401results about How to "Improve stealth performance" patented technology

A method of watermark with hybrid halftone dots that is suitable for a printed shadow image. The watermark patterns that are composed of amplitude modulation (AM) and frequency modulation (FM) halftone dots (their concentration has been calibrated) cannot be perceived beyond a certain distance by the human eye. This is done through outputting the density calibration chart to choose the proper density parameters, which are applied to the manufacture process of the watermark with hybrid halftone dots. The hidden patterns of a watermark need to be pre-processed first, and thereby making the image blocks of AM and FM halftone dots to be combined smoothly. The copy machine, the lenticular lens and the optical scanner can detect the hidden watermark in the printed shadow image. Each secured document possesses a different serial number to achieve the document-version control.

A flying-wing double-ducted vertical take-off and landing aircraft. It mainly consists of five parts. The first part is the fuselage 1, the second part is the No. 1 ducted engine 4, the No. 2 ducted engine 5 and the rear engine 6, the third part is the vertical tail 16, the No. 1 horizontal tail 12, the No. 2 horizontal tail 13, No. 3 horizontal stabilizer 14, No. 4 horizontal stabilizer 15, No. 1 winglet 10, No. 2 winglet 11. The fourth part is the support rod 19 , and the fifth part is the externally mounted pan / tilt head and the camera or photoelectric sensor 20 . The fuselage 1 is a flying wing type, the fuselage 1 can be folded, and the fold line 17 and the fold line 2 18 are the folding points of the fuselage. There are No. 1 duct 2 and No. 2 duct 3 distributed on the fuselage 1. No. 1 ducted engine 4 and No. 2 ducted engine 5 are located in the center of No. 1 duct 2 and No. 2 duct 3, respectively, and are connected by connecting The rod 22 is fixed. The No. 1 ducted engine 4 and the No. 2 ducted engine 5 are respectively equipped with a No. 1 propeller 7 and a No. 2 propeller 8 . The rear engine 6 is located in the center of the tail of the fuselage 1 , and a rear propeller 9 is installed on the rear engine 6 . The No. 1 horizontal stabilizer 12 , the No. 2 horizontal stabilizer 13 , the No. 3 horizontal stabilizer 14 , and the No. 4 horizontal stabilizer 15 of the aircraft are respectively located at the rear of the fuselage 1 . The No. 1 winglet 10 and the No. 2 winglet 11 of the aircraft are located on the left and right sides of the fuselage 1 respectively, and are bent downward. The vertical tail 16 of the aircraft is located in the middle of the tail of the fuselage 1 , on the upper part of the fuselage 1 . The support rod 19 is located in the middle of the front part of the fuselage 1 , and is located in the lower part of the fuselage 1 . The camera or photoelectric sensor is located in the middle of the front of the body 1 and is installed under the body 1 . The sweep angle 21 is the sweep angle of the flying wing fuselage 1 .

The invention discloses a stealth single-hull small waterline area hydrofoil unmanned ship sailing on water and a sailing method. The upper portion of the stealth single-hull small waterline area hydrofoil unmanned ship is provided with a control cabin, the middle portion comprises posts, and the lower portion is a submerged body. The front section of the submerged body is a submerged body bow, the middle section of the submerged body is a submerged body middle part, and the rear section of the submerged body is a submerged body stern. Two water ballast spaces, two power supply cell boxes and a hydrofoil control mechanism are arranged inside the submerged body middle part of a hull. The two water ballast spaces are symmetrically arranged front and back; the two power supply cell boxes symmetrical front and back are arranged between the two water ballast spaces; and the hydrofoil control mechanism is arranged in the center of the space between the two power supply cell boxes. A pair of hydrofoils is symmetrically arranged on the left side and the right side outside the submerged body middle part of the hull. A main motor, a coupler, a main shaft and a tail vane control mechanism are arranged inside the submerged body stern of the hull. A pair of tail vanes is symmetrically arranged on the left side and the right side outside the submerged body stern of the hull. The stealth single-hull small waterline area hydrofoil unmanned ship has excellent seakeeping, speedability and resistance properties, and can achieve the three navigational statuses of body navigation, winging operation and submerge navigation.

The invention discloses a fast implementation method for comprehensive minor lobes of an array antenna radiation field and a scattered field. The fast implementation method comprises the following steps of (1) determining structure parameters, electromagnetic working parameters and array surface distribution parameters of an array antenna; (2) determining an initial sparse arrangement scheme of the array antenna to obtain a sparse arrangement matrix of array antenna units; (3) calculating phase difference between the radiation field and a radiation field actinal surface of the array antenna; (4) calculating a radiation pattern function of the array antenna and calculating the maximum minor lobe level of the radiation field of the array antenna under the sparse arrangement scheme; (5) calculating a scattering pattern function of the array antenna and calculating the maximum minor lobe level of the radiation field of the array antenna under the sparse arrangement scheme; and (6) judging whether the radiation field and the scattered field simultaneously meet the requirement on low minor lobes or not under the sparse arrangement scheme of the array antenna until the optimum sparse arrangement scheme by which the requirements on the low minor lobes of the radiation field and the scattered field of the array antenna can be met simultaneously is obtained. By the fast implementation method, the low minor lobe performance of the radiation field of the array antenna and the low minor lobe performance of the scattered field of the array antenna can be simultaneously realized.

The invention discloses a wing-borne low-scattering ultra-wideband conformal phased array based on a strong coupling effect. The whole antenna structure of the array is subjected to conformal processing, and + / -45 degree scanning in the arraying direction is realized within a broadband of 0.5-2GHz. Compared with the traditional planar ultra-wideband phased array, the phased array disclosed by theinvention has significant low-scattering characteristics inside and outside the working band of the antenna. The whole antenna structure mainly includes a coaxial feeding structure of an antenna radiation unit, a gradient line balun used for connecting an antenna radiation patch and the feeding structure, a metal ground plate which is conformal with a flight carrier, a parasitic metal block located on the metal ground plate, a conformal dielectric substrate used for supporting the radiation structure of the whole phased array, connected long-slot conformal radiation patches based on the strongcoupling effect, a conformal dielectric substrate used for supporting a resistive electromagnetic metamaterial, a circular resistive electromagnetic metamaterial with an ultra-wideband electromagnetic wave absorbing effect and parasitic slots on both sides of the antenna radiation unit.

The invention provides a wing with changeable trailing edge camber driven by a shape memory spring, relating to a wing with a changeable trailing edge camber, and aiming at the problems of traditional airplanes that a mechanism is complex and heavy, airflow breakaway is quite early and aerodynamic efficiency is low. The front end face and the back end face of an upper metal plate are fixedly connected with the front end faces of a connecting plate and the trailing edge; the front end face and the back end face of the lower metal plate are fixedly connected with the front end face of the connecting plate and the trailing edge; the same side surface of the upper metal plate and the lower metal plate are fixed with an upper prop stay and a lower prop stay; the two ends of a first shape memory spring are fixedly connected with a fixed plate and the upper metal plate; the two ends of a second shape memory spring are fixedly connected with the front end faces of the upper prop stay and the trailing edge; the two ends of a third shape memory spring are fixedly connected with the fixed plate and the lower metal plate; and the two ends of a fourth shape memory spring are fixedly connected with the front end faces of the lower prop stay and the trailing edge. The invention has the advantages of light weight, simple structure and high aerodynamic efficiency.

The invention provides an airplane with a combined-wing layout of a flying wing and forward-swept wings. The airplane is characterized in that thin-wing type vertical columns A and B are additionally arranged at the 70% wingspan positions of the outer sides of two side wings of a flying-wing airplane with backward-swept wings, a thin-wing type vertical column C is additionally arranged at the tail part of the flying-wing airplane, and horizontal forward-swept wings are additionally arranged at the top ends of the three thin-wing type vertical columns A, B and C so as to form the combined-wing layout of the flying wing and the forward-swept wings; elevators are arranged on the horizontal forward-swept wings and a rudder is arranged on the vertical column C; a duct type air inlet channel is adopted on the upper wing surface of the flying wing, and cracking type drag rudders are distributed at the thin-wing type vertical columns A and B. The airplane provided by the invention has the advantages that under the condition that the structure strength is effectively guaranteed, the effective aspect ratio of the wings is increased, the induced drag is reduced, the lift-drag characteristics of the airplane are improved, the stealth performance of the airplane is improved, direct-force control of the airplane in the vertical direction is realized and the detecting accuracy under the maneuvering condition is improved.

A heating plate 10 includes: a pair of glass plates 11, 12; a conductive pattern 40, 70 disposed between the pair of glass plates 11, 12 and defining a plurality of opening areas 43, 73; and a joint layer 13, 14 disposed between the conductive pattern 40, 70 and at least one of the pair of glass plates 11, 12; wherein the conductive pattern 40, 70 includes a plurality of connection elements 44, 74 that extend between two branch points 42, 72 to define the opening areas 43, 73; and a rate of the connection elements 44, 74, which are straight line segments connecting the two branch points 42, 72, relative to the plurality of connection elements 44, 74, is less than 20%.

The invention discloses an amphibious unmanned aerial vehicle which comprises a vehicle body and wings. Polygonal drivers are arranged in wing ribs of the wings. Each polygonal driver comprises a polygonal connecting rod mechanism and at least one pneumatic muscle driver. Connecting rods of the polygonal connecting rod mechanisms are connected with the wing ribs. The pneumatic muscle drivers are arranged in polygonal spaces formed by the polygonal connecting rod mechanisms, and the two ends of each pneumatic muscle driver are connected with the connecting rods of the corresponding polygonal connecting rod mechanism. The connecting rod mechanisms are used for connecting and fixing the pneumatic muscle drivers, the pneumatic muscle drivers are inflated and shrink in different directions, so that the connecting rod mechanisms output force in different directions, conversion of a concave wing profile and a convex wing profile is achieved, and the vehicle can meet the requirements for different flight speeds. The wings can intelligently and actively deform to meet the requirements for different navigation speeds, the amphibious unmanned aerial vehicle has the beneficial effects of being amphibious, quick to respond, long in time of endurance, capable of achieving formation flight and the like, and the vehicle can finish the tasks of naval vessel formation convoying, diver resistance, miniature submarine resistance and the like.

Disclosed is a visible light part concealing suit, which is provided with an object lens both on the front portion and on the rear portion, the small diameter of the conical light transmitting fiber beam is placed in the casing of the lens opposite the lens, the light transmitting fiber is braided into the garment layer, its major diameter end is arranged on the grids of the concealing surface layer opposite the object lens, the major diameter end of each light transmitting fiber beams are positioned by the same arrangement with the small diameter end. The end face of the light transmitting fiber beam on the front and back surface of the concealing clothes is provided with transparence promoting films.

The invention provides a hybrid AMC (Artificial Magnetic Conductor) tessellate structure loaded SIW (Substrate Integrated Waveguide) cavity-backed slot antenna, and belongs to the technical field of microwave antenna. The hybrid AMC tessellate structure loaded SIW cavity-backed slot antenna is a three-layer printed circuit board PCB structure, and includes a radiation slot, an SIW cavity and a periodic artificial magnetic conductor AMC surface with an opposite reflection phase. The hybrid AMC tessellate structure loaded SIW cavity-backed slot antenna utilizes the backward direction scattered wave constant amplitude inverse-phase offset principle to realize antenna RCS (Radar Cross-Section) suppression of X, K and Ku wave bands. Besides, the SIW cavity-backed structure can effectively reduce the profile size of the antenna, and the radiation characteristic of the slot antenna can generate enhanced effect because of influence of the periodic surface. The hybrid AMC tessellate structure loaded SIW cavity-backed slot antenna can be applied to boat-carrying, airborne, and vehicle communication systems, and can also be applied to an intelligent skinning system for realize the functions of stealth and communication.

The present invention provides a method and a system for embedding and extracting an image digital watermark. The method includes: performing a DWT on an original carrier digital image to obtain two intermediate frequency coefficient matrixes; firstly performing a DCT on one of the two intermediate frequency coefficient matrixes, then performing the DWT, and then selecting an obtained low frequency coefficient matrix as a first low frequency coefficient matrix; performing the DWT on another intermediate frequency coefficient matrix, and then selecting an obtained low frequency coefficient matrix as a second low frequency coefficient matrix; and adjusting magnitude of a first frequency coefficient and a second frequency coefficient according to watermark values to be embedded at said embedment locations to make a magnitude relationship between two adjusted low frequency coefficients comply with a corresponding relationship between a preset embedded value and a magnitude relationship between the two low frequency coefficients.

A method for improving ground movement capability and enhancing stealth in unmanned aerial vehicles is provided. The present method comprises providing, in an unmanned aerial vehicle equipped with wheels, one or more onboard drive means capable of translating torque through the vehicle wheels and controllable to move the unmanned aerial vehicle on the ground without reliance on the unmanned aerial vehicle main motive power source. The onboard drive means is controllably powered by a power source with substantially no acoustic signature to move the unmanned aerial vehicle quietly on the ground with only a minimal audible or visible footprint. This method provides a significant expansion of ground movement capability and expands the potential ground uses of unmanned aerial vehicles, particularly in military applications. The present method can also be applied to move any manned aerial vehicle or aircraft on the ground with only minimal audible or visible footprints.

The invention relates to an axisymmetric convergent and divergent exhaust nozzle. The exhaust nozzle is characterized by mainly consisting of a cylinder, a driving adjusting mechanism, a sealing component, a center shielding component and an outer fairing component, wherein the front end of the cylinder is connected with an engine to serve as a support component of the whole exhaust nozzle, the driving adjusting mechanism mainly consists of action cylinders, a synchronous adjusting ring, pull rods, convergent flaps, air pressure action cylinders, and divergent flaps, the sealing component mainly consists of a convergent sealing sheet and an divergent sealing sheet, and is mainly used for sealing the air flow in the exhaust nozzle, and the divergent sealing sheet is positioned in the inner sides of the circumferentially distributed divergent flaps and between the circumferentially distributed divergent flaps, and is connected with the divergent flaps at the two adjacent sides through a conventional cooperation pressing mechanism. The axisymmetric convergent and divergent exhaust nozzle has the advantages that the influence on the area adjusting range of a throat pipe of the conventional axisymmetric convergent and divergent exhaust nozzle is avoided, the good hiding capability is realized, the defect of hiding function of the conventional axisymmetric convergent and divergent exhaust nozzle is overcome, meanwhile, the structure is simple, and the reliability is high.

Taggant fibers and methods of use provide for enhanced protection and security when the fibers are used in documents such as land titles, currency, passports and other documents of value. The taggant fibers consist of a minimum of two separate zones with each zone containing a different taggant to emit different wave lengths when excited. The taggants may consist of organic or inorganic compounds as are conventionally known and can be manufactured using for example polymeric materials which can be extruded during the fiber manufacturing process. Authentication of the fibers or documents containing such fibers can be readily viewed using conventional techniques.

Taggant fibers and methods of use provide for enhanced protection and security when the fibers are used in documents such as land titles, currency, passports and other documents of value. The taggant fibers consist of a minimum of two separate zones with each zone containing a different taggant to emit different wave lengths when excited. The taggants may consist of organic or inorganic compounds as are conventionally known and can be manufactured using for example polymeric materials which can be extruded during the fiber manufacturing process. A first zone may comprise a fiber sheath which includes a taggant and a second or inner zone or core which may be formed into a company logo having letters with different or the same taggants. Authentication of the fibers or documents containing such fibers can be readily viewed using conventional techniques.

The invention discloses a plasma unmanned aerial vehicle. First plasma exciters are distributed on the leading edges of a left wing and a right wing of the aerial vehicle; second plasma exciters are distributed in the one fourth positions of chord lines; and third plasma exciters are distributed in the maximum thickness positions. Meanwhile, a miniaturized plasma power supply is designed and integrated into the aerial vehicle, and a switch and relevant discharge parameters of the plasma power supply can be controlled through a program or in a remote control manner. When the plasma exciters start to work, the adverse pressure gradient resistance of a boundary layer is enhanced by means of plasma jet generated by the exciters, a flow field of the upper wing surface of the aerial vehicle can be controlled, and the aerodynamic characteristics of the aerial vehicle are improved; starting of the plasma exciters in the different positions is appropriately adjusted, and aerodynamic moment can be produced, so that the flight attitude of the aerial vehicle can be controlled; and the plasma aerial vehicle has the characteristics that the aerodynamic characteristics are improved, control plane flight controlling is not required, the invisibility is good and the like.

The invention provides a frequency selective surface structure with improved angle stability, and mainly aims to solve the problem that the existing frequency selective surface is of poor angle stability. The frequency selective surface structure is composed of M*N frequency selective surface units arranged periodically, wherein M>=3, and N>=3. Each frequency selective surface unit consists of a dielectric substrate (1) and a metal patch (2) printed on the surface of the dielectric substrate (1). The frequency selective surface structure is characterized in that each metal patch (2) includes four symmetrically-arranged patterns (21) shaped like a Chinese character 'au'; for each pattern (21) shaped like a Chinese character 'au', the two outer vertical arms are each provided with a hollowed-out gap (23) in the middle and the lower left end is opened in such a way that a continuous winding strip is formed; and the four winding strips are connected end to end through rectangular strips (22) to form a complete square closed-loop strip. The frequency selective surface structure has high angle stability for differently-polarized incident waves, and can be used in satellite communication, reflector antennas and other fields.

An axisymmetric vectoring nozzle with a good stealth function is characterized in that the axisymmetric vectoring nozzle comprises a barrel, a divergent section adjustment mechanism, a throat adjustment mechanism, a sealing component, a central shielding component and a shroud component; specifically, the front end of the barrel is connected with an engine, and the divergent section adjustment mechanism mainly comprises vectoring actuator cylinders, vector-adjusting rings, pull rods and divergence-adjusting plates; the vectoring actuator cylinders are arranged along the circumference of the nozzle, the front ends of the vectoring actuator cylinders are mechanically connected with the external wall of the barrel, and the rear ends of the vectoring actuator cylinders are connected with the vector-adjusting rings; the rear ends of the vector-adjusting rings are connected with the pull rods through revolute pairs and connected with the barrel through centering mechanisms, so that the radial displacement of the vector-adjusting rings is limited; the pull rods are evenly distributed along the circumference of the nozzle, and the other ends of the pull rods are connected with the outsides of the divergence-adjusting plates through revolute pairs. The axisymmetric vectoring nozzle has the advantages that the axisymmetric vectoring nozzle has good stealth capability, so that the defect in the stealth function of conventional axisymmetric vectoring nozzles is made up for, and meanwhile, the axisymmetric vectoring nozzle has the advantages of simple structure and high reliability.

The present invention relates to a radio frequency identification (RFID) device and method for book tagging, using which a RFID tag which is designed to attach to a book is first being scanned and detected in view of optimizing the RFID tag's signal strength and its effective reading rate as well so as to determine a position on the book for the RFID tag to attach thereat while allowing the detection to the RFID tag to be prevented from being adversely affected by metals or magnetic materials that are situated ambient to the book.

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.

The invention relates to an air intake system which is used in an aircraft, and particularly relates to an invisible air intake system. A total main air intake channel of the invisible air intake system is designed into a bent S-like shape; an air intake bypass, an air accumulation cabin, an air path and an exhaust bypass are connected in sequence so as to form into an auxiliary air flow path; an air intake controller is installed on the air accumulation cabin; an exhaust valve is positioned at an outlet of the exhaust valve at the rear part of the auxiliary air flow path; when the air intake controller is at the opened state, the exhaust valve is at the closed state; and when the air intake controller is at the closed state, the exhaust valve is at the opened state. With the adoption of the air intake system, the influence of a boundary layer generated by a wing / body to an engine, and the requirements of the engine on the quantity and the quality of the air intake at different velocities / different engine states are met; and meanwhile, with the adoption of the air intake system, openings in the surface of the wing / body can be reduced with good invisibility performance.

The invention relates to an on-site dynamic balance monitoring correcting device and an on-site dynamic balance monitoring correcting method of high-speed rotary machinery for a boat. Signals collected by an electricity vortex sensor and a rotating speed key phase sensor are transmitted to a dynamic balance monitoring correcting circuit through a head amplifier, the dynamic balance monitoring correcting circuit receives the signals transmitted by the head amplifier, the signals are transmitted to a front end analog signal processing module to be processed and are then transmitted to a device core circuit module to be calculated and stored, an input and output module and the device core circuit module exchange data, a power supply system module comprises a power supply processing module and a power supply voltage monitoring and resetting circuit, the power supply processing module provides power supply for each module chip, and the power supply voltage monitoring and resetting circuit receives all power supply signals and outputs warning and control signals. The vibration noise level of equipment for the boat is effectively reduced, and the failure handling time of the equipment for the boat is shortened; the dimension of a dynamic balance instrument is reduced; the environment adaptability of the dynamic balance instrument can be improved; the man-machine interaction can be realized; and the fast data collection and storage can be completed, and credible data is provided for monitoring and failure diagnosis.

The invention discloses a truss type wing leading edge camber continuous changing structure, and belongs to the field of design of aircraft wing structure. The structure includes that a wing leading edge cavity enclosed by upper flexible skin and lower flexible skin is internally provided with a plurality of trusses, two ends of each truss are slidingly connected with the upper flexible skin and the lower flexible skin, and the plurality of trusses are mutually hinged and can be linked; each memory alloy rod assembly is composed of a first memory alloy rod and a second memory alloy rod, the first memory alloy rod is heated to extend, and the second memory alloy rod is heated to shorten; the memory alloy rod assemblies are arranged between each two adjacent trusses, and are respectively andevenly distributed along the upper flexible skin and the lower flexible skin; the memory alloy rod assemblies are heated to deform to drive the trusses to move, and make the upper flexible skin and the lower flexible skin deformed. The structure has the advantages of simple mechanism principle, direct stress efficacy and high reliability, and the wing leading edge deformation is flexible, controllable, reversible and repeated intelligent deformation which can continuously change the camber of the wing.

The invention belongs to control technologies of aircraft ejection life-saving systems and relates to an ejection life-saving control method. The ejection life-saving control method specifically comprises the following steps that a pilot sends an ejection command to an ejection life-saving system through an ejection handle, the ejection life-saving system excites two detonation points of a pressure relief port, and the pressure relief port is formed in the top of a high-pressure cabin through cutting; after a delay of X seconds, pressure relief of the high-pressure-difference cabin is completed, and X is determined according to the pressure and ejection height of the cabin during ejection; the delay of X seconds is backed up, and backup time is determined according to an ejection life-saving scheme; after pressure relief of the cabin is completed, two detonation points for cutting a canopy are excited, and the canopy is formed through cutting and released; and after the canopy is released, seat ejection is conducted after a delay of Y seconds, dual-redundancy design is adopted by a feedback signal of the delay of Y seconds, and Y seconds are determined according to the ejection life-saving scheme. According to the ejection life-saving control method, cleaning of an ejection channel and an ejection signal of a seat are integrally controlled, the ejection life-saving system is optimized, and the system weight is reduced.

The invention provides a preparation method for an iron-nickel-copper oxysome long fiber pipe. According to the technical solution, the preparation method comprises the steps of polypropylene fiber surface treatment, polypropylene fiber chemical copper plating, fiber nickel plating, fiber iron plating, polypropylene fiber removing and long fiber metal composite pipe roasting oxidation, so that the iron-nickel-copper oxysome long fiber pipe is prepared. By means of the preparation method for the iron-nickel-copper oxysome long fiber pipe, iron-nickel-copper oxysome long fiber pipes with different specifications and section shapes can be prepared, the attenuation effect of electromagnetic waves is enhanced through the reflection and absorption effects of residual carbon in the long fiber pipe, and compared with a traditional preparation method, the overlong iron-nickel-copper oxysome fiber pipe can be prepared.

Provided are a touch panel, a displaying unit, and a touch panel manufacturing method that make it possible to thin a wiring line and that suppress visibility of a wiring line to improve appearance. A first electrode group extends in a direction intersecting with a second electrode group in plan view. A large part of a first wiring line or the entire first wiring line is arranged so as to overlap a light-shielding part in the entire line width thereof in plan view. On the basis of a display device, a first electrode part is located on an outer side of a dielectric part and the first wiring line and / or a second wiring line has a line width varied according to a height, and has a line width in an outermost region smaller than a line width in an innermost region.

The invention provides a dissipation type broadband frequency selection surface radar cover. The cover comprises a first skin layer, a first frequency selection layer, a first core layer, a second frequency selection layer, a second core layer, a third frequency selection layer and a second skin layer, wherein the first skin layer, the first frequency selection layer, the first core layer, the second frequency selection layer, the second core layer, the third frequency selection layer and the second skin layer are successively arranged in the thickness direction. The first frequency selectionlayer is consistent with the third frequency selection layer.

The invention discloses a wing leading edge continuous bending structure, and belongs to the technical field of design of wing leading edge structure. The structure includes that two ends of each fixed wing rib are respectively fixed on upper flexible skin and lower flexible skin; a memory alloy rod assembly passes through the fixed wing ribs, one end is fixed on the fixed wing ribs, and the otherend is slidingly connected with a wing leading edge; follow-up wing ribs are evenly distributed up and down along the memory alloy rod assembly, one end of each follow-up wing rib is connected with the memory alloy rod assembly, and the other end of each follow-up wing rib is slidingly connected with the upper flexible skin or the lower flexible skin; the memory alloy rod assembly is provided with first memory alloy rods and second memory alloy rods; a deformation temperature of the first memory alloy rods is Ta, and after a heating temperature reaches Ta, the first memory alloy rods performbending deformation; a deformation temperature of the second memory alloy rods is Tb, and after a heating temperature reaches Tb, the second memory alloy rods perform straight deformation; after the memory alloy rod assembly is heated, the follow-up wing ribs are driven to move to make the upper flexible skin and the lower flexible skin bended and deformed, and thus the aerodynamic shape of the wing outer edge is changed.