公开(公告)号：EP1478570A2

公开(公告)日：2004-11-24

申请号：EP03709001.6

申请日：2003-02-06

申请人： MOLLER INTERNATIONAL, INC.

发明人： MOLLER, Paul, S.

IPC分类号： B64C29/00

CPC分类号： B64C37/00 ,  B64C3/56 ,  B64C11/001 ,  B64C11/48 ,  B64C13/503 ,  B64C29/0033 ,  B64D27/06 ,  B64D31/06 ,  Y02T50/14

摘要： A VTOL vehicle including a fuselage with two foldable wings, two tiltable nacelles attached to the wings, a vertical stabilizer, a horizontal stabilizer, and two auxiliary thrusters. Each nacelle contains a system of vanes located at the rear opening thereof, and actuators are provided for extending and retracting the vanes in conjunction with nacelle tilting mechanisms to deflect the airflow over a predetermined range of angles from the horizontal. Each nacelle also contains two rotary engines, each of which directly drives a fan. The fans face each other and operate in counter-rotating directions at the same rotational speed. An alternative embodiment includes two additional nacelles attached to the fuselage instead of having the auxiliary thrusters. A redundant computerized flight control system maintains stability of the vehicle as it transitions from one flight mode to another.

公开(公告)号：EP1141530A1

公开(公告)日：2001-10-10

申请号：EP99963092.4

申请日：1999-12-14

申请人： MOLLER INTERNATIONAL, INC.

发明人： MOLLER, Paul, S.

IPC分类号： F02B53/00

CPC分类号： F02B53/00 ,  F01C1/22 ,  F01C21/06 ,  F02B55/06 ,  F02B55/12 ,  F02B2053/005 ,  F02B2075/027 ,  Y02T10/17

摘要： A charge cooled rotary engine includes a housing (204), a first end plate (206), and a second end plate (208). The housing and end plates combine to define a closed chamber (210). A rotor (202) disposed within the housing includes three flanks (215), a cylindrical hub (213), and a web (214) extending transversely from the hub and joining medial portions of the flanks to the hub. The web, flanks and hub form rotor cavities on opposite ends of the rotor. Inlets formed in the end plates for receiving a fuel/air charge terminate in entry ports (220, 232) facing the closed chamber. Distribution chambers (224, 236), formed in the end plates adjacent the entry ports, are open to the closed chamber. The entry ports directly communicate with the rotor cavities and are isolated from direct communication with any of the intake, compression and combustion chambers by the rotor flanks.

公开(公告)号：EP0513245A1

公开(公告)日：1992-11-19

申请号：EP91905941.0

申请日：1991-01-11

申请人： MOLLER INTERNATIONAL, INC.

发明人： MOLLER, Paul, S.

IPC分类号： B64C29

CPC分类号： B64C29/0025

摘要： Avion à décollage et à atterrissage verticaux comprenant un fuselage (10) présentant quatre nacelles (12, 14, 16 et 18), trois stabilisateurs verticaux (20, 22 et 24) ainsi qu'un stabilisateur horizontal (26) fixés au fuselage (10). Le fuselage (10) et les nacelles (12, 14, 16 et 18) sont des corps de sustentation configurés pour former conjointement un corps de sustentation aérodynamique coopérant avec le stabilisateur horizontal (26) afin de donner à l'avion une sustentation aérodynamique en vol vers l'avant. Chaque nacelle contient deux moteurs rotatifs (60 et 62) entraînant directement des soufflantes correspondantes (64, 66) se faisant face mutuellement et fonctionnant dans des sens de contre-rotation. Chaque nacelle (12, 14, 16 et 18) contient également un système d'aubes (82) situé au niveau de son ouverture arrière (58), ainsi que des dispositifs destinés à étendre et à rétracter les aubes (82). Un système de commande de vol informatisé à triple redondance maintient la stabilité de l'avion lorsqu'il passe d'un régime de vol à un autre, ainsi qu'en vol.

摘要翻译： 飞机起飞和垂直降落包括机身（10），其具有附连到机身4个吊舱（12，14，16和18），三个竖直稳定器（20，22和24）和一个水平稳定器（26）（10 ）。 所述机身（10）和机舱（12，14，16和18）被提升体构造成共同形成一个空气动力学提升体，其与水平稳定器（26）协作，以得到在飞行器气动升力 飞行前进。 每个机舱包含两个旋转马达（60和62），其直接驱动相应的鼓风机（64,66）彼此面对并且在相反的旋转方向上操作。 每个机舱（12,14,16和18）还包括位于其后部开口（58）处的叶片系统（82）以及用于延伸和缩回叶片（82）的装置。 具有三重冗余的计算机化的飞行控制系统保持了飞机从一个飞行状态转换到另一个飞行状态时的稳定性。

公开(公告)号：EP1141530B1

公开(公告)日：2007-10-17

申请号：EP99963092.4

申请日：1999-12-14

申请人： MOLLER INTERNATIONAL, INC.

发明人： MOLLER, Paul, S.

IPC分类号： F02B53/00 ,  F01C1/22 ,  F01C21/06

CPC分类号： F02B53/00 ,  F01C1/22 ,  F01C21/06 ,  F02B55/06 ,  F02B55/12 ,  F02B2053/005 ,  F02B2075/027 ,  Y02T10/17

摘要： A charge cooled rotary engine includes a housing (204), a first end plate (206), and a second end plate (208). The housing and end plates combine to define a closed chamber (210). A rotor (202) disposed within the housing includes three flanks (215), a cylindrical hub (213), and a web (214) extending transversely from the hub and joining medial portions of the flanks to the hub. The web, flanks and hub form rotor cavities on opposite ends of the rotor. Inlets formed in the end plates for receiving a fuel/air charge terminate in entry ports (220, 232) facing the closed chamber. Distribution chambers (224, 236), formed in the end plates adjacent the entry ports, are open to the closed chamber. The entry ports directly communicate with the rotor cavities and are isolated from direct communication with any of the intake, compression and combustion chambers by the rotor flanks.

公开(公告)号：EP1144249B1

公开(公告)日：2003-09-03

申请号：EP99972834.8

申请日：1999-12-10

申请人： MOLLER INTERNATIONAL, INC.

发明人： MOLLER, Paul, S.

IPC分类号： B64C29/02 ,  B64C27/20 ,  B64C39/02

CPC分类号： B64C39/024 ,  B64C29/02 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

摘要： A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct. A centrally positioned plate (112) has a plurality of rods (106), each pivotably connected between the plate (74) and a corresponding lever associated with each of the adjustable half troughs (44) so as to couple the adjustable half trough (44) in or out of the drive air steam according to the position of the plate (74), thereby providing control over the pitch and roll of the flying platform. The plate is driven by first and second motors responding to input control signals. The control signals also direct the yaw of the flying platform by selectively providing independent speed control to each of the clockwise and counter clockwise fan motors resulting in duct rotation in a clockwise or counter clockwise direction accordingly.

公开(公告)号：EP1144249A2

公开(公告)日：2001-10-17

申请号：EP99972834.8

申请日：1999-12-10

申请人： MOLLER INTERNATIONAL, INC.

发明人： MOLLER, Paul, S.

IPC分类号： B64C29/02

CPC分类号： B64C39/024 ,  B64C29/02 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

摘要： A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct. A centrally positioned plate (112) has a plurality of rods (106), each pivotably connected between the plate (74) and a corresponding lever associated with each of the adjustable half troughs (44) so as to couple the adjustable half trough (44) in or out of the drive air steam according to the position of the plate (74), thereby providing control over the pitch and roll of the flying platform. The plate is driven by first and second motors responding to input control signals. The control signals also direct the yaw of the flying platform by selectively providing independent speed control to each of the clockwise and counter clockwise fan motors resulting in duct rotation in a clockwise or counter clockwise direction accordingly.

公开(公告)号：EP0513245B1

公开(公告)日：1995-11-22

申请号：EP91905941.0

申请日：1991-01-11

申请人： MOLLER INTERNATIONAL, INC.

发明人： MOLLER, Paul, S.

IPC分类号： B64C29/00

CPC分类号： B64C29/0025

摘要： A VTOL aircraft including a fuselage (10) with four nacelles (12, 14, 16, and 18), three vertical stabilizers (20, 22, and 24) and a horizontal stabilizer (26) attached to the fuselage (10). The fuselage (10) and the nacelles (12, 14, 16, and 18) are lifting bodies that are configured to jointly form an aerodynamic lifting body which cooperates with the horizontal stabilizer (26) to provide aerodynamic lift to the aircraft in forward flight. Each nacelle contains two rotary engines (60 and 62) directly driving corresponding fans (64 and 66) which face each other and operate in counter-rotating directions. Each nacelle (12, 14, 16, and 18) also contains a system of vanes (82) located at the rear opening (58) thereof, and devices for extending and retracting the vanes (82). A triple redundant computerized flight control system maintains the stability of the aircraft as it transitions from one flight regime to another as well as in flight.

摘要翻译： VTOL飞机包括具有四个机舱（12,14,16和18），三个垂直稳定器（20,22和24）以及附接到机身（10）的水平稳定器（26）的机身（10）。 机身（10）和发动机舱（12,14,16和18）是提升体，其被配置为共同形成空气动力提升体，该提升体与水平稳定器（26）协作以向前飞行中的飞机提供空气动力学升力 。 每个机舱包含两个直接驱动相应的风扇（64和66）的旋转式发动机（60和62），这些风扇相互面对并在相反的旋转方向上运行。 每个机舱（12,14,16和18）还包含位于其后开口（58）处的叶片系统（82）以及用于延伸和缩回叶片（82）的装置。 三重冗余的计算机化的飞行控制系统保持飞机从一个飞行状态转换到另一个飞行状态时的稳定性。