SE184314C1

SE184314C1 -

Info

Publication number: SE184314C1
Application number: SE939557A
Authority: SE
Priority date: 1957-10-16
Filing date: 1957-10-16
Publication date: 1963-06-18

Description

Uppfinnare: A A Griffith Foreliggande uppfinning hanfor sig till flygplan med motorer for flygning framat och fasta barplan, som vid flygning framat alstra lyftkraft samt en motoranlaggning som alstrar lyftkraft oberoende av de yid flygning framat aerodynamiskt alstrade lyftkrafterna, varvid den namnda motoranlaggningen innefattar ett stort antal sma gasturbinmotorer vilka aro stallbara kring en horisontell axel mellan vertikalt och lutande lage. Inventor: A A Griffith The present invention relates to aircraft with engines for forward flight and fixed bar aircraft, which in flight produce generating lifting force and an engine system which generates lifting force independent of the yid flight forward aerodynamically generated lifting forces, said engine system comprising a large number of small gas turbine engines which around a horizontal axis between vertical and inclined layers.

Enligt uppfinningen aro de sma gasturbinmotorerna sä anordnade att de alla pa en gang sta antingen vertikalt eller i liten vinkel mot vertikallinjen, alltid aro helt luneslutna Mom de fasta, aerodynamiskt utbildade ytorna hos flygkroppen och aro grupperade nara och jamnt f5rdelade kring flygplanets langdaxel. According to the invention, the small gas turbine engines are so arranged that they all stand at one time either vertically or at a slight angle to the vertical line, are always completely whimsical Mom the fixed, aerodynamically trained surfaces of the fuselage and are grouped closely and evenly distributed around the longitudinal axis of the aircraft.

Med denna anordning vinner man att lyftmotorerna yid behov kunna anvandas for att aven utova accelererande oiler bromsande kraft, att de tack vare sin inbyggnad inte alstra nagot extra luftmotstand och att nagot storre syangande moment into utovas pa flygplanet, om en lyftmotor skulle stanna, eftersom motorerna aro grupperade intill flygplanets langdaxel. With this device it is gained that the lifting motors can be used as needed to also exert accelerating oil braking force, that due to their incorporation they do not generate any extra air resistance and that somewhat larger sewing moments are exerted on the aircraft, if a lifting motor should stop, because the engines aro grouped next to the long axis of the aircraft.

Ett fOredraget utforingsexempel pa uppfinningen skall nedan beskrivas med hanvisning till bifogade schematiska ritning. A preferred embodiment of the invention will be described below with reference to the accompanying schematic drawing.

Fig. 1 visar en planvy ay ett flygplan med deltavinge, fig. 2 en sektion langs linjen i fig. 1 med en del av motoranlaggningen och fig. 3 en sektion langs linjeni fig. 2. Fig. 1 shows a plan view ay an aircraft with delta wing, Fig. 2 a section along the line in Fig. 1 with a part of the engine system and Fig. 3 is a section along the line Fig. 2.

Flygplanet fir en huvudsakligen deltaformad konstruktion vid vilken lyftkraftsalstrande delar overga i en flygkropp 11. Flygplanet framdrives i den med pilen 12 markerade riktningen av gasturbinreaktionsmotorer 13 anordnade vid vardera vingspetsen. Bransletankarna aro belagna Mom de av streckade linjer begransade areorna 14 i vingarna. The aircraft has a substantially delta-shaped structure in which lift-generating parts merge into a fuselage 11. The aircraft is propelled in the direction marked by the arrow 12 by gas turbine reaction engines 13 arranged at each wingtip. The fuel tanks are covered Mom the areas 14 delimited by dashed lines in the wings.

Forutom med gasturbinmotorerna 13 är flygplanet forsett med oberoende lyftmotorer 15 i motorschakt 16 och ytterligare lyftmotorer 17 i motorschakt 18. Dessa motorer aro ocksa gasturbinreaktionsmotorer. Enligt fig. 1 finnas sammanlagt tolv lyftmotorer i schakten 16, 18, men vilket som hoist lampligt antal motorer av latt konstruktion kan med for-del anvandas for att erhalla en av framatflygning oberoende lyftkraft pa. flygplanet. Motorschakten janate deras motorer aro belagna helt Mom flygkroppens fasta, aerodynamiskt utbildade ytor. In addition to the gas turbine engines 13 are the aircraft is equipped with independent lift engines 15 in engine shaft 16 and additional lift engines 17 in engine shaft 18. These engines are also gas turbine reaction engines. According to Fig. 1, there are a total of twelve lifting motors in the shafts 16, 18, but any high number of motors of light construction can be used to advantage to obtain a lifting force independent of forward flight. the aircraft. The engine shafts janate their engines aro coated entirely Mom the fixed, aerodynamically trained surfaces of the fuselage.

Da flygplanet skall lyfta startas lyftmotorerna 15, 17 och bibringas okad lyftkraft genom oppnande av gasreglage, tills lyftkraften. Overvinner flygplanets tyngd. Nar efter en huvudsakligen vertikal start lamplig hojd uppnatts, startas framdrivningsmotorerna 13 och flygplanet accelereras i framatflykt tills tillracklig aerodynamisk lyftkraft alstras for att bara flygplanet i normal flykt, varefter lyftmotorerna stoppas. When the aircraft is to take off, the lift engines 15, 17 are started and increased lifting power is provided by opening the throttle control, until the lifting force. Overcomes the weight of the aircraft. When, after a substantially vertical take-off height is reached, the propulsion engines 13 are started and the aircraft is accelerated in forward flight until sufficient aerodynamic lift is generated so that only the aircraft in normal flight, after which the lift engines are stopped.

Lyftmotorerna 15 och 17 suga in luft genom Oversidan pa vingen och flygkroppen 10, 11, och motorernas avgasstralar riktas nedat genom undersidan pa vingen och flygkroppen. Nar lyftmotorerna aro igang astadkommes fritt lufttilltrade till lyftmotorerna och frill utlopp for avgaser fran desamma genom att man undanfor bekladnadselement i form av luckor. Luckorna pa Oversidan betecknas 41 och luckorna pa undersidan 42. Luckorna 41 och 42 visas med heldragna linjer i de stangda 'igen som de intaga dá lyftmotorerna aro avstangda, och de streckprickade linjerna visa dem i oppna lagen. De stangda luckornas ytor sammanfalla med den aerodynamiska profilen i ovrigt. Luckorna 41 och 42 stallas i sina Oppna och stangda lagen medelst kolv- och cylinderdon 43 och 44. The lift motors 15 and 17 suck in air through the upper side of the wing and the fuselage 10, 11, and the exhaust jets of the engines are directed downwards through the lower side of the wing and the fuselage. When the lift motors are running, free air access to the lift motors is provided and exhaust fumes from them are released by removing cladding elements in the form of hatches. The doors on the upper side are designated 41 and the doors on the lower side 42. The doors 41 and 42 are shown with solid lines in the rods' again as the intake then the lifting motors are switched off, and the dotted lines show them in the open layers. The surfaces of the closed doors coincide with the aerodynamic profile in general. The doors 41 and 42 are stored in their open and closed layers by means of piston and cylinder members 43 and 44.

Sasom framgar av fig. 2 och 3 aro motorerna 15 sa monterade, att de kunna svanga kring axlar X och Y i flygplanets tvarriktning. I flygplanets langdriktning angransande motorer 15 Oro sammankopplade medelst 2— — lankar 45. Langs axeln X aro motorerna i tvarriktningen sammankopplade medelst ett vridmomentsoverforande ror 46, som är for-sett med ett snackhjul 47 vilket gOr ingrepp med en snackskruv 48, som genom en reduktionsvaxel kan vridas av en elektrisk motor 49. As can be seen from Figures 2 and 3, the engines 15 are so mounted that they can pivot about axes X and Y in the transverse direction of the aircraft. In the longitudinal direction of the aircraft adjacent engines 15 Oro interconnected by 2— - along the axis X, the motors are transversely connected by means of a torque transmitting tube 46, which is provided with a snack wheel 47 which engages a snack screw 48, which can be rotated by a reduction shaft by an electric motor 49.

Genom donna mekanism kunna lyftmotorerna 15 stallas in. Mom en begransad yinkel, I. ex. av storieksordningen 0 ph anise sidor om lodlinjen, och en. sadan snedstallning kommer att alstra en. horisontell drivkomponent, st att snabb acceleration till marschfart efter start och snabb retardation fore landning kan erhallas. Vid landning startas lyftmotorerna och minskas flyghastigheten framat tills flygplanets tyngd uppbares av lyftmotorerna. By means of this mechanism the lifting motors 15 can be set up. Mom and limited yinkel, I. ex. of the order of magnitude 0 ph anise sides of the vertical, and a. such a skew will produce one. horizontal drive component, so that fast acceleration to cruising speed after take-off and fast deceleration before landing can be obtained. Upon landing, the lift engines are started and the flight speed forward is reduced until the weight of the aircraft is carried by the lift engines.

Flygplanets stabilisering vid laga hastigheter kan erhallas ph vilket lampligt satt som heist, I. ex. padel salt som beskrivits i svenska patentskriften 168 396. The stabilization of the aircraft at low speeds can be obtained ph which suitably sat as a lift, I. ex. padel salt as described in Swedish patent specification 168 396.

Lyftmotorerna kunna Oxen vara sa anordnade aft riktningen hos lyftkraften kan regleras i vilken som heist riktning relativt lodlinj en. The lifting motors can be so arranged that the direction of the lifting force can be regulated in any direction relative to the vertical.

Vid en. annan utforingsform kan man i stallet for att installa lyftmotorerna sasom en helhet Ora deras stralmunstycken stallbara, eller ocksa kunna avlankningsorgan anordnas att i lamplig vinkel avlanka motorernas drivstralar. By a. another embodiment can be stalled in the stable to install the lifting motors as a whole Ora their jet nozzles, or also deflection means can be arranged to deflect the drive jets of the motors at an angular angle.

Claims

Patent claim: Aircraft with engines for forward flight and fixed bar aircraft, which mid-flight forward generate lift and an engine system that generates lift independent of the aerodynamically generated lift forces during flight, the said engine system comprising a large number of small gas turbine engines which are stallable around axis between vertical and inclined bearings, characterized in that the small gas turbine engines (15, 17) are arranged so that all ph at once stand either vertically or at a slight angle to the vertical line, are always completely enclosed within the fixed, aerodynamically trained surfaces of the fuselage ( 11) and are grouped closely and evenly distributed around the longitudinal axis of the aircraft. Request publications: Patents, France 971 992; Switzerland 308 179; United Kingdom 653779, 688231, 709731; USA 2 502 045, 2 780 424. Stockholm 1963. Kmmi. Boktr. P. A. Norstedt & Mier. 630089 GENERALSTABE NS LITOC