A power safety system (301) is configured to provide power information in an aircraft (101). The power safety system (301) includes a power safety instrument (303) having a power required indicator (311) and a power available indicator (313), each being located on a display. A position of the power required indicator (311) and the power available indicator (313) represent the power available and power required to perform a hover flight maneuver. The power safety system (301) may be operated in a flight planning mode or in a current flight mode. The power safety system (301) uses at least one sensor (309) to measure variables having an effect on the power required and the power available.
申请公布号
EP2985226(B1)
申请公布日期
2016.11.09
申请号
EP20150174684
申请日期
2010.12.22
申请人
BELL HELICOPTER TEXTRON INC.
发明人
MCCOLLOUGH, JAMES M.;OLTHETEN, ERIK;LAPPOS, NICHOLAS