GB951237A - Improvements in or relating to rocket propulsion units employing solid propellants - Google Patents

Improvements in or relating to rocket propulsion units employing solid propellants

Info

Publication number
GB951237A
GB951237A GB1266960A GB1266960A GB951237A GB 951237 A GB951237 A GB 951237A GB 1266960 A GB1266960 A GB 1266960A GB 1266960 A GB1266960 A GB 1266960A GB 951237 A GB951237 A GB 951237A
Authority
GB
United Kingdom
Prior art keywords
nozzle
propellant
rocket
relating
april
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
GB1266960A
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.)
Dynamit Nobel AG
Original Assignee
Dynamit Nobel AG
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
Priority claimed from DEK37426A external-priority patent/DE1153942B/en
Priority claimed from DEK37924A external-priority patent/DE1172475B/en
Application filed by Dynamit Nobel AG filed Critical Dynamit Nobel AG
Publication of GB951237A publication Critical patent/GB951237A/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
    • F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
    • F02K9/10—Shape or structure of solid propellant charges
    • F02K9/12—Shape or structure of solid propellant charges made of two or more portions burning at different rates or having different characteristics
    • 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
    • F02K9/10—Shape or structure of solid propellant charges
    • 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
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Adhesives Or Adhesive Processes (AREA)

Abstract

951,237. Jet propulsion plant. DYNAMIT NOBEL A.G. April 8, 1960 [April 8, 1959; June 6, 1959J, No. 12669/60. Heading F1J. [Also in Division F3] A rocket propulsion unit comprises a solid propellant 1 in hollow cylindrical form the rear end of the propellant being constricted to form at least part of a nozzle 9 of such a shape that the ratio of the area of the burning surface of a major portion of the propellant to the cross-sectional area of the narrowest portion 8 of the nozzle remains constant during burning. At least the major portion of the rocket is enclosed by a reinforced plastics shell 7, in which the reinforcement may be glass fibres. A disc 15 of readily combustible or evaporatable metal or of a reinforced polyester and provided with annular slots may be arranged in the narrowest portion 8 of the nozzle. The nozzle may be formed of propellant material as a separate unit and secured to the charge by acetone or a plastics adhesive.
GB1266960A 1959-04-08 1960-04-08 Improvements in or relating to rocket propulsion units employing solid propellants Expired GB951237A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DEK37426A DE1153942B (en) 1959-04-08 1959-04-08 Solid propellant rocket
DEK37924A DE1172475B (en) 1959-06-06 1959-06-06 Solid propellant missile

Publications (1)

Publication Number Publication Date
GB951237A true GB951237A (en) 1964-03-04

Family

ID=25983124

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1266960A Expired GB951237A (en) 1959-04-08 1960-04-08 Improvements in or relating to rocket propulsion units employing solid propellants

Country Status (1)

Country Link
GB (1) GB951237A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3719040A (en) * 1968-04-30 1973-03-06 Messerschmitt Boelkow Blohm Gas generator and tubular solid charge construction therefore
US4967599A (en) * 1980-05-19 1990-11-06 Societe Europeenne De Propulsion Mechanical and insulating connection between a nozzle and the filament-wound casing of the combustion chamber of a solid propellant rocket motor
CN105971767A (en) * 2016-05-19 2016-09-28 湖北三江航天江河化工科技有限公司 Solid booster rocket engine
CN110821708A (en) * 2019-08-30 2020-02-21 南京理工大学 Three-combustion-speed variable-thickness combined explosive column structure of jet pipe-free engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3719040A (en) * 1968-04-30 1973-03-06 Messerschmitt Boelkow Blohm Gas generator and tubular solid charge construction therefore
US4967599A (en) * 1980-05-19 1990-11-06 Societe Europeenne De Propulsion Mechanical and insulating connection between a nozzle and the filament-wound casing of the combustion chamber of a solid propellant rocket motor
CN105971767A (en) * 2016-05-19 2016-09-28 湖北三江航天江河化工科技有限公司 Solid booster rocket engine
CN110821708A (en) * 2019-08-30 2020-02-21 南京理工大学 Three-combustion-speed variable-thickness combined explosive column structure of jet pipe-free engine

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