Measurement of the Angle of Attack of an Aerophysical Missile Complex in Flight Based on the Hall Effect Sensor and Electronic Measurement System

The method of direct continuous measurement of the angle of attack of an aerophysical missile complex, with the use of a Hall effect sensor, when in motion in its path for the numbers of Mach of the flow М∞ ≤ 4.5, Reynolds along the forebody length ReL,∞ ≤ 108, acceleration а ≤ 32 g under the operation of a dual-thrust rocket engine (DTRE) is presented. The airborne electronic measurement system of the aerophysical missile complex, including the silicon Hall effect sensor as a sensor of the missile complex orientation in relation to the full vector of the Earth’s magnetic field in this experiment, is described in detail. The Hall effect sensor has been installed between the two concentrators of magnetic flux from permalloy plates to amplify the Earth’s magnetic field. The voltage in the magnetic field measurement channel has been determined by the dependence of u = K·H, where K is the meter conversion coefficient, H is the projection of the magnetic field intensity vector on the meter. A signal from the Hall effect sensor has arrived at the magnetic storage. Based on processing the path data on the angle of elevation, azimuth and range, it is found that the direction of a vector of free external stream velocity in flight of the missile complex with the operating DTRE has not changed, and the angle between the axis of this complex and the full vector of the Earth’s magnetic field has been constant. This has enabled to conclude that the angle of attack in flight of the aerophysical missile complex is equal to zero with a precision of 0.3°. The result corresponds to the known theoretical data and is important for the calculation of thermal flows, surface friction resistance, bottom resistance in the presence of laminar-turbulent transition, turbulent regime of wall boundary flow and its relaminarization on streamlined surfaces. Based on flight data, a scheme of the aerophysical complex for measuring the angle of attack of an uncontrolled supersonic rocket with the aim of studying its oscillations and the problem of flight stability in the active and passive sections of the trajectory is proposed.