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GB1168657A - Rocket Propellent Blocks. - Google Patents

Rocket Propellent Blocks.

Info

Publication number
GB1168657A
GB1168657A GB5353066A GB5353066A GB1168657A GB 1168657 A GB1168657 A GB 1168657A GB 5353066 A GB5353066 A GB 5353066A GB 5353066 A GB5353066 A GB 5353066A GB 1168657 A GB1168657 A GB 1168657A
Authority
GB
United Kingdom
Prior art keywords
elements
propellant
longitudinal axis
points
cupric
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
GB5353066A
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.)
Les Forges de Zeebrugge SA
Original Assignee
Les Forges de Zeebrugge SA
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 Les Forges de Zeebrugge SA filed Critical Les Forges de Zeebrugge SA
Publication of GB1168657A publication Critical patent/GB1168657A/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
    • F02K9/18—Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity

Landscapes

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

Abstract

1,168,657. Rocket propellants. LES FORGES DE ZEEBRUGGE S.A. 30 Nov., 1966 [2 Feb., 1966], No. 53530/66. Heading F3A. [Also in Division C1] Cylindrical rocket propellant blocks giving constant gas emission up to total combustion, comprising internal propellant elements I forming a core with a central hollow, the cross-section of the core being delimited by an outer and inner star shaped curve, and further by external propellant elements II, the element II being focused on the longitudinal axis of the block, the elements I being made of a propellant having a burning rate different from that of elements II and, the elements I each being located, in cross-section, in a sector delimited by outer points B 1 and B 2 and a point O on the longitudinal axis and being focused on a second axis parallel to the longitudinal axis and passing through a point A on the bisector line B 3 O of this sector, the curve L between the two points B 1 , B 2 having the form of a Descartes oval which is the locus of all points M for which AM-nOM is a constant, n being equal to the ratio of the burning rates of the propellants comprising the elements I and II. The elements may be made up from layers of propellant and may comprise, in various proportions, nitrocellulose, nitroglycerine, propyl - di - N - adipate, 2- nitrodiphenylamine, cupric salicylate, lead resorcylate and candelilla wax. The cupric salicylate can be replaced by cupric resorcylate. Powdered aluminium can also be added.
GB5353066A 1966-02-02 1966-11-30 Rocket Propellent Blocks. Expired GB1168657A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE675913 1966-02-02

Publications (1)

Publication Number Publication Date
GB1168657A true GB1168657A (en) 1969-10-29

Family

ID=3848248

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5353066A Expired GB1168657A (en) 1966-02-02 1966-11-30 Rocket Propellent Blocks.

Country Status (4)

Country Link
JP (1) JPS506889B1 (en)
BE (1) BE675913A (en)
FI (1) FI55583C (en)
GB (1) GB1168657A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114483374A (en) * 2022-02-27 2022-05-13 西北工业大学 A solid rocket motor grain structure with embedded metal wires

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS52123883U (en) * 1976-03-18 1977-09-20

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114483374A (en) * 2022-02-27 2022-05-13 西北工业大学 A solid rocket motor grain structure with embedded metal wires

Also Published As

Publication number Publication date
FI55583B (en) 1979-04-30
JPS506889B1 (en) 1975-03-19
BE675913A (en)
FI55583C (en) 1979-08-10

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