481results 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 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.

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.

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.

A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and / or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers. In another embodiment, the shrouded propellers are pivotably mounted to the fuselage.

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.

A method of operating an engine is provided. The engine includes at least one cylinder communicating with an intake manifold via an intake manifold valve and an exhaust manifold via an exhaust manifold valve, the cylinder including a piston arranged within the cylinder, wherein the piston is coupled to a crankshaft of the engine. The method comprises discontinuing combustion in the cylinder during a plurality of cycles of the engine; during the plurality of cycles, operating the exhaust manifold valve and the intake manifold valve to provide a net flow of gases from the exhaust manifold to the intake manifold via the cylinder and adjusting a torque signature provided to the crankshaft during each cycle by the piston responsive to an operating condition.

The invention discloses a highly reliable unmanned aerial vehicle with double engines, four shafts and four rotors. The unmanned aerial vehicle is composed of aero-engines, a rotor machine body, a power distribution transmission system, a flying control system and four rotor assemblies, wherein the rotor machine rotors are pitch-variable rotors and each rotor comprises a rotor rotation driving part and a rotor blade angle adjusting part. According to the unmanned aerial vehicle, two aero-engines are used for driving four rotors; each engine drives a pair of blades on a symmetrical axis and a speed reducing mechanism is additionally arranged between the engine and the blades; the rotor blade angle adjusting mechanism drives the pitch-variable blade to change the pitch, so as to change lifting force; the engines work in a relatively high efficiency section; postures such as hovering, fly forwards and backwards are realized by adjusting the pitch; and the flying control system is composed of an ARM, GPS and a three-axis gyroscope and is accurate and reliable. By adopting the double-engine scheme, when one engine fails, the attitude of the vehicle can be maintained by improving the power of the other engine, so as to land safely; and the unmanned aerial vehicle has high reliability.

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 belongs to the technique area of the computer multi-media. The invention includes the following three steps. Three playback modes: the forcible TCP, the default UDP and the negotiated protocol are preset at the user end. When the user selects the forcible TCP, the server takes TCP as the transfer protocol without the testing between the server and the client end, down sending the visual data packet. When the user selects the default UDP, the server takes UDP as the transfer protocol without the testing, down sending the visual data packet. When the user selects the negotiated protocol, the testing is needed, the server accepts the negotiated protocol, and then down sending the visual data packet. The invention makes the client end possible to select suitable playback protocol in order to obtain the best effect for viewing.

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 convertible aircraft provided with first and second tilt fans disposed on either side of the fuselage a little forward of the center of gravity of the convertible aircraft. In addition, the convertible aircraft includes, in remarkable manner, a non-tilting fan that is permanently in a vertical position and that is contained inside the fuselage.

The invention relates to a tilted four-rotor aircraft. The tilted four-rotor aircraft comprises a fuselage, wherein the fuselage is provided with a front wing and a rear wing, two ends of the front wing and two ends of the rear wing are respectively provided with a set of rotor system, and the front wing and the rear wing are respectively and internally provided with a worm-wheel shaft which passes through the fuselage and is used for driving a rotor wing system to do tilted rotating motion; each set of rotor wing system comprises a direct-current brushless motor and a propeller, and the direct-current brushless motor is arranged at the end of the worm-wheel shaft and provided with the propeller. Compared with a conventional tilted double-rotor aircraft, the safety and reliability of the tilted four-rotor aircraft provided by the invention are higher; four rotors have strong lift force, so that the payload, flight radius and flight stability are all greatly improved. The tilted four-rotor aircraft provided by the invention can realize three flight modes, namely a helicopter mode, a transition mode and a horizontal propulsion mode, and has the characteristics of simple structure, high strength, reliable function realization and the like.

The invention discloses an automobile brake disc which comprises a brake disc body. The brake disc body is made of aluminum alloy. The two work faces of the aluminum alloy brake disc body are each provided with an abrasion-resistant layer in a composite mode. The abrasion-resistant layers are made of a ceramic reinforcing material. The abrasion-resistant layers made of the ceramic reinforcing material are metallurgically combined with the aluminum alloy brake disc body through the squeeze casting technology. The brake disc is low in weight, good in abrasion resistance and cooling performance, long in service life, low in maintenance cost, and capable of reducing automobile oil consumption, improving the passage capacity of an automobile, shortening the brake distance and improving safety of the automobile. According to a manufacturing method of the brake disc, by means of selective local strengthening and the squeeze casting technology, the two work faces of the aluminum alloy brake disc body are each provided with one abrasion-resistant layer made of the ceramic reinforcing material in the composite mode, the abrasion-resistant layers made of the ceramic reinforcing material are metallurgically combined with the aluminum alloy brake disc body so that abrasion resistance of the work faces of the brake disc can be guaranteed, and raw material cost and machining cost of the brake disc are reduced.

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.

The invention discloses a non-sun-synchronous orbit satellite double-shaft sailboard control method. A double-shaft sailboard is a solar sailboard structure which has two rotational degrees of freedom and of which the two rotating shafts can independently control work. The double-shaft sailboard control method comprises a control method of each single-shaft sailboard in the double-shaft sailboard and an implementation method during double-shaft cooperative work of the sailboard. In the single-shaft control method of the sailboard, measurement modes and rotation strategies for the sailboard in different work modes of the satellite are mainly designed. In the double-shaft cooperative work method, the working order of each single shaft and the rotation logic are specified. The inconvenience that a non-sun-synchronous orbit satellite needs to frequently perform attitude maneuver to ensure the sailboard tracks the sun is solved by applying the double-shaft sailboard control method on a satellite. By the method, the satellite can track the sun in real time on orbit by controlling the rotation of the sailboard, so that the energy supply on the satellite is guaranteed, and the requirement of the satellite over the ground directional triaxial stability is met.

The present invention relates to a laser communication and a tracking system for an unmanned aerial vehicle, after tracking and positioning the unmanned aerial vehicle, a photoelectric tracking subsystem sends beacon light and signal light sent by a communication subsystem to the unmanned aerial vehicle through a relay optical subsystem, in the same time receives an unmanned aerial vehicle signal,and realizes wireless laser communication between the unmanned aerial vehicle and a main control computer to transmit position and flight attitude of the unmanned aerial vehicle to a main control computer terminal with a liquid crystal display in real time. When transmitting energy to a moving target, the system has high tracking accuracy and stable energy transmission efficiency, realizes the laser communication and tracking aiming of the unmanned aerial vehicle, and can fully combine structural characteristics of the unmanned aerial vehicle for remote laser charging. The high-precision real-time tracking system provides uninterrupted power to the unmanned aerial vehicle, does not require manual control and adjustment of incident laser angles, ensures that a solar battery always outputsmaximum power, thereby greatly reducing energy storage equipment on the vehicle, and has stable energy transfer.

A method of operating an engine is provided. The engine includes at least one cylinder communicating with an intake manifold via an intake manifold valve and an exhaust manifold via an exhaust manifold valve, the cylinder including a piston arranged within the cylinder, wherein the piston is coupled to a crankshaft of the engine. The method comprises discontinuing combustion in the cylinder during a plurality of cycles of the engine; during the plurality of cycles, operating the exhaust manifold valve and the intake manifold valve to provide a net flow of gases from the exhaust manifold to the intake manifold via the cylinder and adjusting a torque signature provided to the crankshaft during each cycle by the piston responsive to an operating condition.

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.

A deformable multi-mode ground and air flying robot comprises a body, an automatic pilot, wing arm devices, hub devices and a suction device. The body is provided with the four sets of wing arm devices in a cross shape. The wing arm devices comprise large wing arms, small wing arms, rotation joints, installation supports, motors and damping sleeves. The hub devices are installed on the four sets of wing arm devices respectively and are driven to run through motors. The suction device is installed on the upper portion of the body and used for being sucked to the surface of an object with the assigned angle. The automatic pilot is installed on the body and drives the hub devices and the suction device to run. The automatic pilot drives the rotation joints of the wing arm devices to rotate so that the small wing arms can drive the hub devices to rotate to the assigned angle, and thus switching of a flying mode and a ground walking mode is achieved. The deformable multi-mode ground and air flying robot has the advantages of being low in power consumption, high in environment adaptability and multi-task handling capability, good in structural stability and high in mobility, and is suitable for multi-mode operation and capable of meeting various task requirements under various complex severe environments.

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.