FIELD: rocket engineering.
SUBSTANCE: invention relates to rocket engineering, namely, to an apparatus for securing and separating aerodynamic fairings of a launch vehicle. Apparatus for securing and separating aerodynamic fairings of a launch vehicle comprises a breaking ring rigidly connected with two fairings and fixed by two axles in the grooves of the body of the nose. Apparatus for securing and separating additionally comprises a pyrotechnic mechanism consisting of a body and two powder charges and connected via a pipeline with pistons installed in the breaking ring, said ring being made with jumpers for breaking the ring and configured for the halves of the ring to disperse after breaking in opposite directions together with the installed fairings. The pyrotechnic mechanism contains a blade and a pyro cartridge linked with the nose by means of an electrical bundle. The breaking ring is additionally fixed on the body of the LV with detachable screws. The fairings are rigidly connected with semi-rings fixed in an annular duct in the front of the nose body.
EFFECT: increase in the reliability of securing and separating aerodynamic fairings of the launch vehicle.
1 cl, 3 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| CARRIER ROCKET DETACHABLE NOSE CONE | 2010 |
|
RU2428359C1 |
| DEVICE TO SEPARATED AND JETTISON LAUNCH VEHICLE NOSE CONE | 2009 |
|
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| NOSE AERODYNAMIC FAIRING FOR SPACE VEHICLES WITH PARTS PROJECTING BEYOND THE MID-SECTION OF ROCKET BOOSTER | 2003 |
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| SPLIT AND RESET DEVICE OF THE HEAD FAIRING OF THE LAUNCH VEHICLE (OPTIONS) | 2020 |
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| CARRIER ROCKET LARGE-SIZE DETACHABLE NOSE CONE | 2010 |
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| METHOD OF AND DEVICE FOR LOADING NOSE FAIRING WITH FUSELAGE FAIRINGS PROJECTING BEYOND CROSS SECTION INTO CAR WITH EXTENSIBLE FRAME | 2006 |
|
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| METHOD FOR LOADING TO DIMENSIONS CAR WITH EXTENDABLE FRAME OF UPPER AND LOWER LONGITUDINAL FOLDS OF PAYLOAD FAIRING WITH FUSELAGE SPINE FAIRINGS PROTRUDING BEYOND MIDSHIP SECTION AND DEVICE FOR ITS REALISATION | 2007 |
|
RU2360860C2 |
| HEAD OF ANTIHAIL MISSILE | 1992 |
|
RU2045163C1 |
| METHOD OF SEPARATION OF NOSE SECTION AND FAIRING AND NOSE SECTION OF RESEARCH ROCKET | 1991 |
|
SU1834482A1 |
