35results about How to "Improve handling quality" patented technology

A cord material suitable for use in lined textile structures with a gliding component includes a plurality of uniform strands, and a deviant strand. The deviant strand is different from the uniform strands in some characteristic affecting aerodynamic or hydrodynamic properties of the cord, such as size or surface properties. Each uniform strand can have a substantially equal cross section area, while the deviant strand has a cross section area at least five times greater than one of the uniform strands. The strands can be braided or woven together. A major benefit of the material can be that vibration induced drag is significantly reduced or eliminated in lines made with the material. Another advantage is that lines made from the material can have more consistent, predictable line drag, which can improve the quality of handling.

A flight control system includes a collective position command module for a lift axis (collective pitch) which, in combination with an active collective system, provides a force feedback such that a pilot may seamlessly command vertical speed, flight path angle or directly change collective blade pitch. The collective position command module utilizes displacement of the collective controller to command direct collective blade pitch change, while a constant force application to the collective controller within a “level flight” detent commands vertical velocity or flight path angle. The “level flight” detent provides a tactile cue for collective position to reference the aircraft level flight attitude without the pilot having to refer to the instruments and without excessive collective controller movement.

An improved gas block for a firearm has a first longitudinal bore for receiving a firearm barrel, the barrel having a gas port, the gas block having a second longitudinal bore for receiving a gas tube or operating element. The block includes a vertical bore aligned with the barrel gas port and connecting the first and second block bores and permitting passage of cartridge gas from the barrel gas port to the gas tube. The improved gas block may include a military rail, forward of the gas tube, the forward location permitting the rail and accessories to lie close to the barrel, improving handling and reducing bulk. The barrel may include a conical cavity generally opposite the gas port. The block may include a conical point set screw adapted to mate with the barrel conical cavity, the screw when tightened forcing alignment of the block vertical bore with the barrel gas port and simultaneously clamping the block to the barrel. An installation device provides a means for forming a conical cavity in the barrel surface.

Apparatus and method are disclosed for the production of compacted granular potassium chloride with improved handling qualities. A binding ingredient such as sodium hexametaphosphate is blended with the potassium chloride feed material in advance of compaction. The product of this apparatus and method has improved handling, storage, strength and other qualities over compacted granular potassium produced using prior art methods.

Apparatus and method are disclosed for the production of compacted granular potassium chloride with improved handling qualities. A binding ingredient such as sodium hexametaphosphate is blended with the potassium chloride feed material in advance of compaction. The product of this apparatus and method has improved handling, storage, strength and other qualities over compacted granular potassium produced using prior art methods.

The present invention relates to a polarizing plate protective film base comprising a laminated film comprising a biaxially oriented polyester film and a coating layer provided on one side of said biaxially oriented polyester film,the surface resistance of said coating layer being not more than 1×1011Ω,the adhesive force (P2) of the coating layer surface with an acrylic adhesive being not more than 3,000 mN / cm, andthe difference between adhesive force (P1) of the coating layer surface with a rubber adhesive and adhesive force (P2) with an acrylic adhesive (P1−P2) being not less than 100 mN / cm.

A compact gas block with rail interface has a first longitudinal bore for receiving a firearm barrel, the barrel having a gas port, the gas block having a second longitudinal bore for receiving a gas tube or operating element. The block includes a vertical bore aligned with the barrel gas port and connecting the first and second block bores and permitting passage of cartridge gas from the barrel gas port to the gas tube. The improved gas block includes a military rail, forward of the gas tube, the forward location permitting rail and accessories to lie close to the barrel, enabling handguard installation and removal, improving handling, and reducing firearm bulk.

A method of controlling the flight of a rotorcraft in a feed-forward / feedback architecture includes utilizing an aircraft plant model to control the rotorcraft performance; determining when an external load is coupled to the rotorcraft; and modifying an inverse plant when the external load is present.

The invention discloses a variable-pitch slippage circumferential dual-rotor wing. The variable-pitch slippage circumferential dual-rotor wing is used for a helicopter. The variable-pitch slippage circumferential dual-rotor wing comprises an input end, a splined hub, a one-way commutator, a pitching controller, a dual-way deflector, a steering supporting seat, an inner total pitch controller, an outer total pitch controller and two input ends; the input ends are connected with a power device; the one-way commutator comprises a same-direction shaft, a front bevel gear, a commutating bevel gear,a rear bevel gear and a coaxial reversing sleeve shaft; the dual-way deflector comprises a deflecting initiative inner bevel gear, a deflecting initiative outer bevel gear, a passive inner bevel gear, a passive outer bevel gear and an output sleeve shaft; the steering supporting seat comprises a fixed shaft bearing, a steering supporting frame, a movable shaft bearing, a worm wheel and a worm; the inner total pitch controller is connected with an inner total pitch control mechanism, and the outer total pitch controller is connected with an outer total pitch control mechanism; the splined huband the one-way commutator can be replaced with a dual-way side shaft sliding gear transmission mechanism; and control mechanisms of course control, lifting control, pitching control and transverse rolling control are basically independent with each other, and intersecting coupling is eliminated.

The invention provides a system and a method for an unmanned boat for shake reducing and stability increasing based on pitch-rotational speed differential. The system comprises four parts of a propulsion part, a propulsion control part, a tail rudder part, and a tail rudder control part. The propulsion part comprises a left variable pitch propeller, a left drive mechanism, a right variable pitch propeller, and a right drive mechanism, wherein the left variable pitch propeller and the right variable pitch propeller are opposite in steering, and rolling moment is generated by the pitch-rotational speed differential while generating thrust; the propulsion control part comprises a rolling angular rate gyroscope, a rolling angular rate commander, and a rolling angular rate controller for rolling stability increasing and control; the tail rudder part comprises a left rudder, a left steering gear, a right rudder, and a right steering gear, and the left rudder and the right rudder are simultaneously deflected to generate yawing moment; and the tail rudder control part comprises a yawing angular rate gyroscope, a yawing angular rate commander, and a yawing angular rate controller for yawingstability increasing and control. According to the system and the method for the unmanned boat for shake reducing and stability increasing based on the pitch-rotational speed differential, the rolling and yawing operation quality can be improved by taking the pitch-rotational speed differential of the double propeller and the synchronous deflection of a double control surface as the shake reducing and stability increasing mode of the unmanned boat.

A method of controlling the flight of a rotorcraft in a feed-forward / feedback architecture includes utilizing an aircraft plant model to control the rotorcraft performance; determining when an external load is coupled to the rotorcraft; and modifying an inverse plant when the external load is present.

A fixed shaft type full-moving rudder surface mounting structure provided by the invention comprises a rotating shaft, a limiting bolt, a beam, a cushion block, a tightening nut and a rocker arm, andthe rotating shaft is inserted into a fuselage supporting structure and is fixed through the limiting bolt. The beam and the cushion block are sleeved on the rotating shaft and are locked by the tightening nut combined with the rotating shaft, the rocker arm is fixedly connected with the beam through bolts, and a steering engine controls the rocker arm to drive the beam to rotate around the rotating shaft. The fixed shaft type full-moving rudder surface mounting structure has the characteristics of only one key mounting procedure, simple limiting structure and limiting mode, clear limiting effect of each fulcrum, no over-constraint, effectiveness in guaranteeing that the installation position of the full-moving rudder surface is within the reasonable tolerance range relative to the theoretical position of the full-moving rudder surface, stable rudder surface control gap, no increase of the rotating friction force of the rudder surface, and facilitation of improvement of the service life of related structural parts, the airplane flutter speed and the flight quality.

The invention discloses a design method of the influence of the deformation difference between an airplane and a mechanical control system on maneuvering control. The design method comprises the following steps: (1) according to requirements of resultant force and the resultant moment of force during airplane maneuvering, the control surface skewness needed by longitudinal and transverse course maneuvering during airplane maneuvering is calculated; (2) the deviation of deformation of the mechanical control system relative to the airplane in the airplane maneuvering process is calculated; (3) control displacement and control force of a cockpit of the airplane in the airplane maneuvering process are calculated; and (4) according to different object overloads during airplane maneuvering, thestep (1) to the step (3) are repeated, and the rod force gradient and the rod displacement gradient of the target overloads corresponding to the control displacement and the control force of the longitudinal and transverse course cockpit during airplane maneuvering are obtained. The real mechanical control system characteristic determining process of the airplane during flying and a real airplanemaneuvering control characteristic design determining method are achieved, consistency of flying and design is ensured, mechanical control system characteristic errors are corrected, safety of airplane flying is improved, and the control quality is improved.

The invention provides an unmanned boat rotational speed differential anti-rolling stability augmentation system and method. The unmanned boat rotational speed differential anti-rolling stability augmentation system comprises a propulsion part, a propulsion control part, a sternpost rudder part and a sternpost rudder control part. The propulsion part comprises a left propeller, a left driving mechanism, a right propeller and a right driving mechanism, the left propeller and the right propeller rotate in the opposite directions, and rolling moment is generated by rotational speed differential while generating thrust. The propulsion control part includes a rolling angular velocity gyroscope, a rolling angle velocity commander and a rolling angular velocity controller, and is used for rollingstability augmentation and control. The sternpost rudder part includes a left rudder, a left steering engine, a right rudder and a right steering engine, and the left rudder and the right rudder aresimultaneously deflected to produce yawing moment. The sternpost rudder control part includes a yawing angular velocity gyroscope, a yawing angular velocity commander and a yawing angular velocity controller, and is used for yawing stability augmentation and control. The unmanned boat rotational speed differential anti-rolling stability augmentation system and method adopt the double-propeller rotational speed differential and the double-rudder-surface synchronous deflection as the anti-rolling stability augmentation mode of an unmanned boat, and the rolling-yawing control quality can be improved.

The invention provides an unmanned boat rolling-heading coordination stability augmentation control system and method. The unmanned boat rolling-heading coordination stability augmentation control system comprises a propulsion part, a propulsion control part, a sternpost rudder part, a sternpost rudder control part and a coordination control part. The propulsion part comprises a left variable pitch propeller, a left driving mechanism, a right variable pitch propeller and a right driving mechanism, the left variable pitch propeller and the right variable pitch propeller rotate in the opposite directions, and rolling moment is generated by propeller pitch differential and rotational speed differential. The propulsion control part includes a rolling angular velocity gyroscope, a rolling anglevelocity commander and a rolling angular velocity controller, and is used for rolling stability augmentation. The sternpost rudder part includes a left rudder, a left steering engine, a right rudderand a right steering engine, and the left rudder and the right rudder are simultaneously deflected to produce yawing moment. The sternpost rudder control part includes a yawing angular velocity gyroscope, a yawing angular velocity commander and a yawing angular velocity controller, and is used for yawing stability augmentation. The coordination control part is used for rolling-yawing coordinationcontrol. The double variable pitch propellers and double-rudder-surface coordination control are used as the anti-rolling and stability augmentation mode of an unmanned boat, and the rolling-yawing control quality can be improved.

A cord material suitable for use in lined textile structures with a gliding component includes a plurality of uniform strands, and a deviant strand. The deviant strand is different from the uniform strands in some characteristic affecting aerodynamic or hydrodynamic properties of the cord, such as size or surface properties. Each uniform strand can have a substantially equal cross section area, while the deviant strand has a cross section area at least five times greater than one of the uniform strands. The strands can be braided or woven together. A major benefit of the material can be that vibration induced drag is significantly reduced or eliminated in lines made with the material. Another advantage is that lines made from the material can have more consistent, predictable line drag, which can improve the quality of handling.

The invention provides a glass curtain wall construction carrying device. The glass curtain wall construction carrying device comprises a storage frame, two storage chambers, eight limiting plates, four pressure relief structures, four clamping grooves and a protection structure, wherein the two storage chambers which are each of a rectangular structure and are used for storing glass are symmetrically arranged in the storage frame; the four clamping grooves are symmetrically arranged in the storage frame in a two-two corresponding manner, and the clamping grooves are in communication with thestorage chambers; the protection structure comprises an anti-collision sleeves and a limiting rod, the anti-collision sleeve is clamped with the storage frame, the anti-collision sleeve used for sealing the storage chambers is clamped with the clamping grooves, and the limiting rod is connected with the storage frame and the anti-collision sleeve in a penetrating manner; and the limiting rod is rotationally connected with the anti-collision sleeve, and the limiting rod is in threaded connection with the storage frame. The glass curtain wall construction carrying device has the advantages of being flexible in operation, recyclable, high in carrying efficiency and good in anti-collision performance.

The invention provides a glass curtain wall construction and handling device. The glass curtain wall construction handling device includes a storage frame; two storage rooms, two storage rooms with a rectangular structure for storing glass are symmetrically arranged inside the storage frame; eight limiting plates; four pressure relief Structure: four card slots, four card slots are symmetrically arranged in the storage frame in pairs, and the card slots are connected to the storage room; protective structure, the protective structure includes a bumper sleeve and a limit rod , the anti-collision cover is engaged with the storage frame, the anti-collision cover for sealing the storage chamber is engaged with the slot, and the limit rod is connected through the storage frame and the storage room. The anti-collision sleeve, the limiting rod is rotationally connected with the anti-collision sleeve, and the limiting rod is threadedly connected with the storage frame. The glass curtain wall construction transport device provided by the invention has the advantages of flexible operation, recyclable use, high transport efficiency and good anti-collision performance.

The invention discloses an aircraft hydraulic brake valve control force determination method. According to a working operation applied to an aircraft hydraulic brake valve by a pilot, and aiming at gradual building of the brake pressure and dynamic change rules of the brake control force in the pressure keeping and releasing process, the specific and feasible control force determination method isprovided to research and master the change conditions of the needed dynamic control force for detailed dynamic analysis of the brake control process, comprehensive mastering of the control characteristics of the hydraulic brake valve and the change conditions of the control force. In the process of maximizing and keeping the valve element working operation from zero by a period of time and returning to zero, the change conditions of the control force and the valve element working operation, and the brake pressure and the load flow are mastered. The brake system control characteristics are designed based on the method, the pilot control feeling during braking can be optimized and improved, and the control quality of an aircraft brake system is improved.

The invention provides an advanced controller design method for an active side rod, belonging to the technical field of civil aircraft active side rod control. The invention particularly provides a servo controller hardware platform design method for the vector control of a medium and low-power sine wave motor. Through the design of a cabinet, a power board, a current acquisition board and a digital servo control board, the electronic verification platform of an active side rod servo control system is set up, and the relevant technical verification and engineering realization of the active side rod control are completed. A processor and field programmable gate array parallel work structure is adopted, the event manager module of the processor directly outputs the pulse width modulation signal, the decoding chip special for a rotary transformer completes the high-precision demodulation of the rotor position and speed, the high-speed and high-precision current acquisition can be completed by frequency division modulus sampling and properly selected filtering design, so that the problem influencing the medium and low-power sine wave motor vector control performance can be solved, and the accurate control of the active side rod sine wave motor by means of the space vector pulse width modulation technology.

The reversible power-assisted control system comprises an operation pull rod, a steering wheel and a universal ball shaft, pedal devices are located on the two sides of the operation pull rod, the pedal devices are in hydraulic connection with a power assisting device, and the universal ball shaft is connected with the stability augmentation device through a connecting device. The stability augmentation device comprises a support, a sleeve and a first transmission gear, the support is a fixing piece, the sleeve is connected to the support in a sliding mode through a first extrusion spring, the spring is in a compressed state, the sleeve is further provided with threads, the sleeve is in threaded fit with the connecting device, and when the universal ball shaft drives the connecting device to rotate, under the action of the threads, the sleeve is driven to rotate. The first compression spring is further compressed. According to the reversible power-assisted control system, the problem that the airplane pedal is difficult to operate is solved through the power-assisted device, and the control performance is more effectively and directly improved by additionally arranging the stability augmentation device.

The invention discloses an XYZ axis three-direction precision compensation structure suitable for a precision handling mechanism, comprising an upper mounting plate and a lower mounting plate of the mechanism, a guide component and an elastic plunger are arranged on the upper mounting plate of the mechanism; the guide component is arranged on the mechanism At the four corners of the installation plate, elastic plungers are arranged symmetrically on the opposite edges of the upper installation plate of the mechanism, the bottom of the elastic plunger is connected to the lower installation plate of the mechanism, and the guide assembly is inserted into the lower installation plate of the mechanism; the guide assembly includes Guide sleeve and guide shaft, the guide sleeve is fixed on the upper installation plate of the mechanism, the guide shaft is in the guide sleeve and the bottom of the guide shaft is inserted into the lower installation plate of the mechanism, and is squeezed to the elastic plunger by the downward movement of the Z axis of the conveying mechanism The guide shaft and the guide sleeve can be separated, and a matching gap is formed between the separated guide shaft and the guide sleeve; the upper mounting plate of the mechanism is also provided with a top tightening screw. The invention realizes the three-direction precision compensation of the XYZ axis of the transport mechanism, and improves the transport success rate, the transport precision and the transport quality.

The invention discloses an intelligent feeding and discharging carrying system which comprises a rack, a gas tank, a rope lifting hook, a conveying system, a spraying and drying area, a finished product packaging area, a supporting structure and an intelligent mobile robot, the gas tank which is not sprayed and dried is conveyed to the intelligent mobile robot through the conveying system, and the gas tank is hung on the rope lifting hook through the intelligent mobile robot; the gas tank which is not sprayed and dried is installed on a transmission mechanism through the rope lifting hook and reaches the spraying and drying area through the transmission mechanism. And the sprayed and dried gas tank arrives at another intelligent mobile robot through the transmission mechanism again, is placed on the transmission system through the intelligent mobile robot, and enters a finished product packaging area through the transmission system. The automatic and intelligent functions of feeding and discharging carrying are achieved, the problems that manual carrying consumes time and labor and is high in cost are solved, centrality, safety and normalization in the carrying process are guaranteed, and high-efficiency and high-quality feeding and discharging carrying actions are achieved.

Disclosed is a method for determining the pressure of a plane hydraulic brake valve pressure sensing cavity. Through detailed stress analysis of a hydraulic brake valve element and detailed dynamic analysis of the braking controlling process, the specific and feasible pressure sensing cavity pressure determining method is provided from the dynamic changing rules of the pressure of the pressure sensing cavity in the processes of gradual building, maintaining and releasing of braking pressure, the change conditions of the controlling force of a hydraulic brake valve are mastered, control characteristic design of a braking system is conducted on the basis, the controlling feeling of a pilot during braking is optimized, and the controlling quality of the plane braking system is improved. The control characteristic design of the braking system is conducted based on the method, the controlling feeling of the pilot during braking is optimized, and the controlling quality of the plane brakingsystem is improved.

Disclosed is a method for determining the pressure of a plane hydraulic brake valve pressure sensing cavity. Through detailed stress analysis of a hydraulic brake valve element and detailed dynamic analysis of the braking controlling process, the specific and feasible pressure sensing cavity pressure determining method is provided from the dynamic changing rules of the pressure of the pressure sensing cavity in the processes of gradual building, maintaining and releasing of braking pressure, the change conditions of the controlling force of a hydraulic brake valve are mastered, control characteristic design of a braking system is conducted on the basis, the controlling feeling of a pilot during braking is optimized, and the controlling quality of the plane braking system is improved. The control characteristic design of the braking system is conducted based on the method, the controlling feeling of the pilot during braking is optimized, and the controlling quality of the plane brakingsystem is improved.

The invention discloses a method for designing the influence of deformation differences between an aircraft and a mechanical control system on maneuvering maneuvers, comprising the following steps: 1) according to the requirements of the resultant force and moment during the maneuvering of the aircraft, calculating the rudder surfaces required for the longitudinal, lateral and directional maneuvering of the aircraft Skewness; 2) Calculate the deviation of the mechanical control system relative to the deformation of the aircraft during the maneuvering process of the aircraft; 3) Calculate the cockpit control displacement and control force of the aircraft during the maneuvering process of the aircraft; 4) Repeat the steps according to the different target overloads during the maneuvering of the aircraft 1-Step 3, obtain the vertical, horizontal and heading cockpit control displacements, control force gradients and lever displacement gradients of the corresponding target overloads during maneuvering, and the present invention realizes the determination of the real mechanical control system characteristics of the aircraft in flight The process, as well as the actual design and determination method of aircraft maneuvering and control characteristics, ensure the consistency of flight and design, correct the error of mechanical control system characteristics, improve the safety of aircraft flight, and improve the control quality.

The invention provides a technical project of superconductive power device, its character: it has a casing, there is a high-frequency alternative electromagnetic filed generator in the casing, and there is an superconductive disk at the lower part of the high-frequency alternative electromagnetic field generator. The generator and the superconductive disk are separated from each other, and it transmits energy by high-frequency alternative electromagnetic travelling wave. The case is a magnetic screening cover. The method that the superconductive power device inputs energy to the superconductive disk: connects a power supply to the above generator to drive the generator to generate high-frequency alternative electromagnetic traveling wave, and then uses the traveling wave to act on the superconductive disk, and because of extremely high inductivity, the superconductive disk induces extremely strong erratic current on its own surface. It depends on compact strong vector magnetic filed produced by the superconductive disk to act on natural magnetic field and obtains action of force, and the energy source is electronic energy.

The invention relates to the field of building materials, in particular to a high-hardness three-layer co-extrusion wood plastic profile. The high-hardness three-layer co-extrusion wood plastic profile comprises four moving structures, two handling grooves, a driving structure, a support plate, first limiting structures, a fixing structure, a protection structure, second limiting structures, mounting structures and four clamping blocks. The two handling grooves of a rectangular structure and for handling the support plate are formed in the moving direction of the shorter sides of the bottom end of the support plate. The four moving structures for handling the support plate are arranged at four corners of the bottom end of the support plate. The driving structure for driving the sliding ofthe moving structures is disposed in the support plate. The first limiting structures for fixing the wood plastic profile are arranged at the top end of the support plate, and the first limiting structures are provided the second limiting structures for adjusting the stability of the wood plastic profile. Through the arrangement of the handling grooves of a rectangular structure at the bottom endof the support plate, the wood plastic profile is conveniently transferred by a forklift, and the first limiting structures are matched with the second limiting structures to facilitate fixation of the wood- plastic profile layer by layer, so that the stability of the fixation of the profile is improved.