Patent GB-907590-A (GB)
Title: Tilt wing aircraft
IPC: B64C29/00
Filed: 1960-09-16
Abstract: 907,590. Convertible aircraft. HILLER AIRCRAFT CORPORATION. Sept. 16, 1960 [Sept. 21, 1959], No. 31924/60. Class 4. A convertible aircraft comprises wings mounted on a fuselage for pivotal movement about an axis longitudinal of the wings between substantially horizontal and vertical positions, a lift member on each wing capable, when actuated, of generating a force transverse to the plane of the wing and control means to operate the lift members differentially, thrust generating means on each wing capable of generating a force substantially parallel to the plane of the wing and control means to operate the thrust means differentially, separate yaw and roll pilotoperated controls and integrating mechanism connected to both said pilot operated controls and to the lift and thrust differential controls, said integrating mechanism being arranged so that when the wings are horizontal it transmits motion from the roll pilot control to the lift differential control means only and from the yaw pilot control to the thrust differential control means only and when the wings are vertical it transmits motion from the roll pilot control to the thrust differential control means only and from the yaw pilot control to the lift differential control means only. The aircraft comprises a fuselage 2, wing assembly 3 and tail unit 4. The wing unit is mounted for pivotal movement about an axis 13 under the control of a fluid pressure jack system (not shown) between the horizontal position shown in Fig. 1 to a vertical position. Each wing carries a power plant 20, 22 capable of generating thrust substantially co-planar with the wing along an axis 21 at a wing mid-span position so that the slip-stream passes over the major part of the span of ailerons 11, 12 which, when deflected, generate forces substantially normal to the plane of the wings. The power output of the engines may be adjusted differentially by mechanism such as 66a, 67. The usual hand and foot controls 33, 30 are connected through cable runs 34, 31 to sectors 36, 45 respectively. Sector 36 is mounted on a shaft 37 which is connected to a yaw integrator 42 (to be described later) to pivot a yaw integrator output arm 43 through an arc and thus transmit longitudinal movement to a yaw input link 44. A link 43a connects shaft 37 and arm 43 to limit movement of arm 43 to a single plane. Sector 36 also winds cables connected to the tail rudder for yaw control in normal flight. Sector 45 is mounted in a bearing 46 by a shaft having a bifurcated end 47 which is pivoted to a curved roll input arm 48, the opposite end of which swings through an arc. Yaw and roll input motion transmitted through link 44 and arm 48 respectively are mixed by an integrator lever 50 which has one arm 52 connected by a swivel to rod 44 and another arm 53 connected by a swivel joint 54 to arm 48. Consequently movement of pedals 30 is translated into pivotal movement of normally horizontal arm 52 about the axis of arm 53 which normally coincides with vertical axis 55 and movement of wheel 33 pivots normally vertical arm 53 about the axis of arm 52 which normally coincides with horizontal axis 56. Pivotally carried on lever 50 by a trunnion 58 normally concentric with the wing pivot axis 13 is an aileron control arm 59 mounted on a transverse pivot 60 and connected to a thrust control arm 61 which, when pivoted, swings through a connector 61a a thrust sector control arm 62 about a pivot 63 fast with the wing 3. The arm 62 carries a sector 65 which winds cables 66, Fig. 1, over pulleys 67 to operate the device 66a for differential pitch change of the propellers 22. When aileron control arm 59 is pivoted it operates a sector 70 through link 71 to wind aileron control cables 72 over pulleys 74 to impart differential movement to ailerons 11 and 12. Since the pivots for sector arms 62 and 70 are fast with the wing, they swing with the wing about axis 13 and carry the respective control arms 59 and 61 with them. Control in pitch at low forward speeds is provided by upwardly and downwardly directed jet nozzles 27.