US4389028A — Flat trajectory projectile

Claim 1

Independent Claim 106 words

A projectile capable of flat trajectory flight comprising: a payload section; a propulsion unit; a stabilized, aerodynamic lift-generating section rotatably mounted on the projectile to permit free, uncoupled rotation of the projectile relative to the lift-generating section, said stabilized lift generating section producing a resultant lift vertically oriented to counteract the projectile weight in order to obtain a substantially flat flight trajectory, said lift-generating section is gyroscopically stabilized in roll by a stabilizing gyroscope, having an inner and outer gimbal, to fixedly orient the resultant lift irrespestive of projectile rotation; and wherein said lift-generating section is fixedly attached to the outer gimbal of said stabilizing gyroscope.

Claim 2

Dependent Claim 106 words

A projectile capable of flat trajectory flight comprising: a payload section; a propulsion unit; a stabilized, aerodynamic lift-generating section rotatably mounted on the projectile to permit free, uncoupled rotation of the projectile relative to the lift-generating section, said stabilized lift generating section producing a resultant lift vertically oriented to counteract the projectile weight in order to obtain a substantially flat flight trajectory, said lift-generating section is gyroscopically stabilized in roll by a stabilizing gyroscope, having an inner and outer gimbal, to fixedly orient the resultant lift irrespestive of projectile rotation; and wherein said lift-generating section is fixedly attached to the outer gimbal of said stabilizing gyroscope.

Claim 3

Dependent Claim 17 words

The projectile of claim 1 wherein said lift-generating section is rotatably mounted forward of the payload section.

Claim 4

Dependent Claim 21 words

The projectile of claim 2 wherein said lift-generating section comprises an aerodynamically shaped lifting nosetip having a lift-producing, inclined forward surface.

Claim 5

Dependent Claim 64 words

The projectile of claim 3 further comprising: a rotatably-supported shaft joining and lifting nosetip to the outer gimbal of the stabilizing gyroscope; a gas generator for spinning the gyroscope rotor; and caging means to maintain orthogonal orientation of the inner gimbal and the outer gimbal of said gyroscope prior to projectile launch and to provide initial orientation of said lifting nosetip immediately upon launch.

Claim 6

Dependent Claim 35 words

The projectile of claim 4 wherein said caging means are provided with means responsive to initial launch acceleration forces to displace said caging means into a neutral position to uncage the gimbals of said gyroscope.

Claim 7

Dependent Claim 32 words

The projectile of claim 5 further comprising a removable cover shrouding said lifting nosetip prior to projectile launch, said cover being removed by the exhaust of rotor-spinning gas from said gas generator.

Claim 8

Dependent Claim 17 words

The projectile of claim 1 wherein said lift-generating section is rotatably mounted aft of the payload section.

Claim 9

Dependent Claim 50 words

The projectile of claim 7 wherein said lift-generating section comprises: a body section of the projectile fixedly attached to the outer gimbal of said stabilizing gyroscope, said body section freely rotatable relative to the remainder of the projectile during flight; and retractable lifting surfaces pivotally attached to said body section.

Claim 10

Dependent Claim 61 words

The projectile of claim 8 further comprising: openings in said body section to permit entry and egress of said lifting surfaces into and from within said body section; and springs on said body section coacting with said lifting surfaces to bias said surfaces from the folded position interior of said body section to the extended position exterior of said body section.

Claim 11

Dependent Claim 67 words

The projectile of claim 9 further comprising: longitudinal support means extending through said body section to interconnect said payload section and said propulsion unit; and biasing springs on said support means urging apart said payload section and said propulsion unit from said lift-generating body section, whereby said body section is spatially separated to permit free rotation of the projectile relative to said body section during projectile flight.

Claim 12

Dependent Claim 22 words

The projectile of claim 10 wherein said lifting surfaces, in the folded position, coact with said stabilizing gyroscope to cage the gyroscope.

Claim 13

Dependent Claim 17 words

The projectile of claim 9 further comprisings acceleration-responsive means to initiate rotor spin in said stabilizing gyroscope.

Claim 14

Dependent Claim 70 words

The projectile of claim 12 wherein said acceleration-responsive rotor-spinning means comprises: a mass slidably disposed adjacent to said gyroscope; and flexible connecting means joining said mass to the rotor of said gyroscope, said connecting means being wrappingly wound upon the rotor, whereby said mass is displaced by acceleration during projectile launch, drawing upon said connecting means to unwind the connecting means from the rotor to initiate spinning of the rotor.

Claim 15

Dependent Claim 86 words

A flight control mechanism for a self-propelled, unguided projectile comprising: an aerodynamic lift-producing device rotatably coupled to the projectile to permit free rotation relative to the projectile, a gyroscope stabilizing means, having an inner and outer gimbal, fixedly attached to said lift producing device to roll stabilize said device, said lift-producing device being fixedly attached to the outer gimbal of said gyroscopic stabilizing means; and whereby the aerodynamic lift produced by said device counteracts the projectile weight in order to obtain a substantially flat flight trajectory.

Claim 16

Dependent Claim 86 words

A flight control mechanism for a self-propelled, unguided projectile comprising: an aerodynamic lift-producing device rotatably coupled to the projectile to permit free rotation relative to the projectile, a gyroscope stabilizing means, having an inner and outer gimbal, fixedly attached to said lift producing device to roll stabilize said device, said lift-producing device being fixedly attached to the outer gimbal of said gyroscopic stabilizing means; and whereby the aerodynamic lift produced by said device counteracts the projectile weight in order to obtain a substantially flat flight trajectory.

Claim 17

Dependent Claim 24 words

The control mechanism of claim 14 wherein said lift-producing device comprises an aerodynamically-shaped lifting nosetip rotatably supported adjacent the nose portion of the projectile.

Claim 18

Dependent Claim 71 words

The control mechanism of claim 15 further comprising: a rotatably-supported shaft fixedly joining said lifting nosetip to the outer gimbal of said gyroscopic stabilizing means; caging means to maintain orthogonal orientation of the inner gimbal and the outer gimbal of said gyroscopic stabilizing means prior to launch and to provide initial orientation of said lifting nosetip immediately upon launch; and a gas generator to initiate operation of said gyroscopic stabilizing means.

Claim 19

Dependent Claim 27 words

The control mechanism of claim 16 wherein said caging means includes means responsive to initial launch acceleration forces to uncage the gimbals of said gyroscopic stabilizing means.

Claim 20

Dependent Claim 15 words

The control mechanism of claim 17 further comprising a removable cover shrouding said lifting nosetip.

Claim 21

Dependent Claim 20 words

The control mechanism of claim 18 wherein said cover is forcibly ejected by gas pressure produced by said gas generator.

Claim 22

Dependent Claim 53 words

The control mechanism of claim 14 wherein said lift-producing device comprises: an intermediate body section of the projectile fixedly attached to the outer gimbal of said gyroscopic stabilizing means, said body section freely rotatable relative to the remainder of the projectile during flight; and retractable lifting surfaces pivotally supported by said body section.

Claim 23

Dependent Claim 41 words

The control mechanism of claim 20 further comprising: openings in said body section to receive said lifting surfaces within said section; and springs coacting with said lifting surfaces to bias said surfaces into the extended position exterior of said body section.

Claim 24

Dependent Claim 57 words

The control mechanism of claim 21 further comprising: longitudinal support means extending through said body section to rotatably support the flight control mechanism on the projectile; and springs on said support means urging said body section apart from the remainder of the projectile to provide spatial separation between said body section and the remainder of the projectile.

Claim 25

Dependent Claim 34 words

The control mechanism of claim 22 further comprising caging means on said lifting surfaces coacting with said gyroscopic stabilizing means to cage said stabilizing means when the surfaces are folded within said body section.

Claim 26

Dependent Claim 18 words

The control mechanism of claim 23 further comprising acceleration-responsive means to initiate operation of said gyroscopic stabilizing means.

Claim 27

Dependent Claim 52 words

The control mechanism of claim 24 wherein said acceleration-responsive means comprise: a mass slidably positioned adjacent to said gyroscopic stabilizing means; and flexible couplings joining said mass to said stabilizing means, whereby acceleration forces displace said mass to exert a pull on said couplings to initiate spin acceleration within said stabilizing means.

Annuity Stage	Window Opens	Payment Deadline	Surcharge Period Until	Estimated Fee	Status
3.5 Years (Year 4)	1986-06-20	1986-12-20	1987-06-21	$2000.00	Window Closed / Lapsed
7.5 Years (Year 8)	1990-06-20	1990-12-20	1991-06-21	$3760.00	Window Closed / Lapsed
11.5 Years (Year 12)	1994-06-20	1994-12-20	1995-06-21	$7700.00	Window Closed / Lapsed

Flat trajectory projectile

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