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Month in the Patent Office

Month in the Patent Office 690,186. Aircraft flight refuelling or towing systems. Flight Refuelling Ltd. Application August 29, 1950. In a flight refuelling or towing system in which the leading and following aircraft respectively carry the inter-engaging elements of a self-engaging plug and These abstracts of British Patent Specifications are condensed, by permission, from the official socket coupling, of which the socket has a series of specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton spring-loaded latches and the plug is in the form of a nozzle or spigot with a circumferential groove engage- Buildings, W.C.2, price 2s. 8d. each. able by the latches, one of the coupling elements is carried by a forwardly or rcarwardly extending uni­ versally-mounted boom held substantially in the line of flight by centring springs and terminating in the 689,218. Controlling aircraft. Navico (Navigation- collapsible telescopic tie 18 is mounted between the nozzle or spigot. In the refuelling system shown the Commerce-Industrie). Application Jan. 31, 1951. front of the bogie and top of the leg 11 so that down­ socket S is mounted at the tail of the leading machine ward movement of the front wheels is limited. When An aircraft fitted with fixed wings 14 and a con­ A and is connected to a fuel pipe U by a ball-and- the aircraft is airborne and the leg 11 and tie 18 are ventional empennage 12, which would be inclTective socket joint 13 and to a guide funnel 15, the gap both fully extended the bogie is held in a trailing atti­ with the machine hovering or moving forward at very between the latter and the fuselage being sealed by a low speed, is rendered stable under such conditions tude with the rear wheels lower than the front ones, flexible membrane 16. The nozzle 7 is at the end of by fitting slotted flaps 15,16 to the wings 14 to deflect and upon landing the tic 18 prevents rotation of the a plug P forming the forward portion of a telescopic downwardly in the direction of the arrows 18, 18' the bogie about the leg 11 and the downward velocity of boom or probe 8 projecting from the nose of the fol­ slipstreams from symmetrically disposed propellers 17 the front wheels is thus equal to that of the machine. lowing machine JS and connected to a fuel pipe 11 by a capable of tilting in the pitching plane about axes 21 ball joint 10, centering being effected by tension springs and located sufficiently forward of the centre of or rubber cords 12. The probe is extended by a spring gravity 20 to ensure stability, i.e. by more than 80 per 9 which also absorbs the shock of engagement of the cent of the mean wing chord. In the extreme adjusted coupling elements. The arrangement may be reversed, positions the propeller thrust lines 23,24 lie above and the member 8 forming a boom trailing from the lead­ below the centre of gravity respectively. Fio. 2 shows ing machine, the funnel 15 and sockets being mounted the disposition of the controls for an aircraft incor­ at the nose of the following machine. porating two pairs of propellers 50, 506 and 62, 626 691,571. Driving aircraft auxiliaries. Joseph Szydlowski (Turbomcca). Application March 30, Auxiliaries 8a, 9a, 10a such as flight or measuring instruments are driven from a turbine I la through re­ duction gearing 6a, la, the turbine being fed with combustion gases from jet engines 18, 19, 20, 21 through pipes 14,15, 16,17. The turbine feed chamber In is fitted with a manually or automatically operated control valve 2ri, while each of the feed pipes 14—17 is provided with a control valve 22 and non-return valve 23, the latter closing in the event of failure of the associated engine. As shown the turbine is being fed from engines 19, 20, and in the event of failure of one of these either of the other engines 18, 21 may be made to supply the turbine. which are operable conjointly with the normal control surfaces to produce moments augmenting those of the surfaces. Movement of the control column 42 to operate the elevators 45 also effects similar tilting of the inboard propellers 50, 50/) in the pitching plane through links 46, 48, 67, 67/;, while operation of the wheel 43 controlling the ailerons 56,566 causes a cable loop 58 to rotate a nut 59 to effect differential adjust­ ment of the blade pitches of the outboard propellers 62, 626. Movement of the rudder pedals 44, 446 re­ sults in rotation of a nut 51 by a cable 53 to cause tilt­ ing of the inboard propellers 50, 506 in opposite direc­ tions. Collective blade pitch adjustment of all four propellers is effected by a hydraulic jack 63. The in­ board propellers may be capable of bodily tilting movement, or the blades may be cyclically adjusted in pitch by a swash plate to produce virtual tilting. 690,111. Undercarriages. Dowty Equipment Ltd. Application April 20, 1950. The main shock-absorbing leg 11, 12 of a bogie- type undercarriage is pivoted to the bogie 15 midway between the front and rear wheels 16,17, and a freely- November 1953 357 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 25 (11): 1 – Nov 1, 1953

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032360
Publisher site
See Article on Publisher Site

Abstract

690,186. Aircraft flight refuelling or towing systems. Flight Refuelling Ltd. Application August 29, 1950. In a flight refuelling or towing system in which the leading and following aircraft respectively carry the inter-engaging elements of a self-engaging plug and These abstracts of British Patent Specifications are condensed, by permission, from the official socket coupling, of which the socket has a series of specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton spring-loaded latches and the plug is in the form of a nozzle or spigot with a circumferential groove engage- Buildings, W.C.2, price 2s. 8d. each. able by the latches, one of the coupling elements is carried by a forwardly or rcarwardly extending uni­ versally-mounted boom held substantially in the line of flight by centring springs and terminating in the 689,218. Controlling aircraft. Navico (Navigation- collapsible telescopic tie 18 is mounted between the nozzle or spigot. In the refuelling system shown the Commerce-Industrie). Application Jan. 31, 1951. front of the bogie and top of the leg 11 so that down­ socket S is mounted at the tail of the leading machine ward movement of the front wheels is limited. When An aircraft fitted with fixed wings 14 and a con­ A and is connected to a fuel pipe U by a ball-and- the aircraft is airborne and the leg 11 and tie 18 are ventional empennage 12, which would be inclTective socket joint 13 and to a guide funnel 15, the gap both fully extended the bogie is held in a trailing atti­ with the machine hovering or moving forward at very between the latter and the fuselage being sealed by a low speed, is rendered stable under such conditions tude with the rear wheels lower than the front ones, flexible membrane 16. The nozzle 7 is at the end of by fitting slotted flaps 15,16 to the wings 14 to deflect and upon landing the tic 18 prevents rotation of the a plug P forming the forward portion of a telescopic downwardly in the direction of the arrows 18, 18' the bogie about the leg 11 and the downward velocity of boom or probe 8 projecting from the nose of the fol­ slipstreams from symmetrically disposed propellers 17 the front wheels is thus equal to that of the machine. lowing machine JS and connected to a fuel pipe 11 by a capable of tilting in the pitching plane about axes 21 ball joint 10, centering being effected by tension springs and located sufficiently forward of the centre of or rubber cords 12. The probe is extended by a spring gravity 20 to ensure stability, i.e. by more than 80 per 9 which also absorbs the shock of engagement of the cent of the mean wing chord. In the extreme adjusted coupling elements. The arrangement may be reversed, positions the propeller thrust lines 23,24 lie above and the member 8 forming a boom trailing from the lead­ below the centre of gravity respectively. Fio. 2 shows ing machine, the funnel 15 and sockets being mounted the disposition of the controls for an aircraft incor­ at the nose of the following machine. porating two pairs of propellers 50, 506 and 62, 626 691,571. Driving aircraft auxiliaries. Joseph Szydlowski (Turbomcca). Application March 30, Auxiliaries 8a, 9a, 10a such as flight or measuring instruments are driven from a turbine I la through re­ duction gearing 6a, la, the turbine being fed with combustion gases from jet engines 18, 19, 20, 21 through pipes 14,15, 16,17. The turbine feed chamber In is fitted with a manually or automatically operated control valve 2ri, while each of the feed pipes 14—17 is provided with a control valve 22 and non-return valve 23, the latter closing in the event of failure of the associated engine. As shown the turbine is being fed from engines 19, 20, and in the event of failure of one of these either of the other engines 18, 21 may be made to supply the turbine. which are operable conjointly with the normal control surfaces to produce moments augmenting those of the surfaces. Movement of the control column 42 to operate the elevators 45 also effects similar tilting of the inboard propellers 50, 50/) in the pitching plane through links 46, 48, 67, 67/;, while operation of the wheel 43 controlling the ailerons 56,566 causes a cable loop 58 to rotate a nut 59 to effect differential adjust­ ment of the blade pitches of the outboard propellers 62, 626. Movement of the rudder pedals 44, 446 re­ sults in rotation of a nut 51 by a cable 53 to cause tilt­ ing of the inboard propellers 50, 506 in opposite direc­ tions. Collective blade pitch adjustment of all four propellers is effected by a hydraulic jack 63. The in­ board propellers may be capable of bodily tilting movement, or the blades may be cyclically adjusted in pitch by a swash plate to produce virtual tilting. 690,111. Undercarriages. Dowty Equipment Ltd. Application April 20, 1950. The main shock-absorbing leg 11, 12 of a bogie- type undercarriage is pivoted to the bogie 15 midway between the front and rear wheels 16,17, and a freely- November 1953 357

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Nov 1, 1953

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