH VEHICLE AND MULTIPLE CONFIGURRATION TRANSPORTATIOON SYSTEM | 1991 |
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| SOLAR THERMAL ROCKET ENGINE | 1998 |
|
RU2126493C1 |
| MEANS METHOD AND SYSTEM FOR LAUNCHING SPACECRAFT ON BASIS OF TOWED GLIDER | 1995 |
|
RU2175933C2 |
