| 摘要 |
FIELD: transport.SUBSTANCE: invention relates to aircraft engineering and may be used in systems indicating helicopter flight parameters. Proposed system comprises rpm transducer of rotor 1, rotor rpm indicator 2, and rotor limiting rpm signaling unit 6. Said rotor limiting rpm signaling unit consists of rpm transducer current signal normalisation circuit 7, computer 8 and three electronic gates 9, 10, 11. Computer comprises standard means for comparing rotor current rpm with preset maximum and minimum magnitudes (98% and 92% of ratings, respectively) and for defining rotor rpm gradient to be compared with preset limit (not over 2% a second). Said three gates 9, 10, 11 of said rotor limiting rpm signaling unit are connected by their control inputs with appropriate outputs of said function comparator units of computer 8. Outputs of electronic gates 9, 10 are connected to light signaling system board "LOW RPM" and "HIGH RPM" while output of gate 11 is connected to voice warning device "RPM DROP".EFFECT: accurate estimation of flight conditions, higher reliability at limiting flight conditions.2 cl, 1 dwg |
