Bizarre Patents
A Receptacle for supporting, rotating and sculpting a portion of ice cream or similarly malleable food while it is being consumed.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 7338011 | Method making it possible to prevent vibration of a rudder of an aircraft and aircraft using this method A method for preventing vibration of a rudder of an aircraft may have, on a lateral aerodynamic surface of the aircraft's rudder, a protruding aerodynamic element capable of generating an aerodynamic effect tending to rotate the rudder about its articulation axis. A... | 03/04/2008 |
| 7272473 | Methods and systems for analyzing system operator coupling susceptibility Methods for analyzing system operator coupling susceptibility are described herein. In one embodiment, an open loop frequency response can be compared to a related over-steer point. An over-steer point can be the condition where, as operator gain is increased for an... | 09/18/2007 |
| 7258307 | Device and method for damping at least one of a rigid body mode and elastic mode of an aircraft A device for damping at least one rigid body mode and/or at least one elastic mode of an aircraft, especially for blast load reduction and increase of stability and comfort, in an airplane having at least one sensor, a regulation unit connected to the sensor, and at... | 08/21/2007 |
| 7230567 | Azimuth/attitude detecting sensor The sensor successively calculates a rolling angle, pitch angle and azimuth from the coordinate transformation matrix with the level error and azimuth error compensated. It calculates azimuth error compensatory values using the GPS direction signal and calculates a ... | 06/12/2007 |
| 7195200 | Unmanned helicopter, takeoff method of unmanned helicopter, and landing method of unmanned helicopter An unmanned helicopter includes an altitude control device for giving a command of a collective pitch blade angle based on an altitude change rate command, etc., and performing altitude control of an airframe and takeoff device, upon reception of a takeoff start com... | 03/27/2007 |
| 7146299 | Adjustable simulation vehicle capabilities The present invention is a system and method for easily adjusting flight characteristics of a simulated aircraft. The system allows a user to adjust commanded pitch, roll or yaw values or steady state frequency response values that are associated with an atmospheric... | 12/05/2006 |
| 7090172 | Process for countering the vibrations induced in an aircraft by the windmilling of a fan and system of electric flight controls implementing this process A system and process for countering the vibrations induced in an aircraft by the windmilling of an engine fan may produce a first electric flight control command for a servocontrol to use in actuating a control surface of the aircraft. The servocontrol is slaved to ... | 08/15/2006 |
| 7014142 | Low-drag rotor/wing flap Rotor/wing aircraft having a low-drag flap are disclosed. In one embodiment, a rotor/wing aircraft includes an elongated blade having a body portion and a flap portion. The body portion has first and second edges and includes a non-symmetric portion proximate the se... | 03/21/2006 |
| 6976656 | Method for controlling the flight of an aircraft A method for controlling an aircraft includes the steps of receiving acceleration data related to an acceleration of a front portion of the aircraft, and receiving pitch, roll, and/or yaw rate data related to a rate of a center portion of the aircraft. The method al... | 12/20/2005 |
| 6915989 | Aircraft multi-axis modal suppression system Vibrations due to excitation of the natural modes of an aircraft's body are suppressed by an active multi-axis modal suppression system. Dedicated sensors are positioned in the aircraft at optimal locations for sensing modal induced vibrations. The sensor produced s... | 07/12/2005 |
| 6903752 | Method to view unseen atmospheric phenomenon using augmented reality The invention is a method for displaying otherwise unseen atmospheric phenomenon using augmented reality (the mixing of real media with computer generated media). The method uses computer generated images to represent existing weather conditions and presents this da... | 06/07/2005 |
| 6539290 | Method, apparatus and design procedure for controlling multi-input, multi-output (MIMO) parameter dependent systems using feedback LTI'zation A method and apparatus are provided for controlling a dynamic device having multi-inputs and operating in an environment having multiple operating parameters. A method of designing flight control laws using multi-input, multi-output feedback LTI'zation is... | 03/25/2003 |
| 6459228 | Dual input servo coupled control sticks The present invention provides an active control system for coupling the movements of a pair of independently operated manual input devices such as dual flight control sticks operated by a pilot and co-pilot flying an aircraft. Each input device is config... | 10/01/2002 |
| 6253481 | Shotgun mountable shell holder The invention provides for a shotgun mountable shell holder which may be readily attached to the forearm of a shotgun. The present invention includes a first member having a forearm mounting region and a second member having a shell mounting region. The p... | 07/03/2001 |
| 6189836 | Model-following control system using acceleration feedback A feedback system for reducing the effects of destabilizing forces in a vehicle (e.g. helicopter) by utilizing acceleration feedback data sensed by an acceleration sensor located in the vehicle. This sensed acceleration signal is passed through a low-pass... | 02/20/2001 |
| 6062513 | Total energy based flight control system In a method of flight control in which a thrust command is computed based on the total aircraft energy error relative to flight path and speed control commands, and an elevator command is computed based on the energy distribution error relative to the sam... | 05/16/2000 |
| 6064923 | Aircraft with reduced wing structure loading An aircraft having a reduced-load wing structure is provided with a controllable canard stabilizer (5G, 5D) at the front end of the aircraft and a controller that controls the canard stabilizer. The controller generates a turn command corresponding to an ... | 05/16/2000 |
| 5815407 | Method and device for inhibiting the operation of an electronic device during take-off and landing of an aircraft An apparatus (700) for inhibiting operation of an electronic device (702) during take-off and landing of an aircraft (802) has a sensor (704) that measures a lateral acceleration. A control circuit (706) is coupled to the sensor (704) and has an output (7... | 09/29/1998 |
| 5722620 | Aircraft pitch-axis stability and command augmentation Disclosed is a pitch-axis stability and command augmentation system (19) in which a pilot column input (δC) is provided to a pitch command processor (26), the output of which is a C*U feedforward command (C*UFFC) that is supplied as... | 03/03/1998 |
| 5641136 | Combat agility management system A flight control system that provides energy management for an aircraft. The flight control system includes an energy control system which generates a first error signal that is a function of an actual energy characteristic and a threshold energy characte... | 06/24/1997 |
| 5589749 | Closed loop control system and method using back EMF estimator A feedback control system which uses estimated back electromotive force(EMF) from a controlled actuator to provide feedback into the control system and improve control of the actuator. Back EMF is estimated from current through the actuator and voltage ac... | 12/31/1996 |
| 5248114 | Adaptive autopilot An autopilot system including parameter identification circuits wherein the function of the torque and the function of the translational force on a missile are unknown and varying (including approaching zero).... | 09/28/1993 |
| 5186416 | System for reducing the forces applied to the wings and particularly to the root of the wings of an aircraft in flight A system for reducing the forces applied to the wings of an aircraft in flight includes an accelerometer for measuring the vertical acceleration of the aircraft and generators for generating signals to control the aerodynamic surfaces in the wings of the ... | 02/16/1993 |
| 5128671 | Control device having multiple degrees of freedom A hand-held joystick has spaced-apart groups of accelerometers and is free to move or rotate on multiple axes. Each group has, for example, three mutually perpendicular accelerometers, with each one producing an electrical signal responsive to linear acce... | 07/07/1992 |
| 5058836 | Adaptive autopilot A control system for the reentry phase of a reentry type vehicle with the vehicle having aerodynamic control surfaces for controlling the attitude of the vehicle during reentry includes an estimating device, such as an extended Kalman filter, for estimati... | 10/22/1991 |
| 5053767 | Aircraft windshear detection based on energy loss The invention provides for the detection of both longitudinal and vertical windshears during the takeoff and landing phases of aircraft flight. Standard instrumentation available on many aircraft is used to calculate the aircraft's energy loss or gain by ... | 10/01/1991 |
| 4905934 | Universal-type gust alleviation system for aircraft The gust alleviation system was designed to be an add-on to any existing g-command flight control system. The system assumes that there already exists, a stability augmentation system which will hold the aircraft's attitude. This system minimizes the inte... | 03/06/1990 |
| 4857922 | Windshear detection and warning system with evasion command An improved windshear warning apparatus for aircraft, responsive to both the magnitude of the wind shear and the allowable time the windshear can be tolerated at a given magnitude. The sensed magnitude is used to compute the allowable time before providin... | 08/15/1989 |
| 4821981 | Maneuver enchancement and gust alleviation system This invention provides a system for enhancing the performance of an aircraft during flight. The aircraft, which includes at least two control surfaces, such as stabilon and trailing edge flaps, includes devices for: generating a signal representative of ... | 04/18/1989 |
| 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 |
| 4651958 | Method and apparatus for effecting fine control of aircraft velocity In order to achieve fine control of the velocity of an aircraft flying a predetermined flight path at a predetermined nominal speed in the presence of such perturbations as wind gusts, a low inertia, fast acting device is extended or deployed into the air... | 03/24/1987 |
| 4645144 | Method and apparatus for effecting fine control of aircraft velocity In order to achieve fine control of the velocity of an aircraft flying a predetermined flight path at a predetermined nominal speed in the presence of such perturbations as wind gusts, a low inertia, fast acting device is extended or deployed into the air... | 02/24/1987 |
| 4593285 | Windshear detection and warning system with evasion command A windshear warning apparatus which separately compares a plurality of signals derived from horizontal and vertical inertial acceleration and air mass acceleration components to indicate incipient windshear. The compared signals are substantially equal un... | 06/03/1986 |
| 4562546 | Stability augmentation system for a forward swept wing aircraft A stability augmentation system for a forward swept wing aircraft is disclosed that corrects a dynamic instability phenomenon which occurs when the whole vehicle (rigid body) motion couples with the wing structural motion. The sensors are positioned and t... | 12/31/1985 |
| 4229725 | Wind shear warning system for aircraft A system to warn an aircraft pilot of a hazardous wind shear condition in which the rate of change of airspeed is compared to the ability of the aircraft to respond thereto. Any difference therebetween that exceeds a predetermined threshold is used to act... | 10/21/1980 |
| 4127249 | Apparatus for computing the rate of change of energy of an aircraft A rate of change of energy computer utilizing signal processing of the inner vectorial product of inertial acceleration and inertial velocity wherein such parameters are derived utilizing outputs from the aircraft INS (inertial navigation system) and from... | 11/28/1978 |
| 4095271 | Aircraft pitch attitude signal generator In order to provide a more accurate representation of aircraft pitch attitude for use in aircraft head up display devices, a circuit for generating a computed pitch signal responds to a longitudinal accelerometer and a vertical gyroscope within the aircra... | 06/13/1978 |
| 4079905 | System for providing an indication of wind shear The output of a transducer providing a signal representing the instantaneous airspeed of an aircraft is differentiated and fed to a summing device. Also fed to the summing device are a signal representing the horizontal acceleration of the aircraft which ... | 03/21/1978 |
| 4046341 | Aircraft angle-of-attack and sideslip estimator The instant invention relates to a system for estimating aircraft angle of attack and sideslip angle ଲ from measured quantities such as angular body rate and linear acceleration. The estimated angle of attack and sideslip signals are generat... | 09/06/1977 |
| 4012713 | System for providing an indication of wind shear The output of a transducer providing a signal in accordance with the instantaneous air speed of an aircraft is differentiated and fed to a summing device which subtracts therefrom a signal in accordance with the horizontal acceleration of the aircraft, th... | 03/15/1977 |
