3574 results about "Aerospace" patented technology

A noise-free portable EEG system is provided. The system has hardware and software and can evaluate mental state quantitatively. The quantitative data of mental states and their levels can be applied to various areas of brain-machine interface including consumer products, video game, toys, military and aerospace as well as biofeedback or neurofeedback.

A fiber-reinforced thermoplastic composite material having an advantageous combination of smoke generation, heat release, and mechanical property characteristics. The composite generally comprises a fiber-reinforced thermoplastic core containing discontinuous reinforcing fibers bonded together with one or more thermoplastic resins. The core material may further comprise at least one first skin material applied to a first surface of the core and/or one or more second skin material applied to a second surface of the core material. The thermoplastic core material has a maximum smoke density D_s (4 minutes) of less than 200 as measured in accordance with ASTM E662, a maximum heat release (5 minutes) of less than 65 kW/m² as measured in accordance with FAA Heat release test FAR 25.853 (a) Appendix F, Part IV (OSU 65/65), and an average total heat release (2 minutes) of less than 65 kW/m² as measured in accordance with FAA Heat release test FAR 25.853 (a) Appendix F, Part IV (OSU 65/65). The invention is useful in the manufacture of articles for aircraft, automotive, railcar, locomotive, bus, marine, aerospace and construction in which the certain advantages may be provided over other materials utilized for such applications.

Lightweight articles comprising a polymeric material at least partially coated with a fine-grained metallic material are disclosed. The fine-grained metallic material has an average grain size of 2 nm to 5,000 nm, a thickness between 25 micron and 5 cm, and a hardness between 200 VHN and 3,000 VHN. The lightweight articles are strong and ductile and exhibit high coefficients of restitution and a high stiffness and are particularly suitable for a variety of applications including aerospace and automotive parts, sporting goods, and the like.

The invention provides a non-contact free space eye-gaze tracking method suitable for man-machine interaction. The method comprises the steps of positioning and tracking a face and eyes in real time, extracting eye movement biological characteristic information, building an eye movement model based on the eye movement biological characteristic information, building a mapping relational model of the eye movement model and an eye-gazed object and the like. The non-contact free space eye-gaze tracking method suitable for the man-machine interaction relates to multiple crossed fields of image processing, computer vision, pattern recognition and the like and has wide application prospect in the fields of new-generation man-machine interaction, disabled people assisting, aerospace relating field, sports, automobile and airplane driving, virtual reality, games and the like. In addition, the method has great practical significance for improvement of the life and self-care level of disabled people, building of a harmonious society and improvement of independent innovative capability in the national high-and-new technical fields of the man-machine interaction, unmanned driving and the like.

The double bag vacuum infusion process of the present invention provides a low cost method for producing complex composite assemblies without an autoclave. It also enables the production of highly innovative structures. The quality of the composites produced using such an infusion process are comparable to composites made using prepregs, hand layup or fiber placement, and autoclave curing. Double bagging provides vacuum integrity, controls bag relaxation while flow media controls the flow front to allow high quality aerospace-grade products.

The invention discloses a nanometer multiple-layer composite thermal insulation material and a preparation method thereof. The nanometer multiple-layer thermal insulation composite material is formed by alternatively overlapping an infrared reflecting screen and a spacer; the ratio of total layer amounts n of the infrared reflecting screens and the spacers to the total thickness of the nanometer multiple-layer composite thermal insulation material is 0.5-4; the infrared reflecting screen is a metal foil or a metal plated foil; the spacer is a thermostability nanometer porous aerogel composite thermal insulation material; the infrared reflecting screen and the spacer are combined by being adhered with thermostability adhesives or in puncturing connection by thermostability sewing threads. The invention also comprises the preparation method of the nanometer multiple-layer composite thermal insulation material. The nanometer multiple-layer composite thermal insulation material of the invention has low density, favorable mechanical property and favorable high-temperature thermal insulation property, lowers requirements on the vacuum degree by a VIP plate when being used as vacuum thermal insulation plate core materials, does not need getter and can satisfy harsh high-efficiency thermal insulation using requirements on materials by aviation, aerospace and civil fields. The method of the invention can prepare thermal insulation material members with large size and complex shape.

An electromagnetic shielded optical window with ring type of metal cross hatch pattern structure is prepared as arranging ring type of metal cross hatch pattern units in two-dimensional orthogonal mode to from cross hatch pattern array then loading formed array on transparent substrate surface of optical window. The prepared product can be used to carry out electromagnetic shielding in medical treatment and aerospace cause.

The invention discloses a CFD (computational fluid dynamics)/CSD (circuit switch data) coupled solving nonlinear aeroelasticity simulation method, comprising: firstly, carrying out calculation initialization; then solving the CFD of unsteady aerodynamic force; converting boundary load information; solving the CSD of nonlinear structure dynamic response; judging whether to exist computation or notby taking the response of structural finite-element mesh point displacement as a convergence criteria; if not exiting, carrying out the dynamic mesh deformation of a flow field after the surface displacement information of a computation model is converted; and then, continuing to compute until the convergence criteria is satisfied, thus finishing computation. By means of the simulation method disclosed by the invention, the problem of pneumatic nonlinearity and structural nonlinearity coupling and the problem of geometric large deformation dynamic mesh can be solved; and the simulation methoddisclosed by the invention can be applied on the nonlinear aeroelasticity analysis of aerospace aircrafts and the nonlinear aeroelasticity analysis of civil high-rise buildings and bridges.

An optically transparent, ghost-free visual display system that superimposes a virtual image comprising graphical or textual information onto a field of vision. Embodiments of the visual display system utilize illumination and optical components that introduce a virtual image onto a field of vision while minimally obstructing and/or attenuating other objects within the field of vision. Embodiments of the visual display system can be used in numerous applications, including head-up displays (“HUDs”) for automotive, tracked and rail-mounted vehicles, marine, aerospace applications, see-through speech prompt displays, and see-through projection displays.

The invention relates to a nanometer cellulose/polyvinyl alcohol gel composite material, which is characterized by comprising hydrogel and aerogel. A preparation method of the nanometer cellulose/polyvinyl alcohol gel composite material comprises the following process steps of 1, nanometer cellulose preparation by a chemical combination mechanical treatment method; 2, composite hydrogel preparation; and 3, composite aerogel preparation. The nanometer cellulose/polyvinyl alcohol gel composite material has the advantages that the composite aerogel belongs to a porous amorphous solid material consisting of nanometer level colloid particles or high-polymer molecules, and a unique open nanometer level porous structure and a continuous three-dimensional reticular structure are adopted, so the density is extremely low, the specific surface area is high, and the porosity is high, wherein the solid phase of the aerogel accounts for 0.2 percent to 20 percent of the total volume percentage, the characteristics of high adsorption catalytic capability, low thermal conductivity, low sound resistance, low refractive index and the like are shown, and wide application prospects are realized in the fields of aviation, spaceflight, chemical industry, metallurgy, energy-saving building and the like.

The present invention provides a curable polysiloxane composition which is excellent in light resistance (particularly ultraviolet resistance) and adhesion and has a sufficient heat resistance/hydrothermal resistance and film-forming property and which generates little foaming at curing and does not generate cracks, peeling, coloring, and foaming even when used for a long period of time. A curable polysiloxane composition which comprises a specific hydrosilyl group-containing polysiloxane compound, a specific polysiloxane compound comprising two or more silanol groups in one molecule, and a dehydrogenative condensation reaction catalyst.

A cooling system for an electrical motor or generator includes a first cooling loop, a second cooling loop, and a heat exchange system. The first cooling loop may extract heat from an iron stack and winding of the electrical motor or generator. The second cooling loop may extract heat from end turns of the stator winding, the rotor, and the bearings independently from and simultaneously to the first cooling loop. At least the first cooling loop may pass through the heat exchange system. A liquid coolant may circulate in the first cooling loop and a compressed gas, such as compressed air or compressed refrigerant in vapor form, may circulate in the second cooling loop. The cooling system and method for an electrical motor or generator may be suitable for, but not limited to, applications in the aircraft and aerospace industries, such as driving a cabin air compressor of an aircraft.

The invention relates to the field of aerospace engineering, specifically discloses a distributed power multi-rotor VTOL (vertical take off and landing) aircraft and a control method thereof. The aircraft comprises an aircraft body, a plurality of lift power units, a plurality of thrust power units, and a central flight control computer system, wherein the aircraft body is provided with a cowling covering outside the aircraft body; the lift power units and the thrust power units are uniformly arranged on the aircraft body and used for adjusting the attitude and speed of the aircraft; and the central flight control computer system is connected with the lift power units and the thrust power units and used for controlling the lift power units and the thrust power units to adjust the attitude and speed of the aircraft. Through uniformly setting a plurality of lift power units on the aircraft, the reliability, stability and disaster-tolerant capacity of the aircraft are improved, so that the aircraft still can fly normally when the components such as engines or rotors of the aircraft have mechanical failures, thereby reducing crash risk of the aircraft.

A fastener adapted to pass through aligned holes through workpieces is disclosed. The fastener includes a pin member having a transition portion wherein the diameter of the transition portion decreases radially as it extends from the smooth cylindrical shank portion to the threaded portion. The fastener may also comprise a sleeve member and a clamping means. The clamping means includes a collar, a nut, or any other possible clamping means. In exemplary embodiments, the workpieces can be formed with a plurality of materials, the materials including composite, metallic, or composite/metallic structures, any combination thereof. In particular embodiments, the fastener has interference capability of 0.0005 to 0.0100 inches in composite structures without risk of composite delamination or damage. As a result of the fastener interference, gaps between the fastener and the structure are eliminated thereby providing good electrical conductivity between components. As a result, the potential for electrical sparks is reduced, providing a safer fastener for use with aerospace applications.

Multifunctional structures and methods of manufacturing multifunctional structures which function as both electronic devices and load-bearing elements are disclosed. The load-bearing elements are designed to have electronic functionality using electronics designed to be load-bearing. The method of manufacturing the multifunctional structure comprises forming an electronic element directly on at least one ply of arbitrarily shaped load-bearing material using conventional lithographic techniques and/or direct write fabrication techniques, and assembling at least two plies of arbitrarily shaped load-bearing material into a multifunctional structure. The multifunctional structure may be part of an aerospace structure, part of a land vehicle, pan of a watercraft or part of a spacecraft.

The invention provides a three-dimensional assembly process generation method and system for an aerospace product. The system comprises a three-dimensional manufacturing resource library building module, a three-dimensional assembly process design module, a three-dimensional assembly process simulation module and a three-dimensional assembly process release module, the three-dimensional manufacturing resource library building module is used for building a three-dimensional manufacturing resource library containing product, fixture, tool and auxiliary material information, the three-dimensional assembly process design module is used for decomposing process tasks and planning a process according to the built three-dimensional manufacturing resource library to form a process structure tree, the three-dimensional assembly process simulation module is used for building a virtual assembly environment and simulating and analyzing the assembly process according to a three-dimensional model, the assembly process and the process structure tree to form a three-dimensional assembly animation meeting actual assembly requirements, and the three-dimensional assembly process release module is used for integrating process design information and simulation information, forming a three-dimensional assembly process file and releasing the three-dimensional assembly process file to an assembly site. Accurate and visual three-dimensional visual means are provided for aerospace product assembly, so that the problem of information gaps among three-dimensional product design, three-dimensional process design and three-dimensional assembly site implementation in the prior art can be solved.

The invention relates to an autonomous integrated navigation system which belongs to the technical field of navigation systems. The SINS (Strapdown Inertial Navigation System)/SAR (Synthetic Aperture Radar)/CNS (Celestial Navigation System) integrated navigation system takes SINS as a main navigation system and SAR and CNS as aided navigation systems and is established by the following steps: firstly, designing SINS/SAR and SINS/CNS navigation sub-filters, calculating to obtain two groups of local optimal estimation values and local optimal error covariance matrixes of the integrated navigation system state, then transmitting the two groups of local optimal estimation values into a main filter by a federal filter technology for fusion to obtain an overall optimal estimation value and an overall optimal error covariance matrix, and finally, performing real-time correction on the error according to the overall optimal estimation value so as to obtain an optimal estimation fusion algorithm of the SINS/SAR/CNS integrated navigation system. The autonomous integrated navigation system, disclosed by the invention, is less in calculation amount and high in reliability, is applicable to aircrafts in near space, aircrafts flying back and forth in the aerospace, aircrafts for carrying ballistic missiles, orbit spacecrafts and the like, and has wide application prospect.

An aerospace hardware derelict item is salvaged in space, modified, and reused to provide manned facilities in orbit. The hardware packages added onto the salvaged discarded item enhances its value, and incorporates at least the subsystems required to effectively reuse portions of previously discarded launch vehicle components, and other derelict objects in space. The hardware, and technique used reduces the cost of launching comparable hardware to orbit, because of the reuse, and provides a human habitation in orbit. The salvaged items include the external tank of the space shuttle, other derelict orbital hardware, the add-on cargo pod in two forms, and the ability to convert the derelict into a cost effective reusable item. The salvaged hardware is initially capable of contributing mass, length, interior volume, strongback, rotational stability mass, interior pressurized volumes, artificial gravity, and stability with the addition of simple subsystems for salvage, and interior development packages.

A method of preparing a component (60) to be joined to another component (55). The method comprises growing an array of projections (56, 57) on a bond region of the component (55) in a series of layers, each layer being grown by directing energy and/or material from a head to selected parts of the bond region. The joint may be used to join a pair of structural components, for instance in an aerospace application. For instance the joint may be used to join a reinforcing plate, floating rib foot, or stringer to a panel such as a wing or fuselage cover. Alternatively the joint may be used to join adjacent layers in a laminate structure.

This invention relates to the design of a Modular Aerospace Plane (MAP) comprising a forward fuselage section, a main wing section, a tail section and wing attachments. Various sections can be integrated to offer a variety of aircraft characteristics, performance and missions. This modular design offers a new method of aircraft fabrication, maintenance, repair and ground handling to reduce costs for the manufacturers, owners and operators. The forward fuselage and tail sections may utilize a parachute device whereby these sections can separate in an emergency and safely lower the occupants to the ground.

The invention discloses a high-toughness aluminum lithium alloy and a preparation method thereof. The alloy comprises the following chemical components in percentage by weight: 3.2 to 4.2 percent of Cu, 0.7 to 1.8 percent of Li, 0.20 to 0.60 percent of Mn, 0.20 to 0.60 percent of Zn, 0.06 to 0.20 percent of Zr, 0.20 to 0.80 percent of Mg, 0.2 to 0.7 percent of Ag, less than or equal to 0.10 percent of Si, less than or equal to 0.10 percent of Fe, less than or equal to 0.12 percent of Ti, less than or equal to 0.15 percent of other impurities (single impurity is less than or equal to 0.05 percent) and the balance of Al. One or five of alloy elements Mn, Zn, Mg, Ag and Zr can be selectively added. Proportioning is performed according to the alloy components, the raw materials are melted, then furnace refining and standing are performed, and alloy ingots with required specifications are cast. The alloy ingots are preferably homogenized and then molded by any process of hot extruding, hot rolling and the like, and the alloy ingots thermally treated by the preferable process can be used for processing parts. The high-toughness aluminum lithium alloy material has uniform microscopic structure and stable performance, and is suitable for manufacturing thick plates and extruded materials. The ultimate tensile strength can reach over 510MPa, and meanwhile, the elongation rate is more than 8 percent and the KIc can reach over 30MPam1/2. The material product can be used for structural elements of the fields of aerospace, nuclear industry, traffic and transportation, sports goods, weapons and the like.

The present invention relates to a process for the manufacture of short or discontinuous lignocellulosic fibre in combination with synthetic fibre filled thermoplastic composites, in which the process consists of preferably, defiberization and dispersion of the cellulosic fibres in the thermoplastic matrix, further consolidation and dispersion of the blended thermoplastic composition, further blending of the same with inorganic fibres to get the moldable thermoplastic composition and further injection or compression or compression injection molded under high pressure ranging from 100 tones to 1000 tones and a temperature range from 170 to 210 degree centigrade into composite products. The said composites have a tensile strength of at least 75 MPa and a flexural strength of at least 125 MPa. The invention also relates to the use of the said composites in automotive, aerospace, furniture and other structural applications.

Disclosed is a TC4 titanium alloy laser selective melting material additive manufacturing and heat treatment method. According to parameters of a TC4 titanium alloy laser selective melting process, laser power ranges from 300 W to 325 W, the spot diameter ranges from 0.12 mm to 0.14 mm, scanning speed ranges from 500 mm/s to 1,200 m/s, and the thickness of a powder laying layer ranges from 0.03 mm to 0.04 mm. A dual annealing process is adopted in heat treatment of a forming component, a TC4 titanium alloy component is firstly put in a vacuum heat treatment furnace with the temperature of 780 DEG C to 820 DEG C, and temperature is reduced to room temperature in an air cooled manner after heat preservation is carried out for 1.5-2 h; and then the TC4 titanium alloy component is put in the vacuum heat treatment furnace with the temperature of 530 DEG C to 550 DEG C again, and temperature is reduced to room temperature in an air cooled manner again after heat preservation is carried out for 2-3 h. The strength of the TC4 titanium alloy component treated through the process exceeds 1,000 MPa, meanwhile, ductility is not smaller than 10%, and the TC4 titanium alloy component can meet the requirements of aerospace products for the strength and plasticity of TC4 titanium alloy key bearing structural components.

The invention discloses a space rolling bearing comprehensive performance experiment device, relates to an experiment device and provides an experiment device capable of accurately measuring axial and redial united loads of a space rolling bearing and basic data including friction moment, bearing temperature rise, vibration and the like under different rotation speed working conditions. The space rolling bearing comprehensive performance experiment device can simultaneously conduct axial force and radial force accurate load on a measured bearing through an axial loading device and a radial loading device. A three-axis acceleration sensor is used for measuring radial, axial and peripheral vibration situations of the measured bearing. A temperature sensor is used for measuring the temperature rise situation of the measured bearing. A pressure sensor is used for measuring the friction moment of the measured bearing. An annular pressure sensor is used for measuring axial force borne by the measured bearing. Weights are used for marking radial force borne by the measured bearing. The space rolling bearing comprehensive performance experiment device can evaluate the comprehensive performance of the space rolling bearing and provide key scientific technical basis and test platform support for development of high-end bearings in the aerospace field of our country.

Light-weight, heat-managing structures feature open-cell lattice, honeycomb, and/or corrugated (prismatic) arrangements in their substructures, combined with heat pipe/heat plate arrangements for managing heat to which the structures are subjected. The structures are well suited to aerospace applications and may be employed in the leading edge of wings or other airfoil-shaped components; gas turbine engine components; rocket nozzles; and other high-heat, high-stress environments.

The invention provides an integrated Phased Array (PhA) structural radar transducer, permanently bonded to a structure, that can provide reliable electromechanical connection with corresponding miniaturized electronic SHM device installed above it. The integrated PhA transducer consists of a set of aligned piezo-electric discs with wrap around electrodes for transceiving of elastic ultrasonic waves, plurality of electrical traces and contact pads, several layers of a flexible printed circuit board, electromagnetic shielding between channels and overall, one electromechanical multi-pinned connector and all that integrated into one small unit easy for surface installation by bonding and final application on real structures. The integrated PhA transducer, as a key component of SHM (Phased Array Monitoring for Enhanced Life Assessment) system, has two principal tasks to reliably transceive elastic waves and serve as a reliable sole carrier or support for associated sophisticated SHM electronic device attached above.

The invention provides an electromagnetic shielding conformal optical window with a longitude and latitude-shaped mesh structure, which belongs to the technical field of electromagnetic shielding of optical transparent pieces. The electromagnetic shielding conformal optical window comprises a conformal optical window and is characterized in that: (1) a longitude and latitude-shaped metal mesh is manufactured on the inner side surface of the conformal optical window shell; and the longitude and latitude-shaped metal mesh covers the whole inner side surface of the conformal optical window shell; or (2) a longitude and latitude-shaped metal mesh and a conformal optical window inner shell are manufactured on the inner surface of the conformal optical window shell from outside to inside in turn; the longitude and latitude-shaped metal mesh covers the whole inner surface of the conformal optical window shell and outer surface of the conformal optical window inner shell; the latitude-shaped metal mesh consists of metal longitudes and metal latitudes; the metal latitudes are uniformly arranged in an equivalent centre angle along a circumferential direction; the metal longitudes are arranged at equal intervals according to a metal mesh cycle along a generatrix direction; and the metal longitudes and the metal latitudes are electrically connected with one another. The electromagnetic shielding conformal optical window with the longitude and latitude-shaped mesh structure is suitable for electromagnetic shielding technology of military or civil conformal optical windows for remote measuring and sensing, medical diagnosis, secret communication, aerospace equipment and the like.

An aerospace vessel including a fuselage, a means for causing the fuselage to fly coupled to the fuselage, and an environmental control system within the fuselage. The environmental control system includes a duct made of closed cell thermoplastic foam, such as polyvinylidene fluoride foam.

The invention belongs to the fields of aerospace, low temperature refrigeration and heat pump air-conditioning and relates to an anti-icing and anti-frosting polyurethane coating and a preparation method thereof. The anti-icing and anti-frosting polyurethane coating has good film forming properties, low temperature resistance and high hydrophobicity. The preparation method comprises that based on weight parts of a fluorosiloxane-containing polyurethane resin, 20 to 45 parts by weight of the fluorosiloxane-containing polyurethane resin, 40 to 50 parts by weight of one or more organic solvents, 0.2 to 1 part by weight of one or more defoamers, 0.2 to 1 part by weight of one or more anti-settling agents and 0.3 to 1 part by weight of one or more flatting agents are mixed into a mixed solution; 3 to 10 parts by weight of one or more silane coupling agents, 1 to 10 parts by weight of nanoscale inorganic oxide particles and 5 to 10 parts by weight of titanium dioxide are added into the mixed solution; and the mixture is subjected to ball-milling to form the anti-icing and anti-frosting polyurethane coating. Through utilization of the fluorosiloxane-containing polyurethane resin, the anti-icing and anti-frosting polyurethane coating has good adhesion with a base and has good surface hydrophobicity.

Disclosed is a transparent, flame-retardant thermally-insulating, UV-blocking polymer composite film, comprising sequentially from the top: a flame retardant layer, a base layer, a thermal insulation layer, and a UV-blocking layer, having a total film thickness of 1um to 500um, visible light transmittance greater than 80%, UV light transmittance less than 1%, and near-infrared transmittance less than 10%. Also disclosed is a preparation method for the present transparent, flame retardant thermally-insulating, UV-blocking polymer composite film, the technical processes whereof are simple and easy to execute, involve low production costs, and are suitable for industrial mass production. The present transparent, flame retardant thermally-insulating, UV-blocking polymer composite film can be used on such transparent materials and items as glass, windows, protective films, containers and electronic components, and has applications in such fields as construction, transportation, electronics, aerospace and medicine.