RU2014150117A - ON-BOARD SYSTEM FOR MEASURING THE PARAMETERS OF THE WIND SPEED VECTOR AT THE PARKING, STARTING AND TAKE-OFF AND LANDING MODES OF THE HELICOPTER - Google Patents

Abstract

An on-board system for measuring the parameters of the wind speed vector in the parking lot, the launch and take-off and landing modes of a helicopter, which contains a wind receiving device in the form of a fixed multichannel flow airmetric receiver, pneumoelectric converters of informative signals, an analog-to-digital conversion channel and a computing device, characterized in that the stationary multichannel flow the aerometric receiver is mounted on the fuselage in the area of operation of the rotor vortex column and is perceived pressures that determine the magnitude and direction of the wind speed vector in the parking lot before the power plant starts, on the outer surface of the upper shielding disk of the fixed multichannel flow aerometric receiver, in the plane parallel to the plane of symmetry of the helicopter, an axisymmetric, for example, hemispherical, aerometric receiver is installed, on the axis of symmetry of the axisymmetric aerometric receiver hole, which is the receiver of the total pressure of the resulting air flow vortex of the rotor column in a plane parallel to the plane of symmetry of the helicopter, at the same angle to the axis of symmetry of the axisymmetric, for example, hemispherical aerometric receiver, are holes that are pressure receivers that determine the angular position of the velocity vector of the resulting air flow of the rotor column of the rotor relative to the axisymmetric axis of symmetry, for example hemispherical aerometric receiver in the plane of symmetry of the helicopter, in the plane perpendicular to

Claims (1)

An on-board system for measuring the parameters of the wind speed vector in the parking lot, the launch and take-off and landing modes of a helicopter, which contains a wind receiving device in the form of a fixed multichannel flow airmetric receiver, pneumoelectric converters of informative signals, an analog-to-digital conversion channel and a computing device, characterized in that the stationary multichannel flow the aerometric receiver is mounted on the fuselage in the area of operation of the rotor vortex column and is perceived pressures that determine the magnitude and direction of the wind speed vector in the parking lot before the power plant starts, on the outer surface of the upper shielding disk of the fixed multichannel flow aerometric receiver, in the plane parallel to the plane of symmetry of the helicopter, an axisymmetric, for example, hemispherical, aerometric receiver is installed, on the axis of symmetry of the axisymmetric aerometric receiver hole, which is the receiver of the total pressure of the resulting air flow vortex of the rotor column in a plane parallel to the plane of symmetry of the helicopter, at the same angle to the axis of symmetry of the axisymmetric, for example, hemispherical aerometric receiver, are holes that are pressure receivers that determine the angular position of the velocity vector of the resulting air flow of the rotor column of the rotor relative to the axisymmetric axis of symmetry, for example hemispherical aerometric receiver in the plane of symmetry of the helicopter, in the plane perpendicular to the plane and the helicopter symmetry, at the same angle to the axis of symmetry of the axisymmetric, for example, hemispherical aerometric receiver, there are openings that are pressure receivers that determine the angular position of the velocity vector of the rotor rotor column air flow relative to the axis of symmetry of the axisymmetric aerometric receiver in a plane perpendicular to the helicopter symmetry plane this is the pneumatic outputs of a fixed multichannel flow-through aerometric receiver The axisymmetric and, for example, hemispherical aerometric sensors installed on it are connected to the inputs of pneumatic-electric converters, the outputs of which are connected via an analog-to-digital conversion channel to the input of a computing device, which is designed as a microprocessor that implements algorithms for determining the parameters of the wind speed vector as if it were parked before starting the power installation, and on the launch and take-off and landing modes of the helicopter according to the equations: 1) In the parking mode when starting the power plant and rotating the rotor:

2) In the mode of taxiing and maneuvering on the earth's surface:

3) On takeoff and landing modes (takeoff, decline, hovering, landing):

where P ₁ , P ₂ and P ₃ , P ₄ are the pressures perceived by the openings located on an axisymmetric, for example a hemispherical aerometric receiver, at an angle φ ₀₁ and φ ₀₂ to the axis of symmetry of the aerometric receiver; P _ΠΣ , P _CTΣ , - total and static pressure of the resulting incident air flow of the rotor vortex column, perceived by an axisymmetric aerometric receiver; T _TΣ - absolute braking temperature of the resulting air flow of the rotor vortex column perceived by the braking temperature receiver mounted on the fuselage of the helicopter; ρ _Σ is the density of the resulting air flow of the rotor vortex column; V _Σ is the magnitude (module) of the velocity vector of the resulting air flow of the rotor vortex column; φ ₁ and φ ₂ - angles that determine the angular position of the velocity vector of the resulting air flow of the vortex column of the carrier relative to the planes parallel and perpendicular to the plane of symmetry of the helicopter; V _i0 - module of the velocity vector of the inductive flow of the rotor in the hover mode; K _ix , K _iy , K _iz , K _p - dimensionless coefficients determined during ground and flight tests of this type of helicopter; V _{px pz} and V, V _PX and V _pz - longitudinal and lateral components of velocity vector helicopter taxiing on the ground track vector and velocity of the helicopter, the helicopter defined set of satellite navigation system (SNS) and the Doppler velocimeter and the drift angle (DISS); ω _x , ω _y , ω _z - the angular velocity of rotation of the helicopter relative to the axes of the associated coordinate system; x, y, z - coordinates of the installation site of the fixed multichannel flow-through aerometric receiver on the fuselage of the helicopter; V _x , V _y , V _z , α and β are the components and direction angles (angle of attack and slip) of the true airspeed vector of the helicopter; W, W _x , W _y , ψ - module, longitudinal and lateral components, the angle of the direction of the wind speed vector in the horizontal plane; P _n , P ₀ = 101325 Pa and T ₀ = 288.15 K — static pressure at a flight altitude H, static pressure and absolute air temperature at an altitude H = 0 in a standard atmosphere; R = 287.05287 J / kg · K is the specific gas constant of air; τ = 0.0065 K / m is the temperature gradient.