Method and device for measuring the angle of attacks and sliding of the aircraft

FIELD: aviation.

SUBSTANCE: to implement the method, a receiver provided by a central sensor, sensors offset from the center, and side sensors is used, and said receiver is connected to the aircraft with the ability to rotate around two orthogonal axes. In this regard, method is suggested for measuring the angle of attack of aircraft's longitudinal axis in relation to relative airflow, wherein the method uses a receiver that is provided at its forward end with a center-direction sensor, that is located at the intersection of horizontal and vertical midplanes of said receiver, and at least two midplane eccentric-direction sensors, that are parallel to said central sensor and are placed at the same distance from it on either side of said horizontal midplane of said receiver.

EFFECT: enhancing functional capacity.

8 cl, 4 dwg

 



 

Same patents:

FIELD: measurement equipment.

SUBSTANCE: system includes a set of cross-wise located holes for pressure take-off, which are flush-mounted on a nose fairing of an airborne vehicle. Three pressure sensors are connected to each pressure take-off hole through pneumatic tubes for pressure measurement on surface from holes fpr pressure take-off. Individual electric power units are connected to three pressure sensors for energy saving of pressure sensors at each pressure take-off hole. A data processing unit is configured for reception of voltage input data corresponding to the pressure measured on surface from pressure sensors. The data processing unit performs one or more check levels of failures for detection and isolation of failures of pressure sensors and failures related to blockage of pressure take-off holes based on voltage input data.

EFFECT: improving accuracy and reliability of evaluation of pressure in an air cushion in compliance with FADS system.

14 cl, 4 dwg

FIELD: instrument making.

SUBSTANCE: system comprises a primary detection circuit, which includes at least one measurement channel. At the same time the specified measurement channel comprises the following: a device to measure static air pressure; a device to measure sideslip angle of an aircraft; a device to measure dynamic pressure, common temperature and angle of aircraft attack; a device of data processing made as capable of detecting anemobaroclinometric parameters on the basis of measurements of static pressure, sideslip angle, dynamic pressure, common temperature and attack angle; at least one laser anemometer (50) to measure at least one parameter of actual speed of the aircraft.

EFFECT: reliability improvement.

6 cl, 4 dwg

FIELD: physics; measurement.

SUBSTANCE: invention relates to measuring angle of attack and gliding angle. Device consists of seven assemblies: sensor (1) of wind vane type, armature (2), electromagnet (3), amplifier (4), motor (5), reduction gear (6) and synchro transmitter (7). Device operation is based on magnetic-induction principle of signal measurement. Change in position of armature connected to wind vane generates electric signal at signal winding output, which is amplified and transmitted to engine (5). The engine processes signal via reduction gear (6) and moves electromagnet to another position until signal from signal windings becomes totally compensated. Also, this signal, by means of synchro transmitter (7), is used to obtaind data on aerodynamic angle.

EFFECT: increased accuracy of output signal due to utilisation of more precise magnetic induction principle of signal measurement instead of the potentiometric one, together with enhanced operating range of the transducer as a whole (wind vane deflection in the full range of aerodynamic angle measurement).

1 dwg

FIELD: the invention refers to the field of aviation and particular to definition of flight air parameters of flying vehicles.

SUBSTANCE: the arrangement has receivers of air pressures with receiving openings provided with an electro heating and anti-icing system connected with the aid of pneumatic routes with pressure sensors, temperature sensors of external air and calculator of flight parameters. At that all blocks are located in a single special aerodynamically stream-lined frame fastened to the flying vehicle and composed of elements of axial symmetric bodies which are fulfilled in the shape of a cone, an ellipsoid, a cylinder, a pyramid. At that the arrangement is autonomous and is connected with the flying vehicle only through channels of transferring of information and supply of electric energy through electric joints. The technical result is contained in securing of autonomy of the system, reducing preparation time for the flight in case of determination of availability of refuse of the system, simplification of the construction of the heating system of receivers of air pressures, reducing weight of the system of measuring air parameters in the whole, reducing labor capacity and cost and also simplification of adaptation of the system to the changed external construction of the fuselage of the flying vehicle or to another flying vehicle. Expansion of working diapason measuring parameters of the flight right up to attack angles of -180ξ≤α≤180°° and sliding -180ξ≤β≤180ξ that is along the whole sphere.

EFFECT: efficient measuring air parameters.

13 cl, 19 dwg

The invention relates to commercial fishing and can be used for trawl fishing on the ocean waters in areas of ocean currents

The invention relates to measuring technique and is intended to measure the magnitude and direction of the component of the flow velocity in the selected plane

FIELD: the invention refers to the field of aviation and particular to definition of flight air parameters of flying vehicles.

SUBSTANCE: the arrangement has receivers of air pressures with receiving openings provided with an electro heating and anti-icing system connected with the aid of pneumatic routes with pressure sensors, temperature sensors of external air and calculator of flight parameters. At that all blocks are located in a single special aerodynamically stream-lined frame fastened to the flying vehicle and composed of elements of axial symmetric bodies which are fulfilled in the shape of a cone, an ellipsoid, a cylinder, a pyramid. At that the arrangement is autonomous and is connected with the flying vehicle only through channels of transferring of information and supply of electric energy through electric joints. The technical result is contained in securing of autonomy of the system, reducing preparation time for the flight in case of determination of availability of refuse of the system, simplification of the construction of the heating system of receivers of air pressures, reducing weight of the system of measuring air parameters in the whole, reducing labor capacity and cost and also simplification of adaptation of the system to the changed external construction of the fuselage of the flying vehicle or to another flying vehicle. Expansion of working diapason measuring parameters of the flight right up to attack angles of -180ξ≤α≤180°° and sliding -180ξ≤β≤180ξ that is along the whole sphere.

EFFECT: efficient measuring air parameters.

13 cl, 19 dwg

FIELD: physics; measurement.

SUBSTANCE: invention relates to measuring angle of attack and gliding angle. Device consists of seven assemblies: sensor (1) of wind vane type, armature (2), electromagnet (3), amplifier (4), motor (5), reduction gear (6) and synchro transmitter (7). Device operation is based on magnetic-induction principle of signal measurement. Change in position of armature connected to wind vane generates electric signal at signal winding output, which is amplified and transmitted to engine (5). The engine processes signal via reduction gear (6) and moves electromagnet to another position until signal from signal windings becomes totally compensated. Also, this signal, by means of synchro transmitter (7), is used to obtaind data on aerodynamic angle.

EFFECT: increased accuracy of output signal due to utilisation of more precise magnetic induction principle of signal measurement instead of the potentiometric one, together with enhanced operating range of the transducer as a whole (wind vane deflection in the full range of aerodynamic angle measurement).

1 dwg

FIELD: instrument making.

SUBSTANCE: system comprises a primary detection circuit, which includes at least one measurement channel. At the same time the specified measurement channel comprises the following: a device to measure static air pressure; a device to measure sideslip angle of an aircraft; a device to measure dynamic pressure, common temperature and angle of aircraft attack; a device of data processing made as capable of detecting anemobaroclinometric parameters on the basis of measurements of static pressure, sideslip angle, dynamic pressure, common temperature and attack angle; at least one laser anemometer (50) to measure at least one parameter of actual speed of the aircraft.

EFFECT: reliability improvement.

6 cl, 4 dwg

FIELD: measurement equipment.

SUBSTANCE: system includes a set of cross-wise located holes for pressure take-off, which are flush-mounted on a nose fairing of an airborne vehicle. Three pressure sensors are connected to each pressure take-off hole through pneumatic tubes for pressure measurement on surface from holes fpr pressure take-off. Individual electric power units are connected to three pressure sensors for energy saving of pressure sensors at each pressure take-off hole. A data processing unit is configured for reception of voltage input data corresponding to the pressure measured on surface from pressure sensors. The data processing unit performs one or more check levels of failures for detection and isolation of failures of pressure sensors and failures related to blockage of pressure take-off holes based on voltage input data.

EFFECT: improving accuracy and reliability of evaluation of pressure in an air cushion in compliance with FADS system.

14 cl, 4 dwg

FIELD: aviation.

SUBSTANCE: to implement the method, a receiver provided by a central sensor, sensors offset from the center, and side sensors is used, and said receiver is connected to the aircraft with the ability to rotate around two orthogonal axes. In this regard, method is suggested for measuring the angle of attack of aircraft's longitudinal axis in relation to relative airflow, wherein the method uses a receiver that is provided at its forward end with a center-direction sensor, that is located at the intersection of horizontal and vertical midplanes of said receiver, and at least two midplane eccentric-direction sensors, that are parallel to said central sensor and are placed at the same distance from it on either side of said horizontal midplane of said receiver.

EFFECT: enhancing functional capacity.

8 cl, 4 dwg

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