| 摘要 |
1309548 Rockets PAINS-WESSEX Ltd 29 May 1970 [9 June 1969 3 Feb 1970] 28974/69 and 5100/70 Heading F3A [Also in Division C1] A rocket comprises a combustion chamber 2, Fig. 1, a quickmatch 9 or other fuze producing a like energy flame for igniting a plastic propellant charge 8, and copper chromate distributed within the propellant charge and/or exposed on at least part of the propellant surface that is to be ignited, the propellant charge comprising a solid oxidizing agent bound with a viscoelastic, liquid, aliphatic hydrocarbon binder having side groups and a viscosity of from 250,000 to 7,000,000 poises at 25‹ C., e.g. polyisobutene. The oxidizing agent can be ammonium perchlorate. A surface active agent comprising, for example, an admixture of pentaerythritol dioleate, ethyl oleate, and sodium dioctyl sulphosuccinate and a moderating agent such as ammonium picrate or oxamide can be included in the propellant composition. Titanium dioxide may also be included. A fuse composition 7 is provided to ignite flare or smoke producing charges (not shown). The quickmatch 9 is ignitable by means of a cartridge cap or Bickford fuse 10 and is self supporting or is supported in a metal, plastic or paper tube (not shown). In another embodiment, Fig. 2, the quickmatch 17 extends towards a primed cambric element 19 for igniting the propellant charge 16. The copper chromate can be distributed in a discontinuous layer over the exposed surfaces of the propellant charge by sprinkling or dusting, or by applying a slurry of the copper chromate in a volatile liquid which is a solvent for the binder. Alternatively, where the copper chromate is intimately admixed with the propellant, the particles of copper chromate can be exposed by applying a suitable solvent to the propellant composition. The particle size of the copper chromate is less than 120 mesh (B.S.S.). |
