81results about How to "Improve landing accuracy" patented technology

A system for emergency crew return and down-mass orbit comprising a stowable, self-contained, deployable maneuvering reentry vehicle for automated, on-demand reentry to ground for cargo of 1-10 kilograms or up to single or multiple human use for evacuation of orbital facilities. The system includes a deployable “aeroshell” that is contiguous (a single geometric object—surface or hollow shape—that can morph in 3D shape), modular (a collection of modular components externally acting as a contiguous shape, but morphed in 3D via actuators contained in each modular member to create a general asymmetric geometry), or discontiguous (a collection of independently controlled surfaces or bodies that morph to form desirable asymmetric drag configurations). The system contains traditional spacecraft guidance, navigation and control, propulsion, and attitude control elements, in addition to communications, power, and actuator energetics systems for controlling the vehicle aeroshell shape during reentry, thus, minimizing the landing footprint of the vehicle.

The invention provides a control method of accurate landing of an unmanned aerial vehicle. The control method is used for controlling the unmanned aerial vehicle to reach a present landing point. The control method is characterized by comprising the following steps that 1 a sound source is placed at the landing point, regular-tetrahedron-shaped microphone arrays are placed on the unmanned aerial vehicle and a signal amplification circuit and a filtering circuit are arranged at the signal output end of each microphone; 2 GPS navigation is used for controlling the unmanned aerial vehicle to reach the range which is ten meters away from the landing point; 3 a processor on the unmanned aerial vehicle is used for calculating delay generated when sound source signals reach the second microphone, the third microphone, the fourth microphone and the first microphone; 4 the yaw angle and the pitch angle of the unmanned aerial vehicle are calculated through the processor according to the spatial geometric relationship of the sound source and the microphone arrays and delay values; 5 the unmanned aerial vehicle is navigated to the position over the landing point according to the yaw angle and the pitch angle; 6 an air pressure height sensor is used for enabling the unmanned aerial vehicle to be landed at the landing point accurately.

The image forming apparatus comprises: a line type recording head which is arranged so that a longitudinal direction thereof is substantially orthogonal to a conveyance direction of a recording medium; a suction pipe which is disposed in parallel with the recording head and connected to a suctioning device; a rotating body which is supported rotatably on an outer circumference of the suction pipe and has a first opening section and a second opening section; a platen which is arranged in the first opening section of the rotating body movably in parallel with the conveyance direction of the recording medium; and a cap member which is arranged in the second opening section of the rotating body and adapted to cap nozzles of the recording head, wherein the recording medium is suctioned onto the platen and parallelly moved along a conveyance path in a state where the first opening section of the rotating body is connected to the suction pipe.

The invention relates to a finely segmented parafoil homing control method which comprises the following steps: S1, acquiring navigation parameters of the parafoil through a navigation module, wherein the navigation parameters comprise position, height, speed and flight direction of the parafoil and a yaw angle of a target center; S2, performing data analysis on the acquired parameters through the navigation module, and outputting effective data to a parafoil control module; and S3, performing comprehensive analysis and discrimination on the navigation data through the parafoil control module, and transmitting a control signal according to a fine segmentation method. The segmented homing method is subjected to fine segmentation, a homing path of a low-altitude parafoil is reasonably planned in an emphasized mode according to real-time height, position and other information of air-drop system, a corresponding control strategy is formulated, an adverse effect of low-altitude air and other environmental factors on the control precision of the system is reduced, an autonomous homing path of the parafoil is effectively controlled, landing precision is controlled in an effective range, and the landing precision is improved.

The invention relates to a novel thin-interbedded horizontal well landing geosteering method. The horizontal well landing geosteering method includes the following steps: (1) constructing a horizontal well landing geosteering comparison model; (2) vertically correcting an LWD (Logging While Drilling) curve of a curve section; (3) carrying out error judgement and determining structure errors in real time by means of the fine comparison of the landing geosteering comparison model; and (4) determining a trajectory adjustment according to the structure errors scheme. The method realizes the transformation from conventional mark comparison to digitalized continuous comparison, and has the dual characteristics of real-timeliness and accuracy; and the digitized comparison profile of a landing section is established before drilling, the LWD curve is digitized in real time in the process of landing, and is finely compared with the profile after the vertical depth is corrected, the structure is corrected in real time, a result is judged according to the structure errors, the trajectory design is updated in real time, and thereby accurate landing can be realized.

A method of manufacturing a micro lens that can enhance the accuracy of landing positions of droplets and can fabricate a micro lens with good shape accuracy, a micro lens, an optical device, an optical transmitting device, a laser printer, head and a laser printer are provided. In a method of manufacturing a micro lens, a given number of droplets of a lens material are ejected from a droplet ejection head on a base member formed on a substrate. The method includes stopping relative movement between the substrate and the droplet ejection head; and ejecting a plurality of the droplets on a given position on the substrate from the droplet ejection head.

The present invention discloses a multi-mode satellite navigation-based parafoil flight path control system, which comprises a comprehensive solution module arranged on a parafoil, a multi-mode positioning module and a path planning module. The multi-mode positioning module and the path planning module are connected with the comprehensive solution module. The path planning module is also connected with a flight control tracking module. The system further comprises a meteorological testing module and a landform data acquisition module, wherein the meteorological testing module and the landform data acquisition module are arranged at an air-drop place. According to the technical scheme of the invention, the navigation reliability and the navigation precision are improved. At the same time, the blind-action problem during the conventional parafoil flight path control process can be solved. Therefore, the achievable rate of the landing precision is improved.

A droplet discharging head includes a first through hole having an outlet for discharging of a liquid material and a second through hole having an inlet for injection of the liquid material, the second through hole having a protrusion on

The invention discloses a precise landing control system and method based on multi-information fusion. The system comprises: a ground end module used as a UAV accurate landing target point to transmitan infrared image to the sky to be identified by a sky end module; and the sky end module configured to acquire and identify the infrared image transmitted by the ground end module, calculate the relative position of the ground end module, detect the ground relative height, perform data fusion on a visual module, a millimeter wave radar, and the flight control information of a UAV system acquiredin real time, and send a UAV navigation control signal. The method is implemented based on the above system. The system has a long detection distance, high detection precision and a good anti-interference ability.

The present invention relates to an asteroid attachment trajectory robust optimization method, belonging to the technical field of planetary landing. The method comprises a step of using a linear covariance method to deduce the error spreading equation of an asteroid attachment process according to the mathematical model of uncertain factors of an initial state, thrust direction and size, a target celestial parameter and the like, a step of achieving the purposes of suppressing error spreading and improving landing trajectory robustness are achieved through introducing a tracking guide strategy in the trajectory optimization process. According to the method, the fuel consumption in a lander attaching process can be saved, at the same time, the influence of parameter uncertainties on trajectory can be reduced. According to the asteroid attachment robust optimization method, the linear covariance method is used to quantitatively describe the influence of random variables on a landing process, a tracking guide strategy is considered in the trajectory optimization process, thus the spread of various errors can be inhibited in the tracking process, and the purpose of improving the landing precision is achieved.

The present invention relates to a bonding method or an apparatus for projecting a conductive element from a nozzle onto an object to be bonded and electrically bonding the object to be bonded and the conductive element. The method of invention comprises the steps of: preparing the conductive element having an outer diameter with a curvature radius larger than a curvature radius of a portion of an opening of the nozzle which is in contact with the conductive element; pressurizing and attaching the conductive element to the opening of the nozzle; and supplying a compressed gas into an inner space of the nozzle and projecting the conductive element in a solid phase state onto the object to be bonded.

The invention relates to an unmanned aerial vehicle autonomous landing system and landing method based on GPS and vision. The method comprises the steps: enabling an unmanned aerial vehicle to receivea one-key return instruction in a normal flight process, enabling the unmanned aerial vehicle to maintain a normal flight height, starting to fly to a first landing position right above a landing point, and employing a GPS positioning system in the process; after the unmanned aerial vehicle arrives at the first-section landing position, the unmanned aerial vehicle starts to descend to a second-section landing position 5 m away from the position over the target at the vertical speed of 5 m/s, and a GPS is adopted in the process; after the unmanned aerial vehicle reaches the second-section landing position, the unmanned aerial vehicle starts to descend to the ground at the vertical speed of 1 m/s, and a visual positioning system is adopted in the process; and after the unmanned aerial vehicle reaches the ground, the unmanned aerial vehicle blades stop rotating. According to the unmanned aerial vehicle autonomous landing system, a GPS and visual positioning method is adopted, and the landing precision of the unmanned aerial vehicle is improved to the maximum extent.

A UAV having a radar-guided landing function that helps the UAV to land on a landing station is disclosed. The UAV uses a GPS transceiving unit's positioning, and receives a flight path from an external source through a control unit to advance toward the landing station. When the UAV approaches a landing station, the control unit receives an activation signal and activates a landing radar to continuously transmit a frequency sweeping radar wave. When the frequency sweeping radar wave reaches the landing station, a reflected radar wave is generated, so that the landing radar receives the reflected radar wave and transmits it to the control unit. The control unit performs computation based on data related to the reflected radar wave and accordingly controls the UAV to land on the landing station.

The invention discloses a fixed wing aircraft autonomous deck landing method and system; the method and system build a relative motion model between the aircraft and a carrier, build an ideal glide path, convert an autonomous deck landing problem into a path tracking problem, use an aircraft six degrees of freedom non-linear motion model, consider coupling between aircraft longitudinal control with lateral course control, and model the carrier deck motions, so the system and method can approach more to the real motions and be more accurate in control. The method and system and improve the decklanding accuracy of the fixed wing aircraft under a carrier deck motion condition.

A liquid ejecting head unit includes: a liquid ejecting head having a liquid ejecting surface in which a nozzle opening for ejecting liquid is formed; a head fixing substrate which holds the surface sides opposite to the liquid ejecting surfaces of a plurality of liquid ejecting heads; and a height changing-fixing section which is provided between the head fixing substrate and the liquid ejecting head and can adjust a distance between the head fixing substrate and the liquid ejecting head, in which the height changing-fixing section is detachably fixed to the surface opposite to the liquid ejecting surface of the liquid ejecting head, and the height changing-fixing section and the head fixing substrate are detachably fixed to each other by screwing from the surface side opposite to a fixing surface of the head fixing substrate, to which the liquid ejecting head is fixed through the height changing-fixing section.

A liquid jetting apparatus (20) to jet a droplet of a charged liquid solution onto a base material, having: a nozzle (21) in which an edge portion thereof is arranged to face the base material K having a receiving surface to receive the jetted droplet, and an inside diameter of the edge portion from which the droplet is jetted is not more than 30 [μm]; a liquid solution supplying section (29) to supply the liquid solution into the nozzle (21); a jetting voltage applying section (25) to apply a jetting voltage to the liquid solution in the nozzle (21); and a convex meniscus forming section (40) to form a state where the liquid solution in the nozzle (21) protrudes from the nozzle edge portion.

The invention discloses a lateral track motion estimation and compensation method based on a motion platform, and belongs to the technical field of control law design. In order to guarantee the fact that an airplane can track an ideal landing point synchronously, a guidance system must be compensated synchronously. The method aims to the last stage of a motion platform landing stage, the influences of sailing motions and swaying motions of the motion platform on ideal landing point positions are taken into comprehensive consideration, and estimation and compensation of track motions on the motion platform are carried out. Deck lateral motion signals are introduced into a lateral guidance system after estimation and compensation so that the dynamic performance of the system can be improved, errors are restrained, and the tracking precision of the airplane is improved.

A system is described to control the flight path of a parafoil. The physical control mechanism is a series of actuators embedded within the parafoil canopy that open a series of meshed venting systems in the upper surface of the parafoil canopy. Opening and closing the meshed venting system changes the forces and moments acting on the parafoil canopy in a consistent manner such that it can be used for flight control. The meshed venting system includes an internal sealing flap and a mesh member.

The invention discloses a longitudinal track motion estimation and compensation method based on a motion platform, and belongs to the technical field of control law design of a full-automatic landing system on the basis of the motion platform. In order to guarantee the fact that an airplane can track an ideal landing point synchronously, a landing guidance system must be compensated synchronously. The method aims to the last stage of a motion platform landing stage, the influences of sailing motions and swaying motions of the motion platform on the landing of the airplane are taken into comprehensive consideration, and estimation and compensation of motions of a motion track (the ideal landing point) are carried out. In the longitudinal aspect, the longitudinal motion signals of the motion track are introduced into a longitudinal guidance system after estimation and compensation so that the dynamic performance of the system can be improved, errors are restrained, and the tracking precision of the airplane is improved.

The invention provides an aircraft landing method and device. The aircraft landing method comprises the steps of obtaining a current image of a preset take-off and landing point collected by an aircraft in the landing process; obtaining a matching image of the preset take-off and landing point collected by the aircraft in the taking-off stage and attitude information of the aircraft; matching characteristics of the current image and the matching image to obtain each matching characteristic dot pair; according to each matching characteristic dot pair, calculating a characteristic transformationmatrix between the current image and the matching image; according to the characteristic transformation matrix, obtaining an optical center projection point, projected to the current image, of an optical center point of the matching image; and according a coordinate of the optical center projection point, controlling the aircraft to land to the preset take-off and landing point. According to theaircraft landing method and device, an an aircraft landing instruction adjusting method is realized to guide the aircraft to land to the take-off and landing point so that the aircraft landing accuracy is enhanced; only by successfully matching the collected images, the landing instruction can be adjusted to avoid real-time tracking of the landing point and reduce the aircraft accurate landing difficulty is reduced.

The present invention relates to a recording apparatus which stabilizes the locations of a transfer roller and a bearing and prevents the movement of a recording medium caused by the movement of the transfer roller, to thereby improve the sticking accuracy of the recording device without an increase in cost, comprising a conveyance roller; a driven roller rotating as driven from the conveyance roller; pushing means for pushing the driven roller to the conveyance roller; a bearing for supporting the conveyance roller; driving means for rotating the conveyance roller; and drive transmitting means. The bearing includes two contact portions with the circumference of a spindle for supporting the conveyance roller and the bearing supports the conveyance roller as to locate a perpendicular direction of a line coupling the two contact portions within a varying range of a vector direction of exertion force exerted to the bearing at a time of stop and operation of the conveyance roller.

In the full line type droplet discharging head, discharge ports for discharging a liquid supplied by a liquid passage formed by laminating thin plates, as liquid droplets, are arranged in a line direction along a length corresponding to a full width of a recording medium; and a simple rigid member having higher rigidity than that of a structure constituted by laminating the thin plates is provided extending along the line direction.

A fixed wing unmanned aerial vehicle comprises a vehicle body, an electric propulsion mechanism arranged on the head of the vehicle body, wings arranged on the two sides of the vehicle body, and a horizontal tail arranged at the tail of the vehicle body. The wings are arranged on the vehicle body in a tool-free fast disassembly and assembly mode. During large-stall vertical landing, the wings can be taken off forwards along a chute of the vehicle body, energy of landing of the whole unmanned aerial vehicle is absorbed, so that according to stall decomposition technology of the fixed wing unmanned aerial vehicle provided by the invention, the influence of wind is small, and the landing precision is high.

Provided is a continuous liquid ejection head that collects droplets which are not used for printing (unused droplets) without affecting the flight of droplets which are used for printing (used droplets). An ejection nozzle (101) and a collection nozzle (102) collect an unused droplet by causing a liquid surface to project out from the aperture of the collection nozzle (102) so as to be positioned along the trajectory through which droplets ejected from the ejection nozzle (101) fly, causing the unused droplet to collide and unite with the liquid surface projected from the collection nozzle (102), and causing the liquid surface to retreat.

The embodiment of the invention discloses an unmanned aerial vehicle landing method and device, an unmanned aerial vehicle system, an airport, equipment and a medium, and the method comprises the steps: determining the environment state of a landing point when a landing instruction is received, and determining a target positioning mode for positioning the relative position between the unmanned aerial vehicle and the landing point according to the determined environment state of the landing point, and controlling the unmanned aerial vehicle to land according to the target positioning mode. Through the technical scheme of the embodiment of the invention, the unmanned aerial vehicle can accurately land on the automatic airport take-off and landing platform in the automatic airport application, the method is more stable and reliable, and the landing precision of the unmanned aerial vehicle is improved.