GB865206A - Improvements in or relating to propellent charges - Google Patents

Improvements in or relating to propellent charges

Info

Publication number
GB865206A
GB865206A GB3209855A GB3209855A GB865206A GB 865206 A GB865206 A GB 865206A GB 3209855 A GB3209855 A GB 3209855A GB 3209855 A GB3209855 A GB 3209855A GB 865206 A GB865206 A GB 865206A
Authority
GB
United Kingdom
Prior art keywords
burning
propellant
parts
charge
propellent
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
GB3209855A
Inventor
Aubrey Edward Harper
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.)
Imperial Chemical Industries Ltd
Original Assignee
Imperial Chemical Industries Ltd
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 Imperial Chemical Industries Ltd filed Critical Imperial Chemical Industries Ltd
Priority to GB3209855A priority Critical patent/GB865206A/en
Publication of GB865206A publication Critical patent/GB865206A/en
Priority to BE602972A priority patent/BE602972Q/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
    • F02K9/18—Shape or structure of solid propellant charges of the internal-burning type having a star or like shaped internal cavity
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Cosmetics (AREA)
  • Air Bags (AREA)
  • Feeding, Discharge, Calcimining, Fusing, And Gas-Generation Devices (AREA)

Abstract

865,206. Ammunition cartridges; explosive compositions. IMPERIAL CHEMICAL INDUSTRIES Ltd. Aug. 3, 1956 [Nov. 9, 1955], No. 32098/55. Classes 9(1) and 9(2). A perforated propellant charge for a rocket comprises at least two concentric portions of propellent composition of substantially the same physical and thermo-chemical properties in cohesive union, wherein the end surfaces and the external surface of the charge are prevented from burning; each concentric portion has a slower rate of burning than its adjacent inner concentric portion; the configuration of each concentric portion is such that at any instant of time when the propellent charge is burning the sum of the products of the area exposed for each concentric portion and the rate of burning for that portion is such as to give a total rate of evolution of gas which is required for any desired pressure-time relationship; and wherein the burning reaches all points on the periphery of the charge at substantially the same instant of time. In the arrangement shown in Fig. 2 the inner fastburning propellant 7 is star-shaped and is provided with a star-shaped perforation at its centre; the slower burning propellant 6 fills the spaces between the inner propellant 7 and a cylindrical container. The dotted lines in the Figure indicate the intermediate burning position. The propellent compositions may each comprise 62 parts guanidine nitrate, 32À5 parts ammonium nitrate, 3À5 parts pottassium nitrate and 2 parts ammonium dichromate; in addition the faster burning propellant contains 0À2 parts cupric oxalate and 0À4 parts china clay, whilst the slower burning propellant contains 0À5 parts china clay. This gives a ratio of burning speeds of 1À25. In another arrangement, Fig. 3, the inner propellant 15 is provided with an elliptical perforation. The ratio of burning speeds in this case is 2À34.
GB3209855A 1955-11-09 1955-11-09 Improvements in or relating to propellent charges Expired GB865206A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB3209855A GB865206A (en) 1955-11-09 1955-11-09 Improvements in or relating to propellent charges
BE602972A BE602972Q (en) 1955-11-09 1961-04-24 Improvements to propellant charges

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3209855A GB865206A (en) 1955-11-09 1955-11-09 Improvements in or relating to propellent charges

Publications (1)

Publication Number Publication Date
GB865206A true GB865206A (en) 1961-04-12

Family

ID=10333195

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3209855A Expired GB865206A (en) 1955-11-09 1955-11-09 Improvements in or relating to propellent charges

Country Status (2)

Country Link
BE (1) BE602972Q (en)
GB (1) GB865206A (en)

Also Published As

Publication number Publication date
BE602972Q (en) 1961-08-16

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