764results about How to "Reduce 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.

This invention concerns an aircraft propulsion system in which an engine has an engine core comprising a compressor, a combustor and a turbine driven by a flow of combustion products of the combustor. At least one propulsive fan generates a mass flow of air to propel the aircraft. An electrical energy store is provided on board the aircraft. At least one electric motor is arranged to drive the propulsive fan and the engine core compressor. A controller controls the at least one electric motor to mitigate the creation of a contrail caused by the engine combustion products by altering the ratio of the mass flow of air by the propulsive fan to the flow of combustion products of the combustor. The at least one electric motor is controlled so as to selectively drive both the propulsive fan and engine core compressor.

This invention relates to rotary pumps adapted, but not exclusively, for use as artificial hearts or ventricular assist devices and, in particular, discloses in preferred forms a seal-less shaft-less pump featuring open or closed (shrouded) impeller blades with the edges of the blades used as hydrodynamic thrust bearings and with electromagnetic torque provided by the interaction between magnets embedded in the blades and a rotating current pattern generated in coils fixed relative to the pump housing.

The invention relates to a position keeping method of a stationary orbit satellite, particularly to a position keeping method of an electric propulsion stationary orbit satellite, and belongs to the technical field of the orbit control of a satellite. Four thrusters of an electric propulsion system are mounted at the northwest, the northeast, the southwest and the southeast of the satellite back floor. For the four thrusters, the tangential distances and the normal distances relative to a satellite centroid are the same, and the thrust directions pass through the satellite centroid. A position keeping period comprises a one-day orbit determining period and n two-day small control periods, wherein the four thrusters in one small control period are respectively started, and at the same time, the orbit inclination, the flat longitude drifting ratio and the eccentricity ratio are controlled. The position keeping method disclosed by the invention solves the problem of the position keeping of the stationary orbit satellite of the electric propulsion system.

A system for increasing the thrust and power capabilities of a side by side vertical takeoff and landing vehicle and to optimize the coaxial rotor performance. The system including a first coaxial rotor spaced from an aircraft body and a second coaxial rotor spaced from the aircraft body and opposite the first coaxial rotor. The first coaxial rotor having a first top propeller aligned with a first bottom propeller along a first rotational axis. The second coaxial rotor having a second top propeller aligned with a second bottom propeller along a second rotational axis. A gyroscopic moment to maintain pitch stability is controlled by modulating the first and second top propellers having a different angular speed or different torque from the first and second bottom propellers and tilting the first and second coaxial rotors towards the central axis with a common tilt angle and a common tilt rate.

A cutting insert of the present invention includes an upper surface; a lower surface; a side surface; a cutting edge which is located along an intersection of the upper surface and the side surface, and comprises a major cutting edge, a flat cutting edge, and a minor cutting edge located between the major cutting edge and the flat cutting edge; and a land part located along the cutting edge on the upper surface. The land part includes a minor cutting edge land portion located correspondingly to the minor cutting edge. The minor cutting edge land portion is inclined downward toward a central part of the upper surface. The present invention also provides a cutting tool including the cutting insert, and a method of manufacturing a machined product by using the cutting tool.

The invention provides a low-friction halogenated nano- or microparticulate coating and method for forming the coating on articles, such as implantable medical articles. The halogenated nano- or microparticles, desirably fabricated from PTFE, are present on the surface of the coating and covalently coupled to a coupling component, which facilitates formation of the coating. The coatings are biocompatible and can be formed on a selected portion of a medical device in a straightforward process. In some aspects the nano- or microparticulate coatings are formed on a system for the insertion of a medical device, wherein the system includes a catheter.

A portable, vertical tower fan capable of generating a vertically oriented exhaust air stream that conforms better to a user at an elevation above a support surface. The device includes an vertically elongated housing, an air blower assembly located within the elongated housing and a base provides a space saving design.

A drill bit consists of a bit body having a forward end and a slot in the forward end to hold a hardened cutting blade. The bit body has a table near the center of the blade to reduce the speed at which the drill bores into hard material. The blade has a central slot extending into the forward end thereof such that the slot defines inner side walls and a bridge extending between the inner side walls. The bridge has sloping sides the define a central cutting edge so as to cut particles of hard material accumulating in the slot. The inner side walls intersect the leading faces of the blade and form cutting edges which further cut particles loosened at the center of the cut. Also, relief flats relieve the concentration of forces at the ends of the primary cutting edges of the blade.

The invention discloses a method for designing a bias orbit of a spacecraft in a halo orbit in a sun-earth three-body gravitational field. The invention proposes a semi-analytic-solution-based orbit design method for a task demand of thrusting the spacecraft in the halo orbit to a heliocentric grave orbit by adopting a small thrust force in the sun-earth three-body gravitational field. According to the method, the calculation amount can be greatly reduced while the orbit precision is ensured. In addition, the invention proposes a method for realizing orbit maneuvering by adopting a minute continuous thrust system which mixes a variable reflectivity solar sail with electric propulsion. The method for realizing the orbit maneuvering by a mixed thrust force is capable of greatly reducing fuel consumption. The purpose of orbit maneuvering with minimum fuel consumption is achieved through optimization design of a posture angle of the solar sail. Compared with a conventional pulse bias orbit design method, the method proposed by the invention has the advantages that the calculation time can be shortened to a great extent on the premise of ensuring the solving precision.

The invention relates to a circular awning with a cable dome and a spatial steel truss being combined and a construction method of the circular awning. The circular awning comprises an awning roof and a main body; the circular awning is an approximately spherical segment surface; the awning roof is of a cable dome structure; the main body is of a spatial steel truss structure; the bottom end of the cable dome is fixedly connected with the top end of the spatial steel truss structure. The spatial steel truss structure comprises at least one layer of weft curved beam which is a polygonal spatial steel truss. The spatial steel truss structure comprises at least two layers of weft curved beams and radial curved pillars; the radial curved pillars are connected with each layer of weft curved beams, and every two adjacent radial curved pillars are connected through weft pull rods which are arranged at intervals according to fixed latitudes. The circular awning disclosed by the invention combines tensile and rigid structures, integrates inward tension of the tensile structure and outward thrust of the spatial steel truss structure, and realizes self-balance of inside and outside stresses; the stress of an arched steel structure is reduced, the integral structural stability is better, and meanwhile, the horizontal thrust of the lower part of the steel truss structure and a support is reduced, the maintenance cost of late-stage anticorrosion is reduced, and the construction efficiency is high.

A system for increasing the thrust and power capabilities of a side-by-side vertical takeoff and landing vehicle to optimize the coaxial rotor performance. The system includes a first coaxial rotor spaced from an aircraft body and a second coaxial rotor spaced from the aircraft body and opposite the first coaxial rotor. The first coaxial rotor has a first top propeller aligned with a first bottom propeller along a first rotational axis. The second coaxial rotor having a second top propeller aligned with a second bottom propeller along a second rotational axis. A gyroscopic moment to maintain pitch stability is controlled by modulating the first and second top propellers, which have a different angular speed or different torque from the first and second bottom propellers, and tilting the first and second coaxial rotors towards the central axis with a common tilt angle and a common tilt rate.

The method serves to place a space vehicle, such as a satellite, on a target orbit such as the orbit adapted to normal operation of the space vehicle and starting from an elliptical initial orbit that is significantly different from, and in particular more eccentric than the target orbit. The space vehicle is caused to describe a spiral trajectory made up of a plurality of intermediate orbits while a set of high specific impulse thrusters mounted on the space vehicle are fired continuously and without interruption, thereby causing the spiral trajectory to vary so that on each successive revolution, at least during a first stage of the maneuver, perigee altitude increases, apogee altitude varies in a desired direction, and any difference in inclination between the intermediate orbit and the target orbit is decreased, after which, at least during a second stage of the maneuver, changes in perigee altitude and in apogee altitude are controlled individually in predetermined constant directions, while any difference in inclination between the intermediate orbit and the target orbit continues to be reduced until the apogee altitude, the perigee altitude, and the orbital inclination of an intermediate orbit of the space vehicle have substantially the values of the target orbit.

The invention discloses a rotating power-assisted mechanism and a lifting table applying the same. The rotating power-assisted mechanism comprises a transmission shaft arranged on a supporting memberand a driving device driving the transmission shaft to rotate, a slider is connected on the transmission shaft in a threaded manner, an energy storage element with axis parallel to that of the transmission shaft is arranged on the supporting member, the first end of the energy storage element is connected with the supporting member while the second end of the same is connected with the slider, andthe energy storage element is used for applying thrust on the slider and providing power assistance for rotating of the transmission shaft through the slider. The rotating power-assisted mechanism and the lifting table are low in manufacturing cost, simple in structure and high in safety.

The invention discloses a microwave-assisted rock breaking TBM cutter head for hard rocks. The cutter head comprises a TBM cutter head body, wherein the TBM cutter head body mainly comprises a single-edge rock breaking hobbing cutter, a double-edge rock breaking hobbing cutter, a plurality of water injection dedusting openings and a plurality of microwave-assisted rock breaking emitters; the cutter head covers rock breaking paths in different tracks through the combination of the double-edge rock breaking hobbing cutter and the single-edge rock breaking hobbing cutter; a cutter head panel is provided with the water injection dedusting openings; the cutter head panel is provided with the microwave-assisted rock breaking emitters; each microwave-assisted rock breaking emitter comprises a microwave emitting disc, a wave guiding structure and a microwave emitting module. The cutter head has the advantages that a microwave emitting device is started in case of hard strata, rocks are rapidlyheated through microwave, mechanical properties of rocks, such as the point load strength, uniaxial compressive strength and tensile strength, are reduced, rock joint fissure assisted TBM hobbing cutter rock breaking is added, the penetration speed of disc cutters is improved, the rock breaking rate is improved, the thrust and torque of TBM equipment are reduced, abrasion of the hobbing cutters in hard rocks and cutter changing frequency are reduced, the construction period can be greatly reduced, and the construction investment can be reduced.

A system for controlling inbound transition of an aircraft includes a fuselage and first and second freewings pivotably mounted on opposing sides thereof. The system includes an airspeed sensor that outputs an airspeed indication signal. The system includes a controller for increasing aircraft engine thrust to substantially maximum for inbound transition, and for generating pitch and freewing control signals. The system includes actuators for actuating aircraft control surfaces in response to the pitch control signal to rapidly increase pitch of the fuselage to decelerate the aircraft, and for actuating freewing control surfaces in response to the freewing control signal to adjust lift produced by the freewings to oppose climbing of the aircraft due to the increase in engine thrust and the increase in the fuselage pitch. The controller is configured to decrease the engine thrust as the aircraft decelerates until the aircraft is in a hover mode.

A component-placing apparatus for driving a nozzle in the rotational and vertical directions for applying suction to a component includes a rotary actuator and a linear actuator having a stator connected to a stator of the rotary actuator such that these stators are immovable relative to each other. A spline shaft is connected to a rotating shaft of the rotary actuator, and a nozzle connecting shaft having a suction nozzle disposed at the bottom thereof is engaged with the spline shaft and is allowed to move only rectilinearly. A hollow holder encircling the nozzle connecting shaft with rotary bearings being interposed therebetween is connected to a mover of the linear actuator, and the hollow holder is engaged with the stator of the linear actuator with a linear guide being interposed therebetween.

The invention discloses a deviation correcting and resetting method for transverse deviation of beam bodies of a beam bridge. The method comprises the steps that 1) horizontal transverse action force enabling the beam bodies to deviate is eliminated; 2) a whole binding beam body of a unit where the deviated beam bodies are located is temporarily fixed and bound to form a stress whole, and meanwhile the beam bodies of the unit and beam bodies of adjacent bridge spans on the two sides of the beam bodies are disconnected; 3) jacking devices are arranged at the tops of all piers corresponding to the temporarily fixed and bound deviated unit, and the corresponding deviated beam bodies are jacked synchronously; 4) a temporary sliding support is arranged in a clearance formed through jacking in the step 3); 5) reaction frames and deviation correction jacks are arranged on support cushion stone at the tops of the piers corresponding to all the beam bodies of the deviated unit, and all the deviation correction jacks transversely push the beam bodies to be reset; 6) after deviation correction is carried out in place, the beam bodies are finally rehabilitated. The deviation correction push thrust of the method is reduced exponentially, the damage of subsidiary stress generated in the deviation correction process to the structure of the beam bodies is avoided, construction is convenient, the construction period is short, and cost is low.

The invention relates to a waterpower oscillator through which effective pressure can be exerted on a drill bit and well drilling efficiency can be improved in the technical field of oil exploitation. The waterpower oscillator comprises an upper connector, a stator, an outer shell and a lower connector all of which are sequentially connected in a sealed mode. A rotor is eccentrically arranged inside the stator, and the lower end of the rotor is sequentially connected with a cardan shaft upper connector, a cardan shaft and a cardan shaft transmission rod. The lower end of the cardan shaft transmission rod is connected with the outer shell in a sealed mode, the lower end of the outer shell is in threaded connection with the lower connector in a sealed mode, the lower end of the cardan shaft transmission rod is provided with a vibration valve in a matched and sleeved mode, and the vibration valve can do reciprocating sliding motion along the matched surface relative to the cardan shaft transmission rod. The lower end of the vibration valve is provided with a movable valve plate in a sealed and sleeved mode, wherein the movable valve plate and the vibration valve can do the synchronous movement, the upper end of the lower connector is correspondingly provided with a fixed valve plate attached to the movable valve plate, the movable valve plate and the fixed valve plate are respectively provided with a sector channel with the area larger than that of a half circle. An annular hollow part through which liquid can flow is formed among the rotor, the cardan shaft upper connector, the cardan shaft, the stator and the outer shell, the cardan shaft transmission rod is provided with a channel communicated with the annular hollow part, and the channel is communicated with a vibration valve cavity and the sector channels.

A portable, vertical tower fan capable of generating a vertically oriented exhaust air stream that conforms better to a user at an elevation above a support surface. The device includes an vertically elongated housing, an air blower assembly located within the elongated housing and a base provides a space saving design.

Provided are a slant grouting control steel anchor pipe frame and a construction method thereof. A primary grouting body is poured to the peripheral space of a steel anchor pipe through a primary grouting pipe; after the primary grouting body is solidified, a secondary grouting body is poured to the outside through a secondary grouting hole in the steel anchor pipe wall in a compression mode, the secondary grouting body splits the primary grouting body through the secondary grouting hole and is diffused to a peripheral rock and earth mass and forms a mixed grouting body with the primary grouting body. A concrete beam is poured along a slope to wrap the top of the steel anchor pipe in the beam. The slant grouting control steel anchor pipe frame combines the advantages of an anchor rod frame and a grouting control technology, the steel anchor pipe is used as a protection measure and a secondary grouting channel, and by means of improvement of the strength of the peripheral rock and earth mass through the secondary grouting, a steel pipe and the peripheral rock and earth mass form a whole body to defend a slope together. A slant grouting control steel anchor pipe frame structure has the advantages of being advanced in technology, reasonable in economy, fast in construction and the like and is a novel slope reinforcing technology with good developing prospects.

A lens barrel includes: a lens holding member that holds a lens; a drive coil attached to an outer peripheral portion of the lens holding member; a magnet attached to face the drive coil; a barrel member in which the lens holding member is disposed; and a cover member attached to the barrel member with the lens on a light incident side of the lens holding member facing to an outside. The cover member is magnetic, and the magnet is directly attached to the cover member at a position acing the drive coil.

A constant velocity universal joint comprises a plurality of trunnions which are formed to be spherical, sliding surfaces which extend in a flat configuration along an axial direction of an outer cup, and pairs of slipper members having one side surfaces which are formed with recesses for making contact with spherical surfaces of the trunnions and the other side surfaces which are formed with flat surfaces to make contact with the sliding surfaces, wherein the pair of slipper members are provided slidably with respect to the sliding surface and the spherical surface of the trunnion.

A system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, cruise, descent, landing) to pilots in response to situations wherein the measured air data should not be relied upon. This information is presented in an intuitive and expedient manner exactly when and where it is needed on the primary flight display. The displayed information dynamically changes in response to airplane parameters.

A pulse detonation engine including one or more fuel injectors comprising one or more piezoelectric driving stacks wherein a flow control member of each injector is driven directly by the one or more piezoelectric stacks without additional amplification means or interposing elements while a flow area of the nozzle is variably adjustable to deliver controlled flow rates in a desired flow profile to improve engine performance and reduce emissions. The pulse detonation engine configured to support variable mission and operational requirements including delivery of required thrust using specific fuel types and with power and performance of the pulse detonation engine variably adaptable. The fuel injectors associated with the pulse detonation engine configure to deliver specified flow rates with minimal linear movement of the flow control member. The injector and drive electronics configured to deliver higher frequency operation and response with increased operational stability.

A liquid supply mechanism includes a lower cover, an upper cover, a plunger, at least one resilient member and at least one damping member. The lower cover has a liquid outlet and the upper cover is connected to the lower cover. A chamber is formed between the lower cover and the upper cover. The chamber communicates with the liquid outlet and contains a cooling liquid. The upper cover has an axial hole. The plunger is movably disposed in the chamber. The plunger has an axial rod and the axial rod is inserted into the axial hole. The resilient member is disposed in the chamber. Opposite ends of the resilient member abut against the upper cover and the plunger. The damping member is disposed on the axial rod and abuts against an inner wall of the axial hole.

According to an aspect of the present invention, there is provided a lid system including: a lid mounted to a recess to be opened and closed; a locking unit that retains the lid in a locked state to keep the lid closed; and a lock releasing unit that releases the locked state to open the lid. The locking unit includes: a pin that is protruded from a peripheral edge of the lid to be engaged with a hole on the recess in the locked state and retreated to release the locked state. The lock releasing unit includes: a push button pushable in a pushing direction; and a pushing element moved to push the lock pin in an opposite direction of the pushing direction by being linked with the push button.