SLD Ice Detector Design With Numerical Simulation And Experiments

In high-altitude clouds, supercooled water droplets are widespread. If the supercooledwater droplets’ diameter is larger than50um, they can be called supercooled largedroplets(SLD). Due to the larger size, SLD icing are slower and happens gradually inprocess of flowing on the surface. It is similar to the melt ice near de-icing heating device,forms a mixture of ice water sliding to the wing rear, which can make an ice ridge andchange the aircraft shape envelope. So SLD icing destroy the aircraft pneumatic structureand posed a serious threat to flight safety.Because SLD beyond the existing standard”Appendix C of American FederalAviation Regulations Section25”, which is for anti-icing system design, the conventionalanti-icing system is not so effective against SLD icing. A new type of ice detector isneeded to solve this problem.In this thesis, numerical simulation software is used to simulate SLD icing in flight.Different environment parameters were setted to research the in-flight SLD icing law. Aparametric model was established for the SLD ice detector probe and a variety of detectorprobes with different parameters were designed. The numerical simulation software useicing model based on N-S equations to validate different designs. With the comparison ofcalculation results, the optimized design was created. The probe, optical fiber icing sensorand the related signal detection processing hardware and software system were allprocessed. At last, the whole system conducted several experiments in icing wind tunnel.This thesis offers a systematic exploration of SLD icing law, provide basis for SLDicing detection, and lay the foundation for further experiments and optimization of SLDicing detector.