398results 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 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 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.

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 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 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.