121results about How to "Good stealth" patented technology

The invention discloses an estimation method of an atmosphere angle of attack and an angle of sideslip in a high-angle-of-attack flight status. Under the premise that the structure of an aircraft is not changed and additional measuring devices and hardware devices are not added, the parameters output by the existing onboard strapdown inertial navigation system, a GPS (Global Position System) system, a flight control system and a fuel measuring system are fully used for resolving the angular acceleration, the rotational inertia, the product of inertia, the coefficient of a moment equation set and the total mass of the aircraft; based on a flight dynamics model, by establishing an extended Kalman filter, and integrating the processes of resolving the flight dynamics model and the status estimation together, accurate estimation of the current angle of attack, the angle of sideslip and the true airspeed is realized, and then the current air speed and the change rate of the air speed are resolved and input into the extended Kalman filter as the feedback information so as to finish the real-time accurate estimation of the angle of attack and the angle of sideslip of next time; the real-time accurate estimation of the angle of attack and the angle of sideslip is realized by a recursive resolving mode, measurement range and measurement precision of an atmosphere data system are improved, and adaptability to complex flight environment is also improved.

The invention discloses a BP (Back Propagation) neural network-based method for measuring air data in a flight state with a high angle of attack. According to the method, on the premise of not changing the configuration of an aircraft and not adding extra measurement devices and hardware equipment, the traditional airborne inertial navigation system, a global positioning system (GPS) and a flight control system are sufficiently utilized to output parameters, and the precise estimation of air data in a flight state with a high angle of attack is realized on the basis of a BP neural network. The method is beneficial to aircraft stealth, and meanwhile, the measurement range and the measurement precision of an air data system and the adaptability to a flight environment with a high angle of attract are improved, so that the method has the advantages of relative economy and easy engineering realization and has important practical significance to enlarging the measurement range of a new generation of aircrafts in the flight state with a high angle of attract and improving the flight performance of the aircrafts.

The invention discloses a broadband bionic yagi antenna with a low radar cross section and mainly solves the problems of high radar cross section and relatively narrow band width in the traditional yagi antenna. The antenna simulates an opposite phyllotaxis plant leaf structure and comprises a director (2), a radiating element (3), a parallel strip line (4), a reflector (5) and a coaxial conversion joint (6). The radiating element (3) is of an oval structure, the director (2) simulates a feather-shaped leaf structure, and the reflector (4) is a rectangle patch with a tooth-shaped structure. The radiating element (3) is printed on a top layer and a bottom layer of a double-layer medium material plate (1) and respectively connected with an inner core and an outer core of the coaxial conversion joint (6) by the parallel strip line (4); the director (2) is printed on the top layer of the double-layer medium material plate (1); and the reflector (4) is printed between two layers of the double-layer medium material plate (1). The broadband bionic yagi antenna with the low radar cross section has the advantages of wide frequency band and good invisibility performance and can be used on an invisible target carrier.

An electromagnetic radiation interface is provided that is suitable for use with radio wave frequencies. A surface is provided with a plurality of electrically conductive bristles. A corresponding plurality of termination sections are provided so that each bristle is terminated with a termination section. The termination section may comprise one or more different termination packages for operating on received electromagnetic radiation and / or producing desired reflections and transmissions. In one embodiment, switches and termination packages may be implemented within integrated circuits wherein the switches may be utilized to switch between different termination packages. The termination packages may include selected fixed reactances and / or modulators designed to produce desired reflections, e.g., Doppler effects to make it appear the surface of the interface is moving a speed different than the actual speed.

The invention provides optical fiber grating type optical fiber hydrophone-based paved type conformal array sonar equipment, which comprises a laser source array, a time division / space division / wavelength division hybrid multiplexer, an optical fiber grating type optical fiber hydrophone array, an interferometric phase inverter, a dense wavelength division demultiplexer, a phase generated carrier modulator-demodulator and a data generator, wherein the laser source array emits laser beam pulses with various wavelengths; the time division / space division / wavelength division hybrid multiplexer mixes the laser beam pulses and projects the laser beam pulses into the optical fiber grating type optical fiber hydrophone array respectively; the optical fiber grating type optical fiber hydrophone array modulates the laser beam pulses according to a submarine sound signal; the interferometric phase inverter performs the phase conversion of the modulated laser beam pulses; the dense wavelength division demultiplexer demultiplexes and separates mixed interferometric laser beam pulses; the phase generated carrier modulator-demodulator performs corresponding phase detection, photoelectric conversion, digital sampling and digital demodulation of interferometric laser beams; and the data generator generates conformal-array multichannel digital sonar signals.

The invention provides a preparation method of an interlayer frequency selective surface composite material, comprising 12 steps. The technical scheme comprises: manufacturing frequency selective surface films; and adding the thin films among prepreg layers of glass fibre cloth and epoxy resin to be laminated together. The method obtains conspicuous hiding effects under the condition of not changing the profile design of an original aircraft radome, and has no reverse impact on the electrical characteristics of an original radar system and the mechanical strength of a radome; a frequency selective surface bandpass radome is practical and feasible to solve the technical problem of invisibility of a radar antenna system.

The invention provided a paving type conformal array sonar device based on interference optical fiber hydrophone, comprising a laser source array, an interference optical fiber hydrophone time division multiplexing array, a wave-divided mixer, a dense wavelength division demultiplexer, a phase generation carrier wave demodulator and a data generator, wherein the laser source array transmits laser beam pulses of different wavelengths to be input into the interference optical fiber hydrophone time division multiplexing array; the interference optical fiber hydrophone time division multiplexing array modulates the laser beam pulses according to underwater acoustic signals to generate interference laser beam pulses; the wave-divided mixer processes wave-divided mixing on all interference laser beam pulses; the dense wavelength division demultiplexer demultiplexes and separtes the mixed interference laser beam pulses into a plurality of interference laser beam pulse groups of single wavelength; the phase generation carrier wave demodulation processes phase detection, photoelectric conversion and digital demodulation on the interference laser beam pulses; and the data generator generates multi-path sonar digital signals of conformal array according to the digital demodulation result.

The invention discloses a polyxeny aircraft additionally provided with a hydrofoil, and belongs to the field of aslant-rotation aircrafts, hydrofoils and ducted propellers. A hydrofoil device is installed at the belly part of the lower end of an aircraft body, and a tail part ducted propeller is installed at the tail part of the upper end of the aircraft body; a set of V-shaped empennages are installed at the two sides of the tail part ducted propeller; a left ducted propeller and a right ducted propeller are installed at the upper ends of the ends of left and right aerofoils respectively; floats are symmetrically installed at the lower ends of the aerofoils. According to the polyxeny aircraft, the ducted propellers are utilized for replacing propellers, the performance of the aircraft canbe improved, the left ducted propeller, the right ducted propeller and the tail part ducted propeller can aslant rotate, and vertical take-off and landing of the aircraft on the water surface and theground can be achieved; meanwhile, the hydrofoil device is adopted, so that the aircraft has the quick and flexible water surface movement capability, and has the features of aslant-rotation aircrafts and foilcrafts.

An electromagnetic radiation interface is provided that is suitable for use with radio wave frequencies. A surface is provided with a plurality of metallic conical bristles. A corresponding plurality of termination sections are provided so that each bristle is terminated with a termination section. The termination section may comprise an electrical resistance for capturing substantially all the electromagnetic wave energy received by each respective bristle to thereby prevent reflections from the surface of the interface. Each termination section may also comprise an analog to digital converter for converting the energy from each bristle to a digital word. The bristles may be mounted on a ground plane having a plurality of holes therethrough. A plurality of coaxial transmission lines may extend through the ground plane for interconnecting the plurality of bristles to the plurality of termination sections.

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 a wing of an aircraft, in particular to a wing deformation structure of a water and air amphibious aircraft, aiming at solving the problems that the wing, adopting a vertical fin discontinuous deformation structure, of the existing antisubmarine aircraft is poor in stealth performance and aerodynamic performance, has influence on the flight speed and is not beneficial to reduction of radar return signals, and the wing, adopting a structure without a vertical fin, of the existing antisubmarine aircraft is poor in controllability and maneuvering characteristic. The wing deformation structure of the water and air amphibious aircraft comprises a rigidity-variable wing spar, two bending torsion deformation components and two wing ribs; two pneumatic muscle actuators of each bending torsion deformation component are arranged crosswise; the two bending torsion deformation components are respectively arranged at two sides of the rigidity-variable wing spar; two ends of each pneumatic muscle actuator are respectively connected with the two wing ribs; the rigidity-variable wing spar comprises a flexible bearing pneumatic muscle actuator and a wing spar main body; the flexible bearing pneumatic muscle actuator is inserted into a tubular elastic beam; two ends of the tubular elastic beam are respectively connected with the two wing ribs. The wing deformation structure is used for the water and air amphibious aircraft.

The invention relates to the technical field of unmanned vehicles, in particular to a fast disassembling and assembling semi-submersible three-body unmanned vehicle. The fast disassembling and assembling semi-submersible three-body unmanned vehicle include a main body and two auxiliary bodies, the main body is made from high-strength carbon fiber reinforced glass steel, the two auxiliary bodies adopt inflatable PVC buoys, and the auxiliary bodies and the main body are fixed through two high-strength carbon fiber connecting assemblies correspondingly; a plane groove type stabilization ballast tank is arranged in the center of the interior of the main body, a water inlet is formed in the bottom of the plane groove type stabilization ballast tank, a drainage port is formed in the side of theplane groove type stabilization ballast tank, and the water inlet and the drainage port are provided with electromagnetic valves; and oil-driven propeller is installed at the tail of the main body, and electric screw propellers are installed at the tails of the two auxiliary bodies. The unmanned vehicle adopts a three-body structure, has the better wave resistant stability, can effectively adjustthe draft and diving states, and provide the good working environment for carried acoustic instruments.

The invention discloses a novel trans-domain multiphibious carrier, which includes a fuselage, a tail, a V-tail, a landing gear, first to second wings, first to second buoys, first to fourth hydrofoils, first to fourth angle adjustment modules, first to second deflection motors, first to second power motors, first to second built-in propellers, and first to second auxiliary flight modules. The invention adopts unique shark-like shape design, has excellent aerodynamic and hydrodynamic performance, and can realize rapid motion under water and in the air. The use of hydrofoils enables the vehicleto move quickly and flexibly on the water surface, and the use of tilting ducts and tilting propellers enables the vehicle to move vertically and flexibly. The carrier of the invention has the characteristics of a tilting aircraft, a hydrofoil boat and a submarine.

The invention discloses an air inlet duct suitable for a small jet unmanned aerial vehicle with a flying wing configuration. The air inlet duct is in a Y shape and is divided into air inlet shaping sections, diffusion sections, mergence sections and a shrinking rectifying section. Two air inlets are formed in the upper surface of a flying wing, and the lower edges of the air inlets and the front edge of the flying wing are overlapped. The air inlet shaping sections each are in a bell shape, and the outlet area is 90% smaller than the inlet area of each air inlet shaping section. The diffusionsections on the two sides are merged through the mergence sections after complete diffusion and subjected to shrinking rectifying through the shrinking rectifying section. Internal structure arrangement is facilitated. The double-side air inlet layout is adopted on the small unmanned aerial vehicle, electronic equipment can be easily arranged on a nose, and meanwhile vehicle trim is facilitated.

The invention relates to a sawtoothed angle regulation mechanism for a two-dimensional spray pipe. The sawtoothed angle regulation mechanism comprises a mounting base, an actuator cylinder, a pull rod, a right sealing plate, a right baffle plate, a mounting base, a pull rod, a mounting seat, a left baffle plate and a left sealing plate, and is specifically characterized in that the mounting base is fixedly arranged on a two-dimensional spray pipe constriction regulation plate; a side sealing baffle plate is fixedly arranged on the left and right mounting edges of a round-to-square cylinder; one end of the actuator cylinder is connected with the mounting base, the other end of the actuator cylinder is connected with the hinged position of the pull rods through a rotating pair; the right baffle plate and the left baffle plate are connected at a tip end position through a rotating pair, and the rotating pair is kept being perpendicular to the constriction regulation plate; the outer end surfaces of the right sealing plate, the right baffle plate, the left baffle plate and the left sealing plate are guaranteed to be in the same one plane; the right sealing plate and the left sealing plate slide in the right baffle plate and the left baffle plate through sliding pairs, so that the effective regulation on the sawtoothed angle of the two-dimensional spray pipe can be realized. The sawtoothed angle regulation mechanism has the advantages of being simple in structure, fewer in movement connecting parts, good in stealth performance, and capable of realizing the regulation on the sawtoothed angle of a two-dimensional spray pipe outlet.

The invention relates to a hydrodynamic force catapulting device of a carrier-borne aircraft and relates to the technical field of weapon launching. The medium state and energy conversion processes from seawater to fresh water and then from fresh water to high-pressure steam are not need for achieving the catapulting device, and a seawater medium in the ocean is directly used for transmitting energy and acting, so that the device is simple in structure, compact in size, low in energy consumption in the catapulting process and high in energy use rate. In addition, the catapulting device uses high-pressure seawater as catapulting power, no electromagnetic interference is generated, and invisibility of a naval ship and reliable and stable work of mechanical and electrical equipment on the naval ship are facilitated.

The invention relates to a space-borne plasma antenna generation and emission device and a communication method. The device comprises a discharge tube, solenoid coils, an antenna, an air chamber, a radio frequency (RF) power source, a VLF / ELF wave feed source and a matching network. Space-borne plasma antenna submarine communication is used, and super-long plasma jet flows are jetted from a low-orbit satellite to be used as the VLF / ELF transmitting antenna, so that the device has high elusiveness, flexibility and maneuverability, weaknesses of foundation / shore-based submarine communication are prevented, and communication requirements of strategic nuclear submarines are fully met.

The Duffel Bag Airplane is an inflatable flying wing unmanned airborne vehicle (UAV). The fuselage will house everything but the wings. The wing can be rolled up around the fuselage into a small package when deflated for easy transportation, such as by being carried in a duffle bag. Fabric construction, a small internal combustion engine with cooled exhaust, and wing warping controls combine to make the airplane inexpensive and extremely stealthy. All the usual signatures have been suppressed, which allow it to be used to make observations from close range under combat conditions. Control of this airplane is accomplished by warping the wings and is supplemented with stability augmentation.

Belonging to the technical field of functional materials, the invention relates to a stealthy coating compatible with laser and infrared and a preparation method thereof. The stealthy coating compatible with laser and infrared is composed of filler and a resin matrix, wherein the filler is a composite filler composed of samarium oxide, lanthanum oxide, flake aluminum powder and indium tin oxide, and the resin matrix is polyurethane resin. The invention adopts the composite filler composed of samarium oxide, lanthanum oxide, flake aluminum powder and indium tin oxide to cooperate with the resin matrix and an assistant, the combined action endows the coating with low emissivity at the infrared band and low reflectivity at the laser waveband. By using polyurethane resin as the resin matrix and cooperating with specific spray coating process, the coating provided by the invention has good stealth performance, and also has good mechanical properties and environmental resistance at the same time. Also the preparation method is simple and is easy for operation.

The invention discloses an amphibious cruise missile based on a throat offset type pneumatic thrust-vectoring nozzle and a posture control method of the amphibious cruise missile. The amphibious cruise missile comprises a missile body, a switching section and the throat offset type pneumatic thrust-vectoring nozzle. The advancing direction of the missile is changed and jumping out of water is achieved by controlling the tail throat offset type pneumatic thrust-vectoring nozzle. Compared with a traditional missile, the amphibious cruise missile has the beneficial effects that a rudder and other structures are removed, smaller radar reflection area is achieved, and therefore the stealth performance is better. When the throat offset type pneumatic thrust-vectoring nozzle works underwater, water serves as a working medium, and the beneficial effects that no gas is exhausted, no sailing path exists, the noise is small and the stealthiness is good are achieved; and when the throat offset type pneumatic thrust-vectoring nozzle works in the air, high-temperature fuel serves as a working medium of the thrust-vectoring nozzle, and the beneficial effects that reaction is sensitive, the flight speed is high, and the voyage is far are achieved.

The invention provides a thin-wall whirl central body structure which consists of a thin-wall annular structure and a thin-wall whirl blade-shaped structure and is characterized in that the thin-wall annular structure is positioned at the outside, connected with a cylinder of an axially symmetrical nozzle by virtue of a support member and used for fixing the thin-wall whirl blade-shaped structure and meanwhile changing the flow direction of airflow flowing through the thin-wall whirl blade-shaped structure into a direction along the axial direction of the nozzle; the thin-wall whirl blade-shaped structure is positioned at a front middle section inside the thin-wall annular structure, arranged along the circumferential direction of the thin-wall annular structure and fixedly connected with the thin-wall annular structure; the sections of the front and rear ends of the thin-wall whirl blade-shaped structure form a certain angle in the circumferential direction, so that the thin-wall whirl blade-shaped structure can shield a hot end member at the front end of the engine, and a hiding function is achieved. The thin-wall whirl central body structure has the following advantages that the regulation range of the throat area of a traditional axially-symmetrical plug nozzle is not influenced; the thin-wall whirl central body structure can be applied to other types of traditional axially-symmetrical nozzles, so that a favorable hiding function is achieved, the structure is simple, and hidden sawtooth shaping can be performed conveniently.

The invention discloses a low-profile bilayer printing ultra-wideband antenna, comprising a transverse dielectric plate, a longitudinal dielectric layer, a reflecting plate, a base plate and a supporting column, wherein four supporting rods are arranged between the transverse dielectric plate and the base plate, and the longitudinal dielectric plate is arranged between the transverse dielectric plate and the base plate. Two back strips are machined on an upper plate surface of the transverse dielectric plate through a copper cladding technique, and two butterfly-shaped vibrators are machined on a lower plate surface of the transverse dielectric plate through the copper cladding technique. Baluns are machined on two plate surfaces of the longitudinal dielectric plate through the copper cladding technique. A reflection plate is machined on the base plate through the copper cladding technique. According to the low-profile bilayer printing ultra-wideband antenna disclosed by the invention, the bilayer printing antenna consisting of the antenna back strips and the vibrators is variety of a folding vibrator and is a high-grain directional novel bilayer printing vibrator antenna capable of working in an S-waveband and a C-waveband so that the miniaturization is not only realized, and wider frequency band and higher grain are provided; therefore, the antenna has very excellent characteristics of a folding vibrator, in particular the small structure size and the ultra-wide working frequency band.

The invention provides a novel axial-symmetry convergence and expansion spray pipe using a single actuation system. The novel axial-symmetry convergence and expansion spray pipe mainly comprises a cylinder body (1), an actuation cylinder (2), a pull rod (4), a convergence adjustment plate (5), an expansion adjustment plate (6), a support (7), an outer cover (8), an expansion sealing plate (9), a thin-wall rotational flow center body (10), a support (11) and a convergence sealing plate (12). The cylinder body (1) serves as a supporting component of the whole spray pipe. The actuation cylinder (2), the pull rod (4) and the convergence adjustment plate (5) serve as a throat area adjustment mechanism and also drive the expansion adjustment plate (6) to move, so that an outlet area changes according to a fixed rule. The thin-wall rotational flow center body (10) is used for shielding a front-end component. The novel axial-symmetry convergence and expansion spray pipe has the advantages that adjustment of the throat area and the outlet area is realized through the single actuation system, the spray pipe is good in invisibility on the premise that the adjustment range of the throat area is not affected, and the spray pipe is simple in structure and high in reliability.

The invention discloses a three-dimensional band absorption-type absorptive frequency selective structure, which is a periodically distributed structure. A structure unit adopts a mode of stacking oftwo layers of step-impedance parallel plate waveguides, loading of lumped capacitors and resistors is combined, and the performance of low-frequency wave transmission and high-frequency wave absorption is realized. The structure unit is composed of an upper parallel plate waveguide and front and rear loading parts, and a lower parallel plate waveguide and the rear loading part. The structure disclosed in the invention can be used for a stealth radome of a low frequency antenna in a military field. The three-dimensional band absorption-type absorptive frequency selective structure can transmitelectromagnetic waves at low frequencies without loss and can realize the wave absorption function in a wide frequency band at high frequencies, thereby reducing reflection of out-of-passband electromagnetic waves and realizing good stealth characteristics.

The invention discloses a high-invisibility lifting-body configuration aircraft without a horizontal tail. The high- invisibility lifting-body configuration aircraft comprises a fuselage(1), a left main wing (21) and a right main wing (22) on both sides of the fuselage (1), a nozzle (3) located on the rear part of the fuselage, and air inlet ducts (41,42)located on the side parts of the fuselage (1), wherein a left winglet (51) is arranged at one end, away from the fuselage (1), of the left main wing (21), and a right winglet (52) is arranged at one end, away from the fuselage (1), of the right main wing (21); the appearance of the left winglet (51) is the same as the appearance of the right winglet (52); the camber angle of left winglet (51) is parallel to the camber angle of the lip of the air inlet duct (41) on the left part of the fuselage (1); and the camber angle of the right winglet (52) is parallel to the camber angle of the lip of the air inlet duct (42) on the right part of the fuselage (1). The high-invisibility lifting-body configuration aircraft without the horizontal tail disclosed by the invention is high in aerodynamic performance and good in invisibility effect.

The invention discloses a basalt fiber prepreg comprising basalt fiber, epoxy resin and release paper, wherein the epoxy resin is soaked into a basalt fiber layer; and the release paper is directly attached to the outer surface of the basalt fiber layer. In addition, the invention discloses a two-step hot melting preparation method of the basalt fiber prepreg, and the preparation method comprises the steps of film preparation and presoaking. The method disclosed by the invention is simple, and the prepared basalt fiber prepreg is favorably applied to the market field of composite materials such as plates, fishing poles and profiled bars. The basalt fiber and a product thereof have abnormally excellent performances on the following aspects of remarkable high temperature resistance and thermal shock resistance, relatively low heat conduction coefficient, high elasticity modulus and tensile strength, good chemical stability, relatively high sound absorption coefficient, favorable electric insulation and dielectric properties, relatively low moisture absorptivity and natural silicate intermiscibility.

The invention discloses an electrically-controlled plasma yagi-uda antenna, belonging to the technical field of antennae, which is characterized in that: the electrically-controlled plasma yagi-uda antenna comprises an active dipole at the center, and reflecting / director dipoles in ring shape and symmetrically arrayed at the periphery of the active dipole. The number of the reflecting / director dipoles is 2N (N represents a natural number that is more than or equal to 1). The reflecting / director dipoles can act as both reflecting dipoles and director dipoles, wherein, every two reflecting / director dipoles which are centrosymmetric with the active dipole are a pair of reflecting dipoles and a pair of director dipoles. Within a same period, only one pair of the reflecting dipoles and the director dipoles are in working states. The electronically-controlled plasma yagi-uda antenna is provided with flexible directionality.

The invention discloses a time domain cloaking device based on a micro loop resonator. The time domain cloaking device based on the micro loop resonator comprises a light frequency comb generator, the micro loop resonator, a single mode fiber, a Mach-Zehnder modulator, a dispersion compensation fiber, a random waveform generator connected with the micro loop resonator, and a code stream generator connected with the Mach-Zehnder modulator, wherein the light frequency comb generator, the micro loop resonator, the single mode fiber, the Mach-Zehnder modulator and the dispersion compensation fiber are connected in sequence. The Mach-Zehnder modulator modulates an optical signal with a time gap through a modulation electric signal and outputs a modulated optical signal, the modulated optical signal passes through the dispersion compensation fiber to stitch the time gap, the original optical signal is recovered, and then cloaking of the optical signal in a time domain is realized. The micro loop resonator adopted for the time domain cloaking device is relatively easy to manufacture and obtain compared with a time division prism, so that the structure is simple, cost is low, and the achieved cloaking effect is obvious; by means of adjusting the random waveform generator and changing the length of the single mode fiber and the length of the dispersion compensation fiber, cloaking time periods can be changed, and cloaking in the time domain within a long time period is realized.

The invention belongs to the technical field of metasurface stealth, and particularly relates to fully-polarized metasurface carpet stealth garment based on a geometrical phase and a transmission phase and a design method of the fully-polarized metasurface carpet stealth garment. The carpet stealth garment is of any three-dimensional structure and is formed by splicing a plurality of planar metasurfaces. Each planar metasurface is formed by periodically extending a plurality of metasurface units; each metasurface unit comprises an upper-layer flexible dielectric plate, middle-layer engineeringresin and a lower-layer flexible dielectric plate, wherein one side of the upper-layer flexible dielectric plate comprises a metal arc electric resonator, the other side of the upper-layer flexible dielectric plate is fully corroded, and one side of the lower-layer flexible dielectric plate is fully metal while the other side is fully corroded; structural parameters and azimuth angles of the arcelectric resonator are changed along with different unit positions, and the arc electric resonator is designed through a full-polarization metasurface carpet stealth garment method. The carpet stealthgarment shows excellent electromagnetic stealth performance under the excitation of linearly polarized waves, circularly polarized waves or elliptically polarized waves with different polarization angles, and has the advantages of arbitrary polarization, arbitrary shape, excellent stealth characteristic, easiness in assembly and the like.