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Month in the Patent Office

Month in the Patent Office flaps 5 through arms 12 and levers 11. A spring 23 exerts through arm 32 of lever 22 a force tending to Month in the Patent Office move sleeve 30 towards the position shown. 612,880. Jet-propelled aircraft. Anderson, J. R. These abstracts of British Patent Specifications are taken, by permission, from the officially prepared June 4, 1946, Nos. 16982/46 and 11786/47. (Classes 4 abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, and 114.) (Also in Groups XXIV and XXVI.) 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies An aircraft is provided with one or more gas tur­ bines for providing motive power and adapted todrive of the full specifications are obtainable at the same address, price Is. each. one or more propellers through disconnectable clutch means of the positive engagement type and also to provide an exhaust jet or jets for propelling the air­ craft by jet reaction, means being provided for bring­ 612,468. Helicopters. Pullin, C. G., Shapiro, J. S., plied to reproduce the control movements. The inven­ ing the mating elements of the clutch into synchron­ and Cicrva Autogiro Co. Ltd. May 24, 1946, No. tion is shown applied to a training helicopter fitted ism prior to their engagement. A single turbine may 15802. Drawings to Specification. (Class 4.) (Also in with dual control columns 10, 11 mounted on a trans­ drive a single variable pitch propeller, or as shown in Groups XXVI and XXIX.) verse torque tube 12, the columns having downwardly- n c 2, two turbines 35 may drive contra-rotating pro­ extending members 15 connected together by a link 16, pellers 39 through gearing 48, 50 and clutches 28a. Prime-movers of the type having propulsive ducts and also connected to converging push-pull rods 17, The aircraft is intended to take off in a vertical posi­ at the ends of rotating radial arms constitute the 18. The latter are connected by vertical links 38 to a tion in the manner of a helicopter, the propellers pro­ power plant of a helicopter. second pair of converging rods 29, 30 which control viding direct lift, as described in Specification 568,548. the movements of a universally-mounted rod 26 Each clutch comprises an element 52 with two sets 612,688. Rotary-wing aircraft. Bristol Aeroplane carrying the pitch-control spider 23. Movement of of concentric integral teeth engagcablc by a second Co. Ltd., and Wotton, J. May 30, 1946, No. 16485. cither control column in a fore-and-aft direction member 55, of which the outer ring of teeth are (Class 4.) moves both pairs of converging rods in the same formed on a separate ring 57, riG. 7. The clutch ele­ direction, resulting in the rod 26 being tilted in the ments are coupled to synchronizing alternators 64, 65. fore-and-aft plane. Transverse movement of either To effect engagement of the clutch elements, the pitch column causes approximately equal movements in of the propellers is decreased so that they are rotated opposite directions of the push-pull rods, with conse­ by the air-stream, and the pitch is then automatically quent transverse tilting movement of the member 26. adjusted by a contactor operated by the alternators Collective pitch control is effected by a hand lever 42 64, 65, to bring the propellers and turbines into syn­ and links 43, 44. chronism, upon which solenoids 63 are energized to move the ring member 57 into engagement with the clement 52, such movement resulting in the closing 612,799. Controlling aircraft: retractable landing- of the circuit for a motor 59 which rotates a screwed gear. Morane-Saulnier Soc. Anon. June 4, 1946, spindle 60 by which the second portion of the clutch No. 16979. Convention date, Mareh 7. (Class 4.) element 55 is engaged with the clement 52 (see In a control system for aircraft a single casing 24 Group XXIV). When the aircraft is being propelled contains the parts controlling the landing flaps 5 of by the jets only, the blades of the propellers 39 are the wing 2, shown in plan, no. 2, and also the parts feathered and brought to an approximately hori­ controlling the retractable three-wheel landing-gear zontal position to serve as auxiliary wings. Upon the (of which only the rear wheels 4 are shown), the above blades being brought to rest, a motor 73, no . 6, is two controls being operated through a common single energized to engage clutch elements 69, 72 and also to member such as the horizontal shaft 25 shown in close contacts 78, 79 controlling a second motor 71 n c 3. In the construction shown, the control of the which rotates the propeller, through a worm 70 gear­ flaps is free for operation only while the landing-gear ing with the clutch member 69, until a projection on is in its lowered condition. The shaft 25, which can be the propeller boss engages the contact arm 79 to open rotated by a crank turned by the pilot and acting the circuit of the motor 71. Each jet nozzle 41 is pro­ through sprocket-wheels and a chain 9, has freely vided with pairs of vertical and horizontal deflectors mounted on it two worms 33 and 26, which can be 42 which may be moved into the jet stream for control alternatively coupled by lugs such as 27, 29 to a sliding purposes. The horizontal deflectors are operated by a sleeve 30 splined to shaft 25 so as to rotate therewith. control member 161, n c 14, through bevel gearing In the position shown in no . 3, the worm 33 coupled to sleeve 30 can be driven from shaft 25 to turn 154, 155 in a casing 151 operating racks 150 engaging pinions 149 which actuate pulleys and cables 146, 145. worm-wheels 34, 40, to act one through arms 15 upon Upon moving the lever 161 in a fore-and-aft direc­ the two under-carriage wheels 4 to lower them and the tion, both upper or both lower deflectors are moved other through an arm 17 to lower the third wheel; a A control for adjusting the pitch of the blades of a into the jet streams, while one lower and the opposite pivoted lever 38 with an arm 39 locking sleeve 30 from sustaining rotor comprises a cockpit control member upper deflector are moved into the streams upon sliding is turned down to withdraw arm 39 during the movable in two directions at right angles, a pair of transverse movement of the lever 161. The vertical ending of the rotation of wheel 40, so that sleeve 30 articulated, converging rods jointed together and deflectors are operated by the rudder. The control can then be moved by means of a wire 7 connected movable by the control member in one direction to surfaces may be operated jointly with the deflectors, to a pilot's control-lever, acting on lever 22 having pull or push both rods, and in the other direction to being capable however of being disconnected there­ an arm 32 to move sleeve 30 into connexion with pull one rod and push the other, and a connexion from and locked in the neutral position. Specification worm 26, which can then be rotated by further turning. between the rods and an element of the pitch-adjusting 565,912 also is referred to. of shaft 25 to drive worm-wheel 36 and lower wing mechanism to which the movement of the rods is ap­ November 1951 http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Month in the Patent Office

Aircraft Engineering and Aerospace Technology , Volume 23 (11): 1 – Nov 1, 1951
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032104
Publisher site
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Abstract

flaps 5 through arms 12 and levers 11. A spring 23 exerts through arm 32 of lever 22 a force tending to Month in the Patent Office move sleeve 30 towards the position shown. 612,880. Jet-propelled aircraft. Anderson, J. R. These abstracts of British Patent Specifications are taken, by permission, from the officially prepared June 4, 1946, Nos. 16982/46 and 11786/47. (Classes 4 abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, and 114.) (Also in Groups XXIV and XXVI.) 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies An aircraft is provided with one or more gas tur­ bines for providing motive power and adapted todrive of the full specifications are obtainable at the same address, price Is. each. one or more propellers through disconnectable clutch means of the positive engagement type and also to provide an exhaust jet or jets for propelling the air­ craft by jet reaction, means being provided for bring­ 612,468. Helicopters. Pullin, C. G., Shapiro, J. S., plied to reproduce the control movements. The inven­ ing the mating elements of the clutch into synchron­ and Cicrva Autogiro Co. Ltd. May 24, 1946, No. tion is shown applied to a training helicopter fitted ism prior to their engagement. A single turbine may 15802. Drawings to Specification. (Class 4.) (Also in with dual control columns 10, 11 mounted on a trans­ drive a single variable pitch propeller, or as shown in Groups XXVI and XXIX.) verse torque tube 12, the columns having downwardly- n c 2, two turbines 35 may drive contra-rotating pro­ extending members 15 connected together by a link 16, pellers 39 through gearing 48, 50 and clutches 28a. Prime-movers of the type having propulsive ducts and also connected to converging push-pull rods 17, The aircraft is intended to take off in a vertical posi­ at the ends of rotating radial arms constitute the 18. The latter are connected by vertical links 38 to a tion in the manner of a helicopter, the propellers pro­ power plant of a helicopter. second pair of converging rods 29, 30 which control viding direct lift, as described in Specification 568,548. the movements of a universally-mounted rod 26 Each clutch comprises an element 52 with two sets 612,688. Rotary-wing aircraft. Bristol Aeroplane carrying the pitch-control spider 23. Movement of of concentric integral teeth engagcablc by a second Co. Ltd., and Wotton, J. May 30, 1946, No. 16485. cither control column in a fore-and-aft direction member 55, of which the outer ring of teeth are (Class 4.) moves both pairs of converging rods in the same formed on a separate ring 57, riG. 7. The clutch ele­ direction, resulting in the rod 26 being tilted in the ments are coupled to synchronizing alternators 64, 65. fore-and-aft plane. Transverse movement of either To effect engagement of the clutch elements, the pitch column causes approximately equal movements in of the propellers is decreased so that they are rotated opposite directions of the push-pull rods, with conse­ by the air-stream, and the pitch is then automatically quent transverse tilting movement of the member 26. adjusted by a contactor operated by the alternators Collective pitch control is effected by a hand lever 42 64, 65, to bring the propellers and turbines into syn­ and links 43, 44. chronism, upon which solenoids 63 are energized to move the ring member 57 into engagement with the clement 52, such movement resulting in the closing 612,799. Controlling aircraft: retractable landing- of the circuit for a motor 59 which rotates a screwed gear. Morane-Saulnier Soc. Anon. June 4, 1946, spindle 60 by which the second portion of the clutch No. 16979. Convention date, Mareh 7. (Class 4.) element 55 is engaged with the clement 52 (see In a control system for aircraft a single casing 24 Group XXIV). When the aircraft is being propelled contains the parts controlling the landing flaps 5 of by the jets only, the blades of the propellers 39 are the wing 2, shown in plan, no. 2, and also the parts feathered and brought to an approximately hori­ controlling the retractable three-wheel landing-gear zontal position to serve as auxiliary wings. Upon the (of which only the rear wheels 4 are shown), the above blades being brought to rest, a motor 73, no . 6, is two controls being operated through a common single energized to engage clutch elements 69, 72 and also to member such as the horizontal shaft 25 shown in close contacts 78, 79 controlling a second motor 71 n c 3. In the construction shown, the control of the which rotates the propeller, through a worm 70 gear­ flaps is free for operation only while the landing-gear ing with the clutch member 69, until a projection on is in its lowered condition. The shaft 25, which can be the propeller boss engages the contact arm 79 to open rotated by a crank turned by the pilot and acting the circuit of the motor 71. Each jet nozzle 41 is pro­ through sprocket-wheels and a chain 9, has freely vided with pairs of vertical and horizontal deflectors mounted on it two worms 33 and 26, which can be 42 which may be moved into the jet stream for control alternatively coupled by lugs such as 27, 29 to a sliding purposes. The horizontal deflectors are operated by a sleeve 30 splined to shaft 25 so as to rotate therewith. control member 161, n c 14, through bevel gearing In the position shown in no . 3, the worm 33 coupled to sleeve 30 can be driven from shaft 25 to turn 154, 155 in a casing 151 operating racks 150 engaging pinions 149 which actuate pulleys and cables 146, 145. worm-wheels 34, 40, to act one through arms 15 upon Upon moving the lever 161 in a fore-and-aft direc­ the two under-carriage wheels 4 to lower them and the tion, both upper or both lower deflectors are moved other through an arm 17 to lower the third wheel; a A control for adjusting the pitch of the blades of a into the jet streams, while one lower and the opposite pivoted lever 38 with an arm 39 locking sleeve 30 from sustaining rotor comprises a cockpit control member upper deflector are moved into the streams upon sliding is turned down to withdraw arm 39 during the movable in two directions at right angles, a pair of transverse movement of the lever 161. The vertical ending of the rotation of wheel 40, so that sleeve 30 articulated, converging rods jointed together and deflectors are operated by the rudder. The control can then be moved by means of a wire 7 connected movable by the control member in one direction to surfaces may be operated jointly with the deflectors, to a pilot's control-lever, acting on lever 22 having pull or push both rods, and in the other direction to being capable however of being disconnected there­ an arm 32 to move sleeve 30 into connexion with pull one rod and push the other, and a connexion from and locked in the neutral position. Specification worm 26, which can then be rotated by further turning. between the rods and an element of the pitch-adjusting 565,912 also is referred to. of shaft 25 to drive worm-wheel 36 and lower wing mechanism to which the movement of the rods is ap­ November 1951

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Nov 1, 1951

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