475results about How to "Increase payload" patented technology

A novel modified release dosage form comprising of a high solubility active ingredient, which utilizes dual retard technique to effectively reduce the quantity of release controlling agents. Present invention can optionally comprise additionally another active ingredient as an immediate release form or modified release form. Present invention also relates to a process for preparing the said formulation.

Methods for adapting the operation of a system in response to the detection of embedded watermarks from a digital host content are provided. A digital host content is received and examined for the presence of watermarks. In response to the detection of embedded watermarks and in accordance with the value, type, density or spacing of the detected watermarks, one or more system reactions may take place. These reactions include conditionally allowing the system to resume its normal operation, prohibiting the system from resuming its normal operation, degrading the quality of the digital host content or changing the security status of the digital host content. In response to the extraction of weak watermarks that do not meet the desired system requirements, the extraction operation may be modified or extended to enable the detection of strong watermarks.

A multiple-degree-of-freedom anti-explosion mechanical arm relates to an anti-explosion mechanical arm. The anti-explosion mechanical arm comprises a six-degree-of-freedom joint component, a double-camera system, a distributed control system and an expansion system, wherein a front paw can be operated flexibly and diversely through the cooperative control of six joints; the double-camera system is used to provide front vision for rear operating staff so that the mechanical arm can be conveniently controlled to complete special tasks, the double-camera system comprises a main camera fixed on a front arm and a front-end camera fixed on a paw joint; the main camera has broad vision, the focus of the front-end camera is fine; the distributed control system is used to control the synergy movement of the six-degree-of-freedom component and various movements of the six-degree-of-freedom component, the distributed control system comprises a distributed control module, a magnetic absolute position sensing system and the like; and the expansion system is used to add different functions to meet different demands and increase the application range of the mechanical arm.

The composite rotating fixed-wing aircraft consists of the coaxial counter-paddle, reverse gear, engine output shaft, engine with a starter-generator, wings, tail blades, landing device, culvert, steering gear, fairing, fuselage, motor, motor drive shaft, wing control unit of small angle of attack, aileron rudder surface, and tailplane rudder surface. Co-axial counter-blade is located in the upper part of the aircraft, which connects with the engine output shaft; the reverse gear is installed between the co-axial counter-propellers; the motor connects with motor drive shaft powered by the starter-generator of the engine; the wings are located on both sides of aircraft and connect with the fuselage; the tail blades are located at the aircraft tail, which are installed behinde motor drive shaft; the landing device is located under the lower part of the fuselage and fixed with it; the culvert connects with the landing device; the fairing is installed in the culvert and connects with the steering gear; the wing control unit of small angle of attack is installed on the wing. The aircraft design method has six steps with strict scientific idea; this invention has a wide range of practical value and application prospect.

The invention relates to a gyroplane and further relates to a variable-torque four-rotor aircraft with large load capacity. The variable-torque four-rotor aircraft with large load capacity contains a fuselage, four rotor arms which are connected with the fuselage and are symmetrically distributed, and rotors positioned on the rotor arms. Among the four rotors, two adjacent rotors rotate in opposite directions. The included angle of each rotor blade 1201 to the water level can be adjustable, thus making the lift force adjustable and further adjusting the attitude of the aircraft. According to the invention, operationality of the aircraft is substantially raised.

The present invention provides a convertible aircraft provided with first and second tail booms together with first and second tilt fans disposed on either side of the fuselage a little forward of the center of gravity of said aircraft. In addition, the convertible aircraft includes, in remarkable manner, a third tilt fan arranged between the first and second tail booms.

The invention discloses a pilotless helicopter, comprising a main rotor system, a swash plate device, a drive system, a starting device, an engine, a body frame, a tail rotor device, a landing device and at least one auxiliary lift, anti-twisting force and cooling functional device, wherein the auxiliary lift, anti-twisting force and cooling functional device comprises ducts and a lift fan, the lift fan is annularly embraced in the ducts, and the ducts are arranged symmetrical about a central axis which is the advancing direction of the pilotless helicopter; the ducts are fixed above the engine, and an air guide passage is designed below the ducts and guides air to a cylinder of the engine; and the swash plate device is a four-channel hybrid control swash plate device. A part of additional lift and anti-twisting force are provided for the pilotless helicopter by using the power of the cooling engine, so that the pilotless helicopter has larger effective load and higher efficiency. Four steering engines of the four-channel hybrid control swash plate device are arranged in a manner of backing up each other, so that the stability is improved.

A flying drone includes a flight control computer, a parachute system with a parachute, a power supply system, a propulsion system, and an actuating drive system, without any of these systems being redundantly duplicated. To prevent uncontrolled crashing of the drone due to a critical error of any subsystem, signals or data are supplied from the power supply system, the propulsion system, and the actuating drive system, to an error detection or recognition device, which detects defined errors or error combinations in the provided signals or data and then supplies a deployment signal to the parachute system, which responsively generates a control signal that triggers an ejection mechanism to eject the parachute.

A module levitation control method for the frequently conducting electromagnetic-type low-speed magnetic levitation train features that a levitation control system has only one levitation controller consisting of signal processing unit, A/D converter, clock signal generator, master DSP unit, PWM wave generator and auxiliary DSP unit. Said method includes such steps as measuring the levitation states of ends A and B of a module by two levitation sensors, calculating their control values, and controlling the current values of electromagnets A and B and in turn their electromagnetic forces, so ensuring the gap between module and track to be constant.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a tandem double-duct type flight robot and a dynamics cooperative control method thereof. The invention provides a whole dynamics modeling and cooperative control strategy of an aerial vehicle and a mechanical arm based on the tandem double-duct type flight robot and the dynamics cooperative control method thereof. In a controlling process, an acting force of the mechanical arm is not considered as disturbance on the aerial vehicle, and the mechanical arm and the aerial vehicle are not controlled respectively; a whole flight robot platform is considered as a complete dynamic system; the aerial vehicle participates in adjustment of postures of a tail end of the mechanical arm through position control; the changes of a gravity center and a joint torque of the mechanical arm are caused by motions, and a corresponding moment is generated to assist the control on the postures of the aerial vehicle. The flight robot can realize automatic hovering and environment interaction, and has the advantages of small spatial size, large effective load, high passibility and accessibility, high control response sensitivity, great improvement of system stability and robustness, and the like.

The present invention relates to a water hyacinth rescure vessel flow line equipment, belonging to the field of environment protection technology. Said invention includes double-body vessel vessel-body, high-pressure water gun, telescopic crawler wheel, press-filtering cabin, fixed crawler wheel, storage cabin and drive cabin. Said invention also provides their connection mode and working mode. Said invented cutting mode is novel, does not wear cutting tool and can prevent serious secondary pollution, and can raise working efficiency by 30%-50%.

An external load mass rope for attachment to a cargo hook device of a rotorcraft that comprises at least one first cargo hook and at least one second cargo hook, the external load mass rope comprising at least one first rope leg and at least one second rope leg, wherein the at least one first rope leg is adapted for attachment to the at least one first cargo hook and the at least one second rope leg is adapted for attachment to the at least one second cargo hook, characterized in that at least one of the first and second rope legs comprises an associated length adjustment unit that is adapted to shorten or lengthen the at least one of the first and second rope legs in operation on the basis of associated operating parameters.

An aircraft (1) having an airframe (4) extending from a rear end (4″) to a front end (4′), a rotary wing (2), and a tail rotor (10). The aircraft (1) also includes a power plant (20) driving said rotary wing (2) via a main power gearbox (30) secured to a mast (31) of said rotary wing (2), said power plant (20) driving said tail rotor (10) via a tail power gearbox (40). The aircraft possesses pivot means (43) for causing the tail rotor (10) to swivel in a reversible manner from a stationary first position (POS1) towards a second position (POS2). The aircraft also includes tilt means (50) for tilting said mast (31) in a reversible manner.