Abstract: [Object] To provide a technique for reducing the fluctuation of an airplane when an airplane enters turbulence without using prior information of two-dimensional or more airflow vectors. [Solving Means] A system includes: a measurement unit 10 that emits electromagnetic waves toward a planned flight direction of the airplane, receives scattered waves of the emitted electromagnetic waves in atmosphere, and measures a remote wind speed in a radiation axis direction of the emitted electromagnetic waves based on a Doppler shift amount of a frequency between the emitted electromagnetic waves and the scattered electromagnetic waves; a spoiler 221 that controls a lift of the airplane; and a control calculation unit 30 that calculates an angle of attack with less lift inclination and calculates an angle of the spoiler 221 that controls the lift so that the lift does not change when it is determined that the airplane will receive a gust, based on a measurement result of the measurement unit 10.

Abstract: [Object] To appropriately evaluate reliability of a reception signal. [Solving Means] A signal processing unit 20 includes a first integration unit 21, a Doppler detection unit 22, and a comparator circuit 28 as a reliability index calculation unit. The first integration unit 21 intermittently integrates a pulse train corresponding to a reception signal by using two systems and obtains two pieces of integrated data. The Doppler detection unit 22 divides each of the two pieces of integrated data into a plurality of range bins in time series, obtains a relationship between a frequency and intensity in each range bin for each of the two pieces of integrated data, and detects a Doppler shift amount from the relationship. The comparator circuit 28 calculates a reliability index of the reception signal by comparing the Doppler shift amounts (wind velocity values) of the two pieces of integrated data.

Abstract: [Object] To provide a remote airflow observation device, a remote airflow observation method, and a program that are capable of eliminating the influence of scattered waves from the ground or some object and improving the reliability of airflow observation. [Solving Means] A Doppler Lidar 100 includes: a measurement unit 110 that radiates transmission light including pulse-form laser light, receives reflected light of the radiated transmission light as reception light, and outputs a received signal for calculating a wind speed value on the basis of the transmission light and the reception light; and a signal processor 8 that performs processing for distributing the received signal to range bins by time-dividing the received signal and for removing a signal derived from a hard target from the received signal.

Abstract: [Object] To provide a technique for reducing the fluctuation of an airplane when an airplane enters turbulence without using prior information of two-dimensional or more airflow vectors. [Solving Means] A system includes: a measurement unit 10 that emits electromagnetic waves toward a planned flight direction of the airplane, receives scattered waves of the emitted electromagnetic waves in atmosphere, and measures a remote wind speed in a radiation axis direction of the emitted electromagnetic waves based on a Doppler shift amount of a frequency between the emitted electromagnetic waves and the scattered electromagnetic waves; a spoiler 221 that controls a lift of the airplane; and a control calculation unit 30 that calculates an angle of attack with less lift inclination and calculates an angle of the spoiler 221 that controls the lift so that the lift does not change when it is determined that the airplane will receive a gust, based on a measurement result of the measurement unit 10.

Abstract: [Object] To appropriately evaluate reliability of a reception signal. [Solving Means] A signal processing unit 20 includes a first integration unit 21, a Doppler detection unit 22, and a comparator circuit 28 as a reliability index calculation unit. The first integration unit 21 intermittently integrates a pulse train corresponding to a reception signal by using two systems and obtains two pieces of integrated data. The Doppler detection unit 22 divides each of the two pieces of integrated data into a plurality of range bins in time series, obtains a relationship between a frequency and intensity in each range bin for each of the two pieces of integrated data, and detects a Doppler shift amount from the relationship. The comparator circuit 28 calculates a reliability index of the reception signal by comparing the Doppler shift amounts (wind velocity values) of the two pieces of integrated data.

Abstract: An object of the present invention is to provide a method for preventing turbulence-induced accidents that can expand a detection range to about 20 km without increasing the size of a device or increasing the energy consumption, can perform planar distribution monitoring of turbulence when the turbulence is detected in the flight direction and also can output a signal for autopilot steering input that decreases the fuselage shaking when the turbulence is difficult to avoid, as well as to provide a device having those functions.

Abstract: An object of the present invention is to provide a turbulence avoidance operation assist device that automatically generates an optimal trajectory of emergency avoidance and reports this trajectory to a pilot when distant turbulence is detected during an aircraft flight. The turbulence avoidance operation assist device in accordance with the present invention includes: means for detecting the presence of a danger region such as a turbulence region ahead of aircraft in a flight direction; means for representing the danger region as an assembly of rectangular solids when the detection means recognizes the danger region, and generating a flight trajectory by a local optimum solution of an avoidance trajectory using a convex quadratic programming method in which deviation from a reference trajectory is the smallest on the basis of an initial estimation solution obtained by a semidefinite programming method; and means for reporting the flight trajectory to a pilot.

Abstract: An object of the present invention is to provide an optical remote airflow measurement apparatus with which even colored noise corresponding to an external environment of the apparatus can be reduced, thereby reducing measurement reliability deterioration and enabling long-distance measurement in a wide flying speed range. A colored noise reduction method according to the present invention includes: considering a signal strength of scattered light to be substantially non-existent in a remotest region and beyond; calculating a noise distribution by performing processing to average the signal strength in respective Doppler frequency components divided at intervals of a certain frequency in the remotest measurement region and beyond, and performing subtraction processing in each of the Doppler frequency components on all signal strength distributions of the measurement region, which are obtained by dividing the noise distribution at intervals of a certain distance.

Abstract: A laser light reflection device for an aircraft-installed laser apparatus with which, when a function check is performed on the aircraft-installed laser apparatus by emitting laser light from a parked aircraft to a body exterior, the emitted laser light can be reflected in a desired direction safely and efficiently. A reflection mirror is capable of autorotation about at least an in-plane horizontal axis thereof, and a support ring is attached to the reflection mirror to be capable of rotating about an in-plane vertical axis and the in-plane horizontal axis of the reflection mirror. A laser pointer unit formed by inserting a laser pointer into a sleeve pipe is attached to the support ring so as to be oriented toward an in-plane of the reflection mirror. A guide scope is attached to the support ring such that an optical axis thereof matches an optical axis of the laser pointer unit.

Abstract: An object of the present invention is to provide a device which detects matter suspended in air, represented by, for example, ice crystals, volcanic ash, in the forward direction of the flight of an aircraft. A method of detecting matter suspended in air of this invention is characterized in that, in airborne Doppler LIDAR using laser light, components of matter subjected to laser light reflection and scattering are remotely measured on a basis of an angular difference in planes of polarization of transmitted light which is laser light radiated into the atmosphere, and received light scattered by matter suspended in air in a remote region.

Abstract: The object of the present invention is to provide an air data sensor that does not require an external input of a reference velocity as a Doppler LIDAR, has a function of autonomously determining the absolute airspeed, and has no position error.

Abstract: An object of the present invention is to provide a device which detects matter suspended in air, represented by, for example, ice crystals, volcanic ash, in the forward direction of the flight of an aircraft. A method of detecting matter suspended in air of this invention is characterized in that, in airborne Doppler LIDAR using laser light, components of matter subjected to laser light reflection and scattering are remotely measured on a basis of an angular difference in planes of polarization of transmitted light which is laser light radiated into the atmosphere, and received light scattered by matter suspended in air in a remote region.

Abstract: An object of the present invention is to provide a method enabling measurement in a wider range than a conventional LIDAR system and capable of measuring airflow information, which is used to reduce shaking of an airframe when an aircraft collides with turbulence, in a shorter period, and a device having corresponding functions. A multi-LIDAR system according to the present invention includes at least two optical remote airflow measurement devices of a Doppler LIDAR system employing laser light that are provided in a fixed relative position relationship, has functions for emitting lasers of identical wavelengths from the respective devices and receiving scattered light by the respective devices, thereby improving redundancy with respect to defects, and improves a detectability by increasing an integration amount of respective measurement signals.

Abstract: The object of the present invention is to provide an air data sensor that does not require an external input of a reference velocity as a Doppler LIDAR, has a function of autonomously determining the absolute airspeed, and has no position error.

Abstract: An object of the present invention is to provide a turbulence avoidance operation assist device that automatically generates an optimal trajectory of emergency avoidance and reports this trajectory to a pilot when distant turbulence is detected during an aircraft flight. The turbulence avoidance operation assist device in accordance with the present invention includes: means for detecting the presence of a danger region such as a turbulence region ahead of aircraft in a flight direction; means for representing the danger region as an assembly of rectangular solids when the detection means recognizes the danger region, and generating a flight trajectory by a local optimum solution of an avoidance trajectory using a convex quadratic programming method in which deviation from a reference trajectory is the smallest on the basis of an initial estimation solution obtained by a semidefinite programming method; and means for reporting the flight trajectory to a pilot.

Abstract: An object of the present invention is to provide a method for preventing turbulence-induced accidents that can expand a detection range to about 20 km without increasing the size of a device or increasing the energy consumption, can perform planar distribution monitoring of turbulence when the turbulence is detected in the flight direction and also can output a signal for autopilot steering input that decreases the fuselage shaking when the turbulence is difficult to avoid, as well as to provide a device having those functions.

Abstract: The wind turbulence prediction system according to the present invention provides a measurement system, which is capable of measuring three-dimensional wind turbulence, exhibits limited aerodynamic and structural effects when mounted on an aircraft, is capable of measurement even in cases in which the velocity is equal to or less than 20 to 30 m/s, at which velocity a Pitot tube is incapable of measurement, and even in cases where the air flow direction differs greatly from the axis of aircraft body, and does not produce an error resulting from disruption of the air flow by the aircraft body itself. The wind turbulence prediction system of the present invention adopts a system that measures the speed of remote three-dimensional air flow by mounting a laser wind speed indicator utilizing the Doppler effect on an aircraft, irradiating laser light while scanning same in a cone shape, and then receiving scattered light from wind turbulence regions forward of an aircraft body in flight.

Abstract: The wind turbulence prediction system according to the present invention provides a measurement system, which is capable of measuring three-dimensional wind turbulence, exhibits limited aerodynamic and structural effects when mounted on an aircraft, is capable of measurement even in cases in which the velocity is equal to or less than 20 to 30 m/s, at which velocity a Pitot tube is incapable of measurement, and even in cases where the air flow direction differs greatly from the axis of aircraft body, and does not produce an error resulting from disruption of the air flow by the aircraft body itself. The wind turbulence prediction system of the present invention adopts a system that measures the speed of remote three-dimensional air flow by mounting a laser wind speed indicator utilizing the Doppler effect on an aircraft, irradiating laser light while scanning same in a cone shape, and then receiving scattered light from wind turbulence regions forward of an aircraft body in flight.