波音 VERTOL YUH-61A 直升机

FLIGHT International, 21 August 1976 Sikorsky YUH-60A 451 Anti-vibration self-tuning rotor- head damper Blade damper unit Bifiiar bearings Blade pitch-change links Nicke l -coated abras ion-proof leading edge Main rotor blades from titanium spars, with bonded Nomex honey- comb core-filled glass-fibre skins Constant-section blades with rear- ward-swept tips Modular main gearbox GE T700-GE-700 engine Exhaust temperature and infra-red reduction fan Infra-red suppressed exhaust Accessories driven off gearbox transmission Engine oil tank Forward-sliding fairing (access to control linkage and air condition- ing) Main-transmission oil cooler and fan Rearward-sliding fairing Auxiliary power unit Engine cowlings form built-in working platforms Large-diameter tail-rotor shaft Lubrication-free bearings Sealed-for-life grease-packed disc- type gearboxes Tail rotor with graphite and glass- fibre continuous-spar blades Sideways-folding tailboom Large-area cambered vertical stabil- iser Trimming horizontal stabiliser Attachment points for ground maintenance steps (both sides) High flare angle, energy-absorbing shock-strut and tailwheel Pressure and gravity fuel-tank fillers Fuel vent Two separate self-sealing fuel cells 31 Folding maintenance steps 32 Rearward-sliding door (both sides give access for troops) Undercarriage (kneels for air- lifting) Maintenance steps Forward-sliding window panel (both sides) Crew entry door (both sides) Armoured crew seats (folding shoulder side-panels) Third crew member's position (incorporating gunner and load observer) Shrouded instrument panel Collective-pitch control (both sides) Avionics and electronics bay (upward-hingeing panel) Pitot tubes 33 38 Uttas comparison US Army constraints and guidelines laid down for its new utility and squad-carrying helicopter resulted in two very similar-looking aircraft. Both have relatively highly loaded rotors by comparison with that of the Huey, and need pro- portionately more power to drive them. The UH-1 has a 48ft-diameter rotor and weighs 9,0001b, while the Boeing Uttas has a 49ft rotor and grosses at 18,7001b; the Sikorsky- design is slightly larger, with a 53ft rotor, and weighs a maximum of 22,0001b. The commercial versions of both air- craft are temporarily on backburners while the companies devote their energies to the all-important military Hy-off. 450 FLIGHT International, II August 1976 Boeing Vertol YUH-61A Constan t -sec t ion glass-f ibre c o m - posi te blades T i t a n i u m leading edge, N o m e * h o n e y c o m b core w i t h glass-f ibre skins and aft f a i r i ng Hingeless r o t o r hub T i t a n i u m b lade - roo t f i t t ings V i b r a t i o n dampers Main t ransmiss ion gearbox Transmiss ion suspension F o r w a r d — a n d r e a r w a r d — s l i d i n g panels i n c o r p o r a t i n g w o r k i n g p lat - f o r m s F o r w a r d aux i l i a r y gearbox , d r i v i n g e lect r ica l and hydrau l i c genera to rs and pumps A i r - c o n d i t i o n i n g e q u i p m e n t Rear aux i l i a r y gearbox d r i v i n g e lec t r ica l and hydrau l i c genera to rs and pumps A u x i l i a r y p o w e r u n i t G E T 7 0 0 - G E - 7 0 0 eng ine Engine t ransmiss ion and cross- shaft Engine tank Separate fan, d i lu tes engine exhaust and reduces in f ra - red emiss ion Engine cow l ings and comb ined w o r k i n g p la t fo rms Large-d iamete r t a i l - r o t o r d r i ve - shaft , dual redundan t bearings S ideways- fo ld ing ta i l u n i t F lex-st rap ta i l r o t o r (glass-fibre cons t r uc t i on ) T r i m m i n g h o r i z o n t a l stabi l iser T a i l - r o t o r c o n t r o l push-pu l l rods Shock-absorb ing ta i l bumper H y d r a u l i c and fuel systems bay ( b o t h sides) Pressure and g rav i t y f i l lers ( le f t side on l y ) Foam-f i l led fuel cells Underca r r i age (kneels l i f t ing) Drawing by "Fl ight" artist John A. Marsden Copyright IPC Business Press Ltd., London 1976 f ^ i 28 29 =,30 = 34 35 I bin / i V j ~&- Four independent rea rward -s l i d i ng d o o r s C e i l i n g - a t t a c h e d , c r a s h - r e s i s t a n t t r o o p seats D r o p - d o w n f r o n t gunner ' s w i n d o w ( t h i r d c rew m e m b e r and load c o n t r o l l e r ) C r e w e n t r y doo rs A r m o u r e d c r e w seats ( fo ld-away shou lde r panels) Dual-redundant collective and cyc- lic pitch-control circuits Pi tot tubes Windsh ie l ds , p i t o t tubes and r o t o r blades e lec t r ica l ly ant i - iced Elect ronics and avionics bay (up- w a r d h inge ing panel) Knee l ing nose undercar r iage %%iilft