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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. 713,426. Boundary layer control. Handley Page Ltd. 714,101. Braking systems. Dunlop Rubber Co. Ltd. Application October 31, 1950. Application February 26, 1952. In a braking system for a pilotless aircraft a sole­ An aircraft structural member such as a wing or noid valve 12 controls the admission of pressure fluid fuselage is provided with a series of suction ducts from a supply pipe 14 to the brake actuators 3, the formed in transversely disposed structural elements solenoid coil being incorporated in a circuit including and embodying porous portions through which suc­ a radio-controlled master switch 16 and a pair of tion of the boundary layer is effected. The skin con­ micro-switches 17, 18. The master switch 16 is closed sists of outer and inner sheets 2, 13 connected by as the machine approaches the ground, and the micro- transverse channel members or, as shown in no. 1, switches 17, 18 are closed, to initiate brake applica­ by corrugated sheets 12, the outer sheet 2 being locally tion, by the deflexion of the undercarriage legs under thickened at intervals for the reception of strips 1 of load, thus avoiding wheel lock. In addition, a dif­ sintered bronze, rolled gauze or perforated material. ferential relay 8 is operable by a radio-controlled The portion of the sheet 2 below each strip 1, and the auto-pilot to enable the machine to be steered when walls of the associated duct 5 are perforated, the ducts on the ground by differential braking. 714,169. Supersonic wind tunnels. Bristol Aero­ plane Co. Ltd. Application October 9, 1951. In a supersonic wind tunnel a compressor 5 delivers inoperative by the springs 24, which press abutments air to a convergent throat 7, arranged to produce a 36 on the frame 1 against the ends 14 of the guide throat velocity of Mach number equal to unity, from pulley spindles, variations in the lengths of the cables which it passes through a duct 8 of uniform cross- due to temperature changes or structural deformation section and in whose walls are evenly distributed being taken up by rotation of the whole device about longitudinal slots 9 which bleed off a steady flow of the shaft 5. If an operating tension is applied to cable air to permit progressive fall of the static pressure 35 the abutments 36 remain in contact with the pulley in the duct, the length of the slots being such that the spindles so long as the tension in the return cable 34 pressure falls to that of the ambient atmosphere at or overcomes the springs 31, but should the tension fall before the ends of the slots. The duct 8 may be of below this value the associated spindle 14 moves back circular or rectangular cross section, and in the latter to depress a lever 16 pivoted to the frame 1 and thus cause engagement of teeth 20 with teeth on a fixed sector 33. This has the effect of locking the frame 1 and thus preventing movement of the pulley 9a, which functions as a fixed guide member. Any reduction in the tension in cable 34 allows the spindle 14 to ride over an arcuate surface 23 at the end of the lever 16, the extent of the surface being sufficient to allow the cable to become completely slack. Rearward move­ ment of the plates 10 and pulley 9 is limited by the engagement of a projection 37 with a stop 38. 714,849. Controlling aircraft. Fairey Aviation being placed in communication with one or more suc­ Co. Ltd. Application July 9, 1951. tion pumps. In an alternative construction the strips To maintain control during flight at transonic 1 are replaced by sets of spanwise rows of fine, closely speeds the wings are provided with transverse bars spaced perforations in the sheet 2. These rows of D, E which can be projected to positions just clear perforations may, in a further arrangement, be formed of the boundary layer to initiate the generation of in shallow recessed grooves in the outer surface of the strong shock waves. The bars are of aerofoil section sheet 2, which is covered with a thin continuous sheet case the slots 9 may be provided in cither or both and are normally housed in recesses B1, B2 to present of porous material, such as steel or nickel alloy gauze. pairs of opposite walls. The duct is surrounded by a smooth outer surfaces, the upper one being placed In another construction, FIG. 2, the outer sheet 2a screen 15 in which the model 17 under test may be near the section of maximum wing thickness and the is formed with ridges 22 defining rectangular or housed. polygonal recesses, a continuous outer layer 2b of lower one slightly aft of this position. The bars are porous material being secured by gluing or bonding operated by hydraulic rams D2, E2, their actuation 714,174. Tensioning control cables. Societe Na- to the ridges 22. In the case of a wing the members being related to that of the adjustable tail plane to tionale de Constructions Aeronautiques du Sud-est. constituting the ducts 5 act as stringers, while in the compensate for sudden variations of pitching moment. Application October 31, 1951. On approaching transonic speed the bars are pro­ case of a fuselage they serve as frames. The porosity A device for automatically tensioning control cables jected, while at full supersonic speed they are retracted of the inserts, or the capacity of the pumps may be 34, 35 consists of a frame 1 rotatable on a horizontal simultaneously with the adjustment of the tail plane varied to modify the degree of suction over different shaft 5 under the constraint of springs 24, the shaft 5 to its supersonic setting. Upon decreasing speed, if it portions of the surface. also carrying pairs of plates 10 and 10a between which falls rapidly to subsonic the tail plane only is re­ are mounted guide pulleys 9, 9a. Springs 31 are fitted turned to the subsonic and transonic setting, but if the between the pairs of plates, their ends bearing against machine is to operate in the transonic range the bars blocks 32 secured to the plates, and against the frame are projected simultaneously with the return move­ 1, respectively. The cables are maintained taut when ment of the tail plane. December 1954 431 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 (12): 1 – Dec 1, 1954
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032507
Publisher site
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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. 713,426. Boundary layer control. Handley Page Ltd. 714,101. Braking systems. Dunlop Rubber Co. Ltd. Application October 31, 1950. Application February 26, 1952. In a braking system for a pilotless aircraft a sole­ An aircraft structural member such as a wing or noid valve 12 controls the admission of pressure fluid fuselage is provided with a series of suction ducts from a supply pipe 14 to the brake actuators 3, the formed in transversely disposed structural elements solenoid coil being incorporated in a circuit including and embodying porous portions through which suc­ a radio-controlled master switch 16 and a pair of tion of the boundary layer is effected. The skin con­ micro-switches 17, 18. The master switch 16 is closed sists of outer and inner sheets 2, 13 connected by as the machine approaches the ground, and the micro- transverse channel members or, as shown in no. 1, switches 17, 18 are closed, to initiate brake applica­ by corrugated sheets 12, the outer sheet 2 being locally tion, by the deflexion of the undercarriage legs under thickened at intervals for the reception of strips 1 of load, thus avoiding wheel lock. In addition, a dif­ sintered bronze, rolled gauze or perforated material. ferential relay 8 is operable by a radio-controlled The portion of the sheet 2 below each strip 1, and the auto-pilot to enable the machine to be steered when walls of the associated duct 5 are perforated, the ducts on the ground by differential braking. 714,169. Supersonic wind tunnels. Bristol Aero­ plane Co. Ltd. Application October 9, 1951. In a supersonic wind tunnel a compressor 5 delivers inoperative by the springs 24, which press abutments air to a convergent throat 7, arranged to produce a 36 on the frame 1 against the ends 14 of the guide throat velocity of Mach number equal to unity, from pulley spindles, variations in the lengths of the cables which it passes through a duct 8 of uniform cross- due to temperature changes or structural deformation section and in whose walls are evenly distributed being taken up by rotation of the whole device about longitudinal slots 9 which bleed off a steady flow of the shaft 5. If an operating tension is applied to cable air to permit progressive fall of the static pressure 35 the abutments 36 remain in contact with the pulley in the duct, the length of the slots being such that the spindles so long as the tension in the return cable 34 pressure falls to that of the ambient atmosphere at or overcomes the springs 31, but should the tension fall before the ends of the slots. The duct 8 may be of below this value the associated spindle 14 moves back circular or rectangular cross section, and in the latter to depress a lever 16 pivoted to the frame 1 and thus cause engagement of teeth 20 with teeth on a fixed sector 33. This has the effect of locking the frame 1 and thus preventing movement of the pulley 9a, which functions as a fixed guide member. Any reduction in the tension in cable 34 allows the spindle 14 to ride over an arcuate surface 23 at the end of the lever 16, the extent of the surface being sufficient to allow the cable to become completely slack. Rearward move­ ment of the plates 10 and pulley 9 is limited by the engagement of a projection 37 with a stop 38. 714,849. Controlling aircraft. Fairey Aviation being placed in communication with one or more suc­ Co. Ltd. Application July 9, 1951. tion pumps. In an alternative construction the strips To maintain control during flight at transonic 1 are replaced by sets of spanwise rows of fine, closely speeds the wings are provided with transverse bars spaced perforations in the sheet 2. These rows of D, E which can be projected to positions just clear perforations may, in a further arrangement, be formed of the boundary layer to initiate the generation of in shallow recessed grooves in the outer surface of the strong shock waves. The bars are of aerofoil section sheet 2, which is covered with a thin continuous sheet case the slots 9 may be provided in cither or both and are normally housed in recesses B1, B2 to present of porous material, such as steel or nickel alloy gauze. pairs of opposite walls. The duct is surrounded by a smooth outer surfaces, the upper one being placed In another construction, FIG. 2, the outer sheet 2a screen 15 in which the model 17 under test may be near the section of maximum wing thickness and the is formed with ridges 22 defining rectangular or housed. polygonal recesses, a continuous outer layer 2b of lower one slightly aft of this position. The bars are porous material being secured by gluing or bonding operated by hydraulic rams D2, E2, their actuation 714,174. Tensioning control cables. Societe Na- to the ridges 22. In the case of a wing the members being related to that of the adjustable tail plane to tionale de Constructions Aeronautiques du Sud-est. constituting the ducts 5 act as stringers, while in the compensate for sudden variations of pitching moment. Application October 31, 1951. On approaching transonic speed the bars are pro­ case of a fuselage they serve as frames. The porosity A device for automatically tensioning control cables jected, while at full supersonic speed they are retracted of the inserts, or the capacity of the pumps may be 34, 35 consists of a frame 1 rotatable on a horizontal simultaneously with the adjustment of the tail plane varied to modify the degree of suction over different shaft 5 under the constraint of springs 24, the shaft 5 to its supersonic setting. Upon decreasing speed, if it portions of the surface. also carrying pairs of plates 10 and 10a between which falls rapidly to subsonic the tail plane only is re­ are mounted guide pulleys 9, 9a. Springs 31 are fitted turned to the subsonic and transonic setting, but if the between the pairs of plates, their ends bearing against machine is to operate in the transonic range the bars blocks 32 secured to the plates, and against the frame are projected simultaneously with the return move­ 1, respectively. The cables are maintained taut when ment of the tail plane. December 1954 431

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Dec 1, 1954

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