RU95120995A - COMPRESSED GAS ROCKET ENGINE - Google Patents

COMPRESSED GAS ROCKET ENGINE

Info

Publication number
RU95120995A
RU95120995A RU95120995/06A RU95120995A RU95120995A RU 95120995 A RU95120995 A RU 95120995A RU 95120995/06 A RU95120995/06 A RU 95120995/06A RU 95120995 A RU95120995 A RU 95120995A RU 95120995 A RU95120995 A RU 95120995A
Authority
RU
Russia
Prior art keywords
rocket engine
compressed gas
gas rocket
gas
heat exchanger
Prior art date
Application number
RU95120995/06A
Other languages
Russian (ru)
Other versions
RU2125176C1 (en
Inventor
В.Н. Виноградов
А.Г. Нятин
Original Assignee
Опытное конструкторское бюро "Факел"
Filing date
Publication date
Application filed by Опытное конструкторское бюро "Факел" filed Critical Опытное конструкторское бюро "Факел"
Priority to RU95120995A priority Critical patent/RU2125176C1/en
Priority claimed from RU95120995A external-priority patent/RU2125176C1/en
Publication of RU95120995A publication Critical patent/RU95120995A/en
Application granted granted Critical
Publication of RU2125176C1 publication Critical patent/RU2125176C1/en

Links

Claims (1)

1. Ракетный двигатель на сжатом газе, содержащий подводящий трубопровод с установленным управляющим клапаном, теплообменник с блоком регулирования тепловой мощности и сопло, отличающийся тем, что между управляющим клапаном и теплообменником установлено не менее одного газодинамического дросселя, проходное сечение которого выбрано из условия обеспечения критического перепада давления
2. Ракетный двигатель по п. 1, отличающийся тем, что газодинамические дроссели установлены по схеме параллельного соединения.1. A compressed gas rocket engine containing a supply pipe with a control valve installed, a heat exchanger with a heat power control unit and a nozzle, characterized in that at least one gas-dynamic inductor is installed between the control valve and the heat exchanger, the passage section of which is selected from the condition for ensuring a critical differential pressure
2. The rocket engine according to claim 1, characterized in that the gas-dynamic inductors are installed according to the parallel connection scheme.
RU95120995A 1995-12-13 1995-12-13 Compressed gas propellant rocket engine RU2125176C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU95120995A RU2125176C1 (en) 1995-12-13 1995-12-13 Compressed gas propellant rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU95120995A RU2125176C1 (en) 1995-12-13 1995-12-13 Compressed gas propellant rocket engine

Publications (2)

Publication Number Publication Date
RU95120995A true RU95120995A (en) 1997-12-20
RU2125176C1 RU2125176C1 (en) 1999-01-20

Family

ID=20174646

Family Applications (1)

Application Number Title Priority Date Filing Date
RU95120995A RU2125176C1 (en) 1995-12-13 1995-12-13 Compressed gas propellant rocket engine

Country Status (1)

Country Link
RU (1) RU2125176C1 (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007006444B4 (en) * 2007-02-05 2015-05-13 Airbus Defence and Space GmbH Micro-engine, in particular for use as attitude control engine, small engine and method for manufacturing a micro-engine
RU2478063C1 (en) * 2011-07-20 2013-03-27 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Space system for production of materials in space
CN113525708B (en) * 2021-09-06 2023-09-26 中国人民解放军战略支援部队航天工程大学 Unmanned aerial vehicle transmitting device and using method

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