8342 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.

The heat insulating composite aerogel material consists of silica aerogel, titania as infrared opacifier and reinforcing fiber in the weight ratio of 1 to 0.1-0.7 to 0.7-3. Its preparation process includes compounding sol with silanolate, surface modifier, titanolate, alcohol solvent, acid catalyst and alkaline catalyst in certain proportion; soaking fiber felt or prefabricated fiber part in the sol; and supercritical fluid drying. The material of the present invention has high blocking effect on solid heat transfer, air heat transfer and infrared radiation heat transfer, excellent hydrophobicity, simple preparation process, low cost, mechanical strength over 2 MPa, and wide application range, and may be used in strict heat protection condition in aeronautics, astronautics, military and civil uses.

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.

The present invention provides a coating inorganic fiber toughened MAX phase ceramic composite material and a preparation method thereof. The composite material adopts a MAX phase ceramic material as a matrix and adopts coating inorganic fibers as a toughening phase, wherein the coating inorganic fiber content is 0.5-90% (by volume), and the coating inorganic fibers are completely dispersed in the matrix and are inorganic fibers with the surface coated with the coating. Compared with the composite material in the prior art, the composite material of the present invention has the following characteristics that: the interface reaction between the inorganic fibers and the MAX phase ceramic can be effectively inhibited, the thermal expansion coefficient and elasticity modulus matching degree between the inorganic fibers and the MAX phase ceramic can be effective regulated, the effective improvement of the fracture toughness and the high temperature resistance of the MAX phase ceramic composite material can be achieved, the problems of high brittleness and insufficient use reliability of the MAX phase ceramic can be fundamentally solved, and the coating inorganic fiber toughened MAX phase ceramic composite material has potential application prospects in the high technology fields of civil use, aviation, aerospace, nuclear industry and the like, and is especially for the fission and fusion reactor nuclear power plant inner wall structure material.

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.

A 7XXX series aluminum alloy having reduced quench sensitivity suitable for use in aerospace structural components, such as integral wing spars, ribs, extrusions and forgings comprises, in weight %: 6 to 10 Zn, 1.3 to 1.9 Mg, 1.4 to 2.2 Cu, wherein Mg<=Cu+0.3, one or more of 0 to 0.4 Zr, up to 0.4 Sc, up to 0.2 Hf, up to 0.4 Cr, up to 1.0 Mn and the balance Al plus incidental additions including Si, Fe, Ti and the like plus impurities. By controlling the Mg content to 1.3 to 1.7 wt. %, limiting Mg<=Cu+0.3 and 6.5<=Zn<=8.5, the alloy provides significantly improved combined strength and fracture toughness in heavy gauges. For example, in a six-inch thick plate there is provided a combination of about 75 ksi quarter-plane tensile yield strength (L) with a fracture toughness (L-T) of about 33 ksi{square root}in which progresses by artificial aging/tempering to a combined strength and fracture toughness of about 67 ksi tensile yield strength (L) and a fracture toughness (L-T) of about 40 ksi{square root}in. The alloy product possesses equally attractive combinations of strength and fracture toughness when intentionally quenched slowly following solution heat treatment so as to lessen dimensional distortion, particularly in shapes of varying cross section.

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.