RU2001128237A - Solid propellant rocket engine - Google Patents

Solid propellant rocket engine

Info

Publication number
RU2001128237A
RU2001128237A RU2001128237/06A RU2001128237A RU2001128237A RU 2001128237 A RU2001128237 A RU 2001128237A RU 2001128237/06 A RU2001128237/06 A RU 2001128237/06A RU 2001128237 A RU2001128237 A RU 2001128237A RU 2001128237 A RU2001128237 A RU 2001128237A
Authority
RU
Russia
Prior art keywords
rocket engine
solid propellant
propellant rocket
charge
protrusion
Prior art date
Application number
RU2001128237/06A
Other languages
Russian (ru)
Other versions
RU2206778C1 (en
Inventor
Георгий Николаевич Амарантов
Генрих Николаевич Баранов
Виктор Яковлевич Шамраев
Анатолий Петрович Талалаев
Виталий Иванович Колесников
Владимир Семёнович Хренов
Геннадий Эдуардович Кузьмицкий
Николай Николаевич Федченко
Николай Михайлович Вронский
Семён Ионович Гринберг
Владимир Михайлович Лисовский
Original Assignee
Фгуп "Ниипм"
Filing date
Publication date
Application filed by Фгуп "Ниипм" filed Critical Фгуп "Ниипм"
Priority to RU2001128237A priority Critical patent/RU2206778C1/en
Priority claimed from RU2001128237A external-priority patent/RU2206778C1/en
Application granted granted Critical
Publication of RU2001128237A publication Critical patent/RU2001128237A/en
Publication of RU2206778C1 publication Critical patent/RU2206778C1/en

Links

Claims (1)

Заряд ракетного двигателя твердого топлива тороцилиндрической конструкции с центральным каналом, прочноскрепленный с корпусом с неотъемным днищем, отличающийся тем, что на канале заряда со стороны переднего торового днища выполнен кольцевой выступ, торцевая поверхность которого образована двумя сопряженными поверхностями с радиусами кривизны (0,02-0,05) и (0,005-0,01) длины заряда, а высота выступа составляет (0,09-0,1) диаметра заряда.The charge of a solid propellant rocket engine of a torocylindrical design with a central channel, firmly bonded to a body with an integral bottom, characterized in that an annular protrusion is made on the charge channel from the front torus bottom, the end surface of which is formed by two mating surfaces with radii of curvature (0.02-0 , 05) and (0.005-0.01) the length of the charge, and the height of the protrusion is (0.09-0.1) of the diameter of the charge.
RU2001128237A 2001-10-18 2001-10-18 Solid-fuel rocket engine charge RU2206778C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2001128237A RU2206778C1 (en) 2001-10-18 2001-10-18 Solid-fuel rocket engine charge

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2001128237A RU2206778C1 (en) 2001-10-18 2001-10-18 Solid-fuel rocket engine charge

Publications (2)

Publication Number Publication Date
RU2001128237A true RU2001128237A (en) 2003-06-20
RU2206778C1 RU2206778C1 (en) 2003-06-20

Family

ID=29210672

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2001128237A RU2206778C1 (en) 2001-10-18 2001-10-18 Solid-fuel rocket engine charge

Country Status (1)

Country Link
RU (1) RU2206778C1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111810318B (en) * 2020-06-28 2022-04-22 北京凌空天行科技有限责任公司 Single-chamber double-thrust solid rocket engine and rocket

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