The Boeing Company

Other

Lawrence E Fink

Eric Evin Adamson

Spencer Robert Fugal

Braxton M Dunn

A ramjet projectile comprising: an outer assembly that is tubular and comprises first, second and third portions; solid ramjet fuel attached to and disposed inside the first portion of the outer assembly; an inner assembly disposed inside the outer assembly and comprising a first portion threadably coupled to the second portion of the outer assembly and a second portion surrounded by the third portion of the outer assembly to form an annular air passageway having an air inlet. The first portion of the inner assembly comprising a plurality of openings spatially distributed about a circumference. The inner assembly is rotatable relative to the outer assembly between first and second locations displaced by a distance from each other during travel along the gun barrel. The openings are not in flow communication with the annular air passageway when the inner assembly is at the first location and are in flow communication with the annular air passageway when the inner assembly is at the second location. Preferably the solid ramjet fuel comprises boron and a binder.

Solid-fuel ramjet ammunition

A supersonic inlet includes a supersonic section including a cowl which is at least partially elliptical, a ramp disposed within the cowl, and a flow inlet disposed between the cowl and the ramp. The ramp may also be at least partially elliptical.

Supersonic elliptical ramp inlet

A collapsible flow control structure for an axisymmetric inlet employs trapezoidal alternating actuated and non-actuated strips having leading edges hinged to a missile forebody and free trailing edges extending into an inlet aperture, the strips positionable to form a variable angle frustum of a cone. An interengagement mechanism secures adjacent strips and actuators are attached to an inner surface of the actuated strips for urging the strips between a collapsed, retracted position for a first angle frustrum to an extended position for a second angle frustrum for aerodynamic flow control.

Collapsible supersonic inlet centerbody

A stowable wing structure incorporates a wing having a span equal to a fuselage length and movable from a stowed position longitudinally aligned with the fuselage to a deployed position perpendicular to the fuselage. A pivot offset laterally from a centerline of the fuselage and aft from a symmetry point on the centerline with a corresponding offset forward toward the leading edge from a chord centerpoint on the wing allows rotation of the wing from the stowed position to the deployed position with the rotation resulting in an aft position of the chord center point relative to the fuselage symmetry point.

Air vehicle wing pivot

Slurry fuels and associated methods are disclosed herein. One aspect of the invention is directed toward a slurry fuel that includes a liquid hydrocarbon based fuel suitable for use in an air-breathing power plant, metallic particles (e.g., boron), and a fluoropolymer (e.g., polytetrafluoroethylene). In selected embodiments the slurry fuel can further include a surfactant (e.g., polyolefin amide alkeneamine and/or Product NB463S84 produced by GE Betz, Inc.). Other aspects of the invention are directed toward a slurry fuel that includes a liquid hydrocarbon based fuel, metallic particles, and a surfactant having a composition that lowers the surface tension of the liquid hydrocarbon based fuel and reduces the tendency for the metallic particles to separate from the liquid hydrocarbon based fuel.

Slurry fuels and associated methods

A nozzle for a jet engine generally includes a nozzle rim and a bendable duct for communicating an exhaust flow generated by the engine to the nozzle rim. A gimbal joint pivotably couples the nozzle rim to supporting structure. The gimbal joint allows the nozzle rim to be pivoted about a first axis and a second axis, thereby allowing changes to the vector at which the exhaust flow is discharged from the nozzle rim.

Two-axis thrust vectoring nozzle

A velocity controller for a ramjet missile, having a supersonic inlet proximate the peripheral skin thereof for admitting air to a combustion zone of a ramjet engine, is comprised of a variable pitch cover disposed in pivotable engagement within the inlet and an actuator in operative engagement with the cover for adjustably positioning same over an angular range and thereby modulating airflow for the purpose of controlling flight characteristics and, principally, velocity of the missile. A sensing system is provided for detecting a dynamic flight parameter indicative of velocity of the missile and generating an output characteristic thereof for controlling the actuator and, in turn, the pitch of the cover. Methods for improving the flight performance of both solid fuel ramjet missiles and ducted rocket missiles are also disclosed herein.

Velocity controller for ramjet missile and method therefor

An LED (18) is spaced from and directed toward a photosensitive member such as a photoresistor (16). A shutter plate (38) positioned between the photoresistor (16) and the LED (18) varies the amount of light received by the photoresistor from the LED. The shutter plate (38) is connected to one end of a cantilever beam (20) which deflects in response to acceleration forces. The shutter plate (38) variably interferes with the amount of light the photoresistor (16) receives as the cantilever beam (20) deflects. The photoresistor (16) has a plurality of photosensitive grid lines (58) which change the resistance of the photoresistor in proportion to the number of grid lines which receive light from the LED (18). The photoresistor (16), LED (18), and cantilever beam (20) are connected to electrically conductive mounting pins (14) which are inserted in a base member (12) and extend downwardly therethrough.

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Renton, WA, United States of America

Lawrence E Fink