Reactionless flare-launching apparatus

Claim 2

A reactionless flare-launching apparatus for use in an aircraft comprising: an open-ended elongated tube having a central longitudinal axis, piston means centrally positioned within said tube, said piston means including first and second longitudinally spacedapart pistons defining a gas expansion chamber therebetween, a frangible member located within said tube between said pistons, said member being secured to said pistons and arranged to fail upon the application of a predetermined gas pressure in said chamber, illuminating flare means slidably positioned within said tube outwardly of said piston means, said flare means including first and second flares each having an inner end adjacent to said pistons, said flares arranged to slide longitudinally outward from said tube, and means for generating a gas pressure within said chamber in response to an operator''s signal, said pressure being sufficient to break said frangible member and expel said flares from said tube in a direction away from said aircraft.

Claim 3

The launching apparatus of claim 1 wherein each inner end of said flares has a pyrotechnic timer contained therein, said timer including an arcuate explosive train positioned transversely to said tube longitudinal axis and having a preselected burning rate, said arcuate train having one end in contact with said flare for ignition thereof after a predetermined time interval; each of said pistons has means for preventing rotation thereof relative to said tube and each piston has an aperture therein in communication with said chamber and in registry with a portion of said arcuate explosive train for igniting said train by communicating therewith gases generated within said chamber; each of said flares has an outer end having grip means for manually rotating said flare through an arc relative to said tube and indicator means for determining the amount of flare rotation so that an operator may set each flare to ignite at a predetermined time interval by rotating said flare and said arcuate train relative to said piston aperture.

Claim 4

The launching apparatus as defined in claim 2 wherein said rotation-preventing means includes a pin slidably positioned within a radial cavity in said piston, and means within said cavity for biasing said pin radially outwardly thereof, said tube interior wall having a recessed surface portion in engagement with said pin.

Claim 5

The launching apparatus as recited in claim 1 wherein said tube is positioned transversely to a longitudinal axis of a rotary wing aircraft for ejecting said flares laterally therefrom.

Claim 6

The launching apparatus of claim 1 wherein said frangible member is an elongated metal cord coaxially aligned with said tube longitudinal axis.

Claim 7

The launching apparatus of claim 5 wherein said metal is steel.

Claim 8

The launching apparatus as defined in claim 1 wherein said gas-generating means includes a pyrotechnic mixture contained with a perforated cup secured centrally within said chamber.