IL28733A - Rocket-motor using a double-base propellant - Google Patents

Description

Rooket motor eirig a base propellant LBS FORGES Cs 27290 la The present invention concerns rocket motors containing a power source that prises a propellant and a tic adjuvant which acts by external application as a ballastic modifier for said Power sources comprising a double base propellant and a ballastic adjuvant are cribed and claimed in United Kingdom fication In that specification the terras base and are clearly defined and those terms and their definitions are accordingly adopted as The expression base means a composition having one ingredient in which the slope of the curve of a logarithmic plot of its burning rate pressure relationship approaches zero in a favourable ing pressures while for the other substance the slope of a corresponding curve attains a negative value in a region of useful operating The expression is intended to mean a material which enhances the ballistic performance of the jet actuated rocket motor in the present in which the propellant is 2 In accordance with the present there is provided a rocket motor comprising a propellent and a ballistic juvant which acts as a ballistic modifier for the propellant by external without being incorporated in the by being disposed so as to act in the gaseous jet at high temperature inside the motor for stabilising combustion and venting the formation of postcombustion gleam and a detrimental evolution of the ballistic adjuvant comprising at least a plastics binding agent and an oxide of iron or The propellant preferably prises ocellulose and nitroglycerine or an equivalent diethylene glycol nitrate or Preferably the ballistic adjuvant also comprises at least one of the following potassium potassium potassium barium nitrate and potassium The ballistic adjuvant may also comprise silicon dioxide or magnesium Preferred ballistic adjuvant compositions comprising the 3 by weight Potassium sulphate Ethyl cellulose Dibutyl phthalate Butyl methacrylate Polyglycol Benzoyl peroxide oxide remaining portion Ballistic adjuvants in accordance with the present invention may be used as ballistic fiers for propellants comprising nitrocellulose and nitroglycerine or an equivalent compound stabilising plasticising organic salts of copper or and powdered nitroglycerine may be replaced by equivalent for instance glycol me methane trinitrate diethylene glycol dinitrate and metriol Suitable lead salts include lead lead acetyl lead lead lead stearate and lead Suitable copper salts include monobasic salicylate and cupric Preferred propellent tions i addition to nitrocellulose and nitroglycerine or equivalent compounds additives comprising the 4 a or monobasic copper cylic acid and salicylic acids this composition nay further comprise a lead salt powdered aluminiumj lead lead acetyl lead and lead lead ealicylate or lead acetyl salicylate in an amount not more than by composition containing lead salicylate raay further comprise not than by weight of lead propyl di 2 nitrodiphenyl cupr c monobasic lead and candelilla propyl di 35 2 monobasic lead cupric candelilla and additional aliphatic or aroiaatic lead copper A preferred sition by weight Nitrocellulose Nitroglycerine cupric salicylate Monobasic lead wax in the of ballistic adjuvant in the presence of correlative proportion of molybdenum by sulphate Ethyl cellulose Butyl Polyglycol di peroxide Preferably ballistic adjuvant in a central longitudinally extending eavity provided in the The ballistic adjuvant be disposed at a certain distance from or make contact with the double base ballistic adjuvant a portion disposed at a tance from the propellant or portion in contact with the of the construction of power sources for rocket motors comprising a pellant and a ballistic adjuvant in accordance with present invention will now be described with reference to the accompanying drawing in 6 Figure 1 is a or a rocket motor showing one form of a ballistic Figure 2 is a of a similar motor as that of Figure showing a second form of ballistic Figure 3 and 4 are partial longitudinal sections showing two dispositions of the ballistic adjuvant with respect to the propellant Figures 6 and 7 are longitudinal sections of a rocket motor showing the disposition of the ballistic adjuvant within a eentral cavity of the With reference to Figure casing 1 of a rocket motor encloses a propellant 2 provided with a central longitudinally extending cavity which is generally in A ballistic adjuvant 3 also generally in is axially disposed in the central the arm of the ballistic adjuvant projecting into corresponding recesses of the central The ballistic adjuvant 3 is rigidly supported on radial members 4 and axial member thickness of the layer may be or vary gradually or along the length of the casing to allow for variation of the rate of combustion of the propellant The adjuvant 3 may comprise two more 28733 2 With reference to Figure 2 a ballistic adjuvant 3a comprises a cylinder having radial apertures the ballistic adjuvant 3a in this case being With reference to Figure 3 in addition to the ballistic adjuvant 3b longitudinally disposed in the central cavity provided in the double base propellant 2 a ballistic adjuvant 3c in the form of a corrugated disc is provided adjacent to the end of the double base propellant The ballistic adjuvant 3c may be in the form of a flat comprise two or more be or be shaped in order to present as large a surface A spring 7 maintains the propellant charge 2 in the correct position through the ballistic adjuvant 3c which is in the form of a corrugated A contact ring 11 is disposed between the propellant charge 2 and the ballistic adjuvant 3 in order to give good continuous Supporting plate 8 for the axial member 5 is attached to a BBpporting gallows A percussion cap is schematically shown at 10 and an envelope 12 is provided to enclose and protect the propellant charge This also facilitates the mounting of the With reference to Figure in addition to the longitudinally disposed ballistic adjuvant 3d an additional ballistic adjuvant in the form of an annulus is disposed between the end of the 8 ballistic adjuvant 2 and the nozzle 7 of the jet actuated The ballistic adjuvant 3e may be hollow or have a generally uniform or a contoured inner To facilitate a 13 is placed between the body 1 and the rear assembly including the nozzles and vanes of the annular element only a part of which is is the interconnection between the body and the rear A contact ring 15 is provided as the equivalent of the in Figure Part of the nozzle of the which is with is shown at The rear end of the ballistic adjuvant 3c is denoted by In Figure 5 the ballistic adjuvant 3f posed in the axial longitudinally extending cavity provided in a double base propellent 2 varies stepwise in thickness along the length of the casing of the jet actuated to allow for variation of the conditions of bustion of the double base propellent In the manner in which the thickness of the ballistic adjuvant varies from the length of the casing of the device pends on the particular configuration and perties of the particular double base propellent Figure 6 shows a ballistic adjuvant 3g dis osed in a central lon itudinally extendin 9 The thickness of the double base propellant varies continuously from one end of the casing of the device to the In Figure 7 a ballistic adjuvant 3h disposed in a central longitudinally extending cavity provided in double base propellant 1 is helical in order to present large effective This embodiment includes an envelope 12 to protect the propellant charge 2 and also the spring plate 8 and gallows 9 shown in Figure A ring 18 is disposed between the propellant charge 2 and the spring insufficientOCRQuality

Claims (1)

1. 28733/2 - 10 - CLAIMS , 1, A rocket motor comprising a double-base propellant and a ballistic adjuvant which acts as a ballistic modified for the double-bast- propellant by external application, i.e, •without being incorporated in the propellant by being disposed so as to act in the gaseous jet at high temperature inside the motor for stabilizing the combustion and preventing the formation of postcombustion gleam and a detrimental evolution of fumes, the ballistic adjuvant comprising at least a plastics binding agent and an oxide of molybdenum, tin, chromium, tungsten, zirconium, -eea?i¾Ha, lanthanum, cobalt, nickel, iron or magnesium, 2, A rocket motor according to claim 1, in which the ballistic adjuvant also comprises at least one of the following salts; potassium sulphate, potassium nitrate, potassium chloride, barium, nitrate and potassium perchlorate* 3, A rocket motor according to Claim 1 or 2, in which the ballistic adjuvant also comprises silicon dioxide* 4· A rocket motor according to claim 1 or 2, in which the ballistic adjuvant also comprises magnesium silicate, 5, A rocket motor according to claim 1, in which the ballistic adjuvant comprises from 67 to 76 weight percent of potassium sulphate, 10 to 15.5 weight percent of ethyl cellulose, 2 to 7 weight percent of dibutylphthalate, 6.5 to 10,6 weight percent of butyl methacrylate, 0,9 to 1.6 weight percent of polyglycol diacrylate, 0.09 to 0.16 weight percent of benzoylperoxide and a correlative amount of molybdic oxide* 6» A rocket motor according to any one of the preceding claims, in which the double base propellant comprises ni ro» 28733/2 - 11 -a normal or monobasic copper salt, salicylic acid, β-resorcylic acid, 2,5-dihydroxybenzoic acid and 5-methylene disalicylic acid* 7« A rocket motor according to claim 6, in which the double-pbase propellant further comprises a lead salt* 8· A rocket motor according to claim 6 or claim 7» in which the double-base propellant comprises powdered aluminium* 9. A rocket motor according to any one of claims 1 to 5» in which the double-base propellant comprises nitrocellulose and nitroglycerine or an equivalent compound thereto, lead salicylate, lead acetyl salicylate, lead 2,4-dihydrcxy-benzoate and lead 2-eth lhexoate. 10· A rocket motor according to any one of claims 1 to 5, in which the double-base propellant comprises nitrocellulose and nitroglycerine or an equivalent compound thereto and not more than 5 by weight of lead salicylate, 11· A rocket motor according to any one of claims 1 to 5, in which the double-base propellant comprises nitrocellulose and nitroglycerine or an equivalent compound thereto and not more than 5 of lead acetyl salicylate. 12, A rocket motor according to claim 10, in which the double-base propellant comprises no more than 2$ by weight of lead 2-ethyl-hexoate» 13· A rocket motor according to any one of claims 1 to 4# in which the double-base propellant comprises nitrocellulose and nitroglycerine or an equivalent compound thereto, organic salts of copper or lead, powdered aluminium, stabilizing agents and plasticizing agents. 14» A rocket motor according to any one of claims 1 to 5, in which the double-base propellant comprises nitrocellulose 28733/2 -12» with propyl di-H-adipate, 2-nitrodiphenylamine, monobasic cupric salicylate, monobasic lead »resoreylate and candellila w x. 15· A rocket motor according to any one of claims 1 to 5, in which the double-base propella t comprises nitrocellulose and nitroglycerine or an equivalent compound thereto, together with propyl di-N-adipate, 2-nitrodiphenylaraine, monobasic and lead {3-resorcylate, cupric ^resorcylate, candelilla wax and additional aliphatic or aromatic salts of lead and/or copper* 16, A rocket motor according to any one of claims 5 to 15» in which the equivalent compound to nitroglycerine is dimethylene glycol dinitrate, methyltrimethylol methane trinitrate, diethylene glycol dinitrate or metriol trinitrate* 17, A rocket motor according to claim 1, in which the double-base propellant comprises 40 to 51 weight percent of nitrocellulose (12,6 percent of nitrogen), 38 to 50 weight percent of nitroglycerine, 0.1 to 0.6 weight percent of propyl di-K-adipate, 1 to 3 weight percent of 2-nitrodiphenylaraine, 2 to 4.5 percent of 1 monobasic cupric salicylate,/to 3 weight percent of monobasic lead resorcylate and 0.08 to 0.3 weight percent of candelilla wax* 18. A rocket motor according to any one of the preceding claims, in which the ballistic adjuvant comprises an element disposed in an axial passage provided in the double-base propellant and in contact with the double-base propellant, 19. A rocket motor according to any one of claims 1 to 17» in which the ballistic adjuvant comprises an element disposed ±n an axial passage provided in the double-base propellant at a small distance from the double-base propellant, and another element in contact with the double-base propellant* 28733/2 -13- element of the ballistic adjuvant disposed in the axial passage provided in the double-base propellant gradually varies in thickness along its length. 21. A rocket motor according to claim 19, in which the thickness of the ballistic adjuvant disposed in the axial passage provided in the double-base propellant varies stepwise along its length* 22, A rocket motor according to any one of the preceding claims, in which the ballistic adjuvant comprises layersβ 23· A rocket motor according to any one of the preceding claims, injwh ch an elemenx of the ballistic adjuvant is disposed adjacent to the part of the double-base propellant adjacent to an outlet of the motor. 24. A rocket motor substantially as hereinbefore described with referenceto the accompanying drawings. for the Applicants DR. SEIHHOLD CQHN AND PARTNERS By: