RU1821558C - Variable-expansion nozzle - Google Patents

Variable-expansion nozzle

Info

Publication number
RU1821558C
RU1821558C SU4903960A RU1821558C RU 1821558 C RU1821558 C RU 1821558C SU 4903960 A SU4903960 A SU 4903960A RU 1821558 C RU1821558 C RU 1821558C
Authority
RU
Russia
Prior art keywords
collectors
conical
nozzle
variable
broadening
Prior art date
Application number
Other languages
Russian (ru)
Inventor
Владимир Степанович Телешевский
Андрей Егорович Цветков
Владимир Николаевич Кузин
Михаил Юрьевич Смык
Original Assignee
Войсковая Часть 11284
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Войсковая Часть 11284 filed Critical Войсковая Часть 11284
Priority to SU4903960 priority Critical patent/RU1821558C/en
Application granted granted Critical
Publication of RU1821558C publication Critical patent/RU1821558C/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • F02K9/976—Deployable nozzles

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Abstract

Изобретение относитс  к ракетно-кос- мической технике и может быть использовано дл  создани  реактивных двигателей ракет-носителей. Цель изобретени  состоит в уменьшении массогабаритных характеристик и упрощении конструкции. В сопле с измен емой степенью уширени  между со- осно расположенными подвижными коническими по сами 2 размещены выполненные из материала с пам тью формы коллекторы 3. Конические по са выполнены из материала с капилл рной структурой, а коллекторы снабжены нагревател ми. 5.1 з.п.ф-лы, 1 ил. 00 ю ел ел 00 The invention relates to space rocket technology and can be used to create rocket propulsion engines. The aim of the invention is to reduce weight and size characteristics and simplify the design. In the nozzle with a varying degree of broadening, collectors 3 made of material with a shape memory are arranged between coaxially arranged movable conical ones. The conical belts are made of a material with a capillary structure, and the collectors are equipped with heaters. 5.1 c.p. f-ls, 1 ill. 00 yu ate at 00

Description

Изобретение относитс  к ракетно-кос- мической технике и может быть использовано дл  создани  реактивных двигателей ракет-носителей.The invention relates to space rocket technology and can be used to create rocket propulsion engines.

Целью изобретени   вл етс  упрощение конструкции сопла и снижение его массово-габаритных характеристик.The aim of the invention is to simplify the design of the nozzle and reduce its mass-dimensional characteristics.

Это достигаетс  тем, что в сопле с измен емой степенью уширени , содержащем расположенные сооснр подвижные кониче- q-кие пб са и прйв оды их выдвижени , оно снабжено, коллекторами, размещенными между коническими по сами и выполненными из материала с пам тью формы, причем конические по са: выполнены из материала е капилл рной структурой, а коллекторы снабжены нагревател ми.This is achieved by the fact that, in a nozzle with a variable degree of broadening, containing movable conical q-shaped baffles located right in front and right of their extension, it is equipped with collectors placed between the conical ones and made of material with shape memory, moreover conical belts: made of material with a capillary structure, and the collectors are equipped with heaters.

На чертеже представлена схема сопла с измен емой степенью уширени , состо щего из основного коллектора 1, конических по сов 2, охлаждаемых компонентами топлива , промежуточных полых коллекторов 3, теплоизол ционных прокладок 4, нагрева тельных элементов 5.The drawing shows a diagram of a nozzle with a variable degree of broadening, consisting of a main collector 1, conical struts 2, cooled by fuel components, intermediate hollow collectors 3, heat-insulating spacers 4, heating elements 5.

Устройство работает следующим образом .;..The device operates as follows.; ..

В йсхоДном положении насадок с измен емой геометрией, состо щий из конических по сов 2 и промежуточных полыхIn the final position of the nozzles with variable geometry, consisting of conical slots 2 and intermediate hollow

00

55

00

55

00

коллекторов 3, располагаетс  коаксиально вокруг части сопла с неизмен емой геометрией . В момент запуска двигател  происходит разогрев ближайшего к факелу промежуточного коллектора 3 с одной стороны факелом, с другой - нагревательным элементом, на который подаетс  ток от бортовых источников энергии. В результате происходит разогрев промежуточного коллектора 3 выше температуры мартенситных превращений, при этом сопло разворачиваетс  на величину одного конического по са 2 итак последовательно до полного раскрыти  сопла.manifolds 3 are coaxially arranged around a portion of the nozzle with unchanged geometry. At the moment of starting the engine, the intermediate collector 3 closest to the torch is heated with a torch on one side and a heating element on the other, to which current is supplied from onboard energy sources. As a result, the intermediate collector 3 is heated above the temperature of the martensitic transformations, and the nozzle rotates by the size of one conical belt 2 so that it is successive until the nozzle is fully opened.

Claims (2)

1. Сопло с измен емой степенью уширени , содержащее неподвижную часть, расположенные соосно подвижные конические по са и приводы их выдвижени , о т ли ч а- ю щ е е с   тем, что. с целью уменьшени  массогабарйтных характеристик и упрощени  конструкции,оно снабжено коллекторами , размещенными между коническими по сами и выполненными из материала с пам тью формы.1. A nozzle with a variable degree of broadening, comprising a fixed part, located coaxially movable conical belts and actuators for their extension, which is different from that. in order to reduce mass and size characteristics and simplify the design, it is equipped with collectors placed between the conical ones and made of material with shape memory. 2. Сопло по п. 1, о т ли ч а ю ще е с   тем, что конические по са выполнены из материала с капилл рной структурой, а коллекторы снабжены нагревател ми.2. The nozzle according to claim 1, moreover, the conical belts are made of a material with a capillary structure, and the collectors are equipped with heaters.
SU4903960 1991-01-22 1991-01-22 Variable-expansion nozzle RU1821558C (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU4903960 RU1821558C (en) 1991-01-22 1991-01-22 Variable-expansion nozzle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU4903960 RU1821558C (en) 1991-01-22 1991-01-22 Variable-expansion nozzle

Publications (1)

Publication Number Publication Date
RU1821558C true RU1821558C (en) 1993-06-15

Family

ID=21556425

Family Applications (1)

Application Number Title Priority Date Filing Date
SU4903960 RU1821558C (en) 1991-01-22 1991-01-22 Variable-expansion nozzle

Country Status (1)

Country Link
RU (1) RU1821558C (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2773850A1 (en) * 1998-01-16 1999-07-23 Daimler Benz Ag Combustion chamber and nozzle with outer pressure envelope especially for rocket

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
Патент US № 4754926. кл. F 02 К 1/08, опублик. 1988. Патент US №3183664, кл. 239-265.35. опублик. 1965.. *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2773850A1 (en) * 1998-01-16 1999-07-23 Daimler Benz Ag Combustion chamber and nozzle with outer pressure envelope especially for rocket

Similar Documents

Publication Publication Date Title
US2638738A (en) Ramjet engine having inlet cone diffuser automatically adjustable as to length and cone angle
US3172253A (en) Combination turbo and ramjet propulsion apparatus
SE7706503L (en) RADIATIVE ENERGY POWER SOURCE
RU1821558C (en) Variable-expansion nozzle
BILLIG SCRAM-A supersonic combustion ramjet missile
JPS56168012A (en) Heater for mass fuel combustion
JP2002012198A (en) Solar heat rocket
US4368620A (en) Windmills for ramjet engine
US3078660A (en) Convertible ram-jet pulse-jet engine
CN107100760B (en) Rocket based combined cycle engine chamber
Künkler Possibilities of adapting by-pass-engines to the requirements of higher supersonic flight
Kamo et al. Ceramics for Adiabatic Diesel Engine
RU2269022C2 (en) Aircraft ramjet engine
US3841092A (en) Regenerative ram jet engine
Hagemann RH Goddard and solar power 1924–1934
RU2018704C1 (en) Solid-propellant rocket engine
Borozhtsov et al. Experimental studies of solid propellant ignition in water
MADY Effect of configuration variables on performance of solid fuel ramjets[M. S. Thesis]
BUSCHULTE Research on the energy conversion in liquid rockets in connection with thrust control
HEISE Comparative study of various flight vehicle propulsion systems, using an air-to-air missile as an example
SMIRNOV et al. Existence of steady self-sustained regimes of combustion of porous fuels and fuels with channels(O sushchestvovanii statsionarnykh samopodderzhivaiushchikhsia rezhimov sgoraniia poristykh i kanal'nykh topliv)
FISHBEIN Characteristics of afterburning bypass turbojet engine with oxygen injection into the afterburner chamber(study of fuel injection into thrust chambers for thrust augmentation)
LINDEMANN Investigations of the ignition and flame stabilization in a ramjet engine(Performance of ignition and flame stabilization using gas generator in different ramjet combustion chamber configurations)
SU1613795A1 (en) Steam generator
Trexler et al. Design and performance at a local Mach number of 6 of an inlet for an integrated Scramjet concept(wind tunnel models- aircraft design)