By Glomb W.L.
This paper describes a layout for fiber-optic sensing and regulate in complex plane digital Engine keep watch over (EEC). The steered structure is an on-engine EEC which includes electro-optic interface circuits for fiber-optic sensors. measurement and weight are lowered through multiplexing arrays of functionally comparable sensors on a pairs of optical fibers to universal electro-optical interfaces. The structure comprises interfaces to seven sensor teams. 9 special fiber-optic sensor kinds have been discovered to supply the sensing capabilities. research printed no powerful discriminator (except reliability of laser diodes and distant electronics) on which to base a range of hottest universal interface kind. A attempt software is suggested to evaluate the relative adulthood of the applied sciences and to figure out genuine functionality within the engine surroundings.
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Additional resources for Architecture for Fiber-Optic Sensors and Actuators in Aircraft Propulsion Systems
11. 12. 13. 14. 15. 16. 17. 18. 2) ATTITUDE INDICATOR 19. 20. 21. 22. 23. 24. 25. 26. 27. 28. 29. 30. 31. 32. 33. 34. 35. 36. 37. 38. ,. • 32 INSTRUMENT PANEL F-86D-5 AND SUBSEQUENT AIRPLANES 3tl 1. 2. 3. 4. 5. 6. 7. B. 9. 10. 11. 12 13. 14. 15. 16. 26 25 24 23 20. 21. 22. 23. LOCKUP INDICATOR LIGHT' RIGHT INSTRUMENT SUBPANEL STAND-BY COMPASS FUEL FLOWMETER' VARIABLE-NOZZLE POSITION INDICATOR' 24. LOCKUP INDICATOR LIGHT' 25. CANOPY LOCK HANDLE' 26. FUEL QUANTITY GAGE TEST SWITCH' 27. FUEL QUANTITY GAGE 28.
10-10 Lynch removed aspirator, added ADB fillets, 11 ° cone, ,45UD. 10-10 Lynch none, broken microswitch on nose gear door. 10-10 Lynch removed vortex gen. from fus. and stabilizer. aborted-gear unsafe light flickering. 10-11 Lynch none, aborted-main gear door microswitch broke. 10-11 Lynch none, aborted-gear unsafe light on. 10-12 Lynch none, performance flight. 10-12 Lynch added vortex generators as on flight #46. 10-13 Baker none. 10-13 Darnell none. 10-15 Lynch replaced vortex gen. with 2"x25" vanes in same location.
Above, dual vortex generators fitted to the fuselage fillet saddle on 5-17-54. At left, dual short vortex generators were tried on 6-4-54. Below left, a single-row vortex generator was tried on 5-24-54. Below, the almost finalized vortex generator arrangement as tested during Phase III Stability and Control Tests. (all photos NAA via Bill Simone) Bottom, finalized vortex generator arrangement as utilized on all drag chute equipped F-86Ds. (Bob Stollof & USAF) 48 F-100 - STYLE LOW TAIL REAR Above, low-set horizontal tail on YF-86D, 50-577, also necessitated moving the speed brakes to the upper portion of the fuselage.