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Month in the Patent Office

Month in the Patent Office same extent so that there is no force on the piston 15, but as the control member 10 is moved from its neutral position, a rack and pinion connection 30, 31 to rod 29 causes this rod to move a lever 27 engaging a slot in rod 29 about its pivot 28, so moving a member These abstracts of British Patent Specifications are taken, by permission, from the officially prepared abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, 25 Southampton Buildings, W.C.2 , sheet by sheet as issued, a t a subscription of 10s. per Group. Copies of the full specifications are obtainable at the same address, price 1s. each. 619,984. Aircraft control systems. Saunders-Roe, 619,987. Aircraft controls. Saunders-Roe, Ltd., Ltd., Knowler, H., and Robertson, F. H. Oct. 7, 1946, Knowler, H., and Knowler, P. H. Oct. 16, 1946, No. 29,844. (Class 4.) (Also in Groups XXIX and No. 30805, (Class 4.) XXXVIII.) An arrangement for simulating 'feel' with power- The pilot's control member 10 of an aircraft con­ operated control surfaces comprises a pair of levers trols two power units 25, 125 which each execute 21, 22 coupled by a pin 28 engaging slots 29, 31 movements corresponding in amount and direction to therein, the lever 21 being rotated by a wheel 14 the movement of the control member and thus, connected to the pilot's control member to move the through a differential gear 31, drive a torque shaft 32 second lever 22 against the resistance imposed by which drives the irreversible gearing 50 associated torque tubes 24, 25. The torque exerted by the tubes with the control surface, and means are provided to is controlled in accordance with airspeed by varying slotted to receive the lever 27 and on which both prevent reverse rotation of one power unit, should it the velocity ratio of the levers by adjustment of the valves 23 are mounted, to close one of the valves 23 fail, by the other. The control member 10 is con­ position of the pin 28 in the slots 29, 31. This is and to open the other. A force is thus set up on piston nected by a chain drive 11, shaft 12 and chain drives effected by a screwed shaft 32 driven by an electric 15 which corresponds to the movement of the control 13, 14 to two selsyn transmitters 16, 116 adapted to motor 40 through worm gearing 42 and a shaft 33, the member 10 and tends to return this member to its control the power units 25, 125 respectively. Each motor being controlled by the movements of a capsule neutral position. The rate at which this force increases power unit comprises a constantly rotating constant 4 mounted in a casing 44 with a connexion 45 to a with increase of movement of the member 10 is caused speed electric motor 26 driving a variable delivery pitot head, the capsule being connected to a hori­ to increase with airspeed by mounting the pivot 28 pump 27 which provides pressure fluid to drive a zontal shaft 46, the end of which carries a contact 48 on a strap 32 depending from a pressure-sensitive cap­ hydraulic motor 28, and each includes a mechanical disposed between the motor control circuit contacts sule 33 connected at 34 to a pitot tube measuring the lock normally held out of engagement by fluid pres­ 49, 50. The resistance to movement exerted by the dynamic head of air. In two further constructions, sure, but spring-loaded to lock the motor should it torque tubes is approximately proportional to the dis­ the valves 23 are operated by a follower bearing in a fail. The pump 27 normally docs not deliver fluid, but placement of the pilot's control member, and in­ three-dimensional cam: in one, the cam is moved the delivery is controlled by a lever operated by creases approximately as the square of the airspeed. axially by the piston 15 and rotated by a rack and follow-up gears 33 in turn controlled by the output of Specification 619,984 is referred to. the motors 28 and by the selsyn receiver 29 (see also Group XXIX) to provide a correspondence control. The pumps 27 and motors 28 are of the variable stroke rotary type to provide control in two directions of rotation. The motors 28 each drive one sun-wheel 30, 130 of a differential gear 31, the planet carrier of which drives the torque shaft 32, and also the shafts 65 associated with the follow-up gears 33 through gearing 55, 56, 64. The torque shaft 32 drives, through bevel gearing and shafting, jacks 50 each comprising a worm 49 engaging a worm-wheel on a nut 75 engaging a screw 76 to move the surface 24. The surface 24 is in independent sections, each having its own jack, and the worms 49 are secured to the driving shaft 46 by frangible pins which break if the corresponding sec­ tion of the surface jams, so permitting continued operation of the rest of the surface. 'Desynn' (Regis­ tered Trade Mark) transmitters 34, 37, associated with the control member 10 and this surface 24 respec­ tively, control indicators 35, 36 in the pilot's cabin. A device 20 for simulating 'feel', such as described in Specifications 619,987 and 619,988, and a trimming 619,988. Aircraft control systems. Saunders-Roc, device 21 both operate through a differential gear 18 Ltd., Knowler, H., and Swain, A. E. Oct. 16, 1946, and chain drive 17, while the automatic pilot is con­ No. 30,808. (Class 4.) (Also in Group XXXII.) nected to the shaft 12. A further differential gear In order to simulate 'feel' in the power-operated pinion connexion to the capsule 33, in the other the associated with the shaft 32 may provide for opera­ control system of an aircraft, a force which increases piston 15 is replaced by a vane rotatable to vary the tion of the surface by a reversible electric motor if with movement of the pilot's control member 10 and volumes into which a cylinder is divided by a fixed both power units 25 fail. In an aircraft with a pressure also with airspeed is applied to the control member by axial partition and the cam rotates with the vane and is cabin 114, the torque shaft 32 passes through a seal connecting it to a piston 15 movable in a cylinder 16, moved axially by the capsule 33. Specification 619,984 45, the jacks 50 being outside the cabin and the power both ends of which receive liquid from a pump 12, is referred to. units 25 inside, but not necessarily in the pilot's the liquid exhausting through two valves 23 whose 619,390. De-icing aircraft. Lombard, A. A., and compartment. Specification 577,496 is referred to. extent of closure is governed by the two factors men­ Davies, D. O. Dec. 6, 1946, Nos. 36,119 and 38,172. tioned above. The control member 10 is connected to (Class 4.) (Also in Group XXVL) the piston 15 by a rack and pinion 13, 12 and the Ice accretion in the inlet 12 to the axial flow com­ pressure on each side of the piston 15 is governed by pressor 11 of a gas turbine plant is reduced by the cir­ the valves 23 between the delivery of the pump 18 and culation of turbine exhaust gases through a header 15 a reservoir 19. Normally, the valves 23 are open to the at the intake of the duct 12. The header is formed with a grid of aerofoil pipes 18 having gas outlet slots or perforations in their walls. The grid may be a square grid or one formed of rings connected by radial pieces. The header may be divided into segmental compart­ ments. The exhaust gases are taken in pipes 16 from the up-stream end of the exhaust or propulsion tube 14. Or, if a leak pipe 24 is provided, from the up­ stream side of the leak-control valve 25. Valves 17 in the pipes 16 may be controlled by hand or thermo­ metry devices 26 in the air inlet duct 12. Specifications 578,769 and 625,810 (Group XXVI) are referred to. May 1952 151 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 24 (5): 1 – May 1, 1952
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032162
Publisher site
See Article on Publisher Site

Abstract

same extent so that there is no force on the piston 15, but as the control member 10 is moved from its neutral position, a rack and pinion connection 30, 31 to rod 29 causes this rod to move a lever 27 engaging a slot in rod 29 about its pivot 28, so moving a member These abstracts of British Patent Specifications are taken, by permission, from the officially prepared abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, 25 Southampton Buildings, W.C.2 , sheet by sheet as issued, a t a subscription of 10s. per Group. Copies of the full specifications are obtainable at the same address, price 1s. each. 619,984. Aircraft control systems. Saunders-Roe, 619,987. Aircraft controls. Saunders-Roe, Ltd., Ltd., Knowler, H., and Robertson, F. H. Oct. 7, 1946, Knowler, H., and Knowler, P. H. Oct. 16, 1946, No. 29,844. (Class 4.) (Also in Groups XXIX and No. 30805, (Class 4.) XXXVIII.) An arrangement for simulating 'feel' with power- The pilot's control member 10 of an aircraft con­ operated control surfaces comprises a pair of levers trols two power units 25, 125 which each execute 21, 22 coupled by a pin 28 engaging slots 29, 31 movements corresponding in amount and direction to therein, the lever 21 being rotated by a wheel 14 the movement of the control member and thus, connected to the pilot's control member to move the through a differential gear 31, drive a torque shaft 32 second lever 22 against the resistance imposed by which drives the irreversible gearing 50 associated torque tubes 24, 25. The torque exerted by the tubes with the control surface, and means are provided to is controlled in accordance with airspeed by varying slotted to receive the lever 27 and on which both prevent reverse rotation of one power unit, should it the velocity ratio of the levers by adjustment of the valves 23 are mounted, to close one of the valves 23 fail, by the other. The control member 10 is con­ position of the pin 28 in the slots 29, 31. This is and to open the other. A force is thus set up on piston nected by a chain drive 11, shaft 12 and chain drives effected by a screwed shaft 32 driven by an electric 15 which corresponds to the movement of the control 13, 14 to two selsyn transmitters 16, 116 adapted to motor 40 through worm gearing 42 and a shaft 33, the member 10 and tends to return this member to its control the power units 25, 125 respectively. Each motor being controlled by the movements of a capsule neutral position. The rate at which this force increases power unit comprises a constantly rotating constant 4 mounted in a casing 44 with a connexion 45 to a with increase of movement of the member 10 is caused speed electric motor 26 driving a variable delivery pitot head, the capsule being connected to a hori­ to increase with airspeed by mounting the pivot 28 pump 27 which provides pressure fluid to drive a zontal shaft 46, the end of which carries a contact 48 on a strap 32 depending from a pressure-sensitive cap­ hydraulic motor 28, and each includes a mechanical disposed between the motor control circuit contacts sule 33 connected at 34 to a pitot tube measuring the lock normally held out of engagement by fluid pres­ 49, 50. The resistance to movement exerted by the dynamic head of air. In two further constructions, sure, but spring-loaded to lock the motor should it torque tubes is approximately proportional to the dis­ the valves 23 are operated by a follower bearing in a fail. The pump 27 normally docs not deliver fluid, but placement of the pilot's control member, and in­ three-dimensional cam: in one, the cam is moved the delivery is controlled by a lever operated by creases approximately as the square of the airspeed. axially by the piston 15 and rotated by a rack and follow-up gears 33 in turn controlled by the output of Specification 619,984 is referred to. the motors 28 and by the selsyn receiver 29 (see also Group XXIX) to provide a correspondence control. The pumps 27 and motors 28 are of the variable stroke rotary type to provide control in two directions of rotation. The motors 28 each drive one sun-wheel 30, 130 of a differential gear 31, the planet carrier of which drives the torque shaft 32, and also the shafts 65 associated with the follow-up gears 33 through gearing 55, 56, 64. The torque shaft 32 drives, through bevel gearing and shafting, jacks 50 each comprising a worm 49 engaging a worm-wheel on a nut 75 engaging a screw 76 to move the surface 24. The surface 24 is in independent sections, each having its own jack, and the worms 49 are secured to the driving shaft 46 by frangible pins which break if the corresponding sec­ tion of the surface jams, so permitting continued operation of the rest of the surface. 'Desynn' (Regis­ tered Trade Mark) transmitters 34, 37, associated with the control member 10 and this surface 24 respec­ tively, control indicators 35, 36 in the pilot's cabin. A device 20 for simulating 'feel', such as described in Specifications 619,987 and 619,988, and a trimming 619,988. Aircraft control systems. Saunders-Roc, device 21 both operate through a differential gear 18 Ltd., Knowler, H., and Swain, A. E. Oct. 16, 1946, and chain drive 17, while the automatic pilot is con­ No. 30,808. (Class 4.) (Also in Group XXXII.) nected to the shaft 12. A further differential gear In order to simulate 'feel' in the power-operated pinion connexion to the capsule 33, in the other the associated with the shaft 32 may provide for opera­ control system of an aircraft, a force which increases piston 15 is replaced by a vane rotatable to vary the tion of the surface by a reversible electric motor if with movement of the pilot's control member 10 and volumes into which a cylinder is divided by a fixed both power units 25 fail. In an aircraft with a pressure also with airspeed is applied to the control member by axial partition and the cam rotates with the vane and is cabin 114, the torque shaft 32 passes through a seal connecting it to a piston 15 movable in a cylinder 16, moved axially by the capsule 33. Specification 619,984 45, the jacks 50 being outside the cabin and the power both ends of which receive liquid from a pump 12, is referred to. units 25 inside, but not necessarily in the pilot's the liquid exhausting through two valves 23 whose 619,390. De-icing aircraft. Lombard, A. A., and compartment. Specification 577,496 is referred to. extent of closure is governed by the two factors men­ Davies, D. O. Dec. 6, 1946, Nos. 36,119 and 38,172. tioned above. The control member 10 is connected to (Class 4.) (Also in Group XXVL) the piston 15 by a rack and pinion 13, 12 and the Ice accretion in the inlet 12 to the axial flow com­ pressure on each side of the piston 15 is governed by pressor 11 of a gas turbine plant is reduced by the cir­ the valves 23 between the delivery of the pump 18 and culation of turbine exhaust gases through a header 15 a reservoir 19. Normally, the valves 23 are open to the at the intake of the duct 12. The header is formed with a grid of aerofoil pipes 18 having gas outlet slots or perforations in their walls. The grid may be a square grid or one formed of rings connected by radial pieces. The header may be divided into segmental compart­ ments. The exhaust gases are taken in pipes 16 from the up-stream end of the exhaust or propulsion tube 14. Or, if a leak pipe 24 is provided, from the up­ stream side of the leak-control valve 25. Valves 17 in the pipes 16 may be controlled by hand or thermo­ metry devices 26 in the air inlet duct 12. Specifications 578,769 and 625,810 (Group XXVI) are referred to. May 1952 151

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: May 1, 1952

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