GB418377A - A new or improved gyroscopic instrument for aircraft and the like - Google Patents

Abstract

418,377. Gyroscopic apparatus. DOVE, J. S., Hale House, Ockley, Surrey. April 24, 1933, Nos. 11924 and 34829. [Class 97 (iii).] In a gyroscopic instrument particularly for use in navigating aircraft, a rotor with three degrees of freedom is driven by and gyroscopically influenced by the airflow past the aircraft. In the form shown, the rotor comprises a rim 1 interconnecting massive balls 2 on spokes 3 radiating from a hub 4, which is mounted by ball bearings on an annular member 8. The latter is connected by a universal joint to a spindle 12, pivotally mounted in a U-shaped frame 13, which is pivoted at 14 to a supporting disc 16 and adjustable thereon by means of slot 17 and thumb nut 18. The lower part of the rotor: s shielded from the air stream by a screen 19 fixed to the frame 13. The air stream drives the rotor by impinging on the upper balls 2 and also causes a torque on the rotor precessing the latter into alignment with the air stream when it has become displaced by turning of the supporting aircraft. Yawing of the aircraft is indicated by movement of the rim 1 across the graduations 19A on the screen 19 and banking of the aircraft by tilting of the rim 1 relative to the lubber line 19B. Vanes 25 balanced by weights 26 are fixed on the member 8 and provide corrective or damping properties under the action of the air stream. The rotor may be centralized by moving a sleeve along the spindle 12 by links 22, 23, until a flange 21 engages a conical surface on the member 8. Fig. 3 shows the instrument applied as an automatic pilot. The weights 26 are replaced by a tail piece 31 connected by a link 32 and lever 33 to a bracket 34 adjustably fixed to a spindle 35 which is mounted in a bearing rigid with a spindle 37 and carries a vane 36 normally facing the wind. The spindle 37 is carried in a bearing in a lug 38 upstanding from a lever 39 pivoted at 40 and having an adjustable pin 42 engaging a slot 43 in a second lever 44, the spindle 45 of which is fixed to the rudder bar 46. An upstanding bearing 48 on the lever 44 supports a spindle 49 carrying a second servovane 50, normally parallel to the airstream and a pinion 51 geared to a pinion 52 which is connected by universal joints and extensible shaft 53 to the shaft 37. Upon yawing of the aircraft the tail 31 rocks the spindle 35 and gives the vane 36 an angle of incidence, whereupon the shaft 37 and pinion 52 are turned under the influence of the air stream on the vane. The pinion 52 gives an inclination to the second larger servo-vane 50, whereupon the lever 44 is rocked and the rudder bar 46 suitably operated. The pin and slot connection 42, 43 causes the lever 39 and first servo system to follow up the displacements of the rotor 30. A second tail 31 (not shown) may operate a servo system for controlling the ailerons. Three axis control may be obtained by using two rotors. The apparatus is arranged so that only the wind affected parts project from the outer surface 56 of the aircraft.