Patent ID: 7599767

Claim:
A control apparatus for an aircraft, comprising: two gas-turbine engines; two extraction passages through which compressed air discharged from the respective engines flows; an air collecting passage in which the compressed air flowing from one of the two extraction passages and the compressed air flowing from the other extraction passage are gathered, and through which the compressed air flows; a thrust generator that generates thrust using the compressed air flowing from the air collecting passage; and an attitude control portion that performs a control of at least one of thrust and attitude of an aircraft using the compressed air flowing from the air collecting passage, wherein, when both of the two engines operate properly, the attitude control portion performs the control of at least one of thrust and attitude of the aircraft using a two-engine-output that is produced evenly by the two engines, when a failure occurs in one of the two engines, the attitude control portion increases a one-engine-output that is produced by the remaining engine operating properly, and limits an amount of increase in the one-engine-output such that the one-engine-output that is produced by the remaining engine operating properly is less than the two-engine-output that is produced when both of the two engines operate properly, until the remaining engine is enabled to produce an emergency output; and wherein, when the emergency output is produced, the attitude control portion makes an engine speed and a turbine inlet temperature higher than those when both of the two engines operate properly and the two-engine-output is produced evenly by the two engines.