Provided is a flight control apparatus including a pair of sensors that are spaced apart in a vertical direction on a surface of a flying object which uses motive power of a power source powered by a battery to fly and that detect a physical quantity corresponding to a state of an airflow, and a control unit that controls a flight state of the flying object on the basis of a difference between outputs of the pair of sensors.

Provided is a flight control apparatus including a pair of sensors that are spaced apart in a vertical direction on a surface of a flying object which uses motive power of a power source powered by a battery to fly and that detect a physical quantity corresponding to a state of an airflow, and a control unit that controls a flight state of the flying object on the basis of a difference between outputs of the pair of sensors.

A blood measurement device having high bending rigidity and having excellent propulsion properties and rotational force transmission properties in a blood vessel. A blood measurement device has a tubular shaft having flexibility, a tubular connection portion positioned coaxially with the distal end of the shaft and having an inner diameter larger than the inner diameter of the shaft, a slit communicating the inside and the outside of the connection portion, a tubular tip guide portion having flexibility coaxially connected to the distal end of the connection portion, a core material having flexibility fitted into the connection portion and extending to the distal end in the internal space of the tip guide portion to be connected to the tip guide portion, a measurement element positioned in the internal space of the tip guide portion and measuring the physical quantity of blood, and a signal wire which is extended from the measurement element to be inserted into and passed through the internal space of the shaft through the slit.

A blood measurement device having high bending rigidity and having excellent propulsion properties and rotational force transmission properties in a blood vessel. A blood measurement device has a tubular shaft having flexibility, a tubular connection portion positioned coaxially with the distal end of the shaft and having an inner diameter larger than the inner diameter of the shaft, a slit communicating the inside and the outside of the connection portion, a tubular tip guide portion having flexibility coaxially connected to the distal end of the connection portion, a core material having flexibility fitted into the connection portion and extending to the distal end in the internal space of the tip guide portion to be connected to the tip guide portion, a measurement element positioned in the internal space of the tip guide portion and measuring the physical quantity of blood, and a signal wire which is extended from the measurement element to be inserted into and passed through the internal space of the shaft through the slit.

Described are a two-dimensional wind-speed and wind-direction sensor and a system thereof, relating to the field of sensing devices. The two-dimensional wind-speed and wind-direction sensor includes: an X-direction wind speed probe assembly and a Y-direction wind speed probe assembly, the X-direction wind speed probe assembly and the Y-direction wind speed probe assembly are perpendicular to each other, and the X-direction wind speed probe assembly is configured to measure a X-direction wind speed including a wind speed in the reverse direction of an X-axis, Vx−, and a wind speed in the forward direction of the X-axis Vx+; and the Y-direction wind speed probe assembly is configured to measure a Y-direction wind speed including a wind speed in reverse direction of an Y-axis, Vy−, and a wind speed in the forward direction of the Y-axis, Vy+.

Described are a two-dimensional wind-speed and wind-direction sensor and a system thereof, relating to the field of sensing devices. The two-dimensional wind-speed and wind-direction sensor includes: an X-direction wind speed probe assembly and a Y-direction wind speed probe assembly, the X-direction wind speed probe assembly and the Y-direction wind speed probe assembly are perpendicular to each other, and the X-direction wind speed probe assembly is configured to measure a X-direction wind speed including a wind speed in the reverse direction of an X-axis, Vx−, and a wind speed in the forward direction of the X-axis Vx+; and the Y-direction wind speed probe assembly is configured to measure a Y-direction wind speed including a wind speed in reverse direction of an Y-axis, Vy−, and a wind speed in the forward direction of the Y-axis, Vy+.

A method for measuring a windspeed vector is described. A true airspeed vector of a flying machine is measured while the machine is in flight using one or more nanowires on the flying machine. Each nanowire is configured to measure a value of local air velocity relative to the flying machine. A velocity of the flying machine relative to the ground is measured while the machine is in flight, and then (a) the true airspeed vector is subtracted from (b) the velocity of the flying machine relative to the ground. Other applications are also described.

A method for measuring a windspeed vector is described. A true airspeed vector of a flying machine is measured while the machine is in flight using one or more nanowires on the flying machine. Each nanowire is configured to measure a value of local air velocity relative to the flying machine. A velocity of the flying machine relative to the ground is measured while the machine is in flight, and then (a) the true airspeed vector is subtracted from (b) the velocity of the flying machine relative to the ground. Other applications are also described.

A system may include a static air temperature probe attached to an aircraft, an electronic flight instrument system, and a processor. The processor may be configured to measure a static air temperature at the aircraft using the static air temperature probe. The processor may further be configured to calculate a Mach number associated with the aircraft based at least partially on the static air temperature. The processor may also be configured to calculate a true air speed of the aircraft based on the Mach number. The processor may display an indication of the true air speed using the electronic flight instrument system. The processor may also be configured to calculate the speed of sound based at least partially on the static air temperature.

A system may include a static air temperature probe attached to an aircraft, an electronic flight instrument system, and a processor. The processor may be configured to measure a static air temperature at the aircraft using the static air temperature probe. The processor may further be configured to calculate a Mach number associated with the aircraft based at least partially on the static air temperature. The processor may also be configured to calculate a true air speed of the aircraft based on the Mach number. The processor may display an indication of the true air speed using the electronic flight instrument system. The processor may also be configured to calculate the speed of sound based at least partially on the static air temperature.