32results about How to "Sufficient thrust" patented technology

Embodiments of the invention relate to a vehicle comprising a plurality of inclined rotors that are operable to provide at least one of thrust and torque vectoring according to a desired thrust and / or torque vectors.

The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing.

Disclosed is a high-power electric motor and its fabrication technology. The motor and its distributed power electronics are all being fully integrated in a conventional turbofan engine. The rotor drives directly (with no gears) the LP shaft of the jet engine while requiring minimal modification to a basic jet engine and without distortion to the nacelle geometry. In principle such a configuration should be suitable for a power level of 10 to 50 MW, which makes it fully capable of providing a standard flight envelope by only using electric energy.

A catalytically activated transient decomposition propulsion system provides thrust by decomposing flow controlled propellant in contact with a catalyzing agent using a fixed volume of liquid propellant that is placed in contact with the catalyst within the decomposition chamber by a calibrated flow control valve. After injecting the liquid propellant into the decomposition chamber, the valve returns to the closed position while surface tension holds the liquid within the decomposition chamber until complete decomposition and exhaust of the warm gaseous products through a converging and diverging nozzle occurs. The increasing and decreasing transient pressure in the decomposition chamber changes each cycle in response to flow control valve actuation as the decomposition process is repeated.

The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution. The system components and manufacturing cost is presented in comparison to current systems using active stabilization

Disclosed is a micro actuator capable of being formed in compact as a whole, such as 10 mm in diameter by diminishing a difference between a stroke distance of a moving member and an overall length, and by reducing a sectional area taken in a direction orthogonal to a stroke direction. The micro actuator includes: a spline shaft formed as a cylinder with a hollow part and having an axially extending slit opening; a spline nut fit-engaged with the spline shaft and axially guiding the spline shaft; a pair of end caps fixed to openings at both ends of the spline shaft; a magnet rod supported at both ends within the hollow part of the spline shaft by the end caps; and a forcer loosely fit-engaged with a periphery of the magnet rod within the hollow part of the spline shaft to constitute a linear motor together with the magnet rod and connected with the spline nut through the slit opening.

The design and refinement of a tethered hovering platform into a feasible working system is presented. To determine a starting point for the design, a detailed historical search was conducted to find the history and the current state of such technology. Real world current needs are analyzed to produce a mission specification and to drive the preliminary vehicle design. Analysis of environmental conditions and decisions about an initial payload package are made in conjunction with motor and propeller sizing. Initial concept testing to discover feasibility and operational issues was performed; from this, instability issues were discovered. Analyzing these instability issues using known rotorcraft and momentum effects, in conjunction with flight testing, yields possible solutions to the problem. The use of constrained layer dampers as a means of passive stabilization is addressed and suggested as the preferred solution. Testing of passive constrained layer damping verifies the stability of the solution. The system components and manufacturing cost is presented in comparison to current systems using active stabilization.

A ballistically launched foldable multirotor vehicle has a central body frame. A battery is located in an upper vertical location of the vehicle and positions a center of mass of the vehicle to provide aerodynamic stability during a launch. Fins are attached to the central body frame such that aerodynamic forces on the fins shift an aerodynamic center (AC) of the vehicle downward below the center of mass of the vehicle. Three or more foldable arms are attached to the central body frame via a hinge and exist in two states—a closed state where the foldable arms are parallel to a central body axis, and an open state (after launch) where the foldable arms extend radially outward perpendicular to the central body axis. Rotors mounted to each foldable arm are controlled by a motor to enable flight.

A door closer capable of adjusting door closing speed, includes a pneumatic cylinder on the door frame, a hydraulic cylinder on the door, and a lever. One end of the lever is movably connected to the pneumatic cylinder, and the other end is connected to the hydraulic cylinder. The pneumatic cylinder includes a sliding rail, and a sliding member cooperated with the sliding rail. A hermetic chamber is formed by the sliding member and the sliding rail. An adjusting valve, for adjusting the air exhaust of the hermetic chamber, is provided on a wall of the hermetic chamber.

The invention provides a push-lean type rotational guide device which comprises a drill collar body, wing ribs, an outer cylinder and a hydraulic control system, wherein the wing ribs are mounted on the outer circumference of the drill collar body; the drill collar body is sleeved by the outer cylinder; the outer cylinder is kept static relative to the drill collar body; the hydraulic control system comprises an oil storage cavity and an execution mechanism; the execution mechanism comprises an oil cylinder communicated with the oil storage cavity and a piston acting on the wing ribs; the hydraulic control system is capable of conveying hydraulic oil between the oil storage cavity and an oil cylinder, and then the wing ribs can make radial telescopic movement under the action of the piston.

An image stabilizing apparatus of the present invention includes a laminated substrate 19 that has a coil pattern, a hall element 21 fixed to the laminated substrate 19, a magnet 20, a back yoke 22, an opposing yoke 23, and a flexible printed circuit board for wiring the coil pattern on the laminated substrate and the hall element 21, the opposing yoke 23 being stepped (recesses 23a, 23b) in a portion opposing the hall element 21. Reduction in size, weight and cost are thereby realized in a lens-shift image stabilizing apparatus.

Disclosed is a micro actuator capable of being formed in compact as a whole, such as 10 mm in diameter by diminishing a difference between a stroke distance of a moving member and an overall length, and by reducing a sectional area taken in a direction orthogonal to a stroke direction. The micro actuator includes: a spline shaft formed as a cylinder with a hollow part and having an axially extending slit opening; a spline nut fit-engaged with the spline shaft and axially guiding the spline shaft; a pair of end caps fixed to openings at both ends of the spline shaft; a magnet rod supported at both ends within the hollow part of the spline shaft by the end caps; and a forcer loosely fit-engaged with a periphery of the magnet rod within the hollow part of the spline shaft to constitute a linear motor together with the magnet rod and connected with the spline nut through the slit opening.

The invention provides an aircraft launching steam ejection boosting device which has a simple structure, a large ejection boosting force, sufficient continuous thrust, a short repeated ejection time interval, convenience for operation, a wide application range, convenience for transportation and installation and a high battle damage repairing speed. The aircraft launching steam ejection boostingdevice comprises a flight deck, a sliding pipeline, a steam ejection booster and an aircraft connector, wherein a deceleration resetting device is arranged at the front part of the sliding pipeline; and the back part of the sliding pipeline is provided with a heating device; the steam ejection booster comprises a bullet-shaped shell, a clapboard, overheating vaporizers, a water inlet pipe and a water spraying pipe, wherein the bullet-shaped shell is provided with an opening at the back part; the overheating vaporizers are distributed in a high-temperature steam generation room axially; the water inlet pipe arranged at the tail part of the shell passes through the high-temperature steam generation room to communicate with a high-temperature pressure-bearing water tank and has a check valve; the water spraying pipe is arranged on the high-temperature pressure-bearing water tank and is provided with an ejection control valve; the water spraying hole of the water spraying pipe is positioned at the front part of the high-temperature steam generation room; and a waste water recovery pipeline is arranged under the sliding pipeline.

The current invention provides significant performance improvements or significant energy savings for fans used in these applications: personal, industrial and automotive cooling, ventilation, vacuuming and dust removal, inflating, computer component cooling, propulsors for unmanned and manned air vehicles, propulsors for airboats, air-cushion vehicles, airships and model aircraft. Additionally, the invention provides higher performance such as higher lift and higher lift efficiency to small air vehicles. These advantages are achieved by using plasma actuators to provide active flow control effectors into thin fan blades and wing.

The invention provides a visualized test rack for contact engagement of a handcart type breaker, and belongs to the technical field of machinery. The test rack comprises a visualized shell, a rack, a moving-contact mounting and adjusting plate, a moving contact, a fixed contact, a fixed-contact mounting and transferring flange, a support base, a screw rod and double-nut assembly and a hand wheel. The moving-contact mounting and adjusting plate is mounted on the inner side of the left end of the rack, and is used for adjusting a mounting position of the moving contact. The screw rod and double-nut assembly is mounted at the right end of the rack in a sleeved manner. The hand wheel is mounted at the right end of the screw rod and double-nut assembly. The fixed-contact mounting and transferring flange is mounted at the left end of the screw rod and double-nut assembly, and is used for connecting the fixed contact with the screw rod and double-nut assembly. The visualized shell is mounted on the periphery of the rack. By the test rack, the problems such as tedious adjustment, frequent movement and manpower and material resource waste of instruments such as contact engagement depth measuring devices for handcart type breakers of closed armoured high-voltage switch cabinets are solved, and device production efficiency is improved.

A door closer capable of adjusting door closing speed, includes a pneumatic cylinder on the door frame, a hydraulic cylinder on the door, and a lever. One end of the lever is movably connected to the pneumatic cylinder, and the other end is connected to the hydraulic cylinder. The pneumatic cylinder includes a sliding rail, and a sliding member cooperated with the sliding rail. A hermetic chamber is formed by the sliding member and the sliding rail. An adjusting valve, for adjusting the air exhaust of the hermetic chamber, is provided on a wall of the hermetic chamber.

The invention discloses an electric power sand throwing fire extinguishing device. The electric power sand throwing fire extinguishing device includes a launch cylinder and a sand loading cylinder, the upper end of the sand loading cylinder is open, the sand loading cylinder is placed in the launch cylinder with an open upper end and can movably axially move along the launch cylinder, and the bottom of the sand loading cylinder is connected to the launch cylinder through an ejection mechanism. The ejection mechanism comprises springs, guide rods and a push plate, the push plate is fixedly connected to the bottom of the launch cylinder and is connected to the multiple guide rods through through holes in a sleeving mode, and both ends of the multiple guide rods are fixedly connected into thelaunch cylinder and are arranged circumferentially and uniformly in the length direction of the launch cylinder. The guide rods are sleeved with the springs, one ends of the springs are fixedly connected to the push plate, and the other ends of the springs abut against the launch cylinder. A mechanical switch is arranged at the bottom of the launch cylinder, the mechanical switch can be clamped onto the push plate after the push plate retracts. According to the electric power sand throwing fire extinguishing device, long distance fire extinguishing is achieved, the service safety is improved,and the electric shock hazard is avoided.

A satellite thruster increases satellite efficiency. The Linear Actuated μCAT has a stepper motor to move the ablative electrode forward. A LabVIEW program and Arduino microcontroller are used to analyze the Linear Actuated μCAT to determine how many steps are required for re-ignition, arc current, and the validity of the feed system. Results from testing show that micro-stepping the stepper motor is an effective way to replenish the cannibalized electrode for propellant.

The invention discloses an external pressure-storage type perfluoro-hexanone splitting spray head. The splitting spray head comprises a spray head body, a flow guide sleeve and a splitting pipe, wherein a medicament channel and a power gas channel are arranged in the spray head body, one end of the flow guide sleeve is connected with the spray head body, the inner wall of the other end of the flowguide sleeve is provided with a protruding part, the splitting pipe communicates with the medicament channel, and is provided with a plurality of splitting holes in the circumferential direction, thespliting pipe extends to the outside of the flow guide sleeve, and is provided with a shielding part, and a medicament refining channel is formed between the protruding part and the shielding part. The external pressure-storage type perfluoro-hexanone splitting spray head has the advantages that the structure is simple, and the atomization performance and the gasification speed are improved favorably.

The invention provides an aircraft launching steam ejection boosting device which has a simple structure, a large ejection boosting force, sufficient continuous thrust, a short repeated ejection time interval, convenience for operation, a wide application range, convenience for transportation and installation and a high battle damage repairing speed. The aircraft launching steam ejection boostingdevice comprises a flight deck, a sliding pipeline, a steam ejection booster and an aircraft connector, wherein a deceleration resetting device is arranged at the front part of the sliding pipeline; and the back part of the sliding pipeline is provided with a heating device; the steam ejection booster comprises a bullet-shaped shell, a clapboard, overheating vaporizers, a water inlet pipe and a water spraying pipe, wherein the bullet-shaped shell is provided with an opening at the back part; the overheating vaporizers are distributed in a high-temperature steam generation room axially; the water inlet pipe arranged at the tail part of the shell passes through the high-temperature steam generation room to communicate with a high-temperature pressure-bearing water tank and has a check valve; the water spraying pipe is arranged on the high-temperature pressure-bearing water tank and is provided with an ejection control valve; the water spraying hole of the water spraying pipe is positioned at the front part of the high-temperature steam generation room; and a waste water recovery pipeline is arranged under the sliding pipeline.

A method and apparatus generates kinetic and electrical energy using sound waves and is believed to be particularly useful in high efficiency motors and electrical generators. In particular, the method and apparatus uses sound waves as a catalyst to convert ambient heat energy into kinetic and / or electrical energy. In one embodiment, sound waves at particular frequencies are propagated across one side of a plate or other barrier element, causing flow of fluid (e.g. air) across the surface of the plate which, in turn, causes a reduction in the ambient fluid (air) pressure near the surface of the plate. The difference in fluid pressure on opposite sides of the plate results in net positive thrust on the plate, thereby causing movement of the plate. This movement can be harnessed using, for example, a windmill type of rotor and stator arrangement to generate useful kinetic and electrical energy.

The invention relates to a waterjet propulsion system (1) for a watercraft, comprising an intake region (2), an impeller region (3) which adjoins the intake region and in which a one-stage impeller (4) is mounted, and an outlet nozzle (5) which adjoins the impeller region, the waterjet propulsion system having a drive motor (6) which is at least indirectly connected to an impeller driveshaft (7) of the impeller (4). According to the invention, the impeller has only one single blade (8).