US3366347A - Lifting device employing aerodynamic lift - Google Patents

Lifting device employing aerodynamic lift Download PDF

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Publication number
US3366347A
US3366347A US512119A US51211965A US3366347A US 3366347 A US3366347 A US 3366347A US 512119 A US512119 A US 512119A US 51211965 A US51211965 A US 51211965A US 3366347 A US3366347 A US 3366347A
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US
United States
Prior art keywords
air
lifting device
screws
propulsion
girder
Prior art date
Legal 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 - Lifetime
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US512119A
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English (en)
Inventor
Soulez-Lariviere Jean
Current 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.)
Nord Aviation Societe Nationale de Constructions Aeronautiques
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Nord Aviation Societe Nationale de Constructions Aeronautiques
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0091—Accessories not provided for elsewhere
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/0075—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors the motors being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
    • B64D1/22—Taking-up articles from earth's surface

Definitions

  • the present invention relates to a lifting device employing aerodynamic lift, and more particularly to a tripod lifting device which is completely faired.
  • lifting devices which have the essential function of lifting from the ground a generally heavy and bulky load, but these devices most frequently employ, for reasons of efiiciency, a propulsion device which is derived from the helicopter, and this device usually comprises a large lifting screw.
  • the object of the present invention is a lifting device with completely faired air-screws, eliminating all danger, both for the air-screw blades and for the personnel in charge of the lifting operations on the ground, and which, by virtue of a particular arrangement of its control station, provides a perfectly clear panoramic view for the purpose of manoeuvres on the ground and during flight, under particularly ditficult conditions.
  • a propulsion unit comprising a number of faired airscrews is arranged at each extremity of a first girder, each unit being capable of pivoting about a common longitudinal axis of the said first girder, which is coupled rigidly and perpendicularly at its central points to a second girder which forms a T-structure with the first girder.
  • the air-screws are arranged inside each of the two units in such manner that their thrusts are oriented in the same direction, the axes of rotations of the air-screws being parallel to each other and located at equal distance and perpendicularly to the said common rotational axis of the said units.
  • Rotary power and thrust generators turbo-propulsion units for example, are mounted alongside each other in the interior of each main unit, the axes of rotation of the said generators being located in such manner as to intersect the said common pivotal axis and to remain parallel to the axes of the air-screws, the residual reaction thrust having the same sense and direction as the thrust of the air-screws.
  • the structures of the first girder and the second girder are of openwork cross-bracing.
  • a single central mechanical coupling is provided between the generators and the air-screws.
  • Three retractable under-carriage legs of considerable height two of which are located forward, close to the extremities of the transverse girder, and the third at the free extremity of the longitudinal girder, carry wheels elastically coupled to the said legs, the two front wheels being driving and steering wheels.
  • a control cabin is arranged between the rear leg and the longitudinal girder, the field of vision being open in all directions, towards the front, to the sides, upwards and downwards, and a control station permitting action to be effected by differential and overall variation on the pitch of the air-screws and on the speeds of the turbo-prop engines.
  • the fairing of the air-screws is arranged so as to house the whole of the fuel.
  • the arrangement of the under-carriage legs is such that the supporting points of the two front legs on the ground are located in front of and towards the exterior of the articulation points, so as to ensure a maximum passage track and on the other hand the largest possible base of lift on the ground.
  • FIG. 1 is a perspective view of a tripod lifting device with aerodynamic lift, in the operating position on the ground;
  • FIG. 2 is a perspective view of one of the aerodynamic units of the machine shown in FIG. I;
  • FIG. 3 is a perspective view of the machine of FIG. 1 in flight, without load, and with the under-carriage legs retracted.
  • the triangulated lattice structure of a lifting device with three legs comprises (see FIG. 1) on the one hand a transverse girder 1a having its line of orientation y y' intersected perpendicularly at O by a plane of symmetry defined by the orthogonal axes y y' and Z and 2' and each receiving at its extremities a propulsion set 2d and 2g, which can pivot in the direction of the arrow about y y while their axis of symmetry can occupy indifferently all the positions comprised between two adjacent orientations, one parallel to the axis x x' and the other parallel to the axis Z0, 1' and further a longitudinal girder 112 having the line of orientation x x rigidly coupled to the cross-girder 1a and receiving at its free extremity a control cabin 3.
  • the assembly is completed by two under-carriage front legs 4g, 4d, pivoted about the axes x x and x parallel and symmetrically disposed with respect to x x and by a rear under-carriage leg 5 articulated about an axis y y' parallel to y y'
  • These three legs can be folded back in flight in the directions of the arrows f f so as to come into the position shown in FIG. 3.
  • the front legs are inclined so as to move the supporting points B and B towards the front and towards the exterior of the vertical line of the fixing points, so as to increase on the one hand the surface of passageway under the machine and on the other hand the sides of the lifting triangle zx/3-[3'.
  • a hook 6 and a winch 7 located close to O are provided for hooking the load 10, the trimming of which can be completed by slings 3.
  • FIG. 2 there is shown the left-hand propulsion group 2g of the machine, but it is simple to deduce from this the right-hand propulsion set 2d, which is symmetrical to it.
  • a single central transmission shaft 11a located on the axis y y' receives the rotary movement of the shafts of the turbines of the prop units 12a, 12b (left-hand) and 12c, 12d (right-hand) and transmits this motion to the air-screws 13a, 13b (left-hand) and 13c, 13d (right-hand), through the intermediary of the gearboxes 14g (left-hand) and 14d (right-hand).
  • Pivots 15g (left-hand) and 15d (right-hand) having their axes in y y' enable the propulsion units to be pivoted, for
  • Stationary flight is obtained when the general resultant of the thrust reactions with the force of gravity is zero.
  • Flight in longitudinal movement if obtained by simultaneous inclination to the vertical of the two resultants of the thrust reactions of each propulsion group.
  • This inclination has the effect of creating a non-vertical common resultant, for example longitudinal, resulting from the combination of the force of gravity with the said resultants.
  • Control means 100 regulates the pitch of air-screw or propeller 13a and control means 161 regulates the pitch of air-screw or propeller 13b.
  • the two symmetrical propellers in right-hand propulsion set 2d are regulated by another pair of similar control means.
  • the speed of all four turbo-propulsion sets is regulated by a single control means 102, for instance by a foot pedal (not shown).
  • a pilot acts simultaneously on control means 101 and the complementary control means to the opposite propulsion group or on control means 100 and its complementary control means to the opposite propulsion group.
  • the speed of all engines is regulated by the single control means 102.
  • FIG. 3 which shows the machine during convoying without load, the legs 4g, 4d and 5 have been raised by means of suitable hydraulic jacks in order to reduce the aerodynamic drag.
  • the axes of symmetry of the propulsion groups have been inclined to the vertical, in order to permit of lifting, together with propulsion, which is carried out in horizontal flight. It is quite certain that this inclination can varied, depending on whether the machine is unladenor whether it carries a load, by virtue of the variation of the forces produced and of the effect of air resistance on the load.
  • the visibility of the pilots station is excellent and gives a simultaneous view of the loading and the operating controls, together with the whole of the machine and of the devices which control its manoeuvres.
  • a lifting device comprising means for lifting from the ground and moving with complete safety during flight a heavy and bulky load, said means comprising a structure, a plurality of completely faired air-screws, a piloting device in which the visibility of the pilot is substantially ensured in all directions, and a hoisting device, said air-screws divided into two propulsion groups respectively at the two extremities of a first transverse girder of lattice construction, said piloting device comprising a cabin at the free extremity of a second longitudinal girder of lattice construction, the other extremity of which is rigidly fixed to the centre of the first said transverse girder, the assembly of the two girders having the form of a T.
  • each of said propulsion groups is adapted to rotate about a common axis of rotation along the first said girder, and comprises at least two air-screws wholly encased by a common hood on their periphery, and at least two turboprop propulsion units, said two air-screws having their individual axes of rotation parallel and disposed on each side of said common axis of rotation, and the axes of symmetry of said two propulsion groups passing through said common axis of rotation.
  • piloting device comprises means for simultaneously controlling the inclination with respect to the vertical of the axis of symmetry of each of the propulsion groups, means for difierentially controlling, one with respect to the other, the individual inclination of the two axes of symmetry of the two groups with respect to the vertical, means for controlling the speeds of the turbo-propulsion units, and means for transmitting orders from the cabin to the mobile propulsion groups, passing through the zone of said common axis of rotation.
  • a lifting device as claimed in claim 4 comprising a common transmission shaft centered on said common axis of rotation and transmitting the total power of all the turbo-propulsion units of the two sets to two gearboxes located respectively on each group, said gear-boxes each transmitting their movement to the two air-screws of the group.
  • a lifting device comprising means for lifting from the ground and moving with complete safety in flight a heavy and bulky load, said means comprising a structure, a plurality of completely-faked air-screws, a piloting device from which the visibility of the pilot is substantially ensured in all directions, and a lifting device, in which the air-screws are divided into two propulsion groups respectively at the two extremities of a first transverse girder of lattice construction, the piloting device comprising a cabin at the free extremity of a second longitudinal girder of lattice construction, the other extremity of which is rigidly fixed to the centre of said first transverse girder, the assembly of the two girders having the form of a T and comprising three supporting legs located respectively at each extremity of the arms of the T, said legs carrying pivoted wheels and being foldable into a retracted position by means of an articulation in the plane of the T when the machine is convoying without load.
  • a lifting device comprising means for lifting from the ground and moving with complete safety in flight a heavy and bulky load, said means comprising a structure, a plurality of completely-vetted air-screws, a piloting device from which the visibility of the pilot is substantially ensured from all directions, said air-screws divided into two propulsion groups respectively at the two extremities of a first transverse girder of lattice construction, the piloting device comprising a cabin at the free extremity of a second longitudinal girder of lattice construction, the other extremity of which is rigidly fixed to the centre of said first transverse girder, the assembly of the two girders having the form of a T and comprising three supporting legs located respectively at each extremity of the arms of the T, said legs carrying pivoted wheels and being foldable into a retracted position by means of an articulation in the plane of the T when the machine is convoying without load, the legs located at the extremities of said first girder being situated at the front of the machine and their wheels
  • each of said propulsion groups is adapted to rotate about a common axis of rotation along the first said girder, and said hoisting device further comprising a winch, a cable and a hook located substantially in the vertical line of the centre of gravity of the lifting device and in the vertical plane of said common axis of rotation.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Jib Cranes (AREA)
  • Sampling And Sample Adjustment (AREA)
US512119A 1964-12-09 1965-12-07 Lifting device employing aerodynamic lift Expired - Lifetime US3366347A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR998058A FR1427083A (fr) 1964-12-09 1964-12-09 Engin de levage sustenté aérodynamiquement

Publications (1)

Publication Number Publication Date
US3366347A true US3366347A (en) 1968-01-30

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US512119A Expired - Lifetime US3366347A (en) 1964-12-09 1965-12-07 Lifting device employing aerodynamic lift

Country Status (4)

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US (1) US3366347A (de)
DE (1) DE1456061C3 (de)
FR (1) FR1427083A (de)
GB (1) GB1108240A (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003074924A1 (de) * 2002-03-06 2003-09-12 Aloys Wobben Fluggerät mit einer mehrzahl von hub-und schubrotoren
GB2419122A (en) * 2004-10-05 2006-04-19 Alexander Stuart Hardy Vertical take-off and landing aircraft
US20100012769A1 (en) * 2006-07-27 2010-01-21 Alber Mark R Aerodynamic integration of a payload container with a vertical take-off and landing aircraft
CN102491202A (zh) * 2011-12-05 2012-06-13 中联重科股份有限公司 支腿装置和行车式起重机
US20150021430A1 (en) * 2012-02-15 2015-01-22 Aurora Flight Sciences Corporation System, apparatus and method for long endurance vertical takeoff and landing vehicle
US20160090179A1 (en) * 2014-09-29 2016-03-31 The Boeing Company Apparatus, system, and method for flying an aircraft
CN109789927A (zh) * 2016-09-19 2019-05-21 空中机器人有限及两合公司 用于空运物品的装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102013108204A1 (de) * 2013-07-31 2015-02-05 E-Volo Gmbh Bergungsvorrichtung für die Verwendung an einem Fluggerät und Fluggerät, insbesondere Multicopter
CN107745814B (zh) * 2017-11-15 2023-12-22 航宇救生装备有限公司 一种用于空投系统着陆的主动防翻控制机构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2997258A (en) * 1957-01-22 1961-08-22 August C Purpura Helicopter type aircraft
US3170530A (en) * 1961-03-23 1965-02-23 Richard W Black Mobile air supported vehicle
US3176939A (en) * 1963-01-10 1965-04-06 United Aircraft Corp Helicopter pod supporting device

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2997258A (en) * 1957-01-22 1961-08-22 August C Purpura Helicopter type aircraft
US3170530A (en) * 1961-03-23 1965-02-23 Richard W Black Mobile air supported vehicle
US3176939A (en) * 1963-01-10 1965-04-06 United Aircraft Corp Helicopter pod supporting device

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2003074924A1 (de) * 2002-03-06 2003-09-12 Aloys Wobben Fluggerät mit einer mehrzahl von hub-und schubrotoren
US20050061910A1 (en) * 2002-03-06 2005-03-24 Aloys Wobben Aircraft
AU2003218686B2 (en) * 2002-03-06 2007-04-26 Aloys Wobben Aircraft
CN100343120C (zh) * 2002-03-06 2007-10-17 艾劳埃斯·乌本 飞行器
US7364114B2 (en) 2002-03-06 2008-04-29 Aloys Wobben Aircraft
GB2419122A (en) * 2004-10-05 2006-04-19 Alexander Stuart Hardy Vertical take-off and landing aircraft
US8876057B2 (en) * 2006-07-27 2014-11-04 Sikorsky Aircraft Corporation Aerodynamic integration of a payload container with a vertical take-off and landing aircraft
US20100012769A1 (en) * 2006-07-27 2010-01-21 Alber Mark R Aerodynamic integration of a payload container with a vertical take-off and landing aircraft
CN102491202A (zh) * 2011-12-05 2012-06-13 中联重科股份有限公司 支腿装置和行车式起重机
US20150021430A1 (en) * 2012-02-15 2015-01-22 Aurora Flight Sciences Corporation System, apparatus and method for long endurance vertical takeoff and landing vehicle
US9540101B2 (en) 2012-02-15 2017-01-10 Aurora Flight Sciences Corporation System, apparatus and method for long endurance vertical takeoff and landing vehicle
US9682774B2 (en) 2012-02-15 2017-06-20 Aurora Flight Sciences Corporation System, apparatus and method for long endurance vertical takeoff and landing vehicle
US20160090179A1 (en) * 2014-09-29 2016-03-31 The Boeing Company Apparatus, system, and method for flying an aircraft
US10279902B2 (en) * 2014-09-29 2019-05-07 The Boeing Company Apparatus, system, and method for flying an aircraft
CN109789927A (zh) * 2016-09-19 2019-05-21 空中机器人有限及两合公司 用于空运物品的装置
US11148808B2 (en) 2016-09-19 2021-10-19 Airrobot Gmbh & Co. Kg Device for airlifting an object

Also Published As

Publication number Publication date
DE1456061A1 (de) 1970-01-15
DE1456061C3 (de) 1974-07-11
FR1427083A (fr) 1966-02-04
GB1108240A (en) 1968-04-03
DE1456061B2 (de) 1973-11-29

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