SE190854C1

SE190854C1 -

Info

Publication number: SE190854C1
Authority: SE
Publication date: 1964-01-01

Description

Uppfinnare: M J Brennan Foreliggande uppfinning hanfOr sig till flygplan omfattande kombinationen. av en flygkropp, till denna ledat anslutna huvudvingar I stand att fOrandra sin pilform mellan ett utbrett lage lampligt for start och landning och underljudsflykt och ett tillbakasvept lage lampligt for flygning -vid och Over ljudhastigheten, saint en framvinge anbragt pa flygkroppen framfOr huvudvingleden. Det Or utmarkande for dylika flygplan att nar huvudvingarna intaga sitt utbredda lage eller laghastighetslage, utsattes flygplanet for ett stabilitetsminskande stegringsmoment beroende pa framflyttningen av tryckcentrum och medf8ljande ofOrmaga has den av huvudvingarna utOvade lyftkrafteu att motverka denna forskjutning pa grund av framvingen. Det är ett andamal med uppfinningen att astadkomma anordningar, med vilkas hjalp denna nackdel kan undanrojas. Inventor: M J Brennan The present invention relates to aircraft comprising the combination. of a fuselage, to which articulated main wings are able to change their arrow shape between an extended position suitable for take-off and landing and sonic flight and a retracted position suitable for flight-at and above the speed of sound, saint a forewing placed on the fuselage in front of the main wing. It is characteristic of such aircraft that when the main wings occupy their widespread position or team speed law, the aircraft is subjected to a stability-reducing moment of increase depending on the advancement of the pressure center and accompanying power has the lifting force exerted by the main wings to counteract this displacement. It is an object of the invention to provide devices by means of which this disadvantage can be eliminated.

Enligt uppfinningen utforas delar av framvingens lyftkraftskapande ytor eller barytor sa, att de bliva i stand att riira sig till ett overksamt lage, efter eller samtidigt med huvudvingens svangningsrorelse framat, varigenom den av framvingen utovade totala lyftkraften minskas i en sadart utstrackning, som ãr tillracklig for att undvika det stabilitetsminskande stegringsmomentet under dessa forhallanden. According to the invention, parts of the lifting force-creating surfaces or bar surfaces of the front wing are designed so that they are able to move to an inactive position, after or simultaneously with the oscillating movement of the main wing forward, whereby the total lifting force exerted by the wing is reduced to such an extent as to to avoid the stability-reducing step during these conditions.

Uppfinningen kan genomforas genom att Ora samtliga eller en del av de i sidled utskjutande partierna av framvingen ledande kring axlar i huvudsak parallella med flygplanets rollaxel (OX-axel), varvid de ledade partierna aro anordnade att fallas nedat langs flygkroppen eller in i urta:gningar anordnade i denna, och ledrorelsen sker sedan huvudvingarnas svangningsrarelse framat Or i huvudsak fullbordad. The invention can be carried out by aligning all or part of the laterally projecting portions of the wing leading about axes substantially parallel to the plane axis (OX axis) of the aircraft, the articulated portions being arranged to fall down along the fuselage or into recesses. arranged in this, and the joint movement takes place since the oscillating movement of the main wings forward Or is substantially completed.

Alternativt kunna de i sidled utskjutande partierna av framvingen anbringas pa flygkroppen pa ett sadant satt, att de kunna glida in i och ut ur has anordnade i kroppen, varvid en dylik glidrorelse i huvudsak sker i ett plan parallellt med girplanet (XOY-planet). I detta fall kunna framvingens rorliga delar mekaniskt kopplas till samhorande huvudvinge pa ett sadant satt, att framvingdelarnas infallningsrarelse direkt paverkas av huvudvingarnas svangningsrorelse mot sitt utbredda lage eller lAghastighetslage. Onrvant galler, att huvudvingarnas svangningsrorelse till silt tillbakasvepta 'age eller hoghastighetslage automatiskt medfor, att framvingdelarna aterforas till sitt fullt verksamma lage. Alternatively, the laterally projecting portions of the wing can be mounted on the fuselage in such a way that they can slide into and out of hasps arranged in the body, such sliding movement taking place substantially in a plane parallel to the yaw plane (XOY plane). In this case, the movable parts of the front wing can be mechanically coupled to the associated main wing in such a way that the incident motion of the front wing parts is directly affected by the oscillating movement of the main wings towards their widespread bearing or low velocity law. Unsurprisingly, the oscillating motion of the main wings to the silt-swept-back age or high-velocity law automatically causes the front wing members to return to their fully effective position.

Det satt, ph vilket uppfinningen kan genomforas, kommer att beskrivas narmare i det foljande med hanvisning till bifogade ritningar. Fig. 1 Or en: planvy av ett flygplan, vid vilket framvingdelarna Oro anordnade att under en glidrorelse dragas in i flygkroppen, varvid delarna Oro visade i de lagen de intaga med huvudvingarna tillbakasvepta till hoghastighetslage, fig. 2 Or en planvy visande huvudvingarna i deras utbredda 'age eller laghastighetslage, fig. 3 Or en vy motsvarande fig. 1 men visar arrangemanget, nar huvudvingarna aro forskjutna till ett overksamt lage for hangarforvaring, fig. 4 Or en detaljplanvy i storre skala och visar forbindelserna mellan framvingen och huvudvingen, fig. visar en ytterligare detalj av de organ, som anvandas for att styra framvingens rorelse under indragning och utfallning, och fig. 6 Or ett snitt tangs linjen VI—VI i fig. 5. Fig. 7 och 8 Oro detaljvyer rita:de i storre skala av mekanismen for lasning air fOrbindelsen mellan en framvingdel och samverkan.de huvudvinge, varvid forbindelsen eller kopplingen visas i last respektive olast lage. The mode in which the invention may be practiced will be described in more detail below with reference to the accompanying drawings. Fig. 1 Or a: plan view of an airplane, in which the front wing parts Oro arranged to be pulled into the fuselage during a sliding motion, the parts Oro showing in the layers they take with the main wings swept back to high speed, Fig. 2 Or a plan view showing the main wings in their Fig. 3 Or a view corresponding to Fig. 1 but showing the arrangement when the main wings are displaced to an inactive layer for hangar storage, Fig. 4 is a detailed plan view on a larger scale and shows the connections between the front wing and the main wing, fig. shows a further detail of the means used to control the movement of the front wing during retraction and deflection, and Fig. 6 Or a section of the tangent line VI-VI in Fig. 5. Figs. 7 and 8 Concrete detail views are drawn on a larger scale. of the mechanism for welding air The connection between a front wing part and the cooperating main wing, the connection or coupling being shown in load and unloaded position, respectively.

Fig. 9, och 11 illustrera en modifierad 2- - utforingsform, varvid fig. 9 är en planvy av flygplanet med vingarna i hoghastighetslage, fig. 10 en motsvarande vy Hied vingarna i lfighastighetslage, medan fig. 11 är ett schematiskt tvarsnitt visande die organ, som anvandas for Mining av framvingdelarna. Fig. 9, and 11 illustrate a modified 2- embodiment, Fig. 9 is a plan view of the aircraft with the wings in high speed position, Fig. 10 a corresponding view Hied the wings in high speed position, while Fig. 11 is a schematic cross section showing the means , which is used for Mining the wing parts.

Sasom visas i fig. 1-8 omfattar flygplanet en flygkropp 20, huvudvingar 21 och 22, vilka aro ledat infastade i aktre delen av kroppen vid 211 resp. 221, samt en framvinge anbragt vid kroppen framfor huvudvingarna 21, 22 och bestaende av delarna 23, 24. De senare innefatta i sin konstruktion ett flertal styrorgan 25 (fig. 5 och 6), vilka aro anordnade aft samverka med styrskenor 26, som pa lampligt satt uppbaras i hus anordnade i kroppen 20. Vardera styrskenan 26 innefattar en styrflans 261, vars avre och undre ytor tjana som glidbanor for i styrorganen ingaende delar 251, 252, medan rullar 253 pa styrorganen aro anordnade att rulla langs styrflansens 261 sidekanter. Styrskenornas 26 lagen i flygkroppen visas med streckade linjer i fig. 1-3 och med heldragna linjer i fig. 4. As shown in Figs. 1-8, the aircraft comprises a fuselage 20, main wings 21 and 22, which are articulated in the aft part of the body at 211 and 211, respectively. 221, and a front wing arranged at the body in front of the main wings 21, 22 and consisting of the parts 23, 24. The latter comprise in their construction a plurality of guide members 25 (Figs. 5 and 6), which are arranged to cooperate with guide rails 26, which on each guide rail 261 comprises a guide flange 261, the upper and lower surfaces of which serve as slides for parts 251, 252 entering the guide means, while rollers 253 on the guide means are arranged to roll along the side edges of the guide flange 261. The layers of the guide rails 26 in the fuselage are shown in broken lines in Figs. 1-3 and in solid lines in Fig. 4.

Varje huvudvinge 21 eller 22 ãr medelst en lank 27 forbunden med en aktre, yttre punkt 231 resp. 241 ingdende I samverkande framvingdels 23 resp. 24 konstruktion, och formen av styrskenorna 26 hr sadan, att nar huvudvingarna 21, 22 fallas framat fran det i fig. 1 visade hoghastighetslaget till det for laghastighetsflykt, landning eller start lampliga laget med utbredda vingar, vilket visas i fig. 2, dragas fram-vingdelarna 23, 24 automatiskt in genom att styrorganen 25 glida langs sina skenor 26 till det i fig. 2 visade lfiget, i vilket framvingdelarna aro fullstandigt inneslutna sina respektive hus. Sasom torde inses, Aterforas framvingdelarna 23, 24 till sina verksamma lagen, nar huvudvingarna 21, 22 Aterga till hoghastighetslaget enligt fig. 1. Lampliga organ kunna anordnas for att tillsluta framvinghusen, nar delarna 23, 24 firo indragna. Each main wing 21 or 22 is by means of a long 27 connected to a stern, outer point 231 resp. 241 ingdende In cooperating forcing parts 23 resp. 24 construction, and the shape of the guide rails 26 is such that when the main wings 21, 22 fall forward from the high speed layer shown in Fig. 1 to the layer with flight wings, landing or take-off suitable with extended wings, as shown in Fig. 2, the wing parts 23, 24 automatically slide in by the guide means 25 sliding along their rails 26 to the position shown in Fig. 2, in which the front wing parts are completely enclosed in their respective housings. As will be appreciated, the front wing members 23, 24 are returned to their operative layers when the main wings 21, 22 return to the high speed team of Fig. 1. Lampable means may be provided to close the front wing housings when the parts 23, 24 are retracted.

Far all underlatta flygplanets hantering inom tranga utrymmen pa marken eller ombord pa fartyg, nfir det gfiller fartygsbaserade flygplan, hr det onskvart att huvudvingarna 21, 22 skola kunna fallas tillbaka till det i fig. 3 visade hell tillbakasvepta laget. For att medgiva donna rorelse fir det nodvandigt att modifiera forbindelsen mellan huvudvingen och samverkande framvingdel. Ett arrangemang for delta andamal visas i fig. 7 och 8, av torde framga, att lanken 27, i stallet far att bilda en fast forankring pa huvudvingkonstruktionen, är utformad som en tvaskanklad havarm eller vinkelha.varm, som fir ledad mot huvudvingkonstruktionen vid 271. Delen 27 bildar den erforderliga lankkopplingen med framvingdelen 23 (eller 24), medan havarmens andra skankel 272 tjanar som en sparr for en styrbar lasning. I lankens normala lage, som visas i fig. 7, fattas eller engageras ar men 272 av en sparrarm 28, av vilken en lampligt profilerad yta 281 vilar mot en pa motsvarande salt formad yta 273 ph skankeln 272. Sparrarmen 28 hr forbunden med stotstangen 29 i ett fluidumtryckpaverkat manoverdon 29, 30, som vid 31 ar ledat anslutet till vingkonstruktionen. For att medgiva full tillbakafallning av huvudvingarna, paverkas manoverdonen 29, 30 att f5ra sparrarmen 28 till det i fig. 8 visade laget, varvid delarna 281, 273 frigoras fran varandra och havarmen 27, 272 blir fri att vrida sig kring sin lagringspunkt 271 i en sadan utstrackning, som erfordras for att fora huvudvingarna forbi deras hoghastighetslage. Should all facilitate the handling of the aircraft in tight spaces on the ground or on board ships, in the case of ship-based aircraft, it is desirable that the main wings 21, 22 should be able to fall back to the fully swept back team shown in Fig. 3. In order to allow this movement, it is necessary to modify the connection between the main wing and the cooperating front wing part. An arrangement for delta andamal is shown in Figs. 7 and 8, it will be seen that the link 27, instead of forming a fixed anchorage on the main wing structure, is designed as a two-sanked lever or angular heater, which is hinged to the main blade structure at 271. The part 27 forms the required link coupling with the front wing part 23 (or 24), while the second shank 272 of the sea arm serves as a latch for a steerable welding. In the normal position of the lane, shown in Fig. 7, arms 272 are taken or engaged by a ratchet arm 28, of which a suitably profiled surface 281 rests against a corresponding salt-shaped surface 273 ph shank 272. The ratchet arm 28 is connected to the push rod 29. in a fluid pressure actuated actuator 29, 30, which at 31 are articulated connected to the wing structure. To allow full recoil of the main wings, the actuators 29, 30 are caused to move the ratchet arm 28 to the layer shown in Fig. 8, the parts 281, 273 being released from each other and the lever arm 27, 272 being free to rotate about its bearing point 271 in a such extension as is required to pass the main wings past their high-speed position.

Vid den modifierade utforingsform, som visas i fig. 9-11 aro framvingdelarna (liar betecknade 123 resp. 124) ledande i farhallande till flygkroppen 20 kring axlar i huvudsak parallella med flygplanets rollaxel. Vid det i fig. 10 och 11 visade arrangemanget upptagas framvingdelarna, nar huvudvingarna 21, 22 intaga silt laghastighetslage, i (joke visade) hus eller urtagningar placerade langs motsatta sidor av flygkroppen, sâ att i infallt lage ligga framvingdelarnas utat vanda sidor i huvudsak jams med kroppsytan. I fig. 11 visas delarna 123, 124 nedskjutande pa anise sidor om flygkroppen. 20. In the modified embodiment shown in Figs. 9-11, the front wing members (designated 123 and 124, respectively) are conductive in relation to the fuselage 20 about axes substantially parallel to the roll axis of the aircraft. In the arrangement shown in Figs. 10 and 11, the front wing portions, when the main wings 21, 22 occupy silt speed velocity, are accommodated in (joke shown) housings or recesses located along opposite sides of the fuselage, so that in the recessed position the outwardly facing sides of the wing wings are substantially with body surface area. Fig. 11 shows the parts 123, 124 projecting on anise sides of the fuselage. 20.

Framvingdelarna 123, 124 man.ovreras me-deist tryckfluidumpaverkade domkrafter 31, 32, vilka aro ledat anslutna till delarna vid 33 och 34. Nar huvudvingarna 21, 22 fallas framat till laghastighetslaget (fig. 10), paverkas domkrafterna 31, 32 att vrida delarna 123, 124 frail det i fig. 9 visade laget till det i fig. 10 och 11 visade. The front wing members 123, 124 are operated by means of pressure fluid impacted jacks 31, 32, which are articulated to the members at 33 and 34. When the main wings 21, 22 fall forward to the stroke speed (Fig. 10), the jacks 31, 32 are caused to rotate the members. 123, 124 from the layer shown in Fig. 9 to that shown in Figs. 10 and 11.

Claims

Patent claim:

An airplane comprising a fuselage, the main wings connected thereto capable of performing an oscillating motion between an extended bearing and a retracted bearing, saint a front wing mounted on the fuselage in front of the joint connections of the main wings, characterized in that parts (23, 24; 123, 124 ) of the lifting force-creating surfaces of the front wing are challenged to be able to frame themselves to an inactive position after or simultaneously with the oscillating movement of the main wings (21, 22) forward.

Aircraft according to claim 1, characterized in that laterally projecting portions (23, 24) of the wing are arranged on the fuselage (20) with the ability to slide in a plane substantially parallel to the plane into and out of housings arranged in the fuselage. .

Aircraft according to claim 2, characterized in that the respective movable front wing portions (23, 24) are mechanically connected to the corresponding main wing (21 and 22, respectively) on such a salt that the retraction movement of the front wing portions is directly affected by the oscillation movement of the main wings to their widespread position. or team velocity law, while the movement of the main wings in the opposite direction automatically causes the wing to be returned to its fully effective law.

Aircraft according to patent claims 2 and 3, comprising a single, rigid tongue (27) articulated between adjacent points on the main wing and the front wing, respectively, in the area near the leading edge, the front wing parts (23, 24) being supported by guide means (25) arranged to cooperate with tracks. or guide rails (26) arranged in the said housings, which grooves or guide rails aro sa. formed that the front wing portions of them are controlled between a fully retracted bearing and a fully retracted or retracted bearing, when the main wings (21, 22) give frail their bearing too high to their bearing for low speed, and vice versa.

An airplane according to claim 4, may be signed by means (28, 29, 30), for releasing said rigid link (27) so that the main wings (21, 22) are allowed to move to a fully retracted layer to facilitate the aircraft handling mom cramped spaces.

Aircraft according to claim 1, characterized in that the front wing parts (123, 124) are articulated towards the fuselage (20) along axes substantially parallel to the plane axis of the aircraft, so that they are able to fall down to an inactive position, and to drive or motor means (31) are provided for performing such a lowering operation. Request publications: