|국가/구분||United States(US) Patent 등록|
|미국특허분류(USC)||364/434; 364/440; 244/181; 244/182|
|§371/§102 date||[Act 371]19820930 ([Act 101]19820930)|
|발명자 / 주소|
|출원인 / 주소|
|대리인 / 주소||
|인용정보||피인용 횟수 : 50 인용 특허 : 7|
An integrated aircraft longitudinal flight control system uses a generalized thrust and elevator command computation (38), which accepts flight path angle, longitudinal acceleration command signals, along with associated feedback signals, to form energy rate error (20) and energy rate distribution error (18) signals. The engine thrust command is developed (22) as a function of the energy rate distribution error and the elevator position command is developed (26) as a function of the energy distribution error. For any vertical flight path and speed mode t...
1. An aircraft longitudinal flight control system for automatically controlling the aircraft's flight path and speed, using engine thrust and elevator control surface position, comprising: means for developing an incremental net thrust command signal ΔT c which is a linear combination of a signal representative of the aircraft's total energy error with respect to the flight path and speed command targets and a signal representative of the rate of change of the aircraft's total energy; thrust control means for automatically controlling the incremental...