|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||701/004; 701/003; 701/007; 244/1580R; 244/171; 340/967|
|발명자 / 주소|
|출원인 / 주소|
|인용정보||피인용 횟수 : 23 인용 특허 : 2|
An apparatus, method and computer program product useful for supplying the pilot of an aircraft with aircraft attitude information in the event of full or partial failure of the gyroscopic system normally used to supply such data. The pitch angle, roll angle and heading angle estimates provided by the apparatus, method and computer program product can be displayed to the pilot thereby alleviating the requirement that the pilot mentally integrate such data from the remaining aircraft instruments.
1. A system for supplying the pilot of an aircraft with an alternative source of aircraft attitude information comprising:a plurality of sensors including: a first sensor useful for sensing aircraft linear acceleration in a vertical direction; a second sensor useful for sensing an airspeed of the aircraft; a third sensor useful for sensing a roll rate and yaw rate of the aircraft and oriented on an inclined axis; a fourth sensor useful for sensing a magnetic heading of the aircraft; a signal processor, having an input coupled to said suite of sensors, an...