A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Elevon control system

A method for controlling a flying projectile which rotates during flight, comprising: determining an angle of rotation of an inertial mass spinning about an axis during flight; and controlling at least one actuator for altering at least a portion of an aerodynamic structure, selectively in dependence on the determined angle of rotation and a control input, to control aerodynamic forces during flight. An aerodynamic surface may rotate and interact with surrounding air during flight, to produce aerodynamic forces. A sensor determines an angular rotation of the spin during flight. A control system, responsive to the sensor, produces a control signal in dependence on the determined angular rotation. An actuator selectively alters an aerodynamic characteristic of the aerodynamic surface in response to the control signal.

Steerable rotating projectile

A Reconfigurable Nose Control System (RNCS) (100) is designed to adjust the flight path of spin-stabilized artillery projectiles. The RNCS (IOO) uses the surface of a projectile nose cone as a trim tab. The nose cone may be despun by the action of aerodynamic surfaces, to zero spin relative to earth fixed coordinates using local air flow, and deflected by a simple rotary motion of a Divert Motor (132) about the longitudinal axis of the projectile. A forward section (130) of the nose cone having an ogive is mounted at an angle to the longitudinal axis of the projectile, forming an axial offset of an axis of the, forward section (130) with respect to the longitudinal axis of the projectile. Another section of the nose cone includes another motor, the Roll Generator Motor(122), that is rotationally decoupled from the forward section(130) and rotates the deflected forward section (130) so that its axis may be pointed in any direction within its range of motion. Accordingly, deflection and direction of the forward section (130) may be modulated by combined action of the motors during flight of the projectile.

Spin stabilizer projectile trajectory control

A slow rolling projectile comprises a projectile body has a forward section and a rear section and having a longitudinal axis. Two or more canards in the forward section are capable of being extended from and retracted into the projectile body at predetermined frequencies and/or for predetermined times. Two or more tail fins in the rear section are fixed coextensive to or at an angle to the longitudinal axis, and an actuator extends and retracts the canards. The canards are capable of being extended and retracted at a rate based on the rotation of the projectile sufficient to correct for lateral movement. A GPS or INS navigational system activates an actuator to extend and retract the canards.

Rolling projectile with extending and retracting canards

A guidable projectile (20) has a central shaft, a projectile body, and a surface control assembly (600). The projectile body (26) is arranged to rotate around at least a portion of the central shaft during flight of the guidable projectile (20) to provide stabilization. The surface control assembly (600) is supported by the central shaft. The surface control assembly (600) includes a movable member (602) arranged to control a trajectory of the guidable projectile (20) during flight of the guidable projectile (20), and an electromagnetic actuator (50) interconnected between the central shaft and the movable member(602). The electromagnetic actuator(50) is arranged to control movement of the movable member (602) relative to the central shaft.

Techniques for providing surface control to a guidable projectile

Trajectory is controlled by a control system having fins that de-spin a section of the control system relative to a projectile or missile. The control system also includes aero- surfaces that produce a lift when brought to rotation speed of about 0 Hz relative to a reference fame and a brake that couples the guidance package to the rotational inertia of the projectile or missile. In one example, no electric motor is used in the trajectory control system, saving weight and increasing reliability.

Projectile trajectory control system

The invention relates generally to a roll damping apparatus for a spinning projectile having a first section and a second section rotatably attached about a roll axis. The roll damping apparatus comprises a first portion attached to the front section, and a second portion attached to the rear section. The first portion is adapted to cause a braking frictional force to act on the second portion, the braking force being effective to control the spin rate of the front section relative to the rear section. The invention further relates to a spinning projectile having a roll damping apparatus.

Frictional roll control apparatus for a spinning projectile

The invention is a projectile, device and system having a roll control device which may be fixed or deployable, for providing torque counter to the spin of the projectile and providing drag on the projectile. The roll control device includes a guidance collar rotatably attached to the projectile located near a front end of the projectile wherein the guidance collar includes one or more guidance collar aero-surfaces shaped to provide torque counter to the spin on the projectile. The guidance collar aero-surfaces may be controlled by a brake and guidance electronics on the projectile. The invention also includes a body collar fixedly attached to the projectile aft of the guidance collar, wherein the body collar includes one or more body collar aero-surfaces and fixed or deployable drag devices. Another embodiment use only a guidance collar aero-surfaces to orient a fixed drag device relative to an Earth inertial reference frame to create asymmetrical drag on the projectile and thereby altering its trajectory.

Trajectory modification of a spinning projectile

An apparatus and system for controlling the trajectory of a projectile having two rotationally decoupled sections, wherein the first section is rotationally decoupled from the second section. The first section of the projectile contains a navigation system. The first section also contains an actuator by which aero-control surfaces on the second section are actuated. The second section may have external aero-spin surfaces which provide a torque counter to the rotation of the base projectile. The apparatus and system also includes embodiments having applications for nose sections of projectiles.

Trajectory modification of a spinning projectile by controlling the roll orientation of a decoupled portion of the projectile that has actuated aerodynamic surfaces

Douglas L. Smith

Papers

Projectile trajectory control system

Frictional roll control apparatus for a spinning projectile

Trajectory modification of a spinning projectile

Trajectory modification of a spinning projectile by controlling the roll orientation of a decoupled portion of the projectile that has actuated aerodynamic surfaces