JPS5632057A - Rocket engine - Google Patents

Rocket engine

Info

Publication number
JPS5632057A
JPS5632057A JP10827379A JP10827379A JPS5632057A JP S5632057 A JPS5632057 A JP S5632057A JP 10827379 A JP10827379 A JP 10827379A JP 10827379 A JP10827379 A JP 10827379A JP S5632057 A JPS5632057 A JP S5632057A
Authority
JP
Japan
Prior art keywords
nozzle
generated
shock
supersonic
wave
Prior art date
Legal status (The legal status 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 status listed.)
Pending
Application number
JP10827379A
Other languages
Japanese (ja)
Inventor
Masaaki Kusano
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to JP10827379A priority Critical patent/JPS5632057A/en
Publication of JPS5632057A publication Critical patent/JPS5632057A/en
Pending legal-status Critical Current

Links

Landscapes

  • Jet Pumps And Other Pumps (AREA)

Abstract

PURPOSE: To shorten the length of a nozzle as compared with convertional ones and reduce the overall size by a method wherein a shock wave is generated from a shock-wave generating portion by a supersonic flow of exhaust gas in the interior of the nozzle of a rocket engine.
CONSTITUTION: The exhaust gas 2 generated in a combustion chamber 1 flows through a throat 3, expands at a nozzle 4 to attain a supersonic velocity. A shock- wave generating portion 6, where a shock wave is generated by the supersonic gas flow, has a double-wedge cross section 5 and is arranged in the roughly central portion of the nozzle 4. The shock wave 7 generated at the portion 6 produces a localized sharp increase of pressure at a portion 8 of the nozzle 4, to augment the thrust.
COPYRIGHT: (C)1981,JPO&Japio
JP10827379A 1979-08-25 1979-08-25 Rocket engine Pending JPS5632057A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP10827379A JPS5632057A (en) 1979-08-25 1979-08-25 Rocket engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP10827379A JPS5632057A (en) 1979-08-25 1979-08-25 Rocket engine

Publications (1)

Publication Number Publication Date
JPS5632057A true JPS5632057A (en) 1981-04-01

Family

ID=14480458

Family Applications (1)

Application Number Title Priority Date Filing Date
JP10827379A Pending JPS5632057A (en) 1979-08-25 1979-08-25 Rocket engine

Country Status (1)

Country Link
JP (1) JPS5632057A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59143101U (en) * 1983-03-14 1984-09-25 三菱電機株式会社 low pass filter
DE102005002283A1 (en) * 2004-11-20 2006-11-09 SCHÄFER, Alexander Rocket propulsion, has combustion chamber including thrust pipe, where thrust pipe is spaced out simultaneously with presonic velocities of gas and also with supersonic velocities
US8893504B2 (en) 2010-10-01 2014-11-25 Rolls-Royce Plc Igniter

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS59143101U (en) * 1983-03-14 1984-09-25 三菱電機株式会社 low pass filter
DE102005002283A1 (en) * 2004-11-20 2006-11-09 SCHÄFER, Alexander Rocket propulsion, has combustion chamber including thrust pipe, where thrust pipe is spaced out simultaneously with presonic velocities of gas and also with supersonic velocities
US8893504B2 (en) 2010-10-01 2014-11-25 Rolls-Royce Plc Igniter

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