Abstract: Trim adjustment devices 20, 30, 40 at least include trim control switches 21, 31, 41 for performing a trim adjustment; acquisition sections 22, 32, 42 for acquiring a designated value for a position designated through the operation of the switches 21, 31, 41; and converting sections 23, 33, 43 for converting the designated value to a converted designated value expressed in different units. The switches 21, 31, 41 operate at a changeable rate in which the designated value changes at a prescribed amount of change per unit time, the prescribed amount of change expressed in units of the designated value before the conversion. The sections 23, 33, 43 converts the designated value to the converted designated value expressed in minimum units (0.1 UNIT) based on the product of the changeable rate and a click time period required for clicking the switches 21, 31, 41 once.

Abstract: Trim adjustment devices 20, 30, 40 at least include trim control switches 21, 31, 41 for performing a trim adjustment; acquisition sections 22, 32, 42 for acquiring a designated value for a position designated through the operation of the switches 21, 31, 41; and converting sections 23, 33, 43 for converting the designated value to a converted designated value expressed in different units. The switches 21, 31, 41 operate at a changeable rate in which the designated value changes at a prescribed amount of change per unit time, the prescribed amount of change expressed in units of the designated value before the conversion. The sections 23, 33, 43 converts the designated value to the converted designated value expressed in minimum units (0.1 UNIT) based on the product of the changeable rate and a click time period required for clicking the switches 21, 31, 41 once.

Abstract: To provide a warning system that can issue a stall warning taking a flight environment into account. The warning system according to the present invention is a warning system for an aircraft, for issuing a warning in the case where there is a possibility of the aircraft stalling, and includes a selecting section for selecting one of two or more calculation criteria based on an icing state of the aircraft, a calculating section for calculating a stall angle based on the selected calculation criterion, and a warning section for comparing the calculated stall angle with a current angle of attack of the aircraft and issuing a stall warning if the current angle of attack exceeds the stall angle.

Abstract: A warning system 10 that warns of saturation of the control capability for the moving surface such as an elevator 4 and a rudder 8 of an aircraft has a determination section 31 that determines whether or not the control capability for the moving surface is saturated, and a display 50 that issues a warning when the determination section 31 determines that the control capability for the moving surface is saturated. The determination section 31 determines that the control capability for the elevator 4 is saturated, when a control target position of the elevator 4 by, for example, a control stick (column) is larger than a first reference position indicating an operation limit of the elevator 4, and a present position of the column is smaller than a second reference position indicating an operation limit of the column.

Abstract: A warning system 10 that warns of saturation of the control capability for the moving surface such as an elevator 4 and a rudder 8 of an aircraft has a determination section 31 that determines whether or not the control capability for the moving surface is saturated, and a display 50 that issues a warning when the determination section 31 determines that the control capability for the moving surface is saturated. The determination section 31 determines that the control capability for the elevator 4 is saturated, when a control target position of the elevator 4 by, for example, a control stick (column) is larger than a first reference position indicating an operation limit of the elevator 4, and a present position of the column is smaller than a second reference position indicating an operation limit of the column.

Abstract: To provide a warning system that can issue a stall warning taking a flight environment into account. The warning system according to the present invention is a warning system for an aircraft, for issuing a warning in the case where there is a possibility of the aircraft stalling, and includes a selecting section for selecting one of two or more calculation criteria based on an icing state of the aircraft, a calculating section for calculating a stall angle based on the selected calculation criterion, and a warning section for comparing the calculated stall angle with a current angle of attack of the aircraft and issuing a stall warning if the current angle of attack exceeds the stall angle.