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Month in the Patent Office

Month in the Patent Office 728,612. Ailerons. English Electric Co. Ltd. Application, October 3, 1952. The ailerons 21 for an aircraft with strongly swept- back wings are mounted with their hinge lines 31 substantially perpendicular to the longitudinal axis These abstracts of British Patent Specifications are condensed, by permission, from the official of the machine, this arrangement resulting in a reduc­ tion in their size as compared with one in which they specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton are disposed along the tips of the trailing edges 1, Buildings, W.C.2, price 3s. each. 727,159. Transport aircraft. Blackburn & General upon the aircraft becoming fully ground borne the Aircraft Ltd. Application May 21, 1952. skid is lowered by a jack 32 into contact with the ground and the degree of braking controlled by vary­ In a passenger-freight aircraft with an upper pas­ ing the pressure of the medium operating the jack. The senger compartment 8 and a lower freight compart­ skid 31 is carried by a lever arm 28 pivoted on a stub ment 6, access between the two compartments is ob­ arm 26 projecting from the lower end of the leg 21, the tained by an internal stairway constructed partly in arm 28 being connected to the lower end of the jack 32 one and partly in the other of two clam-shell type by an eyebolt 44. The connexion between the skid 31 doors 71,72 closing the rear of the lower compartment and arm 28 is resilient, including a transverse pin 42 6. In the arrangement shown the door 71 carries a and rubber pads 53 to allow the skid to maintain con­ landing 10 and steps 11, together with hand rails tact with the ground irrespective of surface irregulari­ 29,30, while the door 72 carries a second landing 16 ties or changes in attitude of the aircraft. Preferably co-operating with the steps 11, and steps 17 giving ac­ the jack 32 is operated by compressed air to ensure cess to an opening 18 in the floor of the upper com­ resilient contact between the skid 31 and the ground, partment 8. When passengers are carried in the lower but if liquid is used an auxiliary resilient device is in­ compartment additional steps may be fitted between corporated in the jack. In the case of a tandem- the landing 10 and the compartment floor level, and if wheel undercarriage, FIG. 4, with forward and rear they are carried with scats disposed in two tiers an pairs of wheels 105,108 the skid 113 is mounted cen­ additional stairway unit may be mounted on the trally between the wheels and is pivoted at 117 to the since their rolling power is of the same order of magni­ door1. rear end of a drag link 116, whose forward end is tude as that with wings of small sweep back while pivoted at 115 to a downward extension 114 of the leg the transonic airflow characteristics of the highly 102. The skid-operating jack 118 is mounted between swept wings are not impaired. In an arrangement in the pivot 118 and a further pivot 119 on the wheel- which the leading and trailing edges 4, 1 are swept carrying lever 106. In a further arrangement, not back at angles of about 60 deg. and 50 deg. respec­ shown, the skid is mounted on the fuselage entirely tively, each aileron has a constant chord of about independent of the undercarriage. Light-weight park­ one-eighth of the wing chord at the mid-aileron ing brakes may be fitted to each landing wheel. station, the ratio of aileron span to total wing span being between one-fifth and one-quarter, while the area of each aileron is about one-quarter that of the wing ahead of the aileron. 730,069. Vertical take-off. von Zborowski. Appli­ cation in France, February 19, 1952. An aircraft capable of taking off and alighting vertically comprises a single annular wing 1 pro­ viding a tunnel space within which the whole of the propulsion plant, such as a gas-turbine 11, 12 driving contra-rotating propellers 10, 10a is disposed. The cockpit 14 is mounted forward of the propulsion 728,515. Landing flaps. S.N.C.A.N. Application in plant, while a tail unit 4 connected to the wing 1 by France April 8, 1952. struts 6 forms a stand for supporting the aircraft in a vertical position for take-off, and also after it has A landing flap 5a carries an auxiliary flap 6a on alighted. Retractable plates 5 can be opened out to arms 9 so arranged that in the neutral position of the provide additional ground support, while the wing main flap the auxiliary flap bears against the upper portion 1 may be fitted with retractable floats to pro­ surface of the wing 2. When the main flap is lowered vide stability for use on water. Directional control is the aerodynamic force on the flap 6a assists such furnished by diametrically disposed pairs of flaps 24 movement and augments the drag, while at the same time a slot is formed below the auxiliary flap to im­ prove the airflow and thus increase the lift. In a modi­ fied construction the auxiliary flap 6a and the arms 9 are housed in recesses in the surface of the wing 2 so that they do not project when the flap 5a is in the neutral position. at the rear of the wing 1, and spoilers 27 mounted on the radial arms 15 connecting the cockpit 14 and pro­ pulsion plant housing 13 to the wing 1 provide rolling control. The exhaust from the turbine 11 is discharged through the blades of the front propeller 10, and fuel discharged through openings 22 in the blades of the rear propeller 10a is ignited by igniters 23 so that a 728,176. Braking systems. G. H. Dowty. Applica­ ram jet is formed to the rear of the propellers, the jet tion January 30, 1953. thrust being controlled by openings 28 and flaps 29 Each undercarriage of an aircraft is fitted with a disposed around the wing 1. If a turbo-jet engine is braking skid 31 mounted at the lower end of the fitted the effect of the surfaces 24 may be augmented undercarriage leg 21 and normally held retracted, but by similar flaps arranged to deflect the jet. October 1955 355 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 27 (10): 1 – Oct 1, 1955
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032618
Publisher site
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Abstract

728,612. Ailerons. English Electric Co. Ltd. Application, October 3, 1952. The ailerons 21 for an aircraft with strongly swept- back wings are mounted with their hinge lines 31 substantially perpendicular to the longitudinal axis These abstracts of British Patent Specifications are condensed, by permission, from the official of the machine, this arrangement resulting in a reduc­ tion in their size as compared with one in which they specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton are disposed along the tips of the trailing edges 1, Buildings, W.C.2, price 3s. each. 727,159. Transport aircraft. Blackburn & General upon the aircraft becoming fully ground borne the Aircraft Ltd. Application May 21, 1952. skid is lowered by a jack 32 into contact with the ground and the degree of braking controlled by vary­ In a passenger-freight aircraft with an upper pas­ ing the pressure of the medium operating the jack. The senger compartment 8 and a lower freight compart­ skid 31 is carried by a lever arm 28 pivoted on a stub ment 6, access between the two compartments is ob­ arm 26 projecting from the lower end of the leg 21, the tained by an internal stairway constructed partly in arm 28 being connected to the lower end of the jack 32 one and partly in the other of two clam-shell type by an eyebolt 44. The connexion between the skid 31 doors 71,72 closing the rear of the lower compartment and arm 28 is resilient, including a transverse pin 42 6. In the arrangement shown the door 71 carries a and rubber pads 53 to allow the skid to maintain con­ landing 10 and steps 11, together with hand rails tact with the ground irrespective of surface irregulari­ 29,30, while the door 72 carries a second landing 16 ties or changes in attitude of the aircraft. Preferably co-operating with the steps 11, and steps 17 giving ac­ the jack 32 is operated by compressed air to ensure cess to an opening 18 in the floor of the upper com­ resilient contact between the skid 31 and the ground, partment 8. When passengers are carried in the lower but if liquid is used an auxiliary resilient device is in­ compartment additional steps may be fitted between corporated in the jack. In the case of a tandem- the landing 10 and the compartment floor level, and if wheel undercarriage, FIG. 4, with forward and rear they are carried with scats disposed in two tiers an pairs of wheels 105,108 the skid 113 is mounted cen­ additional stairway unit may be mounted on the trally between the wheels and is pivoted at 117 to the since their rolling power is of the same order of magni­ door1. rear end of a drag link 116, whose forward end is tude as that with wings of small sweep back while pivoted at 115 to a downward extension 114 of the leg the transonic airflow characteristics of the highly 102. The skid-operating jack 118 is mounted between swept wings are not impaired. In an arrangement in the pivot 118 and a further pivot 119 on the wheel- which the leading and trailing edges 4, 1 are swept carrying lever 106. In a further arrangement, not back at angles of about 60 deg. and 50 deg. respec­ shown, the skid is mounted on the fuselage entirely tively, each aileron has a constant chord of about independent of the undercarriage. Light-weight park­ one-eighth of the wing chord at the mid-aileron ing brakes may be fitted to each landing wheel. station, the ratio of aileron span to total wing span being between one-fifth and one-quarter, while the area of each aileron is about one-quarter that of the wing ahead of the aileron. 730,069. Vertical take-off. von Zborowski. Appli­ cation in France, February 19, 1952. An aircraft capable of taking off and alighting vertically comprises a single annular wing 1 pro­ viding a tunnel space within which the whole of the propulsion plant, such as a gas-turbine 11, 12 driving contra-rotating propellers 10, 10a is disposed. The cockpit 14 is mounted forward of the propulsion 728,515. Landing flaps. S.N.C.A.N. Application in plant, while a tail unit 4 connected to the wing 1 by France April 8, 1952. struts 6 forms a stand for supporting the aircraft in a vertical position for take-off, and also after it has A landing flap 5a carries an auxiliary flap 6a on alighted. Retractable plates 5 can be opened out to arms 9 so arranged that in the neutral position of the provide additional ground support, while the wing main flap the auxiliary flap bears against the upper portion 1 may be fitted with retractable floats to pro­ surface of the wing 2. When the main flap is lowered vide stability for use on water. Directional control is the aerodynamic force on the flap 6a assists such furnished by diametrically disposed pairs of flaps 24 movement and augments the drag, while at the same time a slot is formed below the auxiliary flap to im­ prove the airflow and thus increase the lift. In a modi­ fied construction the auxiliary flap 6a and the arms 9 are housed in recesses in the surface of the wing 2 so that they do not project when the flap 5a is in the neutral position. at the rear of the wing 1, and spoilers 27 mounted on the radial arms 15 connecting the cockpit 14 and pro­ pulsion plant housing 13 to the wing 1 provide rolling control. The exhaust from the turbine 11 is discharged through the blades of the front propeller 10, and fuel discharged through openings 22 in the blades of the rear propeller 10a is ignited by igniters 23 so that a 728,176. Braking systems. G. H. Dowty. Applica­ ram jet is formed to the rear of the propellers, the jet tion January 30, 1953. thrust being controlled by openings 28 and flaps 29 Each undercarriage of an aircraft is fitted with a disposed around the wing 1. If a turbo-jet engine is braking skid 31 mounted at the lower end of the fitted the effect of the surfaces 24 may be augmented undercarriage leg 21 and normally held retracted, but by similar flaps arranged to deflect the jet. October 1955 355

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Oct 1, 1955

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