| 摘要 |
orientation of flight vehicles. SUBSTANCE: the method consists in simultaneous measurement of modulus B of the vector of magnetic induction, projection B1 of the vector of magnetic induction on the axis of the quantum - mechanical self-generating magnetometer by a component magnetometer oriented in parallel with the axis of the quantum-mechanical self-generating magnetometer, formation of error signal ΔB1 = B1-Bcosgamma, where gamma = 45 to 50 deg - the preset value of the angle between the vector of magnetic induction and the axis of the quantum-mechanical self-generating magnetometer, rotation of the quantum-mechanical self-generating magnetometer and the component magnetometer about the axis located at angle alpha=45 deg to the axis of the quantum-mechanical self-generating magnetometer, up to the zero value of the error angle, additional measurement of projection Bn of the vector of magnetic induction on the direction of the axis of rotation with the aid of the second component magnetometer oriented in parallel with the axis of rotation, reversal of the polarity of radio-frequency communication at a reduction of Bn below level Bcos(45°+gamma) with a simultaneous variation of error signal ΔB1 = B1+Bcosgamma,, and restoration of the original polarity and error signal at a subsequent increase of Bn above level -Bcos(45°+gamma).. EFFECT: provided orientation of the quantum-mechanical self-generating magnetometer at placement on highly maneuverable flight vehicles, excluded necessity of adjustment of angle alpha, depending on the angle of dip. 2 dwg
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