| 摘要 |
FIELD: aircraft engineering.SUBSTANCE: phase incursion varying in time at metre receiver circuit analogue parts are defined. For this, order of measurement matrix elements formation is changed. Namely, phase difference between appropriate reference and measured phase differences of signals from S spacecraft with location known a priori. Signals of one of S detected spacecraft are taken to be reference difference signals. Difference between difference signals of S-1 spacecraft and appropriate difference signals of reference spacecraft. Said signals are squared and summed over all possible pairs of antenna elements and over all spacecraft. Proposed device comprises M identical receiving channels where MM?4, reference signal generators, clock oscillator, S correlators, S analysis unit, S+1 switchboard, correlators initial setting unit, 2S subtractors, two memory units, computer-generator, control unit, decoder, indication unit, three input setting buses, radio navigator and antenna element interconnected in a definite manner.EFFECT: higher precision of determination of bank, pitch and azimuthal angles.2 cl, 13 dwg |
