FR1357065A - Rocket engine combustion chamber - Google Patents

Rocket engine combustion chamber

Info

Publication number
FR1357065A
FR1357065A FR925444A FR925444A FR1357065A FR 1357065 A FR1357065 A FR 1357065A FR 925444 A FR925444 A FR 925444A FR 925444 A FR925444 A FR 925444A FR 1357065 A FR1357065 A FR 1357065A
Authority
FR
France
Prior art keywords
combustion chamber
rocket engine
engine combustion
rocket
chamber
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.)
Expired
Application number
FR925444A
Other languages
French (fr)
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.)
ATK Launch Systems LLC
Original Assignee
Thiokol Corp
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 Thiokol Corp filed Critical Thiokol Corp
Priority to FR925444A priority Critical patent/FR1357065A/en
Application granted granted Critical
Publication of FR1357065A publication Critical patent/FR1357065A/en
Expired legal-status Critical Current

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
    • F02K9/974—Nozzle- linings; Ablative coatings
    • 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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/32—Constructional parts; Details not otherwise provided for
    • F02K9/34—Casings; Combustion chambers; Liners thereof
    • F02K9/346—Liners, e.g. inhibitors

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
FR925444A 1963-02-20 1963-02-20 Rocket engine combustion chamber Expired FR1357065A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR925444A FR1357065A (en) 1963-02-20 1963-02-20 Rocket engine combustion chamber

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR925444A FR1357065A (en) 1963-02-20 1963-02-20 Rocket engine combustion chamber

Publications (1)

Publication Number Publication Date
FR1357065A true FR1357065A (en) 1964-04-03

Family

ID=8797491

Family Applications (1)

Application Number Title Priority Date Filing Date
FR925444A Expired FR1357065A (en) 1963-02-20 1963-02-20 Rocket engine combustion chamber

Country Status (1)

Country Link
FR (1) FR1357065A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6711901B1 (en) * 2000-01-21 2004-03-30 Alliant Techsystems Inc. Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6711901B1 (en) * 2000-01-21 2004-03-30 Alliant Techsystems Inc. Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same
US6904755B2 (en) 2000-01-21 2005-06-14 Alliant Techsystems, Inc. Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same

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