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81. 发明专利

CZ20022622A3 Acrobatic airplane 未知
公开(公告)号：CZ20022622A3
公开(公告)日：2003-06-18
申请号：CZ20022622
申请日：2001-01-31
申请人： WADLEIGH JOHN
发明人： WADLEIGH JOHN
IPC分类号： B64C39/04 , B64D27/08 , B64D27/10 , B64D33/00 , F01M11/06
摘要： An improved aerobatic aircraft design having a first engine located in the nose portion of the fuselage and a second engine located in the tail portion of the fuselage. The thrust components of both the first and second engines are coaxial along the long axis of the fuselage. Both engines can individually provide sufficient power for the aircraft to takeoff, maintain altitude, and/or land.

83. 发明专利

DE19818730A1 Aircraft power plant with turbocharged reciprocating piston internal combustion engine 未知
公开(公告)号：DE19818730A1
公开(公告)日：1999-11-04
申请号：DE19818730
申请日：1998-04-27
申请人： KELLER HANNES
发明人： KELLER HANNES
IPC分类号： B64D33/02 , B64D27/08 , B60K13/02
摘要： The axis of the combustion air inlet (28) for the aircraft engine turbocharger (26) is parallel to the axis of the propeller (22), and the propeller blades (42) cover the air inlet in the radial direction. The axial distance between the path of the propeller blades and an air inlet (32) in the cowl (18) enclosing the internal combustion engine (20) is small in comparison with the diameter of the turbocharger's air inlet, and is in the region of 5 centimeters.

84. 发明专利

DE4112659C2 未知
公开(公告)号：DE4112659C2
公开(公告)日：1999-04-29
申请号：DE4112659
申请日：1991-04-18
申请人： GNIESER GMBH AUTO TECHNIK
发明人： EIERMANN DANKWART , FISCHER MANFRED
IPC分类号： B64C31/02 , B64C31/024 , B64D33/10 , B64D27/08 , B64D33/04 , B64D35/00 , F01N7/08 , F02B53/14 , F02B61/04 , F02B67/06 , F02M35/12

85. 发明专利

AU6809598A Multi-purpose aircraft 未知
公开(公告)号：AU6809598A
公开(公告)日：1998-07-16
申请号：AU6809598
申请日：1998-05-25
申请人： GEVERS DAVID E
发明人： GEVERS DAVID E
IPC分类号： B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C7/00 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/02 , B64C39/00 , B64D27/00 , B64D27/02 , B64D27/08 , B64D29/02 , B64D29/04 , B64D35/00 , B64D35/04

86. 发明专利

AU687466B2 Multi-purpose aircraft 未知
公开(公告)号：AU687466B2
公开(公告)日：1998-02-26
申请号：AU8120294
申请日：1994-08-24
申请人： GEVERS DAVID E
发明人： GEVERS DAVID E
IPC分类号： B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/02 , B64D27/00 , B64D27/02 , B64D27/08 , B64D29/04 , B64D35/04 , B64D25/08
摘要： Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) (24,25) with a belt drive system (84,99) for turning wing-situated propellers (8,9); compound landing gear integrating ski (29,114), pontoon and wheel (18,19,21) subcomponents; pivotal mounting armatures (6,7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure (14,15) featuring extendable wing panels (4,5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

87. 发明专利

CA2170282A1 MULTI-PURPOSE AIRCRAFT 未知
公开(公告)号：CA2170282A1
公开(公告)日：1995-03-02
申请号：CA2170282
申请日：1994-08-24
申请人： GEVERS DAVID E
发明人： GEVERS DAVID E
IPC分类号： B64C1/00 , B64C3/38 , B64C3/54 , B64C3/56 , B64C25/52 , B64C25/54 , B64C25/66 , B64C35/00 , B64C35/02 , B64D27/00 , B64D27/02 , B64D27/08 , B64D29/04 , B64D35/04 , B64C29/00
摘要： Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine( s) (24, 25) with a belt drive system (84, 99) for turning wing-situated propell ers (8, 9); compound landing gear integrating ski (29, 1 14), pontoon and wheel (18, 19, 21) subcomponents; pivotal mounting armatures (6, 7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a co mpound wing structure (14, 15) featuring extendable wing panels (4, 5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enj oy several safety advantages over conventional multi-engine aircraft and will be capabl e of modifications during flight which permit landings o n any of snow, hard surfaces (runways) and water.

88. 发明专利

DE4237642A1 VSTOL aircraft with fuselage and drive - has no movable steering parts, with pilot's steering by weight displacement 未知
公开(公告)号：DE4237642A1
公开(公告)日：1994-05-11
申请号：DE4237642
申请日：1992-11-07
申请人： HAERTEL MARTIN DIPL KAUFM
发明人： HAERTEL MARTIN
IPC分类号： B64C17/02 , B64C29/00 , B64C29/02 , B64D27/24 , B64F1/00 , B64F1/16 , B64C1/00 , B64C15/12 , B64D27/08
摘要： The aircraft starts with the fuselage vertical and transits into horizontal position with increasing speed, but lands with the fuselage again vertical. The drive (5) is typically located in the fuselage axis (12). In the top/front aircraft half is located a propeller (21) changing the flight line by positional changes. The aircraft may have several propellers which are coaxial. It is driven by an accumulator battery or an electric motor. ADVANTAGE - Lightweight design, lowest possible air displacement, low air resistance and consequently high speed.

89. 发明专利

DE3706379A1 未知
公开(公告)号：DE3706379A1
公开(公告)日：1988-09-08
申请号：DE3706379
申请日：1987-02-27
申请人： PORSCHE AG
发明人： BROOCK ULRICH VON DIPL ING DR
IPC分类号： B64C27/00 , B64C27/12 , B64D27/08 , B64D27/02
摘要： A suspension system having elastic bearings for a drive assembly of a helicopter is described that has a belt drive that is arranged between an output shaft and a main rotor. This belt drive comprises a first drum that is connected with the output shaft and a second drum that is connected with an angular drive for the main rotor. Both drums are connected with respect to the drive by a tensionable belt. The suspension system comprises at least two bearings in the area of the belt drums as well as another bearing at the end of the assembly 1 that faces away from the belt drums. The three bearings have a spring rigidity coordination that controls the permitted rigid-body movements of the assembly. This coordination is such that limited swivel movements of the assembly can be carried out around the longitudinal axes of the belt drums as well as parallel lifting movements of the assembly can be carried out in vertical direction.

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