Helicopter engine speed enhancement during heavy rotor load and rapid descent rate maneuvering
CA 2113729 C · Owner: United Technologies Corporation · Inventors: Ebert, Frederick J.; Rice, Robert W.
Overview
Its claims, description and drawings are in the Canadian Patents Database.
Open the CIPO recordAbstract From the Canadian patent
A helicopter engine speed reference (66) is increased (117 118) in response to heavy rotor loading (102) in excess of a threshold at the current descent rate (fig. 4). The reference speed is faded up (117 118) at a rapid rate to 107 % of rated speed (119). After a fixed time interval (129) reduced rotor loading (122), reduced pitch angle below a threshold magnitude (121) and reduced roll angle below a threshold magnitude (120) will cause the reference speed to be faded down slowly (146 147) to rated, speed (148). Automatic increase in engine reference speed is overridden to 107 % of rated speed (203) when a battle switch is activated (201) and weapons are ready (202). Increases in engine …
Read the whole patent
Listed from its CIPO record in Patent Yard's archive of Canadian patents past their term. Its claims, description and drawings are in the CIPO record and on Google Patents, and the Claude kit works from them.
Why it's free to use
- Filed August 27, 1992 and granted June 23, 1998. A Canadian patent filed from October 1, 1989 lasts 20 years from filing, so its term ended August 27, 2012.
- A certificate of supplementary protection adds at most two years for a drug, so even that would have ended by August 27, 2014.
- We check Canadian rights only. A patent in its family in another country could still be in force: check its family on Google Patents.
Timeline
Timeline From CIPO dates
Sources & verification
Official CIPO records
Everything on this page comes from the CIPO record linked above. Contains information licensed under the Open Government Licence – Canada.