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Month in the Patent Office

Month in the Patent Office These abstracts of British Patent Specifications are condensed, by permission, from the official specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton Buildings, W.C.2, price 2s. 8d. each. 698,017. Doors for bomb bays.'Glenn L. Martin Co. Three chordwise ribs 21, 22, 23 only are provided, Application, November 20, 1950. extending rearwardly for the support of the flap 13 A bomb bay is closed by a door 5 which, during and aileron 24. The skins 16, 17 consist of a number normal flight, occupies the position shown in FIG. 1 of light alloy sheets secured together by an adhesive with the bombs resting on the top thereof, but when such as Araldite (R.T.M.), the internal sheets being the bombs are to be released the door is rotated about perforated, for example by rectangular openings with a longitudinal rock shaft 8 by jacks 32, 39 into an rounded corners, to lighten the structure, the extent inverted position, FIG. 2, with the bombs suspended of such perforation increasing from root to tip. from the door, which still closes the bay, thus mini­ mizing turbulence and drag. The door may be fitted 699,290. Emergency escape apparatus. M.L. Avia­ with temporary castors and used as a loading trolley, tion Co. Ltd. Application, December 11, 1950. the door with the load of bombs being wheeled below An emergency escape apparatus consists of a the bay, hoisted into position and secured by the en­ detachable cabin 1 forming the nose portion of the gagement of trunnions in the transverse bay bulk­ fuselage, from which it is forcefully separated by a heads with the end of the shaft 8. Bombs may also be gun 5, which also extends a number of retractable fins suspended from the lower surface of the door, these 17 which serve to stabilize the cabin during its free fall being released before the door is inverted. before the parachute becomes effective. When the gun 5 is fired a primary piston 25 operates racks 6, sectors 7 and links 8, 9, 10 to cause the fins 17, which are normally snugly located on the surface of the cabin 1, as shown in FIG. 5, to open out as shown in riG. 6. Near the end of the travel of the racks, stops 11 engage rocking levers 12 which, through links 13, 14, operate cabin longeron releases 15 and, through links 13, 16, actuate separators 18 for disconnecting the electrical circuits. Each longeron release, riG. 7, includes an element 46 screwed into the fuselage 699,989. Freight-carrying aircraft. Blackburn and structure and furnished with a mushroom head 48 General Aircraft Ltd. Application, October 3, 1953. To facilitate loading and unloading of a freight- carrying aircraft having cargo space in the lower part of the fuselage 1 closed off by doors which fully expose one end thereof when opened, the bottom 8 is made detachable from the remainder of the fuselage, so that the floor may be removed for quick removal of its cargo and replaced by another floor which is already loaded. In operation a transporter vehicle 33 is wheeled into position below the fuselage in align­ ment with the floor portion 8, so that when the upper deck 34 of the vehicle is raised by jacks 35 a longi­ tudinal projection 36 of the floor 8 is engaged by a correspondingly shaped recess in the upper surface of the deck 34. The floor 8 is then detached from the fuselage 1, which is raised automatically by the ex­ tension of the undercarriage legs consequent upon the release of the load, thus enabling the vehicle to be removed. A second loaded floor is then moved into 699,070. Wing structures. Sir W. G. Armstrong position by another vehicle, and raised by the jacks engaged by jaws 52 in a yoke 50 attached to the Whitworth Aircraft Ltd. Application, November 14, 34, correct registering being ensured by the engage­ cabin, the jaws being opened to disengage the head 48 1949. ment of ribs 13 on the floor portion 8 with grooves 14 by toggle links 53 operated by rotation of a plate 60 in the lower edges of the fuselage side walls. If desired To enable the interior space of a thin-section wing consequent upon movement of the link 14. When the the floor 8 may be subdivided into two or more sec­ to remain relatively unencumbered, and thus serve for piston 25 reaches the end of its stroke a port 37 is tions removable and replaceable one after another. the housing of fuel tanks, the wing consists of a uncovered to admit pressure gas to a secondary leading edge portion 11, a trailing section 12 of cylinder provided with a telescopic piston rod, ex­ triangular plan form, and a main intermediate span- tension of which by the gases ensures separation of wise portion 14 comprising upper and lower skins the cabin 1 from the fuselage. Drogue and stabilizing 16,17 which are interconnected by leading and trailing parachutes are then deployed automatically. spanwisc webs 18, 19 with one intermediate web 20. February 1954 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 26 (2): 1 – Feb 1, 1954
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032397
Publisher site
See Article on Publisher Site

Abstract

These abstracts of British Patent Specifications are condensed, by permission, from the official specifications. Copies of the full specifications are obtainable from the Patent Office, 25 Southampton Buildings, W.C.2, price 2s. 8d. each. 698,017. Doors for bomb bays.'Glenn L. Martin Co. Three chordwise ribs 21, 22, 23 only are provided, Application, November 20, 1950. extending rearwardly for the support of the flap 13 A bomb bay is closed by a door 5 which, during and aileron 24. The skins 16, 17 consist of a number normal flight, occupies the position shown in FIG. 1 of light alloy sheets secured together by an adhesive with the bombs resting on the top thereof, but when such as Araldite (R.T.M.), the internal sheets being the bombs are to be released the door is rotated about perforated, for example by rectangular openings with a longitudinal rock shaft 8 by jacks 32, 39 into an rounded corners, to lighten the structure, the extent inverted position, FIG. 2, with the bombs suspended of such perforation increasing from root to tip. from the door, which still closes the bay, thus mini­ mizing turbulence and drag. The door may be fitted 699,290. Emergency escape apparatus. M.L. Avia­ with temporary castors and used as a loading trolley, tion Co. Ltd. Application, December 11, 1950. the door with the load of bombs being wheeled below An emergency escape apparatus consists of a the bay, hoisted into position and secured by the en­ detachable cabin 1 forming the nose portion of the gagement of trunnions in the transverse bay bulk­ fuselage, from which it is forcefully separated by a heads with the end of the shaft 8. Bombs may also be gun 5, which also extends a number of retractable fins suspended from the lower surface of the door, these 17 which serve to stabilize the cabin during its free fall being released before the door is inverted. before the parachute becomes effective. When the gun 5 is fired a primary piston 25 operates racks 6, sectors 7 and links 8, 9, 10 to cause the fins 17, which are normally snugly located on the surface of the cabin 1, as shown in FIG. 5, to open out as shown in riG. 6. Near the end of the travel of the racks, stops 11 engage rocking levers 12 which, through links 13, 14, operate cabin longeron releases 15 and, through links 13, 16, actuate separators 18 for disconnecting the electrical circuits. Each longeron release, riG. 7, includes an element 46 screwed into the fuselage 699,989. Freight-carrying aircraft. Blackburn and structure and furnished with a mushroom head 48 General Aircraft Ltd. Application, October 3, 1953. To facilitate loading and unloading of a freight- carrying aircraft having cargo space in the lower part of the fuselage 1 closed off by doors which fully expose one end thereof when opened, the bottom 8 is made detachable from the remainder of the fuselage, so that the floor may be removed for quick removal of its cargo and replaced by another floor which is already loaded. In operation a transporter vehicle 33 is wheeled into position below the fuselage in align­ ment with the floor portion 8, so that when the upper deck 34 of the vehicle is raised by jacks 35 a longi­ tudinal projection 36 of the floor 8 is engaged by a correspondingly shaped recess in the upper surface of the deck 34. The floor 8 is then detached from the fuselage 1, which is raised automatically by the ex­ tension of the undercarriage legs consequent upon the release of the load, thus enabling the vehicle to be removed. A second loaded floor is then moved into 699,070. Wing structures. Sir W. G. Armstrong position by another vehicle, and raised by the jacks engaged by jaws 52 in a yoke 50 attached to the Whitworth Aircraft Ltd. Application, November 14, 34, correct registering being ensured by the engage­ cabin, the jaws being opened to disengage the head 48 1949. ment of ribs 13 on the floor portion 8 with grooves 14 by toggle links 53 operated by rotation of a plate 60 in the lower edges of the fuselage side walls. If desired To enable the interior space of a thin-section wing consequent upon movement of the link 14. When the the floor 8 may be subdivided into two or more sec­ to remain relatively unencumbered, and thus serve for piston 25 reaches the end of its stroke a port 37 is tions removable and replaceable one after another. the housing of fuel tanks, the wing consists of a uncovered to admit pressure gas to a secondary leading edge portion 11, a trailing section 12 of cylinder provided with a telescopic piston rod, ex­ triangular plan form, and a main intermediate span- tension of which by the gases ensures separation of wise portion 14 comprising upper and lower skins the cabin 1 from the fuselage. Drogue and stabilizing 16,17 which are interconnected by leading and trailing parachutes are then deployed automatically. spanwisc webs 18, 19 with one intermediate web 20. February 1954

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Feb 1, 1954

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