| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 701010000 | Compensation for environmental conditions | 10 |
| 20090048723 | Proactive optical wind shear protection and ride quality improvement system - Embodiments of the present invention automatically compensate control of an aircraft for an environmental condition, such as turbulence or wind shear. A sensor is configured to sense speed of air relative to an aircraft at a predetermined distance in front of the aircraft. A processor is coupled to receive the sensed speed of air from the sensor. The processor includes a first component configured to determine whether the speed of the air at the predetermined distance is indicative of an environmental condition, such as turbulence or wind shear. A second component is configured to automatically generate control signals for controlling the aircraft such that the environmental condition is automatically compensated by a time the aircraft enters the environmental condition. | 02-19-2009 |
| 20090326744 | METHOD AND SYSTEM DISPLAYING CROSSWIND CORRECTION FOR APPROACH TO A RUNWAY - An aircraft display system ( | 12-31-2009 |
| 20100070114 | METHOD AND DEVICE FOR REDUCING ON AN AIRCRAFT LATERAL EFFECTS OF A TURBULENCE - A method and device for attenuating on an aircraft lateral effects engendered by a turbulence. | 03-18-2010 |
| 20110282523 | Control System for Automatic Flight in Windshear Conditions - A flight control system is configured for controlling the flight of an aircraft through windshear conditions. The system has means for measuring values of selected flight performance states of the aircraft and a control system for operating flight control devices on the aircraft. A windshear detection system located on the aircraft uses at least some of the measured values of the selected flight performance states to calculate a gust average during flight for comparison to pre-determined values in a table for determining whether windshear conditions exist. The control system then operates at least some of the flight control devices in response to an output of the windshear detection system. | 11-17-2011 |
| 20120022725 | Method And Device For Updating A Target Altitude For An Emergency Descent Of An Aircraft - Method and device for updating a target altitude for an emergency descent of an aircraft. | 01-26-2012 |
| 20130166113 | LDV System for Measuring Wind at High Altitude - A method of using LIDAR on an airborne vehicle is described. A beam of radiation is transmitted to target areas at least one of above, below, and in front of the airborne vehicle, the target areas including particles or objects. Scattered radiation is received from the target areas. Respective characteristics of the scattered radiation are determined. Air turbulence factor or characteristics are determined from the respective characteristics. The airborne vehicle is controlled based on the air turbulence factor, such that turbulence experienced by the airborne vehicle is minimized. Alternatively, the airborne vehicle is controlled based on the characteristics to avoid colliding with the one or more objects. In another example, the airborne vehicle is controlled based on the characteristics to reduce headwind or increase tailwind, and substantially reduce a carbon footprint of the aircraft. | 06-27-2013 |
| 20130226375 | SYSTEMS AND METHODS FOR UPDATING A SCALE OF A BAROMETRIC ALTIMETER ON AIRCRAFT - Systems and methods for updating a scale of a barometric altimeter on aircraft are provided. The method, for example, may include, but is not limited to, receiving, by an aircraft communication system, barometric altimeter scale data corresponding to an atmospheric pressure at an airport, determining, by the processor, if the altitude of the aircraft is below a transition level for the airport, and adjusting, by the processor, the scale of the barometric altimeter based upon the received barometric altimeter scale data when the altitude of the aircraft is below the transition level for the airport. | 08-29-2013 |
| 20140018980 | SYSTEMS AND METHODS FOR FLIGHT MANAGEMENT - Systems and methods for flight management are provided. One flight control system is provided that includes a flight management system configured to manage aircraft flight control including at least one of a flight path or an altitude for an aircraft. The flight control system also includes a flight parameter selection module configured to determine a Cost Index (CI) and cruising altitude for use by the flight management system to manage the aircraft flight control, wherein the determination is based on a flight cost and predicted weather along the flight path. | 01-16-2014 |
| 20150348421 | SYSTEMS AND METHODS FOR IN-TRAIL OPPORTUNITY WINDOW ESTIMATOR - Systems and methods are operable to identify and indicate opportunities for an In-Trail procedure (ITP) aircraft to make an ITP altitude change. An exemplary embodiment receives information corresponding to a desired ITP altitude for the ITP aircraft and a projected window period; estimates at least one ITP maneuver opportunity window based on the estimated location of each of the plurality of other aircraft and based on a current airspeed and a current altitude of the ITP aircraft; generates a screen shot that presents an ITP maneuver opportunity window icon, wherein the ITP maneuver opportunity window icon graphically indicates the soonest time and the latest time that the ITP aircraft may initiate the ITP maneuver, and wherein the ITP maneuver opportunity window icon indicates an altitude change made by the ITP aircraft will maintain minimum safe self-separation distances from the plurality of other aircraft during the ITP maneuver. | 12-03-2015 |
| 20160052634 | HELICOPTER ROTOR ICING DETECTION SYSTEM AND METHOD - A system includes a signal monitor to monitor a time rate of change of a revolutions per minute (RPM) trim signal that is received from an RPM command path to control a velocity of a helicopter rotor. An icing detector detects for the presence of ice accumulation on the helicopter rotor by comparing the time rate of change of the RPM trim signal to a predetermined threshold for the time rate of change. | 02-25-2016 |
