| 摘要 |
<p>A rocket combustion chamber is lined with a cured plastic composition containing microballoons embedded in a thermosetting resin. The composition is made by mixing a liquid thermosetting resin, e.g. an epoxy novalac, a curing agent, e.g. methyl bicyclo-[2,2,1]- 5 - heptene - 2,3 - dicarboxycylic anhydride, an accelerator for the curing reaction, e.g. tri-dimethylamino ethyl phenol or benzyldimethylamine and microballoons of silica glass or phenol-formaldehyde resin of 50 microns-0.125 inch diameter. A thickening agent, e.g. asbestos, cotton, wool, nylon or rayon fibres, may also be added. The mixture is heated to 160-200 DEG F. After application it is cured at 120-500 DEG F. Layers 12 and 19 of the resin may be applied to the rocket shell 11 by use of a polythene covered mandrel. An adhesive may also be used. Throat insert 13 may be made of molybdenum, tungsten, copper or aluminium and has a metallic oxide coating 14. Specification 917,627 is referred to. <PICT:0984486/C3/1></p> |
