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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...
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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...
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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...
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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....
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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....
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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...
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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...
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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...
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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...
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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...
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5224667 |
System enabling the flutter behavior of an aircraft to be improved
A system for improving the flutter behavior of an aircraft provided with a rudder, said system comprising an accelerometer disposed in the rear portion of said aircraft, filter means, and means for...
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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...
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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...
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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...
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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...
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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...
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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...
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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,...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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4046341 |
Aircraft angle-of-attack and sideslip estimator
The instant invention relates to a system for estimating aircraft angle of attack α and sideslip angle β from measured quantities such as angular body rate and linear acceleration. The estimated...
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3998411 |
Speed overshoot correction system
A system for compensating for certain speed overshoot problems encountered in large instrument-controlled aircraft during long-term deceleration from high speeds, such as may be encountered in...
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3979090 |
Velocity damped erection system for stable gyroscopic attitude and heading reference apparatus
An improved second order gyroscopic attitude and heading reference system including separate variable time constant accelerometer integrators for independently controlling the velocity error...
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3948096 |
Apparatus for computing the acceleration of an aircraft along its flight path
Apparatus for providing a measure of the acceleration of an aircraft along its flight path derived from computations involving inertial measurements of longitudinal and normal accelerations of the...
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3902686 |
Combined vertical and lateral identical location of accelerometer and force system
A structural mode control system having sensing elements to operate control force application devices, such as aerodynamic control vanes. The sensing elements are located at the control force...
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3805033 |
AUTOPILOT GO-AROUND MODE PITCH COMMAND SIGNAL COMPUTATIONS
In a pitch command signal formulation where command error is damped by longitudinal acceleration, negative angular acceleration experienced during throttle retard in flare mode is precluded from...
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3773281 |
AUTOMATIC FLIGHT CONTROL SYSTEM USING INSTRUMENT LANDING SYSTEM INFORMATION AND INCLUDING INERTIAL FILTERING MEANS FOR REDUCING ILS NOISE
A flight control system includes localizer and glide path couplers using instrument landing system (ILS) information and inertially sensed data to generate appropriate control signals, and inertial...
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3761691 |
RUNWAY ALIGNMENT SYSTEM UTILIZING A LATERAL ACCELERATION SIGNAL
A landing control system utilizing a lateral acceleration signal in formulation of roll steering command such that a decrab maneuver effects a "wing down into the wind" forward slip maneuver,...
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3734432 |
SUPPRESSION OF FLUTTER
An active aerodynamic control system to control flutter over a large range of oscillatory frequencies unaffected by mass, stiffness, elastic axis, or center-of-gravity location of the system, mode...
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3724786 |
AIRCRAFT GROUND SPEED CONTROL SYSTEM
An integration of the difference between a desired aircraft acceleration and the actual aircraft acceleration provides a signal which is compared with an aircraft speed dependent parameter for...
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3711042 |
AIRCRAFT CONTROL SYSTEM
An aircraft control system, particularly suited to rotary wing aircraft, in which longitudinal acceleration and course rate commands are derived from a manual control stick to control translational...
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3710086 |
SERVO SYSTEM EMPLOYING SWITCHING TYPE FEEDBACK
The invention provides a servo control system, capable of either a continuous or discontinuous operating mode, which utilizes sign-switched integration circuit to obtain extremely fast response...
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3686626 |
AIRCRAFT INSTRUMENT
An aircraft instrument providing visual flight path guidance to the pilot during landing approach, to clear an obstacle or the like. A head-up collimated display has a transverse bar positioned in...
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3661347 |
GAIN CHANGER
A device for adjusting the gain of the amplifier which drives the control rfaces of an aerodynamic vehicle to compensate for changes in lateral acceleration of the vehicle wherein the acceleration...
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3572618 |
METHOD FOR STABILIZING AIRCRAFT AND MISSILES
STABILITY OF A SAMPLED-DATA FEEDBACK CONTROL SYSTEM FOR AN AIRFRAME IS ENHANCED BY VARYING THE SAMPLING INTERVAL AS A FUNCTION OF THE PARTICULAR BENDING MODE THE AIRFRAME EXHIBITS. A command signal...
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3521838 |
CONTROL APPARATUS FOR VTOL CRAFT
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3448948 |
AIRCRAFT SPEED CONTROLLER
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3412961 |
Means for suppressing or attenuating bending motion of elastic bodies
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3386524 |
Drift stabilizer for ground effects machine
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3359793 |
Aircraft instruments
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3347498 |
Aircraft structural stress alleviators
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3330503 |
Re-entry guidance system
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3309923 |
Aircraft instruments
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3301510 |
Method and apparatus for gage simulation in automatic control systems
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3296422 |
Apparatus for computing true vertical position, velocity and acceleration for aircraft
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