472 results about "Aerospace vehicle" patented technology

Disclosed are particles that have an exterior surface coated with a thin polymeric coating, such as a coating that includes a sulfur-containing polymer. Also disclosed are compositions, such as fuel-resistant sealant and coating compositions, which include such particles. Aerospace vehicles having an aperture at least partially sealed with a sealant deposited from such a sealant composition are also disclosed.

The invention relates to a graphene-organic material layered assembly film and a preparation method thereof. The preparation method comprises: using a graphene material and an organic material as raw materials, utilizing interaction of static electricity, hydrogen bonds, coordinate bonds or charge transfer and the like between the graphene and the organic material, and superposing films layer by layer through the film preparation methods such as spin coating, spraying, dipping, lifting and pulling and the like to prepare the film, wherein the thickness of each layer of the film can be controlled between 10 nanometers and 2 millimeters according to requirement. The layered assembly film and the preparation method have the characteristics that multilayer film materials with different functions are prepared by utilizing unique electric, magnetic, mechanical and chemical properties of the grapheme, and can be used as biomaterials, conductive materials, electromagnetic shielding and wave absorbing materials, photovoltaic materials, electrode materials, film filtering and separating materials, and the like to be applied to chemistry and chemical industry, biology and precision instruments, and manufacture of micro electrons, machinery and aviation and aerospace devices according to the selected different organic materials.

A composite laminate for use on an external part of an aerospace vehicle has improved ultraviolet resistance and resistance to microcracking from thermal cycling. The laminate comprises a nanoreinforcement film, a support veil, and a composite layer. The laminate also can have a lightning strike protection layer and an external paint and primer. The nanoreinforcement film can comprise carbon nanomaterial and a polymer resin, and the composite layer has one or more layers of a reinforcement and a polymer resin. The carbon nanomaterial can be carbon nanofibers, and the nanoreinforcement film can have an areal weight of less than about 100 g / m2. The carbon nanomaterial can also comprise carbon nanofibers and carbon nanotubes.

A cryogenic fuel tank adapted for attachment to an aerospace vehicle includes an exterior layer of reinforced composite insulating foam. The insulating foam is reinforced with an aramid fiber mesh or a closed cell foam may be reinforced with one or more of carbon nanotubes, graphite whiskers, silicon carbide fibers or graphite fibers. The improved composite insulating structure disclosed herein provides a remedy for insulating material breaking off the large external fuel tank attached to the space shuttle during launch and ascent into space.

Addressed are systems and methods for providing to pilots of landing aircraft real-time (or near real-time) information concerning runway conditions and aircraft-stopping performance to be encountered upon landing. The systems and methods contemplate using more objective data than utilized at present and providing the information in automated manner. Information may be obtained by using conventional ground-based runway friction testers or, advantageously, by using air-based equipment such as (but not limited to) unmanned aerospace vehicles (UAVs).

The invention discloses a system failure early warning method based on a baseline model and the Bayesian factor. The system failure early warning method based on the baseline model and the Bayesian factor can be applied to a dynamic complex system and particularly applied to early detection and warning of aerospace vehicle equipment failure. The method includes: using the multivariate state estimation technique to excavate the system 'individuation' baseline model on the basis of system state monitoring data; and using an actual measurement value of a system state parameter to subtract a baseline value so as to obtain a deviation value of a state parameter, analyzing a deviation value sequence by the aid of a Bayesian factor method, monitoring abnormalities of a sequence structure, and timely giving out failure early warning. The system failure early warning method based on the baseline model and the Bayesian factor solves the problems that dynamic complex system performance parameter deviation value dispersion is large, failure early characteristics are easily buried in noise, warning can be given out at the early stage of system failure, and sensitivity and robustness of the monitoring system are improved. Besides, the baseline model is easy to implement from the perspective of engineering, and the method is high in university and capable of meeting the requirements of the dynamic system on real-time monitoring.

Quasi-isotropic chopped prepreg is used to make parts found in aerospace vehicles. Exemplary aerospace parts that are made using quasi-isotropic chopped prepreg include aircraft window frames, wing fairing supports, flange supports, frame gussets, rudder actuator brackets, shear ties, seat pedestals, cargo floor flange supports, storage bin fittings, antenna supports, torque tube pans, handle boxes, side guide fittings, wing box covers and intercostals.

An aerospace vehicle integration performance verification system based on data sharing is divided into a preposition equipment area and a rear end equipment area. The rear end equipment area is divided into a test service area and an operation application area. The preposition equipment area, the test service area and the operation application area are connected through using an optical fiber network. The preposition equipment area is an information interaction link of an aircraft and the rear end equipment area and is formed by subsystem test equipment. The test service area is a core area of the aerospace vehicle integration performance verification system and comprises a test processing server, a data subscription server, a data interpretation server, a database server, a health monitoring and assessment server and a disk array. The operation application area is formed by a control operation platform and a data monitoring terminal. Through using various kinds of services provided by the test service area, functions of remote control / control instruction sending, parameter interpretation and health evaluation rule editing, test flow bookbinding, data display, data query, data playback and test report generation are realized.

The invention relates to a composite layered anti-interference controller, in particular to a design of the composite layered anti-interference controller in a type of multisource jamming control system. The anti-interference controller is designed aiming at the multisource jamming control system containing external model description disturbance, random disturbance and energy-bounded disturbance. Firstly, a reduced-order disturbance observer is structured to estimate and counteract the external model description disturbance of the multisource jamming control system; secondly, the controller having H infinity and guaranteed cost performance index is structured, wherein, the H infinity performance index can be used for inhibiting the energy-bounded disturbance in the system, and the guaranteed cost performance index can be used for inhibiting the random disturbance in the system as well as optimizing the upper bound of variance; the composite layered anti-interference controller can be formed by the reduced-order disturbance observer and the feedback controller with a state of robust H infinity and guaranteed cost; finally, based on convex optimization algorithm, gain array of the composite layered anti-interference controller can be solved. The invention has the advantages of strong anti-interference property, convenient design and the like, and can be applied to a navigation and control system of aerospaceplane, etc.

The invention discloses a rolling compounding method for an aluminum / magnesium / titanium three-layer composite plate. The characteristics of high strength of titanium alloy, low melting point and good vibration reducing performance of magnesium alloy, good plasticity and space adaptation of the aluminum alloy, and the like, are utilized and the excellent characteristics of respective component metals are combined by the aluminum / magnesium / titanium three-layer composite plate provided by the invention, so that the high-speed impact damage resisting property which the component metals do not own is acquired. Through the control on the ratio and interface of the aluminum alloy, the magnesium alloy and titanium alloy, the degree of fragmentation, melting and atomizing of shred cloud after the buffer composite plate is subjected to high-speed impact is changed and adjusted, so that the form of the shred cloud is changed, the degree of impact damage to a backplate is reduced, and the high-speed impact damage resisting property is increased. The aluminum / magnesium / titanium three-layer composite plate is applied to an outer layer buffer plate in an outer layer protecting structure of an aerospace vehicle and can be used for replacing a traditional single aluminum alloy material. The space environmental effect and protecting level of the space vehicle are increased; the design level of the space vehicle are greatly promoted, and the service life of the space vehicle are greatly prolonged.

The invention discloses a low-dielectric high-temperature-resistant phosphate-silicon dioxide coating, with the mass percentage content between the components and the raw material as follows: 50-80% of percentage content of inorganic compound binder, 15-50% of high-temperature filler, 0.5-1.5 wt% of curing agent, 2-5 wt% of thickener, and 0.3-1.5wt% of surfactant; the inorganic compound binder is the mixture of aluminum phosphate or aluminium-chromium phosphate and silicon collosol; the high-temperature resistant filler is the mixture of fused quartz powder and refined quartz powder or alpha-Al2O3 power; the curing agent is MgO; the thickener is fumed silica; the surfactant is non-ionic surfactant. The phosphate binder is firstly prepared, followed by phosphate / silicon collosol compound binder; then the non-ionic surfactant and the high-temperature resistant filler are added to the compound binder, followed by the thickener and the curing agent, then the mixture is evenly mixed. The invention can be used for the surface protection of porous inorganic materials or non-porous inorganic materials and is typically used as wave-transparent material for aerospace crafts.

An integrated inertial stellar attitude sensor for an aerospace vehicle includes a star camera system, a gyroscope system, a controller system for synchronously integrating an output of said star camera system and an output of said gyroscope system into a stream of data, and a flight computer responsive to said stream of data for determining from the star camera system output and the gyroscope system output the attitude of the aerospace vehicle.

The invention relates to a preparation method of a high-temperature resistant polyimide glass fabric laminated board, which comprises the following steps: (1) adding 1,4-bis(2,4-diaminophenoxy) benzene and maleic anhydride to a non-proton organic solvent with strong polarity, then adding aromatic diamine monomer, aromatic dibasic anhydride and initiator, and stirring for dissolving to obtain a component A; (2) adding 1,4-bis(2,4-diaminophenoxy) benzene and maleic anhydride to a non-proton organic solvent with strong polarity, stirring and reacting for 2 hours to obtain a component B; and (3) mixing the component A and the component B evenly to obtain a polyimide precursor resin solution, impregnating the glass fabric in the resin solution, and obtaining the high-temperature resistant polyimide glass fabric laminated board after preliminary drying semi-curing and high-temperature press thermo-curing. The high-temperature resistant polyimide glass fabric laminated board prepared in the invention has excellent heat resistance, can be applied to high-temperature resistant electro-insulating material and high-temperature resistant structural part material of aerospace vehicles, and has wide application prospects.

The invention provides an acoustic emission signal sensing system based on matching-type fiber Bragg grating (FBG), which aims to overcome limitation of the prior art and introduce an FBG sensor into the acoustic emission detection field. The acoustic emission signal sensing system comprises a broadband light source, a first fiber coupler, a second fiber coupler, the FBG, a tunable FBG filter, a first photoelectric detection circuit, a second photoelectric detection circuit, an analog-to-digital conversion circuit, an FBG array (FBGA) and a computer. The acoustic emission signal sensing system is mainly applied to structural safety monitoring of an aerospace plane and damage detection of important components, and has the advantages of high sensitivity, high response speed, long transmission distance and strong resistance to electronic interference; and compared with the power-type FBG acoustic emission sensing system, the acoustic emission signal sensing system based on the matching-type FBG provided by the invention has the beneficial effects that wavelength shift information is demodulated by a matching grating method so as to obtain information of an original acoustic emission wave, the detection object is optical wavelength rather than optical power, and optical wavelength information is not affected by optical power loss during the optical transmission process, thus the detection precision is higher, the resolution power is higher and the noise is smaller.

The invention discloses nanostructure tungsten alloy and a preparation method thereof. The alloy mainly comprises tungsten, and also comprises 0.05 to 1.0wt percent of zirconium and 0.2 to 2.0wt percent of rare-earth metal oxide particles, wherein the rare-earth metal oxide particle adopts yttrium oxide particles, lanthanum oxide particles or cerium oxide particles distributed in tungsten crystal particle. The method comprises the steps of firstly preparing ammonium paratungstate, rare-earth metal nitrate, citric acid and deionized water into transparent mixed liquor, stirring the transparent mixed liquor, obtaining gel after reaction, heating and drying the gel, then calcining the gel, so as to obtain a mixed powder of tungsten oxide and rare-earth metal oxide, putting the mixed powder into hydrogen atmosphere, so as to obtaining a mixed powder of tungsten and rare-earth metal oxide after reduction reaction, mixing the mixed powder with zirconium and zirconium hydride powder, so as to obtain a mixed powder of tungsten, zirconium, or zirconium hydride, and rare-earth metal oxide, and finally performing compaction and sintering to the mixed powder, so as to obtain the nanostructure tungsten alloy. The nanostructure tungsten alloy can be applied to fields of lighting, high-temperature components, aerospace devices, high temperature resistance containers and the like.

The invention relates to a composite layered anti-interference filter, in particular to a design of the composite layered anti-interference filter in a type of multisource jamming system. The anti-interference filter is designed aiming at the multisource jamming system containing random disturbance, energy-bounded disturbance and external model description disturbance. Firstly, a disturbance observer is structured to estimate and counteract the external model description disturbance of the multisource jamming system; secondly, the filter having H infinity and guaranteed cost performance index is structured, wherein, the H infinity performance index can be used for inhibiting the energy-bounded disturbance in the system, and the guaranteed cost performance index can be used for inhibiting the random disturbance in the system as well as optimizing and estimating the upper bound of error variance; the composite layered anti-interference filter can be formed by the disturbance observer and the filter with the robust H infinity and the guaranteed cost; finally, based on convex optimization algorithm, gain array of the composite layered anti-interference filter can be solved. The invention has the advantages of strong anti-interference property, high filtration accuracy and the like, and can be applied to a navigation and control system of aerospaceplane, etc.

A side thruster valve of an aerospace craft is improved to reduce torque of a servo-motor, etc. needed for nozzle opening and closing to thereby realize a compact and light weight device. The side thruster valve comprises a valve plug having its back directed to an axis of the aerospace craft and independently movable between a fully opened position and a fully closed position of the valve plug in a plane orthogonal to the axis of the aerospace craft, an actuating means for moving the valve plug in an axial direction of the valve plug and an elastic member for activating the valve plug in the axial direction of the valve plug. In a side thruster device comprising a plurality of the side thruster valves, the side thruster valves are arranged independently of each other to thereby broaden freedom of combustion control and improve fuel consumption.

The invention discloses a satellite borne or airborne double-slit convex grating imaging spectrometer for observation over the ground, which is composed of a reflection lens, a convex spherical reflection grating and a concave spherical reflector. The invention is characterized in that spectral surfaces respectively corresponding to slits are formed on different positions of an image space by setting two slits in an object space, a plurality of detector modules can be arranged alternately on the spectral surface so as to expand the field of view, and the image quality and the spectral bending can be improved by carrying out spatial position adjustment on a plurality of detectors; and a double-slit spectral imaging can also be formed on the same detector so as to reduce half of the requirement for reading frame frequencies by the detector, thereby solving the problem that the instruments in aerospace vehicles flying at high speed are extra-high in frame frequency. The invention is mainly applied to satellite borne or airborne spectral imaging systems.

The invention discloses a dynamics modeling and analyzing method for an aerospace vehicle and belongs to the technical field of flight dynamics modeling and simulation analysis of aircrafts. According to the dynamics modeling and analyzing method, the variable-span and variable-sweepback aerospace vehicle is simplified and is composed of a fuselage, a left wing inner side, a left wing outer side, a right wing inner side and a right wing outer side, wherein the fuselage, the left wing inner side, the left wing outer side, the right wing inner side and the right wing outer side are independent rigid bodies. The deformation movement of wings relative to the fuselage is represented through a set of constraint equations, so that the freedom degree of a dynamics model is reduced; the aerodynamic force exerted on the aerospace vehicle is simplified to act on the fuselage only, and the dynamics model is established through the Kane method; related items derived from the deformation movement are extracted from the dynamics model to form additional force and additional force moment so that the influence on the dynamics characteristics of the aerospace vehicle by the inertia force and inertia moment caused by the deformation moment can be represented. The dynamics model of the aerospace vehicle is simplified through the dynamics modeling and analyzing method, and integral items and derivation terms of the inertia moment do not appear in the equations. In this way, dynamics modeling and simulating can be easily performed on the aerospace vehicle, and meanwhile accuracy is high.

The present invention provides a thermal management system and a thermal management method for a high-altitude unmanned aerial vehicle fuel cell module, and belongs to the field of aviation spacecraftenergy source systems. According to the present invention, the high-altitude unmanned aerial vehicle fuel cell module comprises a fuel cell reactor, an oxygen supply system and a hydrogen supply system, the thermal management system comprises a heat exchanger and a heat dissipation system, one part of the waste heat generated by the fuel cell reactor heats hydrogen and oxygen through the heat exchanger, the other part of the waste heat generated by the fuel cell reactor heats the environmental space at which the fuel cell reactor is positioned, the fuel cell reactor is an air-cooled fuel cellreactor or a liquid-cooled fuel cell reactor, and the air-cooled fuel cell reactor comprises a closed air-cooled fuel cell reactor and an open air-cooled fuel cell reactor.

An anti-fouling coating is provided, containing a continuous matrix comprising a first component; a plurality of inclusions comprising a second component, wherein the first component is a low-surface-energy polymer having a surface energy, and the second component is a hygroscopic material containing one or more ionic species. The low-surface-energy polymer and the hygroscopic material are chemically connected ionically or covalently, such as in a segmented copolymer composition comprising fluoropolymer soft segments and ionic species contained within the soft segments. The continuous matrix and the inclusions form a lubricating surface layer in the presence of humidity. Coefficient-of-friction experimental data is presented for various sample coatings. The incorporation of ionic species into the polymer chain backbone increases the hygroscopic behavior of the overall structure. Improvement in lubrication enables material to be cleared from a surface using the natural motion of an automotive or aerospace vehicle.

The invention discloses an online adaptive calibration method for inertial sensor errors of an aerospace vehicle. The method comprises the following steps: establishing an error of an inertial sensor in the high dynamic flight process of the aerospace vehicle, wherein the errors comprise an installation error, a calibration factor error and a random constant value error; establishing a high-order online calibration filter state equation comprising error parameters of the inertial sensor and a measurement equation; and finally, performing online adaptive calibration and real-time compensation on the errors of the inertial sensor in the high dynamic flight process of the aerospace vehicle, thereby obtaining the navigation result of the inertial navigation system subjected to error compensation correction of the inertial sensor. According to the method, the real-time calibration and compensation of the installation error, the calibration factor error and the random constant value error of the inertial sensor of the inertial navigation system can be realized in the high dynamic flight process of the aerospace vehicle, the performance of the inertial navigation system in an aerospace flight environment is effectively improved, and the method is applied to engineering application.

The invention discloses a miniaturized linear variable filter type imaging spectrometer with high integration level, which comprises a linear variable filter (LVF) and a detector, wherein the two ends of the LVF are provided with a support wing respectively, the support wings are arranged on a base, one surfaces of the support wings and a non-coating surface of the LVF are positioned on the same plane, a coating surface of the LVF is close to a photosensitive surface of the detector and a certain distance exists from the photosensitive surface to the coating surface. Compared with the conventional imaging spectrometer, the imaging spectrometer disclosed by the technical scheme has the following advantages that 1, the integration level is high, the structure is stable, miniaturization is easy to realize, and the imaging spectrometer can be installed on equipment, such as a moving platform and an aerospace vehicle; 2, the lead time is short, the cost is low, and the application range is wide.

Provided is a Flight Gear general three-dimensional scene data displaying method based on a field programmable gate array (FPGA). The method includes that an FPGA chip is adopted, coding of Verilog hardware description language (HDL) language is conducted on the FPGA chip, and a data transmission protocol 1 is self-defined so as to enable the FPGA chip to finish receiving of serial data of specific frame format and with the baud rate of 115200 bps, analysis of data of a self-definition communication protocol 1 is finished in the FPGA, and the data is processed through corresponding algorithms. Then, the processed data is coded and packaged through another self-definition communication protocol 2 and transmitted to a Simulink project operated on a personal computer (PC) with the baud rate as 115200 bps, a series of data processing is conducted in the Simulink. Finally, corresponding gesture data is transmitted to Flight Gear software through a user datagram protocol (UDP) network transmission module to be displayed in real time in a three-dimensional (3D) mode. The Flight Gear general three-dimensional scene data displaying method has the advantage that design and simulation of an aerospace vehicle controller, simulation of an unmanned aerial vehicle controller, simulation of guided missile control, simulation of vehicle and ship controllers and 3D visual reproduction of actual aircraft test flight data and the like can be well achieved, and a use range is wide.

A mounting set for use in mounting an external stores to a mounting station of an aerospace vehicle includes a mounting bracket arrangement and a strap arrangement. The bracket arrangement is configured for selective reversible engagement with respect to the mounting station and for cooperating with the strap arrangement. The strap arrangement is configured for securing the bracket arrangement to the stores in load bearing abutment therewith to enable transfer of loads between the stores and the mounting station via said bracket arrangement, in operation of said mounting set. A mounting system is also provided for mounting an external stores to an aerospace vehicle having two or more mounting stations, including a mounting set for each mounting station. Mounting methods are also provided.

The invention relates to a method for preparing a titanium alloy TC4 spherical powder by a plasma auxiliary rotation-electrode centrifugal process, comprising the following steps of: generating a glow discharge plasma arc between consumption type electrodes manufactured by a plasma auxiliary electrode and a rotational cylindrical titanium alloy TC4 in a closed container protected by inert gas, wherein a section of the titanium alloy TC4 electrode, which is close to the plasma arc, forms droplets due to high temperature generated by the plasma arc; throwing the droplets by centrifugal force; air-cooling and curing the titanium alloy TC4 droplets into a spherical shape in the inert atmosphere environment of the closed container; and obtaining a titanium alloy TC4 prill. The method can obtain the titanium alloy TC4 prill which has average sphere diameters between 0.08 mm and 1.8 mm and better monodispersity by changing technological parameters; in addition, the prepared powder prill has good sphericity, lower malformed particle proportion and controllable sphere diameter and can be used in the field of laser three-dimensional forming and for preparing special components of aerospace planes.

A bonded metal fuselage for aerospace vehicles includes a monocoque structure having an outer metal skin, metal tear straps bonded to the outer skin and metal stringers bonded to the outer skin and to the tear straps. The outer chords of fuselage frames are fastened directly to tear straps and to the skin, obviating the need for clips to fasten the frames to the stringers.

The invention discloses an aerospace vehicle large envelope switching control method adopting a protection mapping theory. The method is characterized by averaging network division flight envelopes, selecting a balance point and establishing a linear model; then based on a gap metric, selecting a nominal point in a flight large envelope; designing an aerospace vehicle control structure; according to a flight attitude, controlling a target and determining a stability range; according to the protection mapping theory, determining an inner ring attitude controller parameter for a linear system of each balance point; and then calculating and acquiring a transfer function of the linear system; establishing an equivalent low order model of an inner ring system and an equivalent low order model of an outer ring system; extracting a state matrix of each linear system; using a Jacobian linearization method to establish an LPV model; according to a flight locus, controlling the target and determining the stability range; based on a protection mapping parameter, setting an algorithm and calculating an outer ring height controller parameter; and finally, acquiring an analytical expression of a controller.

The invention relates to a fluorescent waveguide light-harvesting type photovoltaic-photothermal combined power generation device. The device comprises a laser type fluorescent waveguide light-harvesting type photovoltaic-photothermal combined power generation device and a solar-energy type fluorescent waveguide light-harvesting type photovoltaic-photothermal combined power generation device; both the two types of the fluorescent waveguide light-harvesting type photovoltaic-photothermal combined power generation devices comprise micro-nano light trap layers, light transmitting heat conduction layers and fluorescent waveguide light-harvesting type photovoltaic-photothermal combined power generation layers; each fluorescent waveguide light-harvesting type photovoltaic-photothermal combined power generation layer comprises a fluorescent waveguide light-harvesting device, a heat conduction layer, a thermoelectric temperature difference power generation device, a photovoltaic power generation device and a radiator; the two types of the devices are capable of producing a photovoltaic power generation effect and a photothermal power generation effect respectively under irradiation of laser, or sunlight, or solar concentrating light, and are capable of outputting externally electricity generated through photovoltaic-photothermal combined power generation. The fluorescent waveguide light-harvesting type photovoltaic-photothermal combined power generation device is capable of being widely applied in the fields of aerospace vehicles, unmanned aerial vehicles, unmanned ships and warships, unmanned vehicles, robots, engineering equipment and the like.