By a News Reporter-Staff News Editor at Defense & Aerospace Week -- Rockwell Collins, Inc (Cedar Rapids, IA) has been issued patent number 8774986, according to news reporting originating out of Alexandria, Virginia, by VerticalNews editors.
The patent's inventors are Theriault, Ricky J. (King City, OR); Chen, Shuncan (Tigard, OR).
This patent was filed on May 31, 2007 and was published online on July 8, 2014.
From the background information supplied by the inventors, news correspondents obtained the following quote: "The takeoff phase of flight, especially during low visibility conditions, presents the pilot of an aircraft with a high workload. During takeoff, an aircraft accelerates on a runway to a takeoff rotation speed. Once takeoff rotation speed is reached, the pitch of the aircraft is increased to increase lift from the wings. The aircraft continues to accelerate to a takeoff liftoff speed and the aircraft lifts off the runway. After liftoff, the aircraft performs an initial climbout by climbing to a climbout altitude whereupon the takeoff phase of the flight is over and the aircraft begins climbing to its cruise altitude. A number of conditions must be monitored by a pilot during takeoff, especially during low visibility conditions, increasing workload for the pilot. High workloads strain pilots. Complications during takeoff such as engine failure conditions in crosswinds may further increase pilot workload. Decreasing pilot workload and strain improves safety and performance.
"Head-up Guidance Systems (HGS) provide enhanced situational awareness for pilots in all flight conditions, reducing pilot workload and strain. In HGS, primary flight data is presented in the pilot's forward field of view on the Head-up Display of the HGS. By focusing critical information at optical infinity, the pilot is able to view the information while viewing the outside world view. This enables a pilot to fly very accurately in all conditions, even in turbulence and crosswinds.
"Consequently, it would be desirable to provide pertinent guidance information on a HUD during the takeoff phase of flight."
Supplementing the background information on this patent, VerticalNews reporters also obtained the inventors' summary information for this patent: "Accordingly, the present invention is directed to a method, system, and apparatus for providing takeoff rotation guidance.
"A takeoff rotation guidance indicator is displayed on a HUD (Head-up Display) of a HGS (Head-up Guidance System) to provide takeoff rotation guidance. The takeoff rotation guidance indicator includes an aircraft reference symbol and a guidance cue. The guidance cue is positioned in relation to the aircraft reference symbol based on a takeoff rotation pitch guidance and a takeoff rotation roll guidance. Thus, pitch and roll guidance information is simply communicated to the pilot of an aircraft who may make appropriate adjustments.
"The takeoff rotation pitch guidance and the takeoff rotation roll guidance are calculated differently at different points during takeoff. When the computed airspeed of the aircraft is less than a takeoff rotation speed, the takeoff rotation pitch guidance is zero. When the computed airspeed of the aircraft is greater than the takeoff rotation speed and the altitude of the aircraft is less than a climbout altitude the takeoff rotation pitch guidance is calculated based on a suggested pitch rate, the engine failure status of the aircraft, the pitch of the aircraft, and the pitch rate of the aircraft. When the computed airspeed of the aircraft is less than the takeoff liftoff speed, the takeoff rotation roll guidance is zero. When the computed airspeed of the aircraft is greater than the takeoff liftoff speed and the altitude of the aircraft is less than the climbout altitude the takeoff rotation roll guidance is calculated based on the track error of the aircraft, the yaw rate of the aircraft, the roll angle of the aircraft, and the roll rate of the aircraft.
"In an alternative embodiment, the takeoff rotation guidance indicator includes a slip-skid symbol. The slip-skid symbol is positioned relative to aircraft reference symbol, but is displaced by the lateral acceleration of the aircraft. Thus, slip/skid guidance information is simply communicated to the pilot of an aircraft who may make appropriate adjustments, for example, to account for sideslip generated due to an engine failure.
"It is to be understood that both the foregoing general description and the following detailed description are exemplary and explanatory only and are not restrictive of the invention claimed. The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate an embodiment of the invention and together with the general description, serve to explain the principles of the invention."
For the URL and additional information on this patent, see: Theriault, Ricky J.; Chen, Shuncan. Method, System, and Apparatus for Takeoff Rotation Guidance. U.S. Patent Number 8774986, filed May 31, 2007, and published online on July 8, 2014. Patent URL: http://patft.uspto.gov/netacgi/nph-Parser?Sect1=PTO1&Sect2=HITOFF&d=PALL&p=1&u=%2Fnetahtml%2FPTO%2Fsrchnum.htm&r=1&f=G&l=50&s1=8774986.PN.&OS=PN/8774986RS=PN/8774986
Keywords for this news article include: Rockwell Collins Inc, Aerospace and Defense Companies.
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