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：US20200056425A1

公开(公告)日：2020-02-20

申请号：US16539077

申请日：2019-08-13

Applicant: VLM CONTAINERS INC.

Inventor： CAMILLO DEL ROSSI

IPC: E06B11/02 ,  E06B11/04 ,  E04H1/12

Abstract: A modular self-contained gate for selectively blocking an entryway comprising an ISO standard shipping container modified such that an existing closed end wall of the shipping container comprises an elongate slot-like opening arranged vertically and adjacent an edge of the closed end wall, a substantially flat and rectangular gate comprising a long edge having a length substantially the same as a length of the shipping container and a height less than a height of the opening, the gate aligned with and linearly displaceable through the opening between a first position wherein the gate is stored inside the shipping container and the entryway is open and a second position wherein the gate is extended outside of the shipping container and passage via the entryway is barred, and a support mechanism inside the shipping container suspending the gate such that the gate remains suspended above the ground.

公开(公告)号：US3606570A

公开(公告)日：1971-09-20

申请号：US3606570D

申请日：1969-08-11

Applicant: VLM CORP THE

Inventor： HAGGERTY WILLETT H

IPC: B64C27/10 ,  B64C27/20

CPC classification number: B64C27/20 ,  B64C27/10

Abstract: A ROTARY WING, VERTICAL LIFT AIRCRAFT INCLUDES A CENTRAL FUSELAGE AND A ROTOR CONSISTING OF AN INNER ANNULAR HUB ROTATABLY SUPPORTED ON AN ENCIRCLING THE FUSELAGE, RADIALLY EXTENDING ROTOR 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 SUPPORT MEMBER IN THE HUB STRUCTURE, AND THE SUPPORT MEMBERS ARE INTERCONNECTED BY TENSION MEMBERS DESIGNED TO SEPARATE FROM THE SUPPORT MEMBERS UNDER PREDETERMINED LOAD WHEREBY THE ROTOR STRUCTURE WILL SEPARATE FOM THE BODY IN THE EVENT THAT ONE ROTOR BLADE IS LOST CREATING AN UNBALANCE IN THE ROTOR.

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：US11319750B2

公开(公告)日：2022-05-03

申请号：US16539077

申请日：2019-08-13

Applicant: VLM CONTAINERS INC.

Inventor： Camillo Del Rossi

IPC: E06B11/02 ,  E04H17/00 ,  E04H1/12 ,  E06B11/04

Abstract: A modular self-contained gate for selectively blocking an entryway comprising an ISO standard shipping container modified such that an existing closed end wall of the shipping container comprises an elongate slot-like opening arranged vertically and adjacent an edge of the closed end wall, a substantially flat and rectangular gate comprising a long edge having a length substantially the same as a length of the shipping container and a height less than a height of the opening, the gate aligned with and linearly displaceable through the opening between a first position wherein the gate is stored inside the shipping container and the entryway is open and a second position wherein the gate is extended outside of the shipping container and passage via the entryway is barred, and a support mechanism inside the shipping container suspending the gate such that the gate remains suspended above the ground.

公开(公告)号：US20190201964A1

公开(公告)日：2019-07-04

申请号：US16311630

申请日：2017-06-19

Applicant: VLM

Inventor： Carlo Vangompel

IPC: B21D37/02 ,  B21D5/02 ,  B21D5/06

CPC classification number: B21D37/02 ,  B21D5/0227 ,  B21D5/06

Abstract: Devices for bending materials generally include a mold and a holder for supporting the mold. The mold generally includes two halves, each of which extend in a longitudinal direction, and which together enclose a mold cavity. The mold has first and second mold outer walls. The mold halves include parallel elements that are arranged alternatingly in the longitudinal direction. Adjusting slats movably positioned on the holder are configured to form a stop for the first or second mold outer wall.

公开(公告)号：US3171676A

公开(公告)日：1965-03-02

申请号：US9155061

申请日：1961-02-24

Applicant: VLM W MURJAHN K G

Inventor： KURT HORN

IPC: H02G3/06

CPC classification number: H02G3/0616 ,  Y10T29/4992 ,  Y10T29/4994

公开(公告)号：US3752418A

公开(公告)日：1973-08-14

申请号：US3752418D

申请日：1972-05-12

Applicant: VLM CORP

Inventor： ROSTA W

IPC: B64C29/00

CPC classification number: B64C29/0041

Abstract: Disclosed ia an anti-torque and yaw control system for rotary wing aircraft employing tip driven rotor blades. The rotor blades are driven by a turbine drive ring powered by high velocity fluid. The drive ring is enclosed in a shroud and fluid passing through the turbine ring is collected in a ducted fan axially alligned tangentially with the dirve ring. The ducted fan is also tip driven by fluid from the main drive fluid supply. Alternative arrangements for varying the thrust of the ducted fan are shown. A jet thruster cooperating with the drive system is used for yaw control.

Abstract translation: 公开了一种采用尖头驱动转子叶片的旋翼飞机的抗扭矩和偏转控制系统。 转子叶片由高速流体驱动的涡轮驱动环驱动。 驱动环被包围在护罩中，并且通过涡轮环的流体被收集在与导向环相切地轴向地定向的管道风扇中。 导管风扇也由主驱动流体供应源的流体提供尖端驱动。 示出了用于改变管道风扇的推力的替代布置。 与驱动系统配合的喷气推进器用于偏航控制。

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.