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US 5,150,861 AGranted
Variable sweep side force generator and roll control device
AssigneeThe Boeing Company
InventorsEdwin W. Merkel, Stephen W. Koontz
Life of this patent
Estimating the term…
Abstract
In an airborne vehicle utilizing tail fins to provide directional control by use of the sideslip maneuver, a variably positionable side force generator airfoil that is positioned in response to the normal load factor of the vehicle to eliminate undesired roll caused by sideslip.
Claims15
An airborne vehicle comprising:
- a main body having a roll axis, a yaw axis, and a pitch axis;
- means, connected to said main body, for providing lift;
- means, connected to said main body, for effecting yaw attitude control about said yaw axis to induce sideslip;
- means, pivotably connected to said main body, for effecting roll attitude control about said roll axis to counteract said sideslip, said roll attitude control means comprising at least an airfoil variably positionable between a retracted position and a plurality of extended positions in a geometric plane defined by said yaw and roll axes;
- and
- means responsive to a normal load factor for automatically positioning said airfoil in a position selected to produce a roll effect to counteract undesired roll effects inherent with sideslip.
3 more elements
An airborne vehicle, comprising:
- a main body;
- a top-mounted, one-piece wing connected to said main body for providing lift;
- a plurality of fins connected to said main body for providing pitch, yaw, and roll attitude control;
- a variably positionable side force generator airfoil pivotably connected to said main body for selective extension from a fully retracted position within said main body to a fully extended position that is substantially perpendicular to the retracted position;
- means in said main body for positioning said airfoil to any intermediate position between said fully retracted position and said fully extended position;
- and
- control means, responsive to load factor forces acting on said main body, for controlling said positioning means to dispose said airfoil in positions between said retracted and extended positions substantially to maintain said main body in a wings level, no-roll attitude during sideslip.
4 more elements
A method of turning an airborne vehicle using sideslip, said airborne vehicle defining independent and orthogonal roll, yaw and pitch axes, comprising the steps of:
- (a) deflecting tail fins on said airborne vehicle to effect yaw which results in sideslip, said sideslip producing a rolling moment;
- (b) automatically detecting changes in load factors on the airborne vehicle;
- (c) electrically generating a positioning signal responsive to changes in said load factors;
- and
- (d) automatically positioning a side force generator airfoil in response to said positioning signal, said side force generator producing a force in the plane defined by the roll and yaw axes to counteract said rolling moment during sideslip.
2 more elements
An aircraft comprising:
- an elongated body defining independent and orthogonal roll, yaw and pitch axes and having a primary airfoil for generating lift;
- adjustable fins mounted on the body for inducing sideslip to the body by effecting yaw;
- a variable sweep side force generator mounted on the body and including a variably positionable airfoil movable in a plurality of predetermined positions between a sweep angle of 0.degree. to 90.degree. in the plane defined by the yaw and roll axes to counter roll introduced to the aircraft by adjustment of the fins to induce sideslip;
- and
- a controller on the body for sensing load factors of the aircraft and for controlling the position of the side force generator airfoil in response to the sensed load factors.
2 more elements
A method of turning an airborne vehicle using sideslip, said airborne vehicle defining independent and orthogonal roll, yaw and pitch axes, comprising the steps of:
- (a) deflecting tail fins on said airborne vehicle to effect yaw which results in sideslip, said sideslip producing a rolling moment;
- (b) detecting changes in load factors on the airborne vehicle;
- (c) generating a positioning signal responsive to changes in said load factors;
- and
- (d) positioning a side force generator airfoil in response to said positioning signal to counteract said rolling moment during sideslip, said positioning of said airfoil occurring in a plurality of positions from a fully retracted to fully extended position and any intermediate position between said fully retracted and said fully extended positions, and said positions being in the plane defined by the yaw and roll axes of the airborne vehicle.
2 more elements
Dependencies are inferred from the claim text.