Abstract: A jet aircraft maneuvering characteristic simulation system for a single propeller aircraft includes a power lever, speed brakes, and a controller. The power lever is configured to change a thrust of the single propeller aircraft. The speed brakes are provided on respective right and left sides of the single propeller aircraft. The controller is configured to, in response to an operation of the power lever to raise the thrust of the single propeller aircraft, deploy both the right and the left speed brakes to cause an increase in speed of the single propeller aircraft to be moderate, and control the speed brakes to cause a force in a yaw direction and a force in a roll direction to be generated that act against a turning tendency of the single propeller aircraft by making amounts of the deployment of the right and the left speed brakes different from each other.

Abstract: A pilot education system includes a learning stage identifier, a teaching information setter, and a practice method setter. The learning stage identifier is configured to identify a learning stage of a trainee to operate either one of an aircraft simulator and an actual aircraft by measuring and analyzing maneuvering skills of the trainee. The maneuvering skills are related to at least one of a sight line or a maneuvering operation. The teaching information setter is configured to set an amount of teaching information to be presented to the trainee in either one of the aircraft simulator and the actual aircraft according to the learning stage identified by the learning stage identifier. The practice method setter is configured to set a practice method for the trainee according to the learning stage identified by the learning stage identifier.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: A self-position measuring device includes an information generator, a position extractor, and a navigation method selector. The information generator generates estimated information that is expected to be obtained when at least one of the ground information and the celestial information is obtained, at each of multiple reference points generated on the basis of measured inertial navigation position. The position extractor checks at least the one of the ground information and the celestial information against the estimated information at each of the multiple reference points and extracts a position of a specific reference point corresponding to specific estimated information with a highest matching degree. The navigation method selector selects, on the basis of the specific reference point, a navigation method with less navigational error as a navigation method for measuring the self-position.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: According to one implementation, a damage detection system includes: a physical quantity detection unit, a flight condition changing part and a damage detection part. The physical quantity detection unit detects a physical quantity of a structural object composing an aircraft during a flight of the aircraft. The flight condition changing part changes at least one flight condition of the aircraft to at least one specific flight condition when the physical quantity of the structural object has been detected by the physical quantity detection unit. The damage detection part determines whether a damage arose in the structural object, based on a physical quantity which has been detected, from the structural object of the aircraft flying with the at least one specific flight condition, by the physical quantity detection unit.

Abstract: A self-position measuring device includes an information generator, a position extractor, and a navigation method selector. The information generator generates estimated information that is expected to be obtained when at least one of the ground information and the celestial information is obtained, at each of multiple reference points generated on the basis of measured inertial navigation position. The position extractor checks at least the one of the ground information and the celestial information against the estimated information at each of the multiple reference points and extracts a position of a specific reference point corresponding to specific estimated information with a highest matching degree. The navigation method selector selects, on the basis of the specific reference point, a navigation method with less navigational error as a navigation method for measuring the self-position.