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RU97121660A - SOLID FUEL ROCKET ENGINE - Google Patents

SOLID FUEL ROCKET ENGINE

Info

Publication number
RU97121660A
RU97121660A RU97121660/06A RU97121660A RU97121660A RU 97121660 A RU97121660 A RU 97121660A RU 97121660/06 A RU97121660/06 A RU 97121660/06A RU 97121660 A RU97121660 A RU 97121660A RU 97121660 A RU97121660 A RU 97121660A
Authority
RU
Russia
Prior art keywords
solid propellant
rocket engine
solid fuel
engine
annular gap
Prior art date
Application number
RU97121660/06A
Other languages
Russian (ru)
Other versions
RU2138670C1 (en
Inventor
В.А. Андреев
Н.Н. Глухарев
В.В. Корнеичев
А.А. Палайчев
Original Assignee
Конструкторское бюро приборостроения
Filing date
Publication date
Application filed by Конструкторское бюро приборостроения filed Critical Конструкторское бюро приборостроения
Priority to RU97121660A priority Critical patent/RU2138670C1/en
Priority claimed from RU97121660A external-priority patent/RU2138670C1/en
Publication of RU97121660A publication Critical patent/RU97121660A/en
Application granted granted Critical
Publication of RU2138670C1 publication Critical patent/RU2138670C1/en

Links

Claims (1)

РДТТ, содержащий бронированный по наружной поверхности заряд, установленный с кольцевым зазором в камеру сгорания, уплотнение, образующее застойную зону, газодинамически сообщенную с камерой сгорания, отличающийся тем, что площадь поперечного сечения кольцевого зазора выполнена с увеличением в сторону уплотнения, причем площадь поперечного сечения на входе в кольцевой зазор (Fвх) определяется из соотношения:
Fвх > Fкр,
где
Figure 00000001
площадь критического сечения двигателя (сопла);
dкр - диаметр критического сечения двигателя (сопла).A solid propellant solid propellant solid propellant rocket solid propellant rocket engine containing a charge on the outer surface mounted with an annular gap in the combustion chamber, a seal forming a stagnant zone, gasdynamically communicated with the combustion chamber, characterized in that the cross-sectional area of the annular gap is made to increase towards the seal, and the cross-sectional area by the entrance to the annular gap (F I ) is determined from the relation:
F in > F cr
Where
Figure 00000001
critical section area of the engine (nozzle);
d cr - the diameter of the critical section of the engine (nozzle).
RU97121660A 1997-12-30 1997-12-30 Solid-propellant rocket engine RU2138670C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU97121660A RU2138670C1 (en) 1997-12-30 1997-12-30 Solid-propellant rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU97121660A RU2138670C1 (en) 1997-12-30 1997-12-30 Solid-propellant rocket engine

Publications (2)

Publication Number Publication Date
RU97121660A true RU97121660A (en) 1999-09-10
RU2138670C1 RU2138670C1 (en) 1999-09-27

Family

ID=20200515

Family Applications (1)

Application Number Title Priority Date Filing Date
RU97121660A RU2138670C1 (en) 1997-12-30 1997-12-30 Solid-propellant rocket engine

Country Status (1)

Country Link
RU (1) RU2138670C1 (en)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2164616C1 (en) * 1999-11-01 2001-03-27 Государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" Solid-propellant charge for rocket engine
RU2179989C1 (en) * 2001-02-05 2002-02-27 Государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" Armoring composition
RU2181441C1 (en) * 2001-02-07 2002-04-20 Государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" Model charge of solid propellant for determination of smoke generation of armour materials
RU2195569C1 (en) * 2001-04-17 2002-12-27 Федеральное государственное унитарное предприятие "Пермский завод им. С.М. Кирова" Solid propellant rocket engine
RU2217460C2 (en) * 2001-07-23 2003-11-27 Федеральное государственное унитарное предприятие "Научно-исследовательский институт полимерных материалов" Protective-adhesion sublayer to armor the charges of solid rocket propellant
RU2201520C1 (en) * 2002-01-29 2003-03-27 Федеральный центр двойных технологий "Союз" Model engine for determining burning rate of solid propellant in stressed-deformed state
RU2222363C1 (en) * 2002-07-17 2004-01-27 Институт прикладной механики УрО РАН Gas generator
RU2290524C1 (en) * 2005-05-23 2006-12-27 Государственное унитарное предприятие "Конструкторское бюро приборостроения" Solid propellant rocket engine
RU2418186C2 (en) * 2005-09-28 2011-05-10 Виктор Фридрихович Ланг Solid-propellant rocket engine housing

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2442082A1 (en) * 1974-09-03 1976-03-25 Dynamit Nobel Ag Solid propellant rocket drive motor - with internal burner type and burn off resisting insulation
FR2557638B1 (en) * 1983-12-29 1986-04-04 Poudres & Explosifs Ste Nale METHOD AND DEVICE FOR INHIBITING THE END FACES OF A PROPERGOL BLOCK AND BLOCK OBTAINED BY THIS METHOD
US4805402A (en) * 1986-08-18 1989-02-21 Power Bernard A Method and apparatus for sealing rocket motor segment joints
RU2079689C1 (en) * 1994-02-08 1997-05-20 Акционерная компания "Туламашзавод" Solid-propellant rocket engine for guided projectile and solid propellant ignitor

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