초록 ▼

A flight path maker (FPM) and a target attitude relative to air display are displayed on a primary flight display (PFD), which is an integrated indicator. The target attitude relative to air display is a mark indicating a target attitude relative to air representing a target angle-of-attack and a ta

A flight path maker (FPM) and a target attitude relative to air display are displayed on a primary flight display (PFD), which is an integrated indicator. The target attitude relative to air display is a mark indicating a target attitude relative to air representing a target angle-of-attack and a target sideslip angle of the aircraft to achieve a target flight path. The PFD displays the relative difference between the FPM and the target attitude relative to air display and shows that the aircraft is flying in the target traveling direction when the FPM matches (is superposed on) the target attitude relative to air display. Thus, controlling with higher trackability than controlling performed based on a target attitude relative to ground is enabled.

대표청구항 ▼

1. A control support system including a sensor section that measures current information about flight in an airplane, which is an aircraft, an autopilot section that derives required information such that the aircraft can fly in a target flight path, and a display apparatus that displays a flying si

1. A control support system including a sensor section that measures current information about flight in an airplane, which is an aircraft, an autopilot section that derives required information such that the aircraft can fly in a target flight path, and a display apparatus that displays a flying situation of the aircraft, the control support system comprising: a controller including: a target angle-of-attack deriving section that derives a target angle-of-attack of the aircraft to achieve the target flight path on the basis of a pitch angle measured by the sensor section and a path angle which is an angle between a horizontal plane and a target traveling direction of the aircraft and which is derived by the autopilot section;a target sideslip angle deriving section that derives a target sideslip angle of the aircraft to achieve the target flight path on the basis of a direction angle measured by the sensor section and a direction angle of the target traveling direction derived by the autopilot section; anda display control section that causes the display apparatus to display a relative difference between a target attitude relative to air, representing the target angle-of-attack that has been derived and the target sideslip angle that has been derived, and a current attitude relative to air, representing a current angle-of-attack and a current sideslip angle of the aircraft. 2. The control support system according to claim 1, wherein the target angle-of-attack deriving section derives the target angle-of-attack by subtracting the path angle derived by the autopilot section from the pitch angle measured by the sensor section, andthe target sideslip angle deriving section derives the target sideslip angle by subtracting the direction angle measured by the sensor section from the direction angle of the target traveling direction derived by the autopilot section. 3. The control support system according to claim 1, wherein the display control section causes the display apparatus to display a first mark corresponding to the target attitude relative to air and a second mark corresponding to the current attitude relative to air. 4. The control support system according to claim 3, wherein the display control section causes the display apparatus to display relative positions of the first mark and the second mark while being changed according to the relative difference between the target attitude relative to air and the current attitude relative to air. 5. The control support system according claim 1, further comprising: a positional information acquisition sensor that measures a current position of the aircraft; anda computer that derives the target flight path based on the measured current position of the aircraft. 6. The control support system according claim 5, wherein the computer derives a target position that the aircraft should reach based on the measured current position and a predetermined condition, andthe target flight path derived by the computer is an optimum flight path from the aircraft to the derived target position. 7. The control support system according claim 6, wherein the predetermined condition is a reachable distance of the aircraft based on remaining fuel of the aircraft. 8. A control support method in a control support system comprising a sensor section that measures current information about flight in an airplane, which is an aircraft, an autopilot section that derives required information such that the aircraft can fly in a target flight path, and a display apparatus that displays a flying situation of the aircraft, the control support method comprising: deriving a target angle-of-attack of the aircraft to achieve the target flight path on the basis of a pitch angle measured by the sensor section and a path angle which is an angle between a horizontal plane and a target traveling direction of the aircraft and which is derived by the autopilot section;deriving a target sideslip angle of the aircraft to achieve the target flight path on the basis of a direction angle measured by the sensor section and a direction angle of the target traveling direction derived by the autopilot section; andcausing the display apparatus to display a relative difference between a target attitude relative to air, representing the target angle-of-attack that has been derived and the target sideslip angle that has been derived, and a current attitude relative to air, representing a current angle-of-attack and a current sideslip angle of the aircraft.