60results about How to "Improved heading stability" patented technology

The invention provides a variant stealth aircraft and a variant method and application thereof. According to stealth requirements, the aircraft is designed by adopting a force-lifting body edge-wing variable-configuration pneumatic layout scheme, and comprises two retractable full-motion canards and two deflectable full-motion empennages. The retractable full-motion canards can be retracted into amachine body during cruising of an aircraft or flying at a high speed, so that the scattering cross section of a radar is reduced, thus improving the invisibility. The deflectable full-motion empennages can be deflected to different angles in different flight states so as to serve as V-shaped tails, flat tails or ventral fins. Thus, transformation of the pneumatic layout of the aircraft is achieved, and the layout comprises a canard-type layout, a tail-free layout and a three-wing-surface layout. Through the switching of the three pneumatic layouts, the advantages of the three pneumatic layouts can be combined, thus better satisfying the requirements for the maneuverability and invisibility of the aircraft under different flight profiles and flight states. As a new-generation manned and unmanned aerial combat platform with high lift-drag ratio, high maneuverability and good invisibility, the variant stealth aircraft can be used for executing air dominant combat tasks.

A hard disc drive (HDD) that has improved head stability at low temperatures and a method of supplying current to a head of the HDD. The HDD includes a disc, a tunneling magneto resistance (TuMR) head to read data recorded on the disc having a heating coil, and a current control unit to supply a current corresponding to the ambient temperature surrounding the HDD to the heating coil. The current control unit supplies a current corresponding to the ambient temperature to the heating coil of the head. Since a heating coil is inserted in the TuMR head, an optimum current corresponding to the ambient temperature can be supplied to the heating coil, and thus, the head instability during a reading operation at low temperatures can be prevented.

The invention relates to a pneumatic layout of dual flying wings of a UAV (Unmanned Aerial Vehicle). The pneumatic layout is characterized by comprising a pneumatic layout of a blended wing body flying wing, a layout of installing a turbofan engine above the rear section of the blended wing body flying wing and a pneumatic layout of installing a stabilator at two sides of a nacelle on the outer wall of the turbofan engine, wherein the blended wing body flying wing with a high lift-to-drag ratio is formed by a fuselage, wings, wingtip winglets and direction ailerons together; the stabilator which is used for providing a positive lifting force during flight trimming of the UAV is formed by horizontal tails and horizontal tail winglets, and the dual flying wings are formed by the blended wing body flying wing and the stabilator together. According to the pneumatic layout of the dual flying wings of the UAV, disclosed by the invention, the UAV has high lift-to-drag ratio, good operability and high stability, and the pneumatic layout has the advantage of good stealth performance.

The invention discloses a double-rotor aircraft with folding wings, and a control method of the double-rotor aircraft, and relates to the field of aircrafts. The double-rotor aircraft comprises a fuselage, and the two wings respectively positioned at the two sides of the fuselage, wherein the two wings are hinged with the fuselage and can rotate around the longitudinal axis of the fuselage; rotorsystems are respectively arranged at the ends, far away from the fuselage, of the two wings; the rotor systems use the periodic variable pitch generated by a built-in automatic tilter to change the aerodynamic forces and aerodynamic moments of rotors, thus realizing the control of the pitch, yaw and rolling motions of the aircraft. The aircraft uses the same set of operating system when operatingin a helicopter mode and an aircraft mode. Compared with the existing vertical take-off and landing aircraft applying two sets of operating systems, the double-rotor aircraft provided by the inventionis simpler and more reliable in design, and does not need a redundant operating mechanism no matter during vertical take-off and landing or flat flight; the utilization rate of the structural components of the aircraft is improved, and the excessive structural weight is reduced. The double-rotor aircraft with the folding wings is applicable to aerial photography and can also be used for individual military investigation.

A disk apparatus includes a ramp which holds a tip end of an arm at a position away from a disk, and a slit shroud having an airflow control plate. A side surface of the airflow control plate is opposed to a side surface of the disk, the airflow control plate spreads to a position where the airflow control plate is superposed on the tip end of the arm held by the ramp. The airflow control plate has the same thickness as that of the disk, and is flush with the disk 12.

The invention discloses a control surface suitable for course autostability and control of a high-aspect-ratio flying wing arranging airplane. The control surface is composed of two control planes symmetrically arranged at the rear portion of an airplane body. Each control plane is controlled by a single steering engine. The rotation axis is identical to the axis of the airplane body in direction. The deflection angle range of the control surface ranges from -90 degrees to 90 degrees. The control surface and the airplane body are combined into a whole after the control surface is closed. Through cracking rotation of the left side and the right side of the control surface, the course stability of the flying wing arranging airplane is effectively improved, and the course operation stability characteristic of the flying wing arranging airplane is improved. Compared with an existing resistance type rudder used for the high-aspect-ratio flying wing arranging airplane, the control surface for course control has the beneficial effects of being simple in mechanical structure, high in operation efficiency, small in channel coupling and small in augmented resistance, the control planes can be freely collected and released according to the airplane hiding characteristic, and the control surface can be used as a course-control control plane of the flying wing arranging airplane.

The invention discloses an autonomous stable multi-degree-of-freedom motion controllable pod type underwater towed body which comprises a main body, a heave control mechanism, a bow turning control mechanism, an instrument pod fixing mechanism, a wing type trim control mechanism, a float type trim control mechanism, a transverse tilt control system and an instrument pod; the left heave control cabin and the right heave control cabin of the main body are of columnar cavity structures, and are arranged on the left side and the right side of the upper end of the main body at intervals; the left heave control cabin and the right heave control cabin are respectively connected with an instrument pod base through two inclined struts, and the left heave control cabin and the right heave control cabin are rigidly connected through a horizontal strut; the middle rear part of the horizontal strut is cut off to form a gap; and the heave control hydrofoil of the heave control mechanism is of a wing-shaped structure arranged in the gap at the rear part of the horizontal strut. The autonomous stable multi-degree-of-freedom motion controllable pod type underwater towed body has the advantages of independent stability, controllable multi-degree-of-freedom motion, good course stability, flexible heave control and the like.

The invention discloses a ship which can advance laterally and reduce the wave resistance. It includes ship body (1), the lateral position below the ship body (1) floating line is equipped with several tunnel (2) passing through the ship body (1), two ends of each tunnel (2) are equipped with propeller (3) respectively, the propeller (3) is connected with the drive device (K1) driving it work and the all-slewing equipment (K2) which can make the propeller (3) generate thrust towards any direction, it is also equipped with the lateral oscillating motion device(K3) which recalls and overhangs the propeller (3) into tunnel (2). The ship has simple structure, it can reduce the ship wave resistance effectively to pushing water navigation, as well as can make the propeller generate thrust towards any direction conveniently and recall or overhang the propeller into tunnel, it can effectively increase the cabin capacity of ship; it can realize turning conveniently and enhance the stability of ship course greatly.

The invention relates to a multi-pose downlink pedestrian position calculation method based on map information assistance, and belongs to the technical field of indoor positioning. Firstly, the problem that in the prior art, when a smart phone is used for pedestrian track plotting, equipment posture limitation exists is solved, and a course estimation algorithm is improved by calculating the acceleration integral in the moving direction of a user. A lightweight algorithm, namely a finite-state machine and a decision tree, is used for monitoring and identifying a mobile phone use mode, and behavior characteristic points are sensed by utilizing the characteristics of a gyroscope at a corner, so that the course estimation performance at a linear stage is improved. In addition, the problem ofoverlarge error accumulation caused by course angle deviation during positioning is solved. Map matching and particle filtering technologies are introduced to constrain the course, and improper transfer of particles, track through-wall and the like are limited by sensing behavior landmarks in indoor movement. According to the method, the heading estimation performance and the positioning robustness of the PDR system can be effectively improved, and the pedestrian experience is enhanced.

The invention relates to the technical field of ship propellers, in particular to a straight-wing rudder steering control method and system. The straight-wing rudder steering control method comprisesthe following steps that (A) an operating device is selected; (B) skipping to the step (C) when the target navigational speed and the target course are input, and skipping to the step (E) when the propelling direction and the rotational speed are input; (C) the course deviation is calculated, a left correction vector or a right correction vector is selected as a correction vector according to thecourse deviation; (D) a control vector is obtained after the correction vector and a propelling vector are added, the rotational speed and the propelling direction of straight-wing rudders are generated according to the control vector, and skipping to the step (E); (E) when the propelling direction is parallel to the central axis of a hull, the propelling direction zeta is corrected according to the inclination angle theta; and (F) the steps C to F are cycled. The straight-wing rudder steering control method and system have the substantial effects that by detecting the inclination angle of thehull, the propelling direction of a straight-wing rudder propeller on the side with small inclination is corrected according to the inclination angle, thus the difference, generated by inclination, of thrust on the two sides is offset, the influence on the course is avoided, and course stability is improved.

The invention provides a method for designing a UAV (unmanned aerial vehicle) provided with a deflectable winglet. The problems that most UAVs nowadays have big height loss when performing dive and climb maneuvers, cannot guarantee cruising property and has poor stalling characteristics are solved by respective design of a main wing, inverted V empennages and the deflectable winglet of the UAV. The inverted V empennage layout and a rear propeller power mode are adopted. According to the layout, interference drag between the empennages as well as between the empennages and the fuselage can be reduced with fewer parts, and downwash of the empennages can be weakened to enhance course stability. Meanwhile, propeller slipstream can be avoided by the layout, so that pitching stability is improved.

The invention discloses an embedded electric drive course stability augmentation type skid landing device and a working method thereof. The embedded electric drive course stability augmentation type skid landing device comprises an outer cylinder, an upper torsion arm, a lower torsion arm, a support, a skid, a guide wheel, an upper end cover, a piston rod, a rocker arm, a mounting plate, a friction plate, a load sensor, a buffer, a skid pitching buffer and an actuator cylinder module. The invention particularly provides an embedded electric drive course stability augmentation type skid landingdevice and a working method thereof. When the aircraft deviates in the sliding direction, the system controls the brushless motor to drive the rocker arm connecting rod mechanism to press the friction plate down the road surface to generate pressure, therefore, the binding force between the single-side landing device and the road surface is changed, the fuselage is subjected to yawing moment, sothat the skating direction of the aircraft is corrected, and the skating course stability of the aircraft is enhanced; the load sensor can measure the pressure of the friction plate on the road surface and provide feedback, the friction plate is made of a heat-resistant composite material, and specific lines are machined at the bottom of the friction plate, so that extra lateral force is provided,and the drifting phenomenon of the aircraft is reduced.

The invention discloses a method for designing a large-scale marine rudder horn. The method includes the following steps that 1, according to design drawing of a rudder blade, a rudder blade offset sheet on the design drawing of the rudder blade and the dimension, a contour line of the rudder blade marked is drawn; 2, a top plate contour line of the whole rudder blade is drawn; 3, according to thedistance from a bottom plate of the rudder blade to the bottom surface of a ship body and a structural form of a ship body stern part, the distance from a top plate of the rudder horn to the bottom plate of the rudder blade is determined, and according to a tabling structure of the rudder blade and the rudder horn, the distance from a bottom plate of the rudder horn to the bottom plate of the rudder blade is determined; 4, stations and station tracks on the bottom plate of the rudder horn and stations and station tracks on the top plate of the rudder horn are drawn; 5, a bottom plate contourline and a top plate contour line of the rudder horn are drawn; and 6, a tail part suspension position and a shape of the rudder horn are determined. According to the method for the designing large-scale marine rudder horn, the designed contour line of the rudder horn is in a good streamline shape and is in natural transition with the line shaped of the rudder blade.

The invention discloses an air inlet lip for improving and adjusting course stability of double-engine wing-body blending tailless configuration, which aims at solving the problems of poor course stability and neutral stability or instability of the existing wing-body blending tailless configuration. The existing common method using a vertical stabilizer for improving the course stability has the problem of increasing of the configuration radar scattering area; the method of increasing the sweepback of a main wing is restricted by the pneumatic efficiency and the structure strength, so the problem of insufficient course stability of the wing-body blending tailless configuration cannot be solved. The air inlet lip has the advantage that on the basis of the symmetric double engines commonly adopted by the wing-body blending tailless configuration, a new oblique type air inlet lip along the unfolding direction is designed, so the air inlet amounts of the engines at the two sides are different when the aircraft generates sideslip because of disturbance, and are increased along with the increase of the sideslip angle, the thrusts of the engines at the two sides are also different, a restoring moment is generated, and an aircraft nose points the incoming flow again.

The invention belongs to the technical field of aircraft structural design, and particularly relates to a variable-configuration cabin door for enhancing aircraft course stability and a control methodthereof. The variable-configuration cabin door comprises a follow-up inner-layer cabin door, an outer-layer cabin door, a driving mechanism and a locking mechanism. The outer-layer cabin door is arranged on the outer side of the follow-up inner-layer cabin door; the driving mechanism comprises a rotating shaft, a rotating actuator, a first rocker arm and a second rocker arm and can drive the outer-layer cabin door to be opened or closed; the locking mechanism comprises a first locking mechanism body and a second locking mechanism body, the first locking mechanism body can lock the follow-up inner-layer cabin door and the machine body, and the second locking mechanism body can lock the outer-layer cabin door and the follow-up inner-layer cabin door. The heading stability of the tailless layout aircraft can be remarkably improved, the flight performance and maneuverability are effectively improved. Meanwhile, a large cavity is prevented from being formed as much as possible after the cabin door is opened, the cavity resistance generated after the outer-layer cabin door is opened is very small and can be almost ignored, and the aerodynamic characteristics of the aircraft are not affected.

The invention provides an aerodynamic layout structure of a high-speed aircraft. A precursor (1), namely, the head of the aircraft, is designed to be an axisymmetric corpus vertebrae. Gas inlets (2) are arranged on two sides of the precursor (1). The installation included angle (19) is selected to be 150-180 degrees. Binary compression gas inlets are adopted as the gas inlets (2). A binary gas inlet profile is designed by using an oblique shock wave theoretical relation according to the principle of "sealing a compression shock wave system (18)". A radar of the aerodynamic layout structure isgood in wave transmission performance and sufficient in installation space, and the lift-to-drag ratio of the aircraft is improved.

There is provided a head-gimbal-assembly for use in heat-assist magnetic recording, excellent in the heat-release characteristic of a laser diode, by inhibiting effects of deterioration in lateral balance, and wind turbulence without adversely affecting efforts to lower a profile of a magnetic disk unit. For this purpose, a sub-mount with a laser diode attached thereto is mounted on either of the right and left lateral faces of a head slider. Further, of two lengths of lead wires for power supply to the laser diode, one length of the lead wire is routed to a lateral face of the head-slider, on the opposite side of a lateral face with the sub-mount attached thereto, after circling around the outer periphery of a head-slider electrode, formed on the gas-outlet side of the head slider.

A TAMR (Thermal Assisted Magnetic Recording) writer has a narrow pole tip with a trailing edge magnetic shield. The narrow pole tipped write head uses the energy of laser generated edge plasmons, formed in a plasmon generating layer, to locally heat a PMR magnetic recording medium below its Curie temperature, Tc. When combined with the effects of the narrow tip, this local heating to a temperature below Tc is sufficient to create good transitions and narrow track widths in the magnetic medium. The write head is capable of writing effectively on state-of-the-art PMR recording media having Hk of 20 kOe or more.

A volute shaped pump casing for a centrifugal pump includes a chamber for housing at least one impeller rotatable around an axis of rotation and a volute shaped chamber which forms a flow channel and which contains a splitter rib for dividing the flow channel formed wherein in a section perpendicular to the axis of rotation a mean camber line is positioned equidistantly between an inner and outer surface of the splitter rib, where the thickness of the splitter rib is varied along the mean camber line and for the mean camber line unwrapped to a straight line there is a maximum in the thickness, s, of the splitter rib, wherein said maximum is positioned at a distance L from the leading edge of the splitter rib, and wherein the distance L is in the range between 1.4 times the maximum thickness s and 6 times the maximum thickness s.

The invention discloses a catamaran and relates to the technical field of ships. Each sheet body of the catamaran has the same structure; the catamaran comprises a bow area, a middle area and a sternarea; the bow area, the middle area and the stern area are in smooth transition connection with each other in sequence; the design of a cylinder bulbous bow can change the bow waveform generated by the catamaran during running at a high speed to form favorable interference; as a stem is of a plate type structure, and the horizontal sections of shell platings on the two sides are laminated on the stem in a V shape, it can be guaranteed that each sheet body has a flooding angle which is small as much as possible; a falling stem makes a waterline of a bow of each sheet body be in an unsymmetricalshape; when the catamaran runs at the high speed, more water at the front ends of the sheet bodies is forced to be shunted to the external side so that water flowing to the internal sides of the sheet bodies are reduced; and therefore, wave making interference between the two sheet bodies is also reduced; and the stern area adopts two concave kunckle lines which are gradually retracted in the lifting process to form integrated stern tower.

The invention discloses a three-channel water surface composite yacht which comprises a main yacht body. Side bodies are arranged on the two sides of the bottom of the main yacht body respectively. Two middle yacht bodies are arranged between the two side bodies. Three channels are formed between the two side bodies and the two middle yacht bodies. Hydrofoil systems are arranged at the front ends or the rear ends of the three channels. Each hydrofoil system comprises a hydrofoil, a rotating rod and a control device, wherein the rotating rod penetrates through the hydrofoil, the rotating rod drives the hydrofoil to rotate, the control device is installed on the corresponding middle yacht body and connected with the hydrofoil through the rotating rod, and the hydrofoil is driven by the control device to rotate. According to the three-channel water surface composite yacht, through the combination of the good layout characteristic, good resistance performance and high shipping-direction stability of a three-channel skimming yacht and the rapidness and good comprehensive navigation performance of a hydrofoil yacht with controllable hydrofoils, the inherent defects of the three-channel skimming yacht and the hydrofoil yacht are well overcome.

An intersection point between a shaft axis Z1 and a sole surface 18 is defined as S1. A point S2, a point S3, and a point S4 are set on the sole surface 18. An intersection point between a straight line passing through a center of gravity of the head and being perpendicular to the horizontal plane and the sole surface 18 is defined as G1. A point R1, a point R2, a point R3, and a point R4 are set on the sole surface 18. A section A1 and a section A2 are set based on the points. An angle between the shaft axis Z1 and a ground plane is defined as θ. The angle θ exists so that at least a point belonging to the section A1 and at least a point belonging to the section A2 are brought into contact with the ground plane.

The invention provides a lateral-drift-resistant damping system of an all-hovering hovercraft. The system comprises damping plates mounted at the bottom of the hovercraft and a control system controlling the damping plates to rise to be folded or drop to be used, and the damping plates are arranged along the navigation direction of the hovercraft. By the lateral-drift-resistant damping system of the all-hovering hovercraft, when the hovercraft navigates, the damping plates can be put down, and direction stability of the hovercraft can be improved greatly; when the hovercraft needs to land, a driver can put the damping plates in a hull, and the hovercraft can land just like an ordinary all-hovering hovercraft and even navigates on land.

The invention discloses an unmanned catamaran having torpedo submerged bodies and driven by multiple renewable energy sources. The unmanned catamaran having the torpedo submerged bodies and driven bymultiple renewable energy sources comprises forward tilting sheet bodies, a watertight box type connecting bridge, wing type stabilizing uprights, the torpedo submerged bodies, a heaving power generation system, a solar power generation system, a propelling system and a control system; the two forward tilting sheet bodies are connected with each other through the watertight box type connecting bridge to form a portal structure; the two torpedo submerged bodies are arranged under the two forward tilting sheet bodies; each torpedo submerged body is connected with the forward tilting sheet body through at least two wing type stabilizing uprights which are arranged in a spaced manner; the wing type stabilizing uprights are of hollow structures with cross sections of NACA wing sections; the upper ends of the wing type stabilizing uprights are fixedly connected with the forward tilting sheet bodies; and the lower ends of the wing type stabilizing uprights are fixedly connected with the torpedo submerged bodies. The unmanned catamaran having the torpedo submerged bodies and driven by multiple renewable energy sources has the advantages of good course stability, long duration, stable overturning resistance and so on; and the unmanned catamaran having the torpedo submerged bodies and driven by multiple renewable energy sources also realizes a self-righting ability after being overturned.

The invention provides a winglet for increasing pneumatic efficiency of a horizontal tail of a time-domain airplane. The winglet has a pneumatic profile as below: a wing root employs a NACA0012 aerofoil profile and has a chord length of 500 mm; a wingtip employs a NACA0009 aerofoil profile and has a chord length of 300 mm; a ratio of wing root to wingtip of the winglet is 0.6; a stretched length of the winglet is 800 mm; a profile from the wing root to the wingtip of the winglet is in linear transition; the winglets are uprightly arranged on stabilizers of horizontal tails on two sides of the airplane and on a position 75% of a horizontal tail stretched length; an upper surface and a lower surface of each horizontal tail are respectively provided with a winglet, and totally four winglets are in symmetry in the left-right direction. The invention has advantages that without changing a basic dimension of the horizontal tail, winglets are added to realize goals of increasing pneumatic efficiency of the horizontal tail and improving airplane course stability. As the basic profile dimension of the horizontal tail remains unchanged, the arrangement positions of the winglets are optimized and have little influence on an elevator; and tests also show that addition of the winglets causes no unfavorable influence on elevator control rule.

The invention provides a novel dead rudder structure of a maritime work auxiliary ship. The novel dead rudder structure comprises a flow guide section, a section connected with a ship body, a main body section, a flow removal section, a lower transition section and a bottom plate. The main body section is connected with the ship body through the section connected with the ship body, the flow removal section is connected to the main body section and the first end of the section connected with the ship body, and the flow guide section is connected to the main body section and the second end of the section connected with the ship body and is connected with the ship body; and the bottom plate is connected with the flow removal section, the main body section and the flow guide section through the lower transition section. According to the novel dead rudder structure of the maritime work auxiliary ship, the hydrodynamic performance is further optimized, and the energy-saving performance andthe navigation performance of the ship are improved.

The invention provides a lateral-drift-resistant damping system of an all-hovering hovercraft. The system comprises damping plates mounted at the bottom of the hovercraft and a control system controlling the damping plates to rise to be folded or drop to be used, and the damping plates are arranged along the navigation direction of the hovercraft. By the lateral-drift-resistant damping system of the all-hovering hovercraft, when the hovercraft navigates, the damping plates can be put down, and direction stability of the hovercraft can be improved greatly; when the hovercraft needs to land, a driver can put the damping plates in a hull, and the hovercraft can land just like an ordinary all-hovering hovercraft and even navigates on land.