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91. 发明专利

DE3318002A1 Flying vehicle having a lifting-body configuration 未知
公开(公告)号：DE3318002A1
公开(公告)日：1984-11-22
申请号：DE3318002
申请日：1983-05-18
申请人： PAHLING WALTER DIPL ING
发明人： PAHLING WALTER DIPL ING
IPC分类号： B64B1/20 , B64C1/34 , B64C39/10
摘要： The subject-matter of the invention is a flying vehicle having a "lifting-body" configuration. This allows the use of dynamic and static lift if the enclosed volume is filled with helium or hot gas. The exhaust gas of the aircraft motor, for example, can be used as the hot gas. The above-mentioned configuration is intended to be implemented by means of a very light supporting structure consisting of CFC tubes and film stretched between them. The proposed flying vehicle offers enormous safety advantages (in addition to low production costs) over conventional (ultra-light) sport aircraft as a result of: - extremely short take off and slow flying characteristics, - maintenance of the flying capability and control ability even if one type of lift is lost, and - protection of the pilot against injuries in the event of a crash, as a result of the air-cushion effect. A car is adequate as transportation means, because of the dismantling capability.

92. 发明专利

ES526099A0 未知
公开(公告)号：ES526099A0
公开(公告)日：1984-08-16
申请号：ES526099
申请日：1983-09-29
申请人： JONES ANDREW WIL , MERRY RAYMOND
IPC分类号： B64C1/34 , B64C31/02 , B64C31/036 , B64D17/00 , B64D17/02 , B64B1/42
摘要： PCT No. PCT/GB83/00242 Sec. 371 Date May 23, 1984 Sec. 102(e) Date May 23, 1984 PCT Filed Sep. 28, 1983 PCT Pub. No. WO84/01346 PCT Pub. Date Apr. 12, 1984.A free flyable structure includes a wing formation (2) including an inflatable container of such form that when it is inflated the container (2) has an aerofoil shaped cross-section whereby relative displacement between the container and surrounding air enables free flight conditions. A substantially rigid means (19) carries the pay load from the wing formation (2). Flight path control of the flyable structure includes producing relative displacement between the load and wing formation. Additional flight path controls may be used. A canard wing assembly (82) is suggested. The structure is power driven and in the disclosure a power unit (85) having a propeller (86) is proposed.

93. 发明专利

AU2070883A FREE FLYABLE STRUCTURE 未知
公开(公告)号：AU2070883A
公开(公告)日：1984-04-24
申请号：AU2070883
申请日：1983-09-28
申请人： JONES ANDREW WIL , MERRY RAYMOND
发明人： WILFRID JONES ANDREW , RAYMOND MERRY
IPC分类号： B64C1/34 , B64C31/02 , B64C31/036 , B64D17/00 , B64D17/02
摘要： PCT No. PCT/GB83/00242 Sec. 371 Date May 23, 1984 Sec. 102(e) Date May 23, 1984 PCT Filed Sep. 28, 1983 PCT Pub. No. WO84/01346 PCT Pub. Date Apr. 12, 1984.A free flyable structure includes a wing formation (2) including an inflatable container of such form that when it is inflated the container (2) has an aerofoil shaped cross-section whereby relative displacement between the container and surrounding air enables free flight conditions. A substantially rigid means (19) carries the pay load from the wing formation (2). Flight path control of the flyable structure includes producing relative displacement between the load and wing formation. Additional flight path controls may be used. A canard wing assembly (82) is suggested. The structure is power driven and in the disclosure a power unit (85) having a propeller (86) is proposed.

94. 发明专利

PT77425A FREE FLYABLE STRUCTURE 未知
公开(公告)号：PT77425A
公开(公告)日：1983-10-01
申请号：PT7742583
申请日：1983-09-29
申请人： JONES ANDREW WIL , MERRY RAYMOND
IPC分类号： B64C31/02 , B64C1/34 , B64C31/036 , B64D17/00 , B64D17/02 , B64C
摘要： PCT No. PCT/GB83/00242 Sec. 371 Date May 23, 1984 Sec. 102(e) Date May 23, 1984 PCT Filed Sep. 28, 1983 PCT Pub. No. WO84/01346 PCT Pub. Date Apr. 12, 1984.A free flyable structure includes a wing formation (2) including an inflatable container of such form that when it is inflated the container (2) has an aerofoil shaped cross-section whereby relative displacement between the container and surrounding air enables free flight conditions. A substantially rigid means (19) carries the pay load from the wing formation (2). Flight path control of the flyable structure includes producing relative displacement between the load and wing formation. Additional flight path controls may be used. A canard wing assembly (82) is suggested. The structure is power driven and in the disclosure a power unit (85) having a propeller (86) is proposed.

95. 发明专利

NL6817355A 未知
公开(公告)号：NL6817355A
公开(公告)日：1969-06-06
申请号：NL6817355
申请日：1968-12-04
IPC分类号： B64B1/00 , B64B1/20 , B64C3/30 , B64C39/10 , B64D9/00 , B64C1/34 , B64B1/06
摘要： 1,245,432. Airship. AEREON CORP. 4 Dec., 1968 [4 Dec., 1967], No. 57692/68. Heading B7W. [Also in Division B8] An airship has a hull 2 with a delta-shaped platform and a longitudinal section approximately that of an airfoil, the maximum lateral dimension of the hull being less than the maximum longitudinal dimension, and a gas space inside the hull and a separate cargo compartment 94 containing cargo-suspending equipment 76, itself suspended from the hull. At the rear of leading edges 6, 8 are provided fixed stabilizing surfaces in the form of end plates 10, 12 cambered inwards towards the top with control surfaces (18) (Fig. 4, not shown), trim tabs (20) and landing wheels 22. Four turboprop engines 28 are mounted at the rear and there is a control station 52 in the centre, for rearward taxi-ing, reached by a corridor 38. Spoiler flap assemblies 30 including upper and lower spoiler flaps are provided along the stern. In the lower half of the shell are provided openings 60, 62, for example, through which pass retractable landing wheels 64, 66 and which are closable by doors 69. Each wheel assembly is permitted to swivel freely to facilitate cross-wind landing. At suspension points at the end of the rigid horizontal beam 82, cables 88, 90 support the cover 74, 76 of the cargo compartment and the lower half shell 36 of the body. Cables 92 are connected between suspension point 84 and various points on the upper half shell 34. The cargo compartment 94 is provided with longitudinally-extending rails 96 for suspending containers, such as large trailers (see Division B8). The interior of nose 4 is separated from the main gas space by a bulkhead 114 to provide a flight station with decks 116, 118. Keel members 136, 138 extend between bulk-heads 32 and 140 and form a Y- keel transmitting the engine thrust to the cargo compartment. The leading edges 6, 8 have longitudinal stiffeners 142 and ring stiffeners 144, the opposite ends of which are connected by columns 146. Diagonal cables 148 connect opposite intersections of the columns 146 and ring stiffeners 144. The hull consists of metal panels (150), Figs. 6, 10 (not shown), with perpendicular sections (152) which are clamped together by a tubular member (154). The panels are connected to the structure 82 by cables 92 attached to the intersections. Fuel compartments 164 are provided in which fuel containers are suspended also from rails.

96. 发明专利

NL6710819A 未知
公开(公告)号：NL6710819A
公开(公告)日：1968-02-06
申请号：NL6710819
申请日：1967-08-04
IPC分类号： B64C1/34 , E04H15/20 , F02K7/00

97. 发明专利

LU54262A1 未知
公开(公告)号：LU54262A1
公开(公告)日：1967-12-06
申请号：LU54262
申请日：1967-08-07
IPC分类号： B64C1/34 , E04H15/20 , F02K7/00

98. 发明专利

GB1090962A Inflatable structures 未知
公开(公告)号：GB1090962A
公开(公告)日：1967-11-15
申请号：GB436664
申请日：1964-02-01
申请人： DUNLOP CO LTD
发明人： MARTIN ERWIN HERBERT ERHARD , THOMSON RICHARD NOEL , NORBURY DONALD
IPC分类号： B64C1/34 , B64C29/00 , B64D33/02 , F02C7/042
摘要： 1,090,962. Inflatable aircraft engine intake. DUNLOP CO. Ltd. Jan. 18, 1965 [Feb. 1, 1964], No. 4366/64. Heading B7G. [Also in Division F1] An aircraft engine air intake, e.g. for a jet lift engine, comprises an inflatable envelope 4 supported on one or more inflatable tubes. In one embodiment a single toroidal inflatable tube 5 is used, the inflation pressure increasing its diameter to extend the envelope from an annular pocket 3 in the fuselage radially outwardly to the position shown. The inflated shape of the envelope is determined by the shape of inextensible webs 11 and the inflated diameter of the tube is limited by circumferential cords 9 and by plies 7, 8, the bias angle of whose cords reduces on inflation from an initial 78 degrees to a stable 58 degrees 44 minutes. The inflation pressures may be 5 p.s.i. for the envelope and 30 p.s.i. for the tube. In another embodiment (Fig. 5, not shown) the envelope 4 is attached to inflatable U-tubes (30), the limbs (33, 34) of which are connected by webs (35), and the envelopes and tubes are retracted into the pocket (3) by resilient bands (36), which may be inclined in the circumferential direction so that the tubes overlap when deflated. In a further embodiment (Fig. 4, not shown) telescoping metal tubes (21, 22) connected by plates (23) are extended by air pressure and retracted by return springs. The envelope is fixed to webs (25) and partially covered by curved plates (24) fixed to the plates (23) and arranged to cover the pocket (3) when the envelope is deflated. In all embodiments retraction may be assisted by the application of a vacuum.

99. 发明专利

FR1189904A 未知
公开(公告)号：FR1189904A
公开(公告)日：1959-10-08
申请号：FR1189904D
申请日：1957-01-25
申请人： GOODYEAR AIRCRAFT CORP
IPC分类号： B64C1/34 , B64C3/30

100. 发明专利

GB811477A Aircraft having inflatable members 未知
公开(公告)号：GB811477A
公开(公告)日：1959-04-08
申请号：GB55857
申请日：1957-01-07
申请人： GOODYEAR AIRCRAFT CORP
IPC分类号： B03B9/00 , B04C5/24 , B04C9/00 , B64C1/34 , B64C3/30 , C03C1/02
摘要： 811,477. Inflatable components for aircraft. GOODYEAR AIRCRAFT CORPORATION. Jan. 7, 1957 [Feb. 10, 1956], No. 558/59. Class 4. An aircraft wherein the fuselage, wings and tail unit may be inflated for use and deflated and packed into a comparatively small space for storage or transport comprises a fuselage 1 consisting of an inflated internally unsupported envelope of airtight rubberised fabric provided at its forward end with patches 19 and cables 23 for the attachment of a frame 2 shaped to fit the fuselage. An inflatable pilots' seat 3 having a base 18 and side walls 17 connected by a seat panel of fabric also carries patches 19 and cable attachments to the frame 2, said frame having rear extensions 24 and 25 to which are secured rigid struts 27 supporting an inflated wing,4. Further supports for the wing are a tube 26 secured to frame 2 and anchored by a cable 30 to an arm 29 forming part of a framework 12 secured to the top of the fuselage to provide a mounting for an engine 11. A tail unit consists of an inflatable fin 6 secured to the fuselage and a tail plane 8 by straps 36 and 38 and a rudder 7 and elevator 9 secured to their respective fixed surfaces by straps 39 which act also as hinges, though conventional hinges may be used. Ailerons 5 are mounted on the wings and all moving surfaces are operated from a control column 44 and rudder bar 45 by cable control runs such as 47, 54 and 61. The fuselage is inflated to a lower pressure than the wing and tail unit elements, all of which are interconnected to safeguard against a sudden drop in pressure in one component, though an engine driven compressor may be provided to maintain internal pressure at an optimum valve. The components of the wing and tail unit and the pilots seat may be individually constructed in the manner shown in Fig. 6 wherein the wing is formed from upper and lower elements 69 and 70 and a spar member .71 each constructed from sealed panels connected by flexible ties 76. The control surfaces may be formed as a shaped envelope with opposite surfaces connected by ties having lengths which determine the sectional contour of the surfaces. Part of the aileron operating mechanism is shown at 65, 67 and 68. Other aircraft layouts are shown wherein the pilot may be housed within the upper surface of the wing in a prone or sitting position and the fuselage may be formed with twin booms. Specifications 691,455 [Group X] and 765,996 are referred to.

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