US 4,302,796 AGranted

Low drag integration of laser beam pointing device into aircraft

AssigneeThe United States of America as represented by the Secretary of the Air Force

InventorsRobert G. Gustavson, Darold B. Cummings

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Abstract

A laser beam pointing system, adapted for use in an aircraft. A preferred embodiment of the system includes: a laser beam source, within the aircraft, emitting a laser beam; and, a plurality of laser beam pointing devices in optical alignment with the laser beam. Each pointing device includes: a cylindrical shaped rotatable housing with a window, and either one or two rotatable optical means in optical alignment with the laser beam. One preferred arrangement is the mounting of one pointing device on the upper external surface of the aircraft fuselage, and of another pointing device on the lower external surface of the aircraft fuselage in a location oppositely disposed to and below the other pointing device, with the two pointing devices being in parallel relationship to each other, and with the pointing devices mounted flush with the aerodynamically configurated external surfaces of the fuselage. Another preferred arrangement is the mounting of one of the pointing devices on the leading edge of a left side fairing of the aircraft, and of another pointing device on the leading edge of the right side fairing of the aircraft angularly positioned with respect to the other pointing device, so that their respective axes are in the same plane and the axes would intersect if extended, and with the pointing devices mounted flush with the aerodynamically configurated leading edge of the respective fairings. This inventive system, unlike the prior art, permits the emitted laser beam to be projected over a broad range of angles with little or no aerodynamic interference with the aircraft on which it is mounted and used.

A laser beam pointing system, adapted for use in an aircraft having a fuselage with an upper external surface and a lower external surface, a left side fairing with a leading edge, a left wing with a wing root, a right side fairing with a leading edge, and a right wing with a wing root, wherein said left side fairing blends into said root of said left wing, and said right side fairing blends into said root of said right wing, and wherein said fuselage, said external surfaces of said fuselage, said fairings, and said wings, with roots are all aerodynamically configurated, comprising:

a. a laser beam source, internal of said aircraft, emitting a laser beam of predetermined width;
b. and, a plurality of laser beam pointing devices, wherein each one of said pointing devices of said plurality includes:
(1) a rotatable housing shaped in the form of a right circular cylinder having a first end with an opening therein to permit the passage into said housing of said emitted laser beam, a second end, and a cylindrical surface with an opening therein to permit the passage of the emitted laser beam out of said housing and out of said aircraft, and with said housing also having a horizontal axis, around which said housing is selectively rotatable;
(2) means for rotating said housing operatively associated with said housing;
(3) a window positioned in, and attached to, said housing at said opening in the cylindrical surface of the rotatable housing, wherein said window is of dimensions to permit the transmission therethrough of the emitted laser beam of predetermined width;
(4) and, at least one selectively rotatable optical means, in optical alignment with the emitted laser beam, and positioned within and attached to said rotatable housing, for directing said emitted laser beam through said window and out of said aircraft;
wherein each one of said plurality of laser beam pointing devices is mounted on and in said aircraft, and is integrated with the aircraft to conform to the aerodynamic configuration of the aircraft.

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Abstract

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