公开(公告)号：US3507461A

公开(公告)日：1970-04-21

申请号：US3507461D

申请日：1967-06-16

Applicant: VLM CORP THE

Inventor： ROSTA WILLIAM N

IPC: B64C39/00 ,  B64C27/20 ,  B64C27/46 ,  B64C27/54

CPC classification number: B64C39/001 ,  B64C27/08

公开(公告)号：US3582023A

公开(公告)日：1971-06-01

申请号：US3582023D

申请日：1969-07-23

Applicant: VLM CORP THE

Inventor： ROSTA WILLIAM N ,  MAXWELL RUSSELLE L

IPC: B64C27/20 ,  B64C29/00

CPC classification number: B64C27/20

Abstract: A rotary wing aircraft includes a central fuselage and a rotor consisting of an inner annular hub rotatably supported on and encircling the fuselage, radially extending radial blades and an outer supporting ring. The rotor is adapted to be driven by a turbine device associated with the rotor outer ring and an outer track nonrotatably attached to the fuselage. Each rotor blade is attached to a radially disposed, rotatable spindle in the hub structure; and pitch control arms are fixed to these spindles for controlling the rotation of the spindles and, therefore, the pitch of the attached rotor blades. An annular, pneumatically controlled bellows system, mounted on the fuselage concentric with the hub selectively controls the oscillation of the pitch control arms and thereby provides collective and cyclic pitch control for the rotor blades. In a rotary wing aircraft, such as a helicopter, it is conventional to provide means for changing the pitch of the rotor blades for control of the aircraft. The changing of the pitch of each of the rotor blades simultaneously and uniformly is referred to as ''''collective pitch control,'''' this control being used to increase or decrease the lift of the rotor. The variable changing of the pitch of a rotor blade in relation to its angular position relative to the aircraft fuselage is referred to as cyclic pitch control. This control is used, during forward motion of the aircraft, to compensate for the fact that the rotor blades moving in the direction of flight should have a different pitch than the retreating blades. This cyclic pitch control may also be used for directional control of the aircraft and for trimming of the aircraft. The use of a cyclic pitch control of a directional control is particularly important in aircraft which does not have any tail structure for directional and attitude control, as do conventional helicopters.

公开(公告)号：US3632065A

公开(公告)日：1972-01-04

申请号：US3632065D

申请日：1969-11-19

Applicant: VLM CORP THE

Inventor： ROSTA WILLIAM N

IPC: B64C27/20 ,  B64C29/00

CPC classification number: B64C27/20

Abstract: This application discloses an improved rotary wing aircraft capable of vertical lift. The aircraft employs airfoils or rotor blades which rotate in tracks surrounding the fuselage with the airfoils being driven by low-pressure air directed through nozzles onto turbine blades in the outer track. Directional control is provided by tilting the plane of rotation of the rotor blades or by cyclic pitch control of the rotors.

Abstract translation: 本申请公开了一种能够垂直升降的改进的旋翼飞机。 该飞机采用机翼或转子叶片，叶片围绕机身转动，机翼由低压空气引导通过外部轨道上的涡轮叶片驱动。 通过倾斜转子叶片的旋转平面或通过转子的循环变桨控制来提供定向控制。

公开(公告)号：US3606209A

公开(公告)日：1971-09-20

申请号：US3606209D

申请日：1970-01-26

Applicant: VLM CORP THE

Inventor： ROSTA WILLIAM N ,  MAXWELL RUSSELLE L

IPC: B64C27/20

CPC classification number: B64C27/20

Abstract: A ROTARY WING, VERTICAL LIFT AIRCRAFT INCLUDES A CENTRAL FUSELAGE AND A ROTOR CONSISTING OF AN INNER ANNULAR HUB ROTATABLY SUPPORTED ON AND ENCIRCLING THE FUSELAGE, RADIALLY EXTENDING ROTOR BLADES AND AN OUTER RING CONNECTING THE OUTER ENDS OF THE BLADES. THE ROTOR RING IS GUIDED IN AN ANNULAR GUIDE TRACK SUPPORTED ON THE BODY BY MEANS OF

RADIAL STRUTS. THE ROTOR RING DEFINES A REACTION TURBINE SUPPLIED WITH PRESSURIZED AIR FROM AIR SUPPLY STATIONS LOCATED IN THE GUIDE TRACK AND SUPPLIED FROM A COMPRESSOR WITHIN THE FUSELAGE THROUGH THE SUPPORTING STRUTS.