FIELD: rocket engines. SUBSTANCE: proposed solid propellant charge for rocket engine is made in form of grain with central star-like section through channel and restriction over outer surface. Restriction of thermoplastic and heat-resistant coatings. Heat resistant coating is applied in helical line with butt joint of edges at angle α to outer surface of grain chosen within the limits from arctg(πD/nL) to argtg(πD/L), where d is diameter of grain; L is length of grain; n is number of arms of grain profile. EFFECT: provision of high level of reliability of grain owing to exclusion of destruction and ejection of fragments of restriction and degressively burning propellant residues. 3 dwg
Title | Year | Author | Number |
---|---|---|---|
SOLID PROPELLANT ROCKET ENGINE | 2001 |
|
RU2195569C1 |
MODEL CHARGE OF SOLID PROPELLANT FOR DETERMINATION OF SMOKE GENERATION OF ARMOUR MATERIALS | 2001 |
|
RU2181441C1 |
ARMORING COMPOUND FOR BALLISTATE SOLID FUEL INSERT CHARGE THERMOPLASTIC COATING | 2002 |
|
RU2217458C1 |
PROTECTIVE-ADHESION SUBLAYER TO ARMOR THE CHARGES OF SOLID ROCKET PROPELLANT | 2001 |
|
RU2217460C2 |
SOLID-PROPELLANT CHARGE FOR ROCKET ENGINE | 1999 |
|
RU2164616C1 |
MOULD | 2003 |
|
RU2248275C1 |
CASTING MOLD | 2001 |
|
RU2209728C2 |
GAS GENERATOR SOLID-PROPELLANT CHARGE | 2002 |
|
RU2232284C2 |
INSERTED SLOW-BURNING SOLID PROPELLANT CHARGE | 2002 |
|
RU2215722C2 |
METHOD OF SOLID ROCKET PROPELLANT CHARGES ARMORING | 2001 |
|
RU2219148C2 |
Authors
Dates
2003-07-20—Published
2001-08-29—Filed