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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. 688,378. Launching Ramps. Fairey Aviation Co. Ltd. Application June 30, 1949. A ramp 15 for launching aircraft or guided missiles is provided near the middle with a lever 18 normally held by toggle links 20 in the path of an abutment 21 691,948. Deflecting fluid jets. Societc Nationale on the flying body, and which is only releasable there­ d'Etude ct de Construction dc Moteurs. d'Aviation. from upon a predetermined propulsive thrust being Application February 27, 1951. developed. The thrust of the main power unit of the In a modification of the arrangement according to flying body causes the abutment 21 to engage the hook FIG. 3 of Specification 691,302 the transverse fluid 18, and separates abutments 22, 23 on the ramp and stream discharged from the slot 7 for effecting de­ flying body, respectively, to operate an electric s witch flexion of the jet is an auxiliary jet supplied from a 24 effecting ignition of booster rockets 30, 31. The source independent of the main jet. As shown in latter then move forward against compression springs n c 7 the auxiliary jet may consist of an annular com­ to close further electric contacts on abutments 35, pressed air jet 8 issuing from an inner axially-disposed and when all the contacts are closed a relay operates casing to produce an outward deflexion of the main the toggle links 20 to withdraw the hook 18 from the jet, or it may issue from an external casing surround­ abutment 21 and thus free the flying body. Alternative ing the nozzle, to produce an inward deflexion of the methods of releasing the hook 18 include the use of jet. the internal pressure developed in a hydraulic dashpot or ram and cylinder opposing the propulsive thrust, 693,681. Jet propulsion plant. Rolls-Royce Ltd. or the pressure, temperature or velocity of the gases in Application April 4, 1949. the combustion chamber or jet pipe of the main The exhaust pipe 15 from a gas turbine 16 is divided motor, while the booster rocket switches may be into two branches 10, 11, disposed in the vertical plane closed by the deflexion of vanes located in the respec­ and terminating in nozzles 13, 14 capable of pivoting tive jet streams. in the vertical and horizontal planes, respectively, about trunnions 36, and operable in conjunction with 691,302. Deflecting fluid jets. Socictc Nationale the control surfaces such as the elevators and rudder. d'Etude et de Construction dc Moteurs d'Aviation. Expansion joints 19 are provided in each of the Application August 8, 1949. branches, which are connected to the aircraft structure An arrangement for deflecting a fluid jet issuing 12 through swinging linkages, each consisting of a from a nozzle 1 along a tangential convex extension 3 yoke 23 pivoting about trunnions 22 perpendicular to of the nozzle wall, particularly adapted for use with the associated trunnions 36 and a link 26 connected pulse jets or thrust spoilers, consists of a deflector 2 to the yoke 23 and structure 12 by brackets 25, 28 per­ located in the region of the transverse plane passing mitting pivoting about axes parallel and perpendicular through the junction of the extension 3 with the nozzle to the trunnions 22 respectively. The tail pipes 13, 14 wall and in such a position that the greater part of the are connected to the branches 10, II by gas-tight nozzle section is not obstructed. The effect may be ball joints 32a mounted within sleeves 34 bolted to the augmented by applying boundary layer suction to the bulkhead 35, and are operated by linkages 45 mounted wall extension 3. FIG. 3 shows an arrangement in on the structure 12. In the case of a normally fixed but which the deflexion is effected by a transverse jet of the adjustable control surface, such as a stabilizing fin or fluid supplied from a point upstream of the throat the chamber 10 or to the nozzle 12. In the case of a tail-plane, the tail pipe may be wholly or partly sur­ through a by-pass 5 and discharged through a slot 6 thrust spoiler, FIG. 5, the jet is deflected through curved rounded by a fairing forming a structural unit coupled in the nozzle wall. As applied to a pulse jet, FIG 4, the slots 26, 27 in the nozzle wall by vanes 30, 31 which, to the control surface. deflector 2 causes the gases issuing rearwardly from when inoperative, form in conjunction with their sup­ the combustion chamber 10 to be reversed through a ports 28, 29 streamlined bodies which do not affect the pipe 13 and thereby augment the thrust of the main jet flow. Alternatively, the vanes may be mounted In jet from the nozzle 12, the pipe 13 discharging directly opposite sides of a member disposed on the nozzle into the atmosphere or being connected to the rear of axis. 694,150. Wind-tunnel testing of athodyds. Rene of the grid are obtained by trial and error in such a Lcduc. Application August 15, 1951. way that the values of the factor A are equal in the ex­ The testing arrangement described in Specification pressions A = V32p3/V02o0, obtained from the total 664,055 (see issue of September, 1953) is modified by pressures p0 and p measured by pitot traverses, and the addition of a grid 3 attached to the nose of the Crt=2(AW — W0)/S, obtained by tunnel balance central core member 2 and arranged to produce a measurement. In these expressions, K p , p and 0) 0 0 pressure drop (pt' —p2 equivalen t to that obtained with Vs< Pa, Pi are the upstream and downstream the given heat input which the model is designed to velocity, pressure and density respectively, C , is simulate. Adequate clearance is provided between the the thrust coefficient referred to the wing area S, edge of the grid and the duct wall 1 to avoid solid while W and 1K are the duct inlet and outlet areas a 3 friction between the grid and wall. The characteristics respectively. 388 Aircraft Engineering 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 (12): 1 – Dec 1, 1953
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032372
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. 688,378. Launching Ramps. Fairey Aviation Co. Ltd. Application June 30, 1949. A ramp 15 for launching aircraft or guided missiles is provided near the middle with a lever 18 normally held by toggle links 20 in the path of an abutment 21 691,948. Deflecting fluid jets. Societc Nationale on the flying body, and which is only releasable there­ d'Etude ct de Construction dc Moteurs. d'Aviation. from upon a predetermined propulsive thrust being Application February 27, 1951. developed. The thrust of the main power unit of the In a modification of the arrangement according to flying body causes the abutment 21 to engage the hook FIG. 3 of Specification 691,302 the transverse fluid 18, and separates abutments 22, 23 on the ramp and stream discharged from the slot 7 for effecting de­ flying body, respectively, to operate an electric s witch flexion of the jet is an auxiliary jet supplied from a 24 effecting ignition of booster rockets 30, 31. The source independent of the main jet. As shown in latter then move forward against compression springs n c 7 the auxiliary jet may consist of an annular com­ to close further electric contacts on abutments 35, pressed air jet 8 issuing from an inner axially-disposed and when all the contacts are closed a relay operates casing to produce an outward deflexion of the main the toggle links 20 to withdraw the hook 18 from the jet, or it may issue from an external casing surround­ abutment 21 and thus free the flying body. Alternative ing the nozzle, to produce an inward deflexion of the methods of releasing the hook 18 include the use of jet. the internal pressure developed in a hydraulic dashpot or ram and cylinder opposing the propulsive thrust, 693,681. Jet propulsion plant. Rolls-Royce Ltd. or the pressure, temperature or velocity of the gases in Application April 4, 1949. the combustion chamber or jet pipe of the main The exhaust pipe 15 from a gas turbine 16 is divided motor, while the booster rocket switches may be into two branches 10, 11, disposed in the vertical plane closed by the deflexion of vanes located in the respec­ and terminating in nozzles 13, 14 capable of pivoting tive jet streams. in the vertical and horizontal planes, respectively, about trunnions 36, and operable in conjunction with 691,302. Deflecting fluid jets. Socictc Nationale the control surfaces such as the elevators and rudder. d'Etude et de Construction dc Moteurs d'Aviation. Expansion joints 19 are provided in each of the Application August 8, 1949. branches, which are connected to the aircraft structure An arrangement for deflecting a fluid jet issuing 12 through swinging linkages, each consisting of a from a nozzle 1 along a tangential convex extension 3 yoke 23 pivoting about trunnions 22 perpendicular to of the nozzle wall, particularly adapted for use with the associated trunnions 36 and a link 26 connected pulse jets or thrust spoilers, consists of a deflector 2 to the yoke 23 and structure 12 by brackets 25, 28 per­ located in the region of the transverse plane passing mitting pivoting about axes parallel and perpendicular through the junction of the extension 3 with the nozzle to the trunnions 22 respectively. The tail pipes 13, 14 wall and in such a position that the greater part of the are connected to the branches 10, II by gas-tight nozzle section is not obstructed. The effect may be ball joints 32a mounted within sleeves 34 bolted to the augmented by applying boundary layer suction to the bulkhead 35, and are operated by linkages 45 mounted wall extension 3. FIG. 3 shows an arrangement in on the structure 12. In the case of a normally fixed but which the deflexion is effected by a transverse jet of the adjustable control surface, such as a stabilizing fin or fluid supplied from a point upstream of the throat the chamber 10 or to the nozzle 12. In the case of a tail-plane, the tail pipe may be wholly or partly sur­ through a by-pass 5 and discharged through a slot 6 thrust spoiler, FIG. 5, the jet is deflected through curved rounded by a fairing forming a structural unit coupled in the nozzle wall. As applied to a pulse jet, FIG 4, the slots 26, 27 in the nozzle wall by vanes 30, 31 which, to the control surface. deflector 2 causes the gases issuing rearwardly from when inoperative, form in conjunction with their sup­ the combustion chamber 10 to be reversed through a ports 28, 29 streamlined bodies which do not affect the pipe 13 and thereby augment the thrust of the main jet flow. Alternatively, the vanes may be mounted In jet from the nozzle 12, the pipe 13 discharging directly opposite sides of a member disposed on the nozzle into the atmosphere or being connected to the rear of axis. 694,150. Wind-tunnel testing of athodyds. Rene of the grid are obtained by trial and error in such a Lcduc. Application August 15, 1951. way that the values of the factor A are equal in the ex­ The testing arrangement described in Specification pressions A = V32p3/V02o0, obtained from the total 664,055 (see issue of September, 1953) is modified by pressures p0 and p measured by pitot traverses, and the addition of a grid 3 attached to the nose of the Crt=2(AW — W0)/S, obtained by tunnel balance central core member 2 and arranged to produce a measurement. In these expressions, K p , p and 0) 0 0 pressure drop (pt' —p2 equivalen t to that obtained with Vs< Pa, Pi are the upstream and downstream the given heat input which the model is designed to velocity, pressure and density respectively, C , is simulate. Adequate clearance is provided between the the thrust coefficient referred to the wing area S, edge of the grid and the duct wall 1 to avoid solid while W and 1K are the duct inlet and outlet areas a 3 friction between the grid and wall. The characteristics respectively. 388 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Dec 1, 1953

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