22 results about "Aerospace" patented technology

The invention relates to a phthalonitrile resin prepreg, a composite material and a preparation method of the composite material. A mode for pre-heat treatment of the phthalonitrile prepreg is adoptedfor controlling the viscosity state of the prepreg during solidification. At the same time, a segmented solidification process is adopted, after auxiliary materials are used for conducting vacuumingsolidification on a product at the temperature lower than or equal to 250 DEG C, post-treatment is conducted at the temperature higher than 300 DEG C without auxiliary materials, so that the limitations of the viscosity of the prepreg and the temperature resistance of the auxiliary materials to the molding process of the phthalonitrile composite material are overcome, and complex components of thephthalonitrile composite material with high temperature resistance, excellent mechanical properties and good molding quality can be industrially produced. The phthalonitrile resin prepreg with good processability, high molding quality, high temperature resistance and excellent mechanical properties is provided and can be widely used in aerospace engineering and ship engineering.

The invention relates to a periodic structure which is based on the local resonance band gap characteristic and has the low-frequency vibration suppression performance, and belongs to the technical field of aviation, aerospace and ship vibration noise control. The periodic structure comprises mass components, elastic components and a base body, and the mass components and the elastic components are periodically distributed. A periodic unit comprises metal structures, namely, the mass components. The side surface of each mass component is surrounded by a circle of rubber or silicone annular structure, namely, the corresponding elastic component. The side surface of the circumference of each mass component is a curved surface with a certain shape. Each elastic component is attached to the corresponding mass component and then surrounds the mass component to serve as a whole period to be arranged in the elastic structure base body. The elastic components are also attached to the base body. The periodic structure has the obvious band gap characteristic. The periodic structure based on the local resonance band gap characteristic has the good low-frequency vibration suppression performance.

A aerospace machine element product (1) to be managed comprises a plurality of assembled components (2) ((1) to (3)). Each of the plurality of components (2) ((1) to (3)) is manufactured through a material purchase process (S1), a forging process (S2), a heat treatment process (S3), a grinding process (S4), surface treatment process (S5), and inspection process (S6). The information of the processes (S1) to (S2) is recorded on an IC tag (4) together with the lot numbers of the processes. After the components (2) have been assembled in the aerospace machine element product (1), the recorded information regarding the components (2) on the IC tag (4) is recorded in a management computer system (11) so as to be related to a manufacturing number or a manufacturing lot number. Another IC tag (10) is attached to the aerospace machine element product (1) and the manufacturing number or the lot number is recorded on the IC tag (10). In addition, processing condition information about the forging, heat treatment, grinding, surface treatment processes is recorded on this IC tag (10).

The invention provides an assistant measurement tool and method for detecting intervals between installation holes of aerospace products. The assistant measurement tool comprises a detection substrate and locating blocks, wherein the detection substrate is provided with scales, and the locating blocks are installed on the detection substrate and used for locating the lengths of hole intervals. The detection substrate comprises two matrix type scale boards perpendicular to each other in direction. Each locating block comprises a locating bottom block and a locating rod. The locating rods are connected with the matrix type scale boards through the locating bottom blocks. The centers of the locating rods coincide with the centers of the locating bottom blocks. The assistant measurement tool and method for detecting intervals between installation holes of aerospace products can conveniently and rapidly detect whether the intervals of installation holes of aerospace products meet the requirement or not, can efficiently and rapidly detect the intervals of installation holes of aerospace products of different sizes, improves the detection efficiency, and is easy to operate and convenient to use.

The invention provides a full-automatic laser splice welding production line which is suitable for full-automatic laser splice welding production lines for the fields of automobile manufacturing, automobile parts machining, engineering machines, sheet-metal working, aerospace and the like. The full-automatic laser splice welding production line achieves the production purposes of automatic feeding, laser welding, weld joint following, weld joint quality detection, production screening and automatic discharging. The full-automatic laser splice welding production line comprises a full-automatic feeding system, an automatic welding system, an automatic discharging system and a control system. The automatic feeding system comprises a feeding robot and a workpiece conveying device (7). The automatic welding system comprises a laser generator, a transmission optical fiber, a laser welding head (10) and a welding head moving device. The automatic discharging system comprises a discharging robot. The control system is used for controlling the automatic feeding system, the automatic welding system and the automatic discharging system.

The invention discloses an environment-friendly polyethylene/polyamide laminated barrier material comprising the following components in parts by weight: 2-5 parts of carbon nano-tubes, 5-10 parts of ethylene-acrylate copolymers, 20-50 parts of polyamide, 20-30 parts of polyethylene, 1-3 parts of a catalyst, 2-5 parts of a stabilizer and 3-6 parts of a lubricating agent. The invention also discloses a preparation method of the laminated barrier material. The polyethylene/polyamide laminated barrier material disclosed by the invention is good in barrier property and compatibility, high in shock resistance and resistant to high temperature and is widely applied to the fields of aviation and aerospace.

Optimizing an "improper" combination, a combination consisting of an even plate or shell and a conceptually irregular set of reinforcing stiffeners, enables to attain said combination's hitherto unknown unique synergetic attribute, the attribute of total disappearance of local buckling phenomena of said combination when compressing thereof up to destruction of structural material(s) thereof, and therefore enables to utilize strength potentialities of the material per se utterly, just us utterly as when stretching thereof, and besides irrespective of plates/shells shape and size, irrespective of structural materials' kind, volume and weight, and irrespective of operational temperatures and type of external load distribution, etc. Accordingly, given equal other conditions, cardinal weight reduction or bearing capacity's raise of thin-walled structure's bearing skin is attainable that can be utilized for any aerospace thin-walled structure, very extensively in naval engineering, and in civil engineering sometimes also; besides a reduction of expenditures, more efficient utilization of energy resources and hence enhancement of the environment of mankind is provided too. I call said synergic attribute "Superstability".

The invention discloses a reusable two-stage injection aircraft with pneumatic combined structures connected in parallel, which comprises a booster-stage aircraft and a track-stage aircraft, a guide plane for mounting the track-stage aircraft is arranged on the upper surface of the booster-stage aircraft, and the guide plane is arranged along the length direction of booster-stage flight. And the guide plane is seamlessly attached to the lower surface of the orbit-level aircraft. According to the aerodynamic combined structure of the two-stage injection aircraft, the boosting-stage waverider base body and the orbit-stage waverider are constructed in a two-stage injection horizontal separation mode, and the aerodynamic layout of the deformable wings and the vertical tail rudder is added to the boosting-stage waverider base body, so that the aerodynamic combined structure of the two-stage injection aircraft has good wide-speed-range aerodynamic performance and stability performance; the technical risk of interstage separation is effectively reduced, and the method can be used as a scheme for transporting a reciprocating aircraft in the field of aerospace and can be repeatedly used.

The invention discloses an aerospace complex product production management method, which includes: sending inquiry information to a task executing end so as to make said task executing end return theproduction schedule of multiple sub-parts of a complex product; establishing a visual 3D model of the complex product based on the production schedule of multiple sub-parts and multi-sub-parts; presenting the visualized three-dimensional model to a user, and performing corresponding operation on the visualized three-dimensional model based on the operation instruction of the user. The invention also discloses an aerospace complex product production management system, a computer device and a computer readable medium. The invention can improve the overall control of the production process of theaerospace complex product, and improve the quality and production efficiency of the aerospace complex product.

The invention discloses an in-situ synthesized Cr3C2 reinforced Ni-based composite material and a hot-press preparation method thereof. Cr2AlC (10-40 vol%) ceramic powder and Ni powder are used as rawmaterials. Under high temperature environment, Cr2AlC dissociates, Al atoms diffuse with part of Cr atoms, in-situ synthesized Cr3C2 ceramic particles are evenly distributed in a matrix, meanwhile, Cr atoms and Al atoms are dissolved in a Ni matrix to form gamma-Ni, and when Cr, Al reaches a certain amount, a precipitated phase Ni3(Al,Cr), that is, a gamma'phase is precipitated out. The masses ofthe Cr2AlC powder and the Ni powder are calculated and weighed, after ball milling and mixing, the Cr2AlC powder and the Ni powder are poured into a hot-press mold for hot-pressing sintering, the sintering temperature is 1,200-1,400 DEG C, 25MPa pressure is applied when the temperature is 1,100-1,200 DEG C, the insulation and pressure maintaining is performed for 30min, pressure relief is performed after the temperature is lowered to 500-600 DEG C due to furnace cooling, a sample is taken up when the temperature is lowered to below 80 DEG C, and the in-situ synthesized Cr3C2 reinforced Ni-based composite material is obtained. The material has comprehensive properties such as high strength, high hardness, wear resistance, corrosion resistance and good high temperature performance, and canbe applied to aerospace, military industry, transportation and other fields.

The invention provides a moon precipice detection and sampling device and an application method thereof, belongs to the technical field of aerospace and in particular relates to the moon precipice detection and sampling device and the application method thereof, aiming at solving the problem that a moon soil sample in a deeper layer is difficult to obtain through an existing moon vertical drillingand sampling manner. The moon precipice detection and sampling device comprises a vehicle body, wheels, a drilling mechanism, a sweeping mechanism and a camera. The moon precipice detection and sampling device is mainly used for detection and sampling of a moon precipice.

The invention relates to a large load-bearing compressed shape-memory polymer composite material release mechanism for space, relating to a polymer composite material release mechanism. In order to solve the problem that the traditional release mechanism produces an impact during the space release process, and the explosion fragments are easy to damage the surrounding equipment. The invention includes a heating drive device and a main structure connector made of shape memory polymer composite material and a release mechanism connector; the main structure connector includes a flanged connection plate and an outer sleeve of the release mechanism; the release mechanism connector includes a connecting chassis and the inner sleeve of the release mechanism; the outer sleeve of the release mechanism is sleeved on the outside of the inner sleeve of the release mechanism, and an external force is applied to make the outer sleeve of the release mechanism and the inner sleeve of the release mechanism relatively fixed; the heating drive device is heated, and the shape memory polymer composite material The outer sleeve of the release mechanism made of high-quality material and the inner sleeve of the release mechanism return to the straight cylinder state after being heated, and are separated from each other to realize the release. The invention is applicable to the release field of aerospace equipment and the like.

The invention discloses a device for placing an optical communication module in an aerospace environment. The device comprises a hexahedron chassis, four surfaces of the hexahedron chassis are integrally formed, the other two surfaces are respectively an upper cover plate and a front panel, a support plate is arranged in the hexahedron chassis, and the support plate is parallel to a bottom plate in the hexahedron chassis. A wavelength division multiplexer and a wavelength division demultiplexer are fixed on the support plate, a group of mounting grooves are formed in a bottom plate in the hexahedron chassis, a heat dissipation boss is arranged beside the mounting grooves, a circuit board is arranged between the heat dissipation boss and the support plate, and a group of screw seats with internal threads are arranged at the periphery of the heat dissipation boss. A group of fixing holes corresponding to the screw seats are formed in the circuit board; and a group of connector mounting holes are further formed in one side plate of the hexahedral chassis. The device is low in cost and compact in structure, and can improve the heat dissipation effect of electronic components in the aerospace optical communication module.

The invention discloses a space six-degree-of-freedom non-contact vibration isolation platform for aerospace, comprising a base, a working platform, and first to fourth electromagnetic vibration isolators arranged between the base and the working platform; each The vibration isolators can achieve vibration isolation in the x and y directions in the plane. The four vibration isolators are evenly distributed on the four sides of the base. The platform has low natural frequencies in the six degrees of freedom, which can effectively suppress the vibration of the six degrees of freedom Low frequency micro vibration. The present invention is applicable to the vibration isolation of equipment in the field of aerospace precision instruments. When the platform base is disturbed and vibrations are generated in six degrees of freedom, these vibrations can only be transmitted to the precision load through the vibration isolation platform, while the platform Its own stiffness is extremely low, which greatly reduces the disturbance of precision loads.

The invention discloses an airplane capable of flying by rising balloons. Therefore, the aircraft is hoisted to the high altitude by the lifting balloon and then flies off; a runway or a warship catapult is replaced cheaply, easily and efficiently; small clamping plates of the small and medium-sized warship tail original take-off and landing helicopters can be easily modified to serve a fighter plane and even rarely influence original things; a mast, an early warning radar tower and the like can be easily replaced by the rising balloons, the rising balloons are connected with a long lifting rope and a long tying rope and respectively have swing rope functions similar to a simple pendulum, so that the airplane is separated from the lifting rope only when swinging to a proper degree; and thus enemy killing at a large height is achieved, birds and wind waves are avoided, and people can escape at more opportunities in case of danger. When the airplane is used, the vertical rod which swingshigh pulls and lifts the airplane to deviate and then starts a large engine to rush forwards, and can be separated from a lifting rope when exceeding the length of a common runway, so that discomfortof passengers caused by backward swinging is reduced; and the new aerospace craft or anti-missile aircraft that can not be launched easily can rise conveniently, an aircraft system can be matched andhung at the lower part of the aircraft, so that a novel, ingenious, light, small and efficient aircraft carrier or vehicle-towed airport with high-hanging early warning and self-defense capabilitiescan be derived.

Compared with a traditional FDD system measurement and control station, an uplink and downlink common-frequency aerospace ground measurement and control station disclosed by the invention has higher measurement and control spectrum efficiency and higher measurement precision. A first-stage interference suppression module is formed by four channels, and a second-stage interference suppression module formed by a sum channel, an azimuth difference channel and a pitch difference channel is arranged between a down-conversion module and a measurement and control baseband module; a time delay estimation module based on a spreading code is added in a second-stage interference suppression module so as to improve the synchronization precision between an interference reconstruction signal and a receiving signal; the antenna feed source adopts a transmitting and receiving feed source split antenna in which a transmitting feed source and a receiving feed source are separated, so that the isolation degree between transmitting and receiving signals is increased; a receiving and transmitting common-local-oscillator scheme is adopted, a unified local oscillator signal is distributed to the up-conversion module and the down-conversion module, it is guaranteed that reference signals and received self-interference have the same phase noise distribution, the self-interference cancellation efficiency is improved, and the technical difficulty of uplink and downlink common-frequency self-interference suppression is reduced.

The invention provides a non-acoustic voice information detection method, a service device and a readable storage medium. The detection method at least comprises the following steps of: acquiring a PPG signal, intercepting a motion artifact signal segment related to voice activity in the PPG signal, and detecting voice information from the signal segment. By adopting the non-acoustic voice information detection method, the service device and the readable storage medium based on the PPG signal, a user can interact with a machine or transmit voice information only by making a talking action without making a sound, so that the user experience comfort degree, the voice interaction privacy and the information detection accuracy under a strong noise environment can be greatly improved. Meanwhile, the method can be used for voice transmission and voice control scenes which lack transmission media, have high noise or have secret content, such as aerospace, military affairs, public security, fire fighting, disaster relief and the like, and noisy public places such as stations, shopping malls, bars and the like, and the method has extremely high application value.

The invention discloses a high-temperature-resistant high-strength aluminum alloy and a preparation method thereof. The high-temperature-resistant high-strength aluminum alloy comprises the followingcomponents in percentage by mass: 5-6% of Cu, 2-3% of Mg, 0.3-0.5% of Sc, 0.2-0.5% of Zr, less than 0.02% of impurity elements in total, and the balance Al. According to the high-temperature-resistanthigh-strength aluminum alloy and the preparation method, the rare earth aluminum alloy Al-Cu-Mg-Sc-Zr has good comprehensive mechanical properties; and after being subjected to solid solution treatment and aging treatment, the rare earth aluminum alloy has the characteristics of high strength, good plasticity and relatively stable performances, and can meet the application requirements of high-precision industries such as aerospace, military and automobiles.