Handley Page Slots
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Wing for aircraft Download PDF
Handley Page slots on the leading edge of the wing outer panels, plus trailing-edge flaps, made possible a low landing speed. Accommodation was provided for a crew of four. Seven weeks after the first flight, the design was put into produc-tion, and the first examples entered RAF service in the autumn of 1938, 49 Squadron being the first unit. The Handley Page H.P.20 was an experimental monoplane modification of a de Havilland DH.9A, built to study controllable slots and slotted ailerons as high lift devices. It was the first aircraft to fly with controllable slots.InfoPublication numberUS1433030AUS1433030AUS469402AUS46940221AUS1433030AUS 1433030 AUS1433030 AUS 1433030AUS 469402 AUS469402 AUS 469402AUS 46940221 AUS46940221 AUS 46940221AUS 1433030 AUS1433030 AUS 1433030AAuthorityUSUnited StatesPrior art keywordswingsectionswing sectionsslotsrailsPrior art dateLegal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)Expired - LifetimeApplication numberUS469402AInventorPage Frederick HandleyCurrent Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.) Handley Page Ltd Original AssigneeHandley Page LtdPriority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)Filing datePublication dateApplication filed by Handley Page LtdfiledCriticalHandley Page LtdPriority to US469402ApriorityCriticalpatent/US1433030A/enHandley Page Slots AppPriority claimed from US581824Aexternal-prioritypatent/US1496733A/enPriority claimed from US581822Aexternal-prioritypatent/US1496731A/enPriority claimed from US581823Aexternal-prioritypatent/US1496732A/enApplication grantedgrantedCriticalPublication of US1433030ApublicationCriticalpatent/US1433030A/enAnticipated expirationlegal-statusCriticalExpired - Lifetimelegal-statusCriticalCurrentLinksHandley Page Slot281000175653Handley Pagecompanies0.000description2239000003570airSubstances0.000description2241000287182SturnidaeSpecies0.000description1238000010276constructionMethods0.000description1238000006073displacement reactionsMethods0.000description1230000000694effectsEffects0.000description1280000528844i, Ltd.companies0.000description1230000002265preventionEffects0.000description1ImagesClassifications
*B—PERFORMING OPERATIONS; TRANSPORTINGB64—AIRCRAFT; AVIATION; COSMONAUTICSB64C—AEROPLANES; HELICOPTERSB64C21/00—Influencing air-flow over aircraft surfaces by affecting boundary-layer flowB64C21/02—Influencing air-flow over aircraft surfaces by affecting boundary-layer flow by use of slot, ducts, porous areas, or the like
*B—PERFORMING OPERATIONS; TRANSPORTINGB64—AIRCRAFT; AVIATION; COSMONAUTICSB64C—AEROPLANES; HELICOPTERSB64C2230/00—Boundary layer controlsB64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
*B—PERFORMING OPERATIONS; TRANSPORTINGB64—AIRCRAFT; AVIATION; COSMONAUTICSB64C—AEROPLANES; HELICOPTERSB64C2230/00—Boundary layer controlsB64C2230/20—Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
*Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTSY02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGEY02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATIONY02T50/00—Aeronautics or air transportY02T50/10—Drag reductionDescription
F. H. PAGE.
WING FOR AIRCRAFT. APPLICATION FILED MAY 14. 1921.
Patented Oct. 24, 1922. Closest casino to st louis.
Ferry Schedule Arizona Time $2.00 Round Trip (800) 307-3610 Weather Conditions May Delay or Cancel. Havasu landing resort and casino ferry schedule.
Patented Get. 24, 1922.
narrate stares earner (EFF-11GB,
FREDERICK HANDLEY PAGE, OF LONDON, ENGLAND, ASSIGNOR T0 i=i LIMITED, 0]? LONDON, ENGLAND.
WING FOR AIRCRAFT.
Application filed May 14, 1921. Serial No. 469,402.
T 0 all whom it may concern: I
Be it known that I, FREDERICK HANDLEY PAGE, a subject of the King of Great Britain, residing at London, England, have invented certain new and useful Improvements in Wings for Aircraft, of which the following is a specification.
In the specification of United States Patent’No. 1353666, dated 21st September. 1920, an invention has been described in which a slot or slots is or are formed in the leading portion of a wing extendin in a direction transverse to the direction of flight, in order to admit of the passage of air from the under side to the upper side, so as to prevent the burbling effect which takes place with wings when inclined to the air at a large angle of incidence, and by prevention of that burbling permitting the wings to be flown at still greater angles, and greatly improved lift coeflicient being thereby obtained.
Ina wing having slots of this kind, the wing has been considered as composed of a main wing and one or more auxiliary wings set in front of the leading edge thereof, and it has been stated in the specification that the auxiliary wings are set at a less angle of incidence than the main wings. Thus if there is a difierence in angle of 30 between the chord of the main wing and the chord of the auxiliary wing, and the main wing happens to be at an angle of incidence of plus 10, then the angle of incidence of the auxiliary wing would be minus 20.
ccording to the present invention a wing structure for aircraft is composed of a plurality of wing sections each of wing form extending transversely to the longitudinal axis of the machine, one wing section being’ located rearward of the otherfrom the leading edge to the trailingedge of said wing structure; a plurality of curved rails are provided, extending transversely of said -wing sections, and one of said wing sections is fixed to the said rails. Means are then provided for slidab’ly connecting the other wing sections composing the wing structure to the said curved rails, to permit said slid able wing sections curved rails. 7
Means are also provided for-sliding said movable’wing sections upon said rails relatively to said fixed wing section and to each to be slidden upon said other, to cause said wing sections to be brought into contactwith each other or to be separated from each other to form comparatively narrow through slots between the said wing sections, each slot extending in a direction transversely of the line of flight, and when so separated to cause said wing structure to be of greater chord than when said wing sections are in contact with each other and said slots closed. When said wing sections are separated from each other, the openings of said slots on the under side of the wing structure are in advance of the openings of said slots on the upper side of the wing structure, all such wing sections whether closed together or separated combining to make up the contour of a whole wing structure, in which portions of the surfaces of each wing section are contained in the contour line surrounding said wing structure.
The term wing section is to be understood as a wing of comparatively high aspect ratio having leading and trailing edges, while the term wing structure used in this specification is to be understood as a structure comprising two or more of such wing sections arranged in tandem from the leading edge to the trailing edge of the wing structure, and all the said wing sections,’
and is influenced by them, and each wing section is masked by the wing section immediately preceding it, and is also at a greater angle ofincidence than the wing sections preceding it. Thus in a wing divided into say five wing sections the leading section may be at an angle of say minus40 the next section at minus 25 the next at minus 10 the next at plus 5 and the last at plus 20.
These examples of relative angles of ,incidence are given not as suitable relative angl’es ofthe wing sections but as an explana tion of the terms referred to.
The invention will be further described with reference to the accompanying drawings. Figs. 1 and 2 are views showing a construction in which the wing sections are so mounted the wing structure as to per-- mit of angular adjustment simultaneously with bodily displacement of the wing sections.
Referring to the drawings, the wing sections 1 are slidable in direction with the lever 12, the ends of the rods 13 being pivot rails, and means for sliding said movable o -curved rails 11 from the ally connected near the trailing edges of the wing sections 1 forward of the lever 12, and being pivotally connected near the leading edges of the wing sections 1 rearward vof the lever 12. Obviously there may be a plurality of such levers 12, and whether tliere is one lever 12 or a plurality, said lever or levers is or are mounted upon a shaft 14,
by the-angular adjustment of which shaft 14 the wing sections 1 will be slidden on the osition shown at Fig. 1 where the wing sections are in contact with each other, to the position at Fig. 2 where the wing sections are separated to form slotsr between themselves and. also where the chord of thewing structure is increased.
VVhat I claim as my invention and desire to secure by Letters Patent is 1. A wing .structure for aircraft, comprised by a plurality of wing sections each of wing form and all extending transversely to the direction of flight, one located rearward .of the other from the leading edge to the trailing edge of said wing structure, a
plurality of curved rails extending transversely of said wing sections, means for fix-’ ’mg one of said wing sections’to said rails, means for slidably connecting the other wing sections composing the wing structure to sa d curved rails to permit said slidable wing sectlonsto be slidden upon said curved wing sections upon said rails relatively to said fixed wing section and to each other to cause-said wing sections to be brought into contact with each other or to be separated from each other to form comparatively narrow through slots between said wing sections each slot. extending in a direction tranversely of the line of flight and when so separated to cause said wing structure to be two-arme said slots closed, the openings of said slots on the under side of said wing structure being located in advance of the openings of said slots on the upper side of said wing structure, all said wing sections whether closed together or separated being contained within contour lines of wing forms surrounding said wing structure.
2. A wing structure for aircraft, comprised by’ a plurality of wing sections each of wing form and all extending transversely to the direction of flight, one located rearward of the other from the leading edge to the trailing edge of said wing structure, a plurality of curved rails extending transversely of said wing sections, means for fixing one of said wing sections to said rails, means for slidably connecting the other wing sections composing the wing structure to said curved rails to permit said slidable wing sections to be slidden upon said curved rails, and a two armed lever, a pivot connecting said two-armed lever to said fixed wing section, connecting rods pivoted to the upper arm of said two-armed lever and pivoted to the trailing edges of said wing sections forward of said lever, and connecting rods ivoted to the lower arm of said 5 lever extending rearwardly and pivoted to the leading edges of said wing sections rearward of said two-armed lever for sliding said movable wing sections upon said rails relatively to said fixed wing section and toeach other to cause said wing sections to be brought into contact with each other or to be separated from each other to form comparatively narrow through slots between said wing sections each slot extending in a direction transversely of the line of flight and when so separated to cause said wing structure to be of greater chord than when said wing sections are in contact with each other and said slots closed, the openings .of said slots on the under side of said wing structure being located in advance of the openings of said slots on the upper side of said wing structure, all said wing sections whether closed together or separated being contained within contour lines of wing forms surrounding said wing structure. Hollywood casino charlestown poker room.
In witness whereof I have hereunto set my hand in the presence of two witnesses.
FREDERICK HANDLEY PAGE.
Witnesses:
THOMAS WILLIAM Rooms, WILLIAM A. MARSHALL.- US469402A1921-05-141921-05-14Wing for aircraft Expired - LifetimeUS1433030A (en) Priority Applications (1)Application NumberPriority DateFiling DateTitleUS469402AUS1433030A (en) 1921-05-141921-05-14Wing for aircraft Applications Claiming Priority (4)Application NumberPriority DateFiling DateTitleUS469402AUS1433030A (en) 1921-05-141921-05-14Wing for aircraft US581824AUS1496733A (en) 1921-05-141922-08-14Wing for aircraft US581822AUS1496731A (en) 1921-05-141922-08-14Wing for aircraft US581823AUS1496732A (en) 1921-05-141922-08-14Wing for aircraft Publications (1)Publication NumberPublication DateUS1433030AtrueUS1433030A (en) 1922-10-24ID=23863644Family Applications (1)Application NumberTitlePriority DateFiling DateUS469402AExpired - LifetimeUS1433030A (en) 1921-05-141921-05-14Wing for aircraft Country Status (1)Handley Page HalifaxCountryLinkUS (1) US1433030A (en) Cited By (4)* Cited by examiner, † Cited by third partyPublication numberPriority datePublication dateAssigneeTitleUS2423803A (en) *1943-12-081947-07-08Edward A StalkerHigh lift device US2538224A (en) *1945-11-131951-01-16Daniel R ZuckWing with interconnected flap and nose slat US2550850A (en) *1943-05-101951-05-01Muller JaquesVariable incidence multiple wing system for aircraft US6905092B2 (en) 2002-11-202005-06-14Airfoils, IncorporatedLaminar-flow airfoil 19211921-05-14USUS469402Apatent/US1433030A/ennot_activeExpired - LifetimeHandley Page SlatsCited By (4)* Cited by examiner, † Cited by third partyPublication numberPriority datePublication dateAssigneeTitleUS2550850A (en) *1943-05-101951-05-01Muller JaquesVariable incidence multiple wing system for aircraft US2423803A (en) *1943-12-081947-07-08Edward A StalkerHigh lift device US2538224A (en) *1945-11-131951-01-16Daniel R ZuckWing with interconnected flap and nose slat US6905092B2 (en) 2002-11-202005-06-14Airfoils, IncorporatedLaminar-flow airfoil Similar DocumentsPublicationPublication DateTitleUS2289704A (en) Aircraft wing US3463418A (en) Vortex generator for airplane wing US2620622A (en) Reverse thrust arrangement for braking jet-propelled aircraft US2444293A (en) Gap seal for flaps US2169416A (en) Slotted deflector flap US2846165A (en) Aircraft control system US3107882A (en) Yaw control system for vtol tilt wing aircraft US1871396A (en) Means of reducing the fluid resistance of automobile bodies US2358985A (en) Aircraft US3478988A (en) Stol aircraft having by-pass turbojet engines US2430793A (en) Aircraft elevator construction US2406475A (en) Slotted airplane wing GB1284108A (en) Improvements in or relating to aircraft wings US2086085A (en) Aircraft control gear GB1435306A (en) Air foil structure US5961068A (en) Aerodynamic control effector US3471107A (en) Stabilizing the vortices over a thin delta wing US3092354A (en) Aerodynamic system and apparatus US3330500A (en) Propulsive wing airplane US2123096A (en) Aeroplane US2191842A (en) Airplane and control apparatus therefor US2670910A (en) Aircraft US3126173A (en) Alvarez-calderdn US2557522A (en) Aerodynes equipped with reaction jet propulsion means gb2076109a (en) improving aircraft stability an air liner which set a new standard of comfort and safety during flightfamous aircraft - 1the handley page 42 type of air liner is one of the most remarkable in the world. eight of these machines were ordered by imperial airways and in june 1931 the first began flying between london and paris. these machines set a new standard of comfort and safety in air liners, a standard which has been reached by few aeroplanes of later design, though the speeds of the newer machines may be much greater. no fleet of air liners in the world can claim the record held by the heracles, horatius, horsa and others of this fleet, of having flown well over 7,000,000 miles while carrying 300,000 passengers. not one single paying passenger has been hurt while travelling in these machines.the heracles has flown over a million miles. she and her sister craft were built specially to fly on the england to india route. two varieties were built. machines of the first variety, known as the western or heracles type, were detailed for the section between england and egypt; the others, known as the eastern or hannibal type, were designed for the section between egypt and india. the main difference between the two types is in the passenger accommodation. the western type normally carries thirty-eight passengers and a crew of four and the eastern type sixteen passengers. in the heracles type the freight compartment has a capacity of 250 cubic feet. for the hannibal type the figure is 500 cubic feet.all the machines have four engines, bristol jupiters, air-cooled and each developing 550 horse-power. the heracles type has jupiter x f.b.m. engines and the hannibal type jupiter xi engines.the wings are of metal construction, covered with fabric. the light aluminium alloy known as duralumin is chiefly used. the wings are fitted with the famous handley page slots, which add so much to safety in flying. the body of the machine is of almost circular cross section in shape and is in two parts. the front portion, which is metal-covered, contains the passengers’ saloons, the pilots’ cockpit and the luggage compartment. the rear portion is fabric-covered and carries the tail unit. the biplane tail unit has three rudders of all-metal construction.the main fuel tanks, holding some 500 gallons, are in the upper wing. the two pilots’ seats are right in the nose of the fuselage, with a small wireless room immediately behind. in the two passengers’ saloons seats are arranged four abreast in the western type, with a gangway in between. between the two saloons is the mail and luggage or freight compartment. the saloons have a double skin, which reduces the noise of the engines.the span of the wings of these machines is 130 feet, the length 89 feet 9 inches and the height 27 feet. when fully loaded they weigh 30,000 lb and carry a payload of 9,000 lb. both types cruise at 95-105 miles an hour.the heracles type has a maximum speed of 127
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Wing for aircraft Download PDF
Handley Page slots on the leading edge of the wing outer panels, plus trailing-edge flaps, made possible a low landing speed. Accommodation was provided for a crew of four. Seven weeks after the first flight, the design was put into produc-tion, and the first examples entered RAF service in the autumn of 1938, 49 Squadron being the first unit. The Handley Page H.P.20 was an experimental monoplane modification of a de Havilland DH.9A, built to study controllable slots and slotted ailerons as high lift devices. It was the first aircraft to fly with controllable slots.InfoPublication numberUS1433030AUS1433030AUS469402AUS46940221AUS1433030AUS 1433030 AUS1433030 AUS 1433030AUS 469402 AUS469402 AUS 469402AUS 46940221 AUS46940221 AUS 46940221AUS 1433030 AUS1433030 AUS 1433030AAuthorityUSUnited StatesPrior art keywordswingsectionswing sectionsslotsrailsPrior art dateLegal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)Expired - LifetimeApplication numberUS469402AInventorPage Frederick HandleyCurrent Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.) Handley Page Ltd Original AssigneeHandley Page LtdPriority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)Filing datePublication dateApplication filed by Handley Page LtdfiledCriticalHandley Page LtdPriority to US469402ApriorityCriticalpatent/US1433030A/enHandley Page Slots AppPriority claimed from US581824Aexternal-prioritypatent/US1496733A/enPriority claimed from US581822Aexternal-prioritypatent/US1496731A/enPriority claimed from US581823Aexternal-prioritypatent/US1496732A/enApplication grantedgrantedCriticalPublication of US1433030ApublicationCriticalpatent/US1433030A/enAnticipated expirationlegal-statusCriticalExpired - Lifetimelegal-statusCriticalCurrentLinksHandley Page Slot281000175653Handley Pagecompanies0.000description2239000003570airSubstances0.000description2241000287182SturnidaeSpecies0.000description1238000010276constructionMethods0.000description1238000006073displacement reactionsMethods0.000description1230000000694effectsEffects0.000description1280000528844i, Ltd.companies0.000description1230000002265preventionEffects0.000description1ImagesClassifications
*B—PERFORMING OPERATIONS; TRANSPORTINGB64—AIRCRAFT; AVIATION; COSMONAUTICSB64C—AEROPLANES; HELICOPTERSB64C21/00—Influencing air-flow over aircraft surfaces by affecting boundary-layer flowB64C21/02—Influencing air-flow over aircraft surfaces by affecting boundary-layer flow by use of slot, ducts, porous areas, or the like
*B—PERFORMING OPERATIONS; TRANSPORTINGB64—AIRCRAFT; AVIATION; COSMONAUTICSB64C—AEROPLANES; HELICOPTERSB64C2230/00—Boundary layer controlsB64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
*B—PERFORMING OPERATIONS; TRANSPORTINGB64—AIRCRAFT; AVIATION; COSMONAUTICSB64C—AEROPLANES; HELICOPTERSB64C2230/00—Boundary layer controlsB64C2230/20—Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
*Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTSY02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGEY02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATIONY02T50/00—Aeronautics or air transportY02T50/10—Drag reductionDescription
F. H. PAGE.
WING FOR AIRCRAFT. APPLICATION FILED MAY 14. 1921.
Patented Oct. 24, 1922. Closest casino to st louis.
Ferry Schedule Arizona Time $2.00 Round Trip (800) 307-3610 Weather Conditions May Delay or Cancel. Havasu landing resort and casino ferry schedule.
Patented Get. 24, 1922.
narrate stares earner (EFF-11GB,
FREDERICK HANDLEY PAGE, OF LONDON, ENGLAND, ASSIGNOR T0 i=i LIMITED, 0]? LONDON, ENGLAND.
WING FOR AIRCRAFT.
Application filed May 14, 1921. Serial No. 469,402.
T 0 all whom it may concern: I
Be it known that I, FREDERICK HANDLEY PAGE, a subject of the King of Great Britain, residing at London, England, have invented certain new and useful Improvements in Wings for Aircraft, of which the following is a specification.
In the specification of United States Patent’No. 1353666, dated 21st September. 1920, an invention has been described in which a slot or slots is or are formed in the leading portion of a wing extendin in a direction transverse to the direction of flight, in order to admit of the passage of air from the under side to the upper side, so as to prevent the burbling effect which takes place with wings when inclined to the air at a large angle of incidence, and by prevention of that burbling permitting the wings to be flown at still greater angles, and greatly improved lift coeflicient being thereby obtained.
Ina wing having slots of this kind, the wing has been considered as composed of a main wing and one or more auxiliary wings set in front of the leading edge thereof, and it has been stated in the specification that the auxiliary wings are set at a less angle of incidence than the main wings. Thus if there is a difierence in angle of 30 between the chord of the main wing and the chord of the auxiliary wing, and the main wing happens to be at an angle of incidence of plus 10, then the angle of incidence of the auxiliary wing would be minus 20.
ccording to the present invention a wing structure for aircraft is composed of a plurality of wing sections each of wing form extending transversely to the longitudinal axis of the machine, one wing section being’ located rearward of the otherfrom the leading edge to the trailingedge of said wing structure; a plurality of curved rails are provided, extending transversely of said -wing sections, and one of said wing sections is fixed to the said rails. Means are then provided for slidab’ly connecting the other wing sections composing the wing structure to the said curved rails, to permit said slid able wing sections curved rails. 7
Means are also provided for-sliding said movable’wing sections upon said rails relatively to said fixed wing section and to each to be slidden upon said other, to cause said wing sections to be brought into contactwith each other or to be separated from each other to form comparatively narrow through slots between the said wing sections, each slot extending in a direction transversely of the line of flight, and when so separated to cause said wing structure to be of greater chord than when said wing sections are in contact with each other and said slots closed. When said wing sections are separated from each other, the openings of said slots on the under side of the wing structure are in advance of the openings of said slots on the upper side of the wing structure, all such wing sections whether closed together or separated combining to make up the contour of a whole wing structure, in which portions of the surfaces of each wing section are contained in the contour line surrounding said wing structure.
The term wing section is to be understood as a wing of comparatively high aspect ratio having leading and trailing edges, while the term wing structure used in this specification is to be understood as a structure comprising two or more of such wing sections arranged in tandem from the leading edge to the trailing edge of the wing structure, and all the said wing sections,’
and is influenced by them, and each wing section is masked by the wing section immediately preceding it, and is also at a greater angle ofincidence than the wing sections preceding it. Thus in a wing divided into say five wing sections the leading section may be at an angle of say minus40 the next section at minus 25 the next at minus 10 the next at plus 5 and the last at plus 20.
These examples of relative angles of ,incidence are given not as suitable relative angl’es ofthe wing sections but as an explana tion of the terms referred to.
The invention will be further described with reference to the accompanying drawings. Figs. 1 and 2 are views showing a construction in which the wing sections are so mounted the wing structure as to per-- mit of angular adjustment simultaneously with bodily displacement of the wing sections.
Referring to the drawings, the wing sections 1 are slidable in direction with the lever 12, the ends of the rods 13 being pivot rails, and means for sliding said movable o -curved rails 11 from the ally connected near the trailing edges of the wing sections 1 forward of the lever 12, and being pivotally connected near the leading edges of the wing sections 1 rearward vof the lever 12. Obviously there may be a plurality of such levers 12, and whether tliere is one lever 12 or a plurality, said lever or levers is or are mounted upon a shaft 14,
by the-angular adjustment of which shaft 14 the wing sections 1 will be slidden on the osition shown at Fig. 1 where the wing sections are in contact with each other, to the position at Fig. 2 where the wing sections are separated to form slotsr between themselves and. also where the chord of thewing structure is increased.
VVhat I claim as my invention and desire to secure by Letters Patent is 1. A wing .structure for aircraft, comprised by a plurality of wing sections each of wing form and all extending transversely to the direction of flight, one located rearward .of the other from the leading edge to the trailing edge of said wing structure, a
plurality of curved rails extending transversely of said wing sections, means for fix-’ ’mg one of said wing sections’to said rails, means for slidably connecting the other wing sections composing the wing structure to sa d curved rails to permit said slidable wing sectlonsto be slidden upon said curved wing sections upon said rails relatively to said fixed wing section and to each other to cause-said wing sections to be brought into contact with each other or to be separated from each other to form comparatively narrow through slots between said wing sections each slot. extending in a direction tranversely of the line of flight and when so separated to cause said wing structure to be two-arme said slots closed, the openings of said slots on the under side of said wing structure being located in advance of the openings of said slots on the upper side of said wing structure, all said wing sections whether closed together or separated being contained within contour lines of wing forms surrounding said wing structure.
2. A wing structure for aircraft, comprised by’ a plurality of wing sections each of wing form and all extending transversely to the direction of flight, one located rearward of the other from the leading edge to the trailing edge of said wing structure, a plurality of curved rails extending transversely of said wing sections, means for fixing one of said wing sections to said rails, means for slidably connecting the other wing sections composing the wing structure to said curved rails to permit said slidable wing sections to be slidden upon said curved rails, and a two armed lever, a pivot connecting said two-armed lever to said fixed wing section, connecting rods pivoted to the upper arm of said two-armed lever and pivoted to the trailing edges of said wing sections forward of said lever, and connecting rods ivoted to the lower arm of said 5 lever extending rearwardly and pivoted to the leading edges of said wing sections rearward of said two-armed lever for sliding said movable wing sections upon said rails relatively to said fixed wing section and toeach other to cause said wing sections to be brought into contact with each other or to be separated from each other to form comparatively narrow through slots between said wing sections each slot extending in a direction transversely of the line of flight and when so separated to cause said wing structure to be of greater chord than when said wing sections are in contact with each other and said slots closed, the openings .of said slots on the under side of said wing structure being located in advance of the openings of said slots on the upper side of said wing structure, all said wing sections whether closed together or separated being contained within contour lines of wing forms surrounding said wing structure. Hollywood casino charlestown poker room.
In witness whereof I have hereunto set my hand in the presence of two witnesses.
FREDERICK HANDLEY PAGE.
Witnesses:
THOMAS WILLIAM Rooms, WILLIAM A. MARSHALL.- US469402A1921-05-141921-05-14Wing for aircraft Expired - LifetimeUS1433030A (en) Priority Applications (1)Application NumberPriority DateFiling DateTitleUS469402AUS1433030A (en) 1921-05-141921-05-14Wing for aircraft Applications Claiming Priority (4)Application NumberPriority DateFiling DateTitleUS469402AUS1433030A (en) 1921-05-141921-05-14Wing for aircraft US581824AUS1496733A (en) 1921-05-141922-08-14Wing for aircraft US581822AUS1496731A (en) 1921-05-141922-08-14Wing for aircraft US581823AUS1496732A (en) 1921-05-141922-08-14Wing for aircraft Publications (1)Publication NumberPublication DateUS1433030AtrueUS1433030A (en) 1922-10-24ID=23863644Family Applications (1)Application NumberTitlePriority DateFiling DateUS469402AExpired - LifetimeUS1433030A (en) 1921-05-141921-05-14Wing for aircraft Country Status (1)Handley Page HalifaxCountryLinkUS (1) US1433030A (en) Cited By (4)* Cited by examiner, † Cited by third partyPublication numberPriority datePublication dateAssigneeTitleUS2423803A (en) *1943-12-081947-07-08Edward A StalkerHigh lift device US2538224A (en) *1945-11-131951-01-16Daniel R ZuckWing with interconnected flap and nose slat US2550850A (en) *1943-05-101951-05-01Muller JaquesVariable incidence multiple wing system for aircraft US6905092B2 (en) 2002-11-202005-06-14Airfoils, IncorporatedLaminar-flow airfoil 19211921-05-14USUS469402Apatent/US1433030A/ennot_activeExpired - LifetimeHandley Page SlatsCited By (4)* Cited by examiner, † Cited by third partyPublication numberPriority datePublication dateAssigneeTitleUS2550850A (en) *1943-05-101951-05-01Muller JaquesVariable incidence multiple wing system for aircraft US2423803A (en) *1943-12-081947-07-08Edward A StalkerHigh lift device US2538224A (en) *1945-11-131951-01-16Daniel R ZuckWing with interconnected flap and nose slat US6905092B2 (en) 2002-11-202005-06-14Airfoils, IncorporatedLaminar-flow airfoil Similar DocumentsPublicationPublication DateTitleUS2289704A (en) Aircraft wing US3463418A (en) Vortex generator for airplane wing US2620622A (en) Reverse thrust arrangement for braking jet-propelled aircraft US2444293A (en) Gap seal for flaps US2169416A (en) Slotted deflector flap US2846165A (en) Aircraft control system US3107882A (en) Yaw control system for vtol tilt wing aircraft US1871396A (en) Means of reducing the fluid resistance of automobile bodies US2358985A (en) Aircraft US3478988A (en) Stol aircraft having by-pass turbojet engines US2430793A (en) Aircraft elevator construction US2406475A (en) Slotted airplane wing GB1284108A (en) Improvements in or relating to aircraft wings US2086085A (en) Aircraft control gear GB1435306A (en) Air foil structure US5961068A (en) Aerodynamic control effector US3471107A (en) Stabilizing the vortices over a thin delta wing US3092354A (en) Aerodynamic system and apparatus US3330500A (en) Propulsive wing airplane US2123096A (en) Aeroplane US2191842A (en) Airplane and control apparatus therefor US2670910A (en) Aircraft US3126173A (en) Alvarez-calderdn US2557522A (en) Aerodynes equipped with reaction jet propulsion means gb2076109a (en) improving aircraft stability an air liner which set a new standard of comfort and safety during flightfamous aircraft - 1the handley page 42 type of air liner is one of the most remarkable in the world. eight of these machines were ordered by imperial airways and in june 1931 the first began flying between london and paris. these machines set a new standard of comfort and safety in air liners, a standard which has been reached by few aeroplanes of later design, though the speeds of the newer machines may be much greater. no fleet of air liners in the world can claim the record held by the heracles, horatius, horsa and others of this fleet, of having flown well over 7,000,000 miles while carrying 300,000 passengers. not one single paying passenger has been hurt while travelling in these machines.the heracles has flown over a million miles. she and her sister craft were built specially to fly on the england to india route. two varieties were built. machines of the first variety, known as the western or heracles type, were detailed for the section between england and egypt; the others, known as the eastern or hannibal type, were designed for the section between egypt and india. the main difference between the two types is in the passenger accommodation. the western type normally carries thirty-eight passengers and a crew of four and the eastern type sixteen passengers. in the heracles type the freight compartment has a capacity of 250 cubic feet. for the hannibal type the figure is 500 cubic feet.all the machines have four engines, bristol jupiters, air-cooled and each developing 550 horse-power. the heracles type has jupiter x f.b.m. engines and the hannibal type jupiter xi engines.the wings are of metal construction, covered with fabric. the light aluminium alloy known as duralumin is chiefly used. the wings are fitted with the famous handley page slots, which add so much to safety in flying. the body of the machine is of almost circular cross section in shape and is in two parts. the front portion, which is metal-covered, contains the passengers’ saloons, the pilots’ cockpit and the luggage compartment. the rear portion is fabric-covered and carries the tail unit. the biplane tail unit has three rudders of all-metal construction.the main fuel tanks, holding some 500 gallons, are in the upper wing. the two pilots’ seats are right in the nose of the fuselage, with a small wireless room immediately behind. in the two passengers’ saloons seats are arranged four abreast in the western type, with a gangway in between. between the two saloons is the mail and luggage or freight compartment. the saloons have a double skin, which reduces the noise of the engines.the span of the wings of these machines is 130 feet, the length 89 feet 9 inches and the height 27 feet. when fully loaded they weigh 30,000 lb and carry a payload of 9,000 lb. both types cruise at 95-105 miles an hour.the heracles type has a maximum speed of 127
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