Appeal 2006-2668
Application 10/264,763
2) Boothe teaches that the ultraviolet curable polymer may be
acrylated polybutadiene and the thermally curable polymer may be a
polybutadiene (Boothe, claim 4).
3) Boothe discloses that the liner formulation may include an
optional solid filler (Boothe, col. 1, ll. 20-21) which “is present in an
amount of between about 0 and about 50% by weight” (Boothe, col. 1, ll.
24-25). “The preferable filler does not absorb ultra-violet radiations, and
can be selected for [sic, from] silica, calcium carbonate and
dicyandiamide” (Boothe, col. 1, ll. 32-34; Specification ¶ [0007]).
4) Nelson discloses a liner for solid propellant rocket motors
“comprising (in unreacted form) binder, curing agent, catalyst, fillers
and thixotropes” (Nelson, col. 3, ll. 39-41).
5) The binder may be a polybutadiene (Nelson, col. 4, ll. 8-9).
6) Nelson discloses that at least two fillers are preferably added to
reinforce the liner and to enable it to exhibit increased erosion resistance
and reduced smoke evolution during use (Nelson, col. 4, ll. 61-64).
7) According to Nelson, the filler generally comprises a metal borate,
such as zinc borate and a metal oxide filler such as alumina trihydrate
(Nelson, col. 4, l. 66-col. 5, l. 2).
8) According to Nelson, zinc borate is a fire retardant and/or
smoke/afterglow suppressant (Nelson, col. 5, ll. 25-26) and alumina
trihydrate is a flame retardant (col. 5, ll. 36-37). Nelson states that these
two components are generally present in an amount of 15-90% by
weight of the liner formula (col. 5, ll. 8-10).
9) Nelson discloses that “other filler materials can additionally be
included in the liner formulation to meet the requirements of a specific
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Last modified: September 9, 2013