US4489638A — Quick conversion missile system for widebody airc…

Claim 1

Independent Claim 145 words

A missile launching system for use in commercial aircraft havin a passenger compartment, said missile launching system comprising: a support structure slidably disposed in said compartment; a plurality of launch tubes disposed on said support structure, said tubes being contiguous to one another in a generally parallel array and being linearly disposed along a lengthwise portion of said compartment at a predetermined angular orientation to the axis of said aircraft; a bulkhead member for mounting in a pre-established opening in the fuselage of said aircraft having at least one exit port and one exit tube for coupling to said launch tubes in succession; sequentially actuable drive means for moving the launch tubes into alignment with the exit tube and exit port in succession; and means for selectively ejecting a missile from the launch tube which is in alignment with the exit tube and exit port.

Claim 2

Dependent Claim 145 words

A missile launching system for use in commercial aircraft havin a passenger compartment, said missile launching system comprising: a support structure slidably disposed in said compartment; a plurality of launch tubes disposed on said support structure, said tubes being contiguous to one another in a generally parallel array and being linearly disposed along a lengthwise portion of said compartment at a predetermined angular orientation to the axis of said aircraft; a bulkhead member for mounting in a pre-established opening in the fuselage of said aircraft having at least one exit port and one exit tube for coupling to said launch tubes in succession; sequentially actuable drive means for moving the launch tubes into alignment with the exit tube and exit port in succession; and means for selectively ejecting a missile from the launch tube which is in alignment with the exit tube and exit port.

Claim 3

Dependent Claim 25 words

The system of claim 1 wherein the system structure is assembled from individual components placed on board the aircraft through a pre-established passenger door opening.

Claim 4

Dependent Claim 29 words

The system of claim 1 wherein the launch tubes are positionable for loading in succession with missiles placed on board the aircraft through the exit port and exit tube.

Claim 5

Dependent Claim 22 words

The system of claim 1 further comprising a plurality of frame members and a track slidably coupled to the frame members therefor.

Claim 6

Dependent Claim 25 words

The system of claim 4 wherein each of the individual frame members is adapted for installation in the standard seat anchoring tracks of the aircraft.

Claim 7

Dependent Claim 25 words

The system of claim 4 wherein the support structure includes a plurality of detachable mounting members for affixing the launch tubes in a rigid array.

Claim 8

Dependent Claim 37 words

The system of claim 6 wherein the frame members, the mounting members, the launch tubes, and all other components of the system are individually sized for placing on board the aircraft through an established passenger door opening.

Claim 9

Dependent Claim 23 words

The system of claim 6 wherein the detachable mounting members comprise separate sections, each having U-shaped cutouts to receive the launch tubes therein.

Claim 10

Dependent Claim 74 words

The system of claim 8 wherein the launch tubes are arrayed in two rows, one above the other, and the detachable mounting members comprise three sections, a lower section having U-shaped cutouts along its upper edge, an intermediate section having U-shaped cutouts along both upper and lower edges, and an upper section having U-shaped cutouts along its lower edge, all of the cutouts being dimensioned to match the outer diameter of the launch tubes.

Claim 11

Dependent Claim 42 words

The system of claim 1 wherein the bulkhead member includes selectively operable valve means for controlling an opening in line with the exit port, the valve means being operable to seal off the opening except when a missile is to be ejected.

Claim 12

Dependent Claim 29 words

The system of claim 10 wherein the ejecting means includes means for selectively pressurizing the breech of a launch tube to eject the missile therein through the exit port.

Claim 13

Dependent Claim 25 words

The system of claim 11 further including a retractable member for selectively coupling the exit tube and a launch tube aligned therewith in sealing relationship.

Claim 14

Dependent Claim 24 words

The system of claim 11 wherein the gas pressurizing means comprises an accumulator for providing compressed air to the breech of the launch tube.

Claim 15

Dependent Claim 34 words

The system of claim 15 wherein the accumulator is positioned opposite the exit port and is selectively movable into engagement with the breech of a launch tube that is aligned with the exit port.

Claim 16

Dependent Claim 48 words

The system of claim 14 further including control means responsive to position sensing signals indicative of the movement of a launch tube into aligned position with the exit port for actuating the valve means, the retractable sealing means and the movable accumulator into positions for launching a missile.

Claim 17

Dependent Claim 33 words

The system of claim 15 wherein the control means further includes means for sensing the gas pressure in the accumulator to withhold actuation of said elements until the pressure reaches a predetermined level.

Claim 18

Dependent Claim 31 words

The system of claim 16 wherein the control means further includes means for actuating the drive means to advance to the next launch tube position after a missile has been launched.

Claim 19

Dependent Claim 55 words

The system of claim 17 wherein the control means is operative to retract the retractable means from engagement with the launch tube, close the valve means, and retract the movable accumulator from coupling to the breech of the launch tube prior to causing the drive means to advance the launch tubes to the next position.

Claim 20

Dependent Claim 142 words

A missile launcher for use in a commercial aircraft having an empty passenger compartment, said launcher comprising: an inclined frame assembly disposed in said passenger compartment and having a predetermined angle of inclination; a slidable track arrangement slidably coupled to said inclined frame assembly; a plurality of missile launch tubes disposed on said track arrangement so as to be contiguous with one another in a generally planar array and oriented to face forward and to the side of said compartment in a predetermined direction and at said predetermined angle of inclination, each of said tubes having at least one open end; and bulkhead means disposed in a pre-established opening in the fuselage of said aircraft for successively coupling to the open end of said launch tubes, the bulkhead means having an opening providing an exit port through which missiles can be launched.

Claim 21

Dependent Claim 142 words

A missile launcher for use in a commercial aircraft having an empty passenger compartment, said launcher comprising: an inclined frame assembly disposed in said passenger compartment and having a predetermined angle of inclination; a slidable track arrangement slidably coupled to said inclined frame assembly; a plurality of missile launch tubes disposed on said track arrangement so as to be contiguous with one another in a generally planar array and oriented to face forward and to the side of said compartment in a predetermined direction and at said predetermined angle of inclination, each of said tubes having at least one open end; and bulkhead means disposed in a pre-established opening in the fuselage of said aircraft for successively coupling to the open end of said launch tubes, the bulkhead means having an opening providing an exit port through which missiles can be launched.

Claim 22

Dependent Claim 45 words

The missile launcher of claim 19 wherein said bulkhead means comprises valve means for selectively providing a passageway to the exit port, and a sealing arrangement coupled to said valve means for slidably coupling said valve means to an adjacent launch tube in sealing relationship.

Claim 23

Dependent Claim 27 words

The missile launcher of claim 20 further comprising gas ejection means for selectively coupling to said launch tubes for pressurizing said tubes to eject a missile therefrom.

Claim 24

Dependent Claim 45 words

The missile launcher of claim 21 further comprising drive means coupled to advance said track arrangement along said frame assembly to successively align each of said launch tubes with said exit port to permit launching of missiles from each of said launch tubes in succession.

Claim 25

Independent Claim 164 words

The method of installing a missile launching system within the passenger compartment of a standard commercial aircraft without the necessity of modifying the aircraft's structure comprising the steps of: removing the passenger seats from the aircraft; placing all of the components making up the system on board the aircraft through a pre-existing passenger door opening; assembling a frame arrangement by mounting individual frame members to the tracks provided for anchoring the passenger seats; installing in bearing elements mounted on the individual frame members a plurality of track members for longitudinal movement relative to the aircraft; placing a plurality of launch tubes in launch tube mounting members in position on the track members to form a rigid array movable therewith; and installing a prefabricated bulkhead in a pre-existing fuselage opening, the bulkhead having means defining an exit port, a valve controlling a passageway accessing the exit port and a slidable coupling member for sealing the passageway from the exit port to an adjacent launch tube.

Claim 26

Independent Claim 164 words

The method of installing a missile launching system within the passenger compartment of a standard commercial aircraft without the necessity of modifying the aircraft's structure comprising the steps of: removing the passenger seats from the aircraft; placing all of the components making up the system on board the aircraft through a pre-existing passenger door opening; assembling a frame arrangement by mounting individual frame members to the tracks provided for anchoring the passenger seats; installing in bearing elements mounted on the individual frame members a plurality of track members for longitudinal movement relative to the aircraft; placing a plurality of launch tubes in launch tube mounting members in position on the track members to form a rigid array movable therewith; and installing a prefabricated bulkhead in a pre-existing fuselage opening, the bulkhead having means defining an exit port, a valve controlling a passageway accessing the exit port and a slidable coupling member for sealing the passageway from the exit port to an adjacent launch tube.

Claim 27

Dependent Claim 67 words

The method of claim 23 further including the steps of installing the launch tube mounting members in sections by affixing a lower tube mounting member section having a plurality of U-shaped cutouts along its upper edge to the track members and attaching an upper section having U-shaped cutouts along its lower edge to the lower section after placing a plurality of launch tubes in the U-shaped cutouts.

Claim 28

Dependent Claim 23 words

The method of claim 23 further including the step of mounting a pressurized gas source at the missile launch position opposite the bulkhead.

Claim 29

Dependent Claim 36 words

The method of claim 25 wherein said last-mentioned step includes mounting the pressurized gas source on a carriage which is movable into engagement with the breech end of the adjacent launch tube in the launch position.

Claim 30

Dependent Claim 67 words

The method of claim 25 further including the steps of advancing the array of launch tubes to move a selected launch tube into the launch position in alignment with the exit port, opening the valve, advancing the slidable coupling member into sealing relationship with the launch tube, and moving the gas source into sealed coupling relationship with the breech of the launch tube in preparation for launching.

Claim 31

Dependent Claim 44 words

The method of claim 27 further including the step of transferring the pressurized gas from the gas source into the breech of the launch tube to eject the missile therefrom in a trajectory which is directed to clear the external structure of the aircraft.

Claim 32

Dependent Claim 40 words

The method of claim 28 further including the steps of closing the valve, disengaging the coupling member from the adjacent launch tube, and uncoupling the gas source from the breech of the launch tube following ejection of the missile therefrom.

Claim 33

Dependent Claim 43 words

The method of claim 29 further including the step of advancing the array of launch tubes after a missile has been launched to bring the launch tube containing the missile to be launched next into alignment with the exit port and gas source.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1987-12-25	1988-06-25	1988-12-25	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1991-12-25	1992-06-25	1992-12-25	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1995-12-25	1996-06-25	1996-12-25	$7700.00	Window Closed / Lapsed

Quick conversion missile system for widebody aircraft

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