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| Number | Title | Issue Date |
| 7362070 | Electric motor control system including position determination and error correction A system for controlling an electric motor includes a controller and a position indicator that provides position information regarding at least one motor component to the controller. The controller utilizes phase relationships indicative of the position information ... | 04/22/2008 |
| 7228739 | Precision flexure plate A precision flexure plate includes a flat disk positioned between two capacitor plates and supported by S-shaped beams. Deflection of the disk due to gravitational loads and resulting capacitance change is used to measure the accelerations in the direction perpendic... | 06/12/2007 |
| 7129876 | Digital-analog converter A digital-analog converter includes a counter (13) for performing counting operation according to clocks (CK1, CK2), a comparator (12) for comparing the count value to a digital input value and outputting the clocks (CK1, CK2 | 10/31/2006 |
| 7124634 | Single plate capacitive acceleration derivative detector A capacitance accelerometer includes a housing, and a plate fixed within the housing. A moveable plate is disposed in substantially parallel relation to the fixed plate and is coupled to the housing along at least an edge. The moveable plate and the fixed plate defi... | 10/24/2006 |
| 6586901 | Methods and apparatus suitable for facilitating control of an aircraft rudder A method and an apparatus for controlling aircraft rudder movement are disclosed. The system including a yaw damping control portion integrated with a directional compensation rudder control portion, such that the system may simultaneously provide yaw dam... | 07/01/2003 |
| 6546317 | Process and device for controlling at least one aerodynamic elevator surface of an aircraft during a takeoff Process and device for controlling at least one aerodynamic elevator surface of an aircraft during a takeoff. The device (1) comprises a control member (3), calculation means (5) and motor means (7) for controlling the aerodynamic elevator surface (2), as a ... | 04/08/2003 |
| 6526338 | Electrical fly-by-wire system for operating an aircraft rudder An electrical fly-by-wire system for operating an aircraft rudder includes a low-pass filter, arranged between a rudder bar and an actuator of a rudder. The low-pass filter receives a control command from the rudder bar corresponding to the degree of trav... | 02/25/2003 |
| 6448734 | Method for current regulation of permanently excited synchronous motors for guided missiles having an electromechanical actuating drive for the rudder In a method for current regulation of permanently excited synchronous motors for guided missiles with an electromechanical actuating drive for the rudder, the commanded current is always guided orthogonally to the magnet-wheel flow. Further: a) from measu... | 09/10/2002 |
| 5719566 | Method and apparatus for detecting dormant actuator failure The actuation system of the present invention is based upon sensing relatively small delta errors over relative short strokes as opposed to absolute travel error. An actuation system in accordance with the invention includes an actuator (30, 40, 50, 60, 7... | 02/17/1998 |
| 5694014 | Active hand controller redundancy and architecture A hand controller system which provides the proper feel of the hand controller during aircraft operation. In both non-redundant and redundant embodiments, torque, and position measurements are made from the hand controller movements and processed to provi... | 12/02/1997 |
| 5489830 | Control system with loadfeel and backdrive The control system includes a control member connected to a control centering device which resists operational control member movement and returns it to a neutral position upon release thereof. Force and position sensors connected to the control member de... | 02/06/1996 |
| 5291113 | Servo coupled hand controllers A servo controlled system is provided for electrically coupling the motions and applied forces of pilot and co-pilot control sticks. Servo-coupling between the two control sticks is accomplished by detecting the position of the control sticks of respectiv... | 03/01/1994 |
| 5015934 | Apparatus and method for minimizing limit cycle using complementary filtering techniques The apparatus controls the positioning of a device in response to a commanded input signal, and comprises an element for moving the device in response to an error signal. A sensor component determines the actual position of the device, the sensor componen... | 05/14/1991 |
| 4935682 | Full authority engine-out control augmentation subsystem A full authority engine-out control augmentation subsystem for use in a flight control system to assist a pilot and/or lateral-directional control subsystem in compensating for the yawing moment produced by the differential engine thrust that occurs when ... | 06/19/1990 |
| 4866361 | Actuator rate saturation compensator A device for compensating for actuator rate saturation is disclosed. The ice is an improvement to a servomechanism of the type wherein a command signal and a position feedback signal from a member being positioned are summed to produce an error signal fo... | 09/12/1989 |
| 4829220 | Electric flight control system with aircraft incidence protection An electric system for controlling a depth aerodynamic surface (1) of an aircraft. The system includes an attitude sensor (3) and an incidence sensor (6). A calculation means (7) in communication with the sensor controls a motor (4) so as the depth aerody... | 05/09/1989 |
| 4825375 | Apparatus and methods for apportioning commands between aircraft flight control surfaces A controller for apportioning high amplitude and low amplitude control signals between two aircraft control surfaces, such as for example, between an elevator and an associated movable horizontal stabilizer. The signals are separated along a first path an... | 04/25/1989 |
| 4797829 | Flight control optimization system for multi-control surface aircraft A flight control system utilizing multi-controlled surfaces to provide the necessary control power and feedback logic to stabilize the aircraft with minimal noise amplification. In addition, a unique performance optimization loop is integrated into the st... | 01/10/1989 |
| 4787042 | Limiting aircraft vertical acceleration response The presently-disclosed invention utilizes sensed pitched rate and sensed vertical acceleration to prevent aberrant pitch rate command outputs as a function of lead compensated sensed acceleration, controlling the vertical acceleration by sensing when a m... | 11/22/1988 |
| 4697768 | Flight control system employing complementary filter Strake, flap and canard control surfaces of an aircraft are driven by an error signal which is comprised of a pilot stick command signal and feedback components including measured vertical acceleration and pitch rate of the aircraft and a third feedback c... | 10/06/1987 |
| 4684085 | Aircraft automatic trim system An aircraft automatic trim system is operable during autopilot control to transfer trim from the elevators to the stabilizers. The thresholds for trim transfer are based on the ratio of elevator demand to available elevator control. Trim commands are prod... | 08/04/1987 |
| 4683407 | Authority limiter An authority limiter includes an input shaft clutched to an output shaft. The output shaft is geared to a motor. Opto-sensors provide control signals to a current source supplying power to the motor. Different amounts of opposing torque are applied by the... | 07/28/1987 |
| 4638229 | Asymmetric torque switching for aircraft autopilot An apparatus for providing asymmetrical torque-switching for an aircraft autopilot. The invention provides an increased amount of available pitch servo torque at high altitude. The direction of pitch of the aircraft is sensed. An increased amount of torqu... | 01/20/1987 |
| 4633404 | Automatic deceleration of aircraft during descent Deceleration control apparatus for an aircraft having an automatic altitude capture and hold system and an airspeed hold system, both systems controlled by controlling pitch attitude wherein during a descent from a higher altitude under airspeed-on-pitch ... | 12/30/1986 |
| 4617633 | Direct lift command blending The rapid and precise control of an aircraft flight path is obtained by a continuous blending of direct lift and conventional longitudinal control system commands by a unit that consists of a combination of a linear gradient and breakout element, a blendi... | 10/14/1986 |
| 4609988 | Automatic prediction and capture of a preselected altitude for aircraft An improved flight control system for initiating and thereafter controlling the automatic capture of a preselected altitude is described. At any point in the flight and in any autopilot pitch submode, the remaining time before an altitude capture is to co... | 09/02/1986 |
| 4607201 | Apparatus for improving the longitudinal or pitching stability of aircraft The control of the longitudinal or pitching stability of aircraft is imprd by providing a corrected control characteristic for the correction adjustment drive which is interposed between the pilot operated control stick and the main control drive, for ex... | 08/19/1986 |
| 4607202 | Apparatus for automatically eliminating control force errors in aircraft, especially helicopters Control force errors are automatically eliminated in aircraft, especially licopters. Such errors may occur because of disturbing forces that act on a control stick (1) for the elevator and/or rotor blade adjustment. The following features are combined. A ... | 08/19/1986 |
| 4584510 | Thumb-actuated two-axis controller A two axis joystick controller (14) produces at least one output signal in relation to pivotal displacement of a member (32) with respect to an intersection of the two axes. The member (32) is pivotally movable on a support (42) with respect to the two ax... | 04/22/1986 |
| 4583030 | Pitch/trim control Aircraft attitude along the pitch axis is controlled by inputting a velocity command to a pitch control subsystem that includes a velocity side channel and a gain side channel of a pitch servo amplifier. An output from each channel of the pitch servo ampl... | 04/15/1986 |
| 4563743 | Maneuver-force gradient system A maneuver force gradient system causes a helicopter, that otherwise tends to pitch up in a banked turn, to pitch nose-down. A command signal (25) is provided as a function of the roll angle to operate the longitudinal trim actuator (27) which automatical... | 01/07/1986 |
| 4513235 | Control apparatus Control apparatus of the kind disclosed in our U.K. patent application No. 2173887 wherein the `mover` or rotor of a linear or rotary electrical stepper motor is coupled to a manual operating member so that, not only can the motor drive the operating memb... | 04/23/1985 |
| 4490794 | Altitude preselect system for aircraft without air data computer An altitude preselect apparatus for use with or incorporation into an automatic flight control system combines the incremental altitude signal from a pneumatic encoding altimeter with a vertical speed computation to generate a smooth, continuous instantan... | 12/25/1984 |
| 4463297 | Controller for mechanically actuated device A controller is described for limiting the rate and acceleration of a device positioned by at least one actuator which responds to a sequence of position commands separated by time intervals incorporating a subtractor for taking the difference of two cons... | 07/31/1984 |
| 4456862 | Augmented proportional navigation in second order predictive scheme A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a second order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal con... | 06/26/1984 |
| 4442490 | Aircraft pitch stabilization apparatus An automatic aircraft pitch axis flight stabilization system which does not require the use of a gyroscope is described. Stability signals are derived from an altitude signal responsive to atmospheric pressure. Means responsive to rate of change of altitu... | 04/10/1984 |
| 4426607 | Differential linkage apparatus for an aircraft series servoactuator apparatus In a servoactuator system for an aircraft, a strapdown series servoactuator having an external linkage assembly is coupled between the pilot's control stick and a control surface member. The external linkage assembly includes a differential link and servo... | 01/17/1984 |
| 4418306 | Directional data stabilization system An azimuth data stabilization system for a shipborne mechanically scanned arch-track system. A unitary package is provided mounted on the roll and pitch stabilized search-track system platform. The package includes a gyro stabilized turntable with the axi... | 11/29/1983 |
| 4382282 | Trim control system for reduced drag In an automatic flight control system of the type having automatic stabilizer trim control, the long term, constant altitude cruise trim threshold limits which alter the maximum and minimum pull-in/drop-out deflection of the elevator relative to the stabi... | 05/03/1983 |
| 4345195 | Strapdown multifunction servoactuator apparatus for aircraft Strapdown, multifunction actuator apparatus comprising one or two integral units adapted for installation in an aircraft, particularly a helicopter, and coupled between the pilot's control stick linkage and the aircraft control surface (or surface servo b... | 08/17/1982 |
