Access the full text.
Sign up today, get DeepDyve free for 14 days.
References for this paper are not available at this time. We will be adding them shortly, thank you for your patience.
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. 711,711. Structures with plastic foam cores. B. shown, the axle is mounted at the lower end of a Jablonski. Application January 10, 1950. forwardly-raked undercarriage leg, the wheels being in a trailing position, and the leg is rotated by a power Components such as propeller or helicopter rotor system for steering. blades, wings, or structural members consist of an outer shell of thin metal, plastic or plywood, with an internal supporting filling of low density (about 711,929. Deflecting jets. M. Kadosch and L. de 4 lb./cu. ft.) and having a closed cellular structure J, de la Salle. Application in France, March 27, 1952. formed by expanding a thermoplastic material such A propulsive jet, which has been partially ionized, as polyrinyl chloride, incorporating a hardening is deflected for control purposes by an electrostatic agent such as phenol formaldehyde or urea resin or field acting transversely to the jet stream. In the ar a paint-hardening material. The manufacturing pro rangement shown (FIG. 3) a thorium-coated grid 17 and 50a fast with the fuselage, movement being effected cess is carried out in two stages, the mix for the inter a positively charged electrode 14 are mounted upstream by a substantially tangential link 66a operated by a nal filling being first placed in a mould similar in of the nozzle throat to provide a stream of positive nut 64a traversing a screwed rod 62. A single rod 62 shape to, but smaller than, the outer shell, and then ions, deflexion of which is effected by an electric may operate both wings or, as shown in FIGS. 4 and 5, heated sufficiently to cause the mix to fill the mould, field established between electrodes 11, 12 on each link may be operated by a separate rod driven from which it is then removed and allowed to cool opposite sides of the nozzle. The strength of the by a hydraulic motor 88 supplied by a pump 158, the to a solid-like mass having a similar shape to the outer field, and hence the degree of deflexion, is con rods being provided with integral pinions 152 mesh shell. The cooled mass is then inserted in the shell and trolled by a rheostat 9. Reversal of the jet for ing with a common intermediate gear wheel 154 to heating continued until the gases liberated expand the braking purposes may be obtained by increasing the ensure equal rotational speeds. The direction of rota mass to fill the shell and apply internal pressure there strength of the electric field to such an extent that the tion is governed by a control valve 162. Provision is to, to impart the desired rigidity to the member. made for preventing overloading of the motors 88 due to binding of the tracks 36a and guides 50a 711,832. Steering undercarriages. Electro-Hydrau under aerodynamic wing loads, for which purpose lics Ltd. Application February 11, 1949. hydraulic piston and cylinder units 76, 82 are fitted, An undercarriage is provided with twin landing the pistons being engaged by the ends 74 of double wheels 4, 5 which, in the arrangement shown in cantilevers 72 whose other ends extend to the regions FIG. 1, are mounted on a rotatable axle 16 and ar of the wing pivots X. Normally each of the pistons is ranged so that they normally rotate together, each at the bottom of its stroke, but in the event of positive wheel being fitted with a friction coupling consisting lift causing binding the pressure in the supply pipe of a disk 17 carried by the axle and pressed into en 164 rises to open a non-return valve 166 or 178 gagement with friction pads 18 by spring plungers (according to the direction of sweep movement) and 20 on the wheel rim, steering being effected by dif restrictor valves 168 to admit pressure liquid under the ferential operation of brakes 9, the application of pistons 76 to relieve the binding. With the load on the either one of which over-rides the associated coupling. motors 88 thus reduced the back pressure drops to In a second arrangement, FIG. 2, the twin wheels 4, 5 cut off the supply to the cylinders 82 and the motors are carried by an axle pivoted to the lower end of the proceed with the sweep movement. Should binding leg 1 by a longitudinal pivot, steering in this case being occur due to negative lift the mechanism must be effected by tilting the axle, e.g. by means of a double- stream is diverted into appropriately shaped channels prevented from operating in the above manner, and acting jack 24, to reduce the effective diameter of the 18 formed by curved vanes. A radial field may be pro under such conditions downward wing movement duced by mounting the anode on the axis of the nozzle, inner wheel. According to a third embodiment, not operates cut-off valves 92 to open by-passes 176 thus producing a flaring of the jet, control effects being whereby liquid passing through valves 168 is led to obtained by differential variation of the strength of the return pipe 174 instead of to the cylinders 82. the field on opposite sides of the axis. 712,682. Ram-jet propulsion. Sir W. G. Armstrong 712,023. Variable-sweep wings. Sir W. G. Arm Whitworth Aircraft Ltd. Application June 29, 1951. strong Whitworth Aircraft Ltd. Application Decem A propulsion plant consists of a pair of turbo-jet ber 7, 1951. units 14 in each wing (FIG. 6), together with an inboard The sweep of each wing 22 is varied by rotation ram-jet 13 intended to be brought into operation at about a vertical pivot X, the wing carrying an arcuate supersonic speeds, the wingportion accommodating the track 36a engaging correspondingly shaped guides ram-jet having leading and trailing edge portions 27, 28 and 34, 35 respectively, which, when the ram jet is inoperative, are closed to maintain an aerofoil section throughout the full chord, as shown in FIG. 7. The leading edge wing portions 27, 28 are hinged to the intermediate section along axes 29 and are opened and closed by a jack 31 supported on struts 32 from the front spar; the trailing edge members 34, 35 are operated by similar mechanism, not shown. Elliptical flow passages are formed in the front and rear spars 30, 42 respectively. November 1954 399
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Nov 1, 1954
Access the full text.
Sign up today, get DeepDyve free for 14 days.