Did You Know...
...that Thomas Edison's patent application on his phonograph was approved by the Patent Office in just seven weeks? In contrast, it took Gordon Gould, the inventor of the laser, 30 years to obtain his patent -- finally awarded in 1988!
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| Number | Title | Issue Date |
| 8181908 | Control surface failsafe drop link An aircraft control surface failsafe hinge configuration is disclosed. The arrangement comprises a drop link configuration which is adapted to attach a control surface to an aircraft structure where the drop link additionally incorporates a failsafe hinge means whic... | 05/22/2012 |
| 7946529 | Detection of effort on a flight-control actuator The use of at least one attachment screw (12) that includes means (14, 15, 17a, 17b, 20) for detecting the secondary path loading of a flight-control actuator, or associated with a bush that includes such means, for the atta... | 05/24/2011 |
| 7866602 | Sensing load relief by a secondary path of a flight control actuator Device for sensing load relief by a secondary path of a flight control actuator having a primary path and a secondary path capable of relieving the load of the primary path in the event of a breakdown thereof, the primary path comprising a screw, the screw terminati... | 01/11/2011 |
| 7789345 | Actuator control apparatus Herein disclosed is an actuator control apparatus, comprising primary control means for producing a control signal used to control an operation of an actuator in accordance with an instruction signal indicative of an operation of the actuator, secondary control mean... | 09/07/2010 |
| 7410133 | Miniature trailing edge effector for aerodynamic control Improved miniature trailing edge effectors for aerodynamic control are provided. Three types of devices having aerodynamic housings integrated to the trailing edge of an aerodynamic shape are presented, which vary in details of how the control surface can move. A bu... | 08/12/2008 |
| 7369922 | Distributed architecture for a system for managing aircraft landing gear The invention relates to a system architecture for managing aircraft landing gear and suitable for extending/retracting retractable undercarriages, steering steerable wheels, and braking braked wheels. According to the invention, the architecture comprises a communi... | 05/06/2008 |
| 7366590 | Impending failure and failure annunciation systems for actuators and drive train components A method of determining variations in operating characteristics of a mechanical system having a rotatory mode of operation. There are provided the steps of first monitoring operating impulses generated by the mechanical system during a first interval of operation; f... | 04/29/2008 |
| 7229046 | Servo mounting system for direct drive of an aircraft control surface This invention is a servo mounting system, which allows a servo with a rotating output shaft to directly power an aircraft control surface. A specially designed servo mount securely positions the servo with the central axis of its rotational output shaft on, and axi... | 06/12/2007 |
| 7185556 | Tie rod jam nut A tie rod jam nut includes a tubular body having an axial bore for receiving a tie rod. A locking portion at a first end of the body can engage the tie rod and a threaded portion of a connecting component attached to the tie rod to lock the connecting component to t... | 03/06/2007 |
| 7175133 | Wing driving apparatus A wing driving apparatus is made up of a flight controller part for generating a drive signal, first and second servo actuators, a first controller unit having a first drive circuit, and a second controller unit having a second drive circuit. The first controller un... | 02/13/2007 |
| 7017861 | Control system for actuators in an aircraft A control system for calculating control commands for actuators in an aircraft, wherein the control commands are calculated by computers distributed in the craft in dependence on input signals containing parameters that serve as the basis for said commands, wherein ... | 03/28/2006 |
| 6704624 | Method and device for controlling an aircraft maneuvering components, with electrical standby modules A device for controlling aircraft maneuvering units includes at least one control unit and a central computing unit. The control unit may be actuated by a pilot for issuing maneuvering commands. The central computing unit is capable of establishing contro... | 03/09/2004 |
| 6659399 | Compact linear split sleeves for accurate rigging in confined space An aircraft control surface actuator assembly 12 is provided, including a flight control surface 14. A mechanical drive mechanism 18 is in communication with the flight control surface 14. An actuator rod assembly 24 is mounted to the mechanical drive mec... | 12/09/2003 |
| 6241182 | Hybrid control system for an aircraft aerodynamic surface System for controlling an aerodynamic surface (1) (flap, aileron, control surface, etc.) of an aircraft. According to the invention, this system comprises: an electric machine (8) which can operate either as a motor or as a generator, the output of which is co... | 06/05/2001 |
| 4765568 | Method and system for controlling the elevator assemblies of an aircraft A fly-by-wire control system for the elevator assemblies of an aircraft is quipped with a mechanical auxiliary control (8) and with a synchronizing coupling (10). The electrical control links connecting the controlling computers to the elevator drives are ... | 08/23/1988 |
| 4759515 | Drive control for a vertical rudder of an aircraft A vertical rudder control and drive system for an aircraft, such as an aiane, is equipped with electrically controllable vertical rudder drive systems on each side of the aircraft. Additionally, the control system is equipped with a mechanically controll... | 07/26/1988 |
| 4533097 | Multi-motor actuation system for a power drive unit The invention is directed to a multi-motor actuation system for a power drive unit. The system includes three independently hydraulically controlled motors adapted to be drivingly coupled to a power drive unit output. Two of the said motors are normally a... | 08/06/1985 |
| 4394999 | Redundant or emergency steering mechanism especially for an aircraft A redundant steering mechanism for a craft, especially an aircraft, comprs redundant control components which become effective when the normal steering components become disabled as a result of an electrical power supply failure. The redundant control co... | 07/26/1983 |
| 3995800 | Fluid control system A fluid-powered control system of a type employing redundant control channels and multiple fluid signal amplifiers. Each fluid amplifier has two fluid outlets having communication with respective portions of a movable, force summing structure but having n... | 12/07/1976 |
