초록 ▼

When both engines operate properly, a control apparatus for an aircraft performs control of thrust and attitude of an aircraft using an output that is produced evenly by the two engines. When a failure occurs in one of the two engines, the control apparatus performs the control of thrust and attitud

When both engines operate properly, a control apparatus for an aircraft performs control of thrust and attitude of an aircraft using an output that is produced evenly by the two engines. When a failure occurs in one of the two engines, the control apparatus performs the control of thrust and attitude of the aircraft by increasing an output of the remaining engine that operates properly to an emergency output. When the failure occurs in one of the two engines, the control apparatus makes an engine output that is used for the control of thrust and attitude of the aircraft lower than an engine output that is used when both engines operate properly, until the remaining engine that operates properly is enabled to produce the emergency output.

대표청구항 ▼

What is claimed is: 1. 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 a

What is claimed is: 1. 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. 2. 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 failure occurs in one of the two engines, the attitude control portion makes the one-engine-output less than the two-engine-output by a predetermined amount, until the remaining engine that operates properly is enabled to produce the emergency output. 3. 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 failure occurs in one of the two engines, the attitude control portion makes the one-engine-output less than the two-engine-output based on an engine speed of the remaining engine that operates properly, until the remaining engine that operates properly is enabled to produce the emergency output. 4. The control apparatus according to claim 3, wherein the attitude control portion reduces an amount of limitation applied on the one-engine-output as the engine speed increases. 5. 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 failure occurs in one of the two engines, the attitude control portion makes the one-engine-output less than a maximum allowable engine output that can be produced by each of the two engines operating properly, until the remaining engine that operates properly is enabled to produce the emergency output. 6. 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 failure occurs in one of the two engines, if the remaining engine that operates properly can produce the emergency output, the attitude control portion permits the remaining engine that operates properly to produce the one-engine-output up to a maximum output.