534 results about "Yaw control" patented technology

The present invention relates to an easy-to-control tool for minimally invasive surgery and a method for using the same. In accordance with an aspect of the present invention, there is provided a tool for minimally invasive surgery and a method for using the same comprising, a main shaft, a first control shaft and a second control shaft positioned in sequence from one end of the main shaft, a first actuating shaft and a second actuating shaft positioned in sequence from the other end of the main shaft, an adjustment handle positioned around one end of the second control shaft, an end effector positioned around one end of the second actuating shaft, a pitch control part positioned around one position of the positions between the main shaft and the first control shaft, between the first control shaft and the second control shaft, and between the second control shaft and the adjustment handle, for transferring a motion of the adjustment handle in a pitch direction to the end effector, a first yaw control part and a second yaw control part positioned around the other positions of the positions between the main shaft and the first control shaft, between the first control shaft and the second control shaft, and between the second control shaft and the adjustment handle, respectively, for transferring a motion of the adjustment handle in a yaw direction to the end effector, a pitch actuating part positioned around one position of the positions between the main shaft and the first actuating shaft, between the first actuating shaft and the second actuating shaft, and between the second actuating shaft and the end effector, a first yaw actuating part and a second yaw actuating part positioned around the other positions of the positions between the main shaft and the first actuating shaft, between the first actuating shaft and the second actuating shaft, and between the second actuating shaft and the end effector, respectively, a first pitch cable and a second pitch cable for transferring motions from the pitch control part, the first yaw control part, and the second yaw control part to the pitch actuating part, the first yaw actuating part, and the second yaw actuating part, respectively, and a yaw cable for transferring a motion from the first yaw control part to the first yaw actuating part with the first pitch cable and the second pitch cable.

A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propulsion units together being located symmetrically, or at substantially symmetric positions, about the approximate center of gravity of the aircraft, when viewed from above. A vertical stabilizer may or may not be employed. If no vertical stabilizer is employed, yaw control during horizontal flight may be achieved through differential thrust using the at least six propulsion units. Yaw control during vertical flight may be provided by a plurality of yaw control panels. Absent yaw control panels, yaw control during vertical flight may be provided using differential propulsion unit tilt angles.

A vertical takeoff and landing aircraft having at least three wings and at least six propulsion units, each of which are located radially from two adjacent propulsion units, by equal or substantially equal angles. The at least six propulsion units together being located symmetrically, or at substantially symmetric positions, about the approximate center of gravity of the aircraft, when viewed from above. A vertical stabilizer may or may not be employed. If no vertical stabilizer is employed, yaw control during horizontal flight may be achieved through differential thrust using the at least six propulsion units. Yaw control during vertical flight may be provided by a plurality of yaw control panels. Absent yaw control panels, yaw control during vertical flight may be provided using differential propulsion unit tilt angles.

A twin bag inflatable rear airfoil for truck or transport trailer with attached shelves that bridge the surface gap between the trailer side and top surfaces, and the corresponding side and top surfaces of the inflatable bags. Shelves also bridge the upper surface gap between the two bags and provide a platform to deploy a collapsible yaw control fin. Another set of panels provide airfoil surfaces in the ground domain and are integral to the organised automatic folding and stowage of the apparatus. Interrupted ribs stiffen the inflatable surfaces while allowing them to fold in an orderly manner.

A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and / or rearward propulsion units to provide yaw control during vertical flight.

A hybrid aerial vehicle is optimized, for example, and not by way of limitation, to operate above 100,000 feet in altitude and provide persistent and maneuverable flight while carrying a wide array of communications and sensing payloads. The hybrid vehicle may use the high altitude winds to gain altitude by pitching up with the center of gravity (CG) control and using its propulsion drive to thrust into the wind to create aerodynamic lift to rise above the neutral buoyancy altitude. The hybrid vehicle will pitch down with the CG control so as to use gravity and propulsion to accelerate. Yaw control directs the flight towards any compass direction by rotating the gondola. This maneuvering capability permits the vehicle to station operate persistently, even in high winds. The lighter-than-air inflatable saucer shape is optimized for maintaining an aerodynamic cross-section to the prevailing wind from any direction in the vehicle horizontal plane. A gondola below the saucer contains a motor, batteries, solar collector, sensors, and yaw and CG control mechanisms.

A tiltrotor aircraft includes a rotatable nacelle that supports a rotor assembly and is pivotally attached to the air-craft's fuselage. A wing extension attaches to an outboard section of the nacelle. The wing extension provides additional yaw control during helicopter mode and additional lift during airplane mode. A method for controlling at least a portion of yaw movement includes positioning the rotor assembly in helicopter mode, creating rotor wash with the rotor assembly, and pivotally rotating the wing extension in the rotor wash.

A twin bag inflatable rear airfoil for truck or transport trailer with attached shelves that bridge the surface gap between the trailer side and top surfaces, and the corresponding side and top surfaces of the inflatable bags. Shelves also bridge the upper surface gap between the two bags and provide a platform to deploy a collapsible yaw control fin. Another set of panels provide airfoil surfaces in the ground domain and are integral to the organised automatic folding and stowage of the apparatus. Interrupted ribs stiffen the inflatable surfaces while allowing them to fold in an orderly manner.

The present invention includes an electric distributed propulsion for anti-torque modules for a helicopter and methods of use comprising: two or more generators connected to a main gearbox transmission; at least a first and a second plurality of variable speed motors connected to one or more fixed pitch blades to provide anti-torque thrust connected to the two or more generators, and at least a first and a second yaw control computer independently connected to each of the at least first and second plurality of variable speed motors, wherein each of the first and second yaw control computer serves as a primary and a backup yaw control computer to provide redundant control to both the first and second plurality of variable speed motors.

Improved methods of controlling the stability of a vehicle are provided via the cooperative operation of vehicle stability control systems such as an Active Yaw Control system, Antilock Braking System, and Traction Control System. These methods use recognition of road surface information including the road friction coefficient (mu), wheel slippage, and yaw deviations. The methods then modify the settings of the active damping system and / or the distribution of drive torque, as necessary, to increase / reduce damping in the suspension and shift torque application at the wheels, thus preventing a significant shift of load in the vehicle and / or improving vehicle drivability and comfort. The adjustments of the active damping system or torque distribution temporarily override any characteristics that were pre-selected by the driver.

An embodiment of the invention discloses a control method and system of a wind turbine. The method includes acquiring the air density of the current environment; adjusting control parameters of the wind turbine according to the air density of the current environment to allow the wind turbine to optimally operate in the current environment. According to the embodiment of the method, the air density of the current environment is measured, the control parameters, such as the electromagnetic torque of a generator, the generator speed, cut-in and cut-out wind speed, torque control determination, a limiting value for starting and shutdown yaw control and pitch control determination, can be calculated during a unit operating in real time, and control strategies can be optimized according to operating situation of the wind turbine, so that the wind turbine can operate at an optimal state in various climates, and the range of generating operation of the wind turbine can be expanded greatly.