155 results about "Astronautics" patented technology

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.

Disclosed is a stereo vision measuring device based on a binocular omni-directional vision sensor. Each ODVS composing the binocular omni-directional vision sensor adopts the design of mean angle resolution. The parameters of two image collection cameras are in complete accord and in possession of a pretty good symmetry, and can quickly realize the point-to-point matching. The device adopts a unified spherical coordinate in the process of data collection, processing, description and representation of space objects in terms of centering on human in visual space, and adopts the elements of distance sense, direction sense and color sense to express features of each characteristic point, thereby simplifying the complication of calculus, omitting the calibration of the cameras, facilitating the feature extraction and realizing the stereo image matching easily, finally realizing the purpose of high-effective, real-time, and accurate stereo vision measurement. The device can be applied in a plurality of fields of industrial detection, object identification, robot automatic guidance, astronautics, aeronautics, military affairs, etc.

The invention provides a control method and a control device used for micro-satellite cluster flying based on atmosphere resistance, and relates to the technical field of micro-aircraft and astronautics measuring and controlling. The signal output terminal of a GPS receiver is connected with the signal input terminal of a track determining device; the signal output terminals of a solar battery array and a three-axis magnetometer are connected with the input terminal of an attitude fusion filter; the output terminal of the three-axis magnetometer is connected with the input terminal of a pure magnetic measuring attitude fusion filter; the signal output terminal of the attitude fusion filter is connected with the second input terminal of a satellite line; the first output terminal of the satellite chain is connected with the input terminal of a cluster formation control law; the second output terminal of the satellite chain is connected with the input terminal of the satellite attitude control law; the formation and attitude of the satellite cluster flying are controlled by controlling a pneumatic plate. The method and the device achieve the objects of long service life of the aircraft, low power dissipation, low cost and no pollution on the basis of atmosphere resistance.

This invention relates to an ultra sparse water conductive fiber. The superficial gable is the fiber of electric conduction polymer which is composed by 20-1000 nanometers thick, diameter of 400-900 nanometer electric conduction high polymer. This fiber is for using electric conduction polymer chemical oxidation position polymerization method in fiber surface gable electric conduction polymer level. This invention also relates to a ultra sparse water electric conduction fabric, it for in the superficial gable a fabris composed of 20-1000 nanometers thick, by the diameter was the electric conduction polymer level fabric which 400-900 nanometer electric conduction high polymer particle. This fabric for use electric conduction polymer chemical oxidation home position polymerization method in fabric surface gable electric conduction polymer level. This invention's fiber or the fabric surface resistance for 200 omega /cm2-300M omega /cm2, the angel contact with water is bigger than 160degree, the roll position is smaller than 14degree. It displays highly clean ability, has the electromagnetic screen, the anti-static electricity, the stealth, the waterproofing, the dustproof function, specially for war industry, astronautics aviation, factory and mining enterprise, health and so on.

A non-scanning 3D imaging laser radar optical system based on an APD array is arranged in a shell of a laser radar system. The non-scanning 3D imaging laser radar optical system is composed of a laser, a Galilean telescope, an optical splitter, an emitting optical unit consisting of an emitting-receiving spectroscope and an emitting lens with the focal length of f1 and a receiving optical unit consisting of a receiving lens with the focal length of f2 and the emitting-receiving spectroscope; the inner wall of the tail part of the shell of the laser radar system is provided with the laser, the Galilean telescope is arranged in front of the laser, the optical splitter is arranged in front of the Galilean telescope, the emitting-receiving spectroscope is arranged in front of the optical splitter, is a plane mirror with a hole provided at the center thereof, is positioned between a light spot and the receiving lens with the focal length of f1 and placed at 45 degrees to an optical axis, a port on the shell of the laser radar system is provided with the receiving lens with the focal length of f2, the emitting lens is positioned in the hole at the center of the receiving lens, and the emitting-receiving spectroscope reflects beams at 90 degrees to a detector at a focal plane position of the receiving lens. The optical system has simple structure and high accuracy, and can be applicable to the fields of plotting, navigation and astronautics.

The invention relates to a halogen-free inflaming-retarding conductive PC resin composition, and a preparation method thereof. The composition is prepared from raw materials of, by weight: 40 to 95% of PC resin, 1 to 10% of an impact modifier, 2 to 15% pf a halogen-free inflaming retardant, 1 to 10% of an inflaming retardant synergist, 0.1 to 1.5% of an anti-dripping agent, 1 to 15% of a conductive material, 0.1 to 2% of a lubricant, and 0.1 to 1% of an anti-oxidant. PC resin is dried in an air dry oven at a temperature of 120 DEG C for 2 to 4 hours; raw materials weighed according to the weight ratio are mixed in a low-speed mixer for 3 to 5 minutes; the mixed raw material is added to a hopper of a twin screw extruder, and is fused, extruded, and granulated. According to the invention, excellent physical properties of PC resin are maintained, and the composite has good inflaming-retarding performance and conductivity. The halogen-free inflaming-retarding conductive PC resin composition can be widely applied in industries of automobiles, astronautics and aerospace, and electronics and electrics.

The invention provides a super-large-sized high-magnesium-content aluminum-alloy slab ingot of which the maximum thickness reaches 1,000mm, the maximum width reaches 2,670mm and the maximum length reaches 8,000mm, and a preparation method thereof. The slab ingot is prepared from the following ingredients in percentage by mass: lower than 0.35% of Si, lower than 0.35% of Fe, lower than 0.15% of Cu, 0.20-1.0% of Mn, 4.0-6.5% of Mg, lower than 0.25% of Cr, lower than 0.25% of Zn, lower than 0.15% of Ti, lower than 0.005% of B, Al and the like. According to the method provided by the invention, the casting stress of the slab ingot is eliminated, the microscopic structure of alloy is uniform, the crystal grain is fine, the cast ingot is flawless, and the mechanical properties of the cast ingot are good. After the large-sized slab ingot is subjected to homogenizing treatment, the slab ingot is divided into thick plates or ingot bars with the thickness of 10-1,000mm through machining, is applied to rolling, mold manufacturing and other machined parts and is extensively applied to the fields of tools/dies, traffic, transportation, aeronautics/astronautics, shipbuilding, vehicles and the like.

The invention discloses a pre-cooling air-breathing type variable cycle engine and relates to the reusable pre-cooling air-breathing type variable cycle engine applied to aeronautics and astronautics devices. The engine mainly consists of a pre-cooler, a turbine engine, a super combustion chamber and a super combustion ramjet engine, wherein the pre-cooler and the super combustion chamber form a subsonic combustion ramjet engine; a turbine subsonic combustion ramjet engine is connected with the super combustion ramjet engine in parallel; working states of the turbine subsonic combustion ramjet engine and the super combustion ramjet engine are selected by adjusting a switching adjusting device, so that the working modal of the whole engine is controlled. The pre-cooler can reduce an inlet gas flow temperature of a super combustion chamber, can increase the efficiency of the super combustion chamber, can expand the working range of a subsonic combustion punching modal, and can make up insufficient thrust force when turbine subsonic combustion ramjet engine is transferred to the super consumption ramjet engine, so that the pre-cooling air-breathing type variable cycle engine has the advantage that the transfer class of a combined engine is stably transferred.

The present invention belongs to the field of multi-variable system application technology. Via one set of simple and practical step response test, the distinction in powerfully coupled multi-variable system is amalyzed into the distinction in several single-in single-out systems so as to obtain precise transfer function model of the multi-variable system. Specially, the process includes four steps of initialization, step response test, synthesis of multi-variable process and parameter distinction in synthesized subprocess. The present invention can realize the real-time on-line distinction of the multi-variable system, and has less impact of step test signal required for system distinction on the normal operation of the control system and no special requirement of distinction algorithm in signal amplitude. The method of the present invention is suitable for industrial process control, robot, aeronautics, astronautics and other multi-variable systems.

The invention discloses an autonomous configuration method for an FPGA (field programmable gate array)-based embedded dual-core system, belongs to the field of embedded systems, and aims to solve the problem of incapability of a conventional FPGA-based embedded dual-core system in the autonomous storage and loading of a configuration file. The method comprises the following steps of enabling two PLBs (processor local buses) to share a FLASH memory by using a PLBv46BRIDGE IP core, designing a hardware structure of the dual-core system in Xilinx Platform Studio, generating a bit stream file, programming the bit stream file in the FLASH memory in Xilinx Software Development Kit, moving an executable file in the FLASH memory into an external memory for execution by using a bootstrapper after the system is powered on or reset, and stopping running the system until a stopping marker bit is discovered. The method can be used for aeronautics and astronautics, consumer electronics, communication, instruments and apparatuses, military equipment and industrial control.

The invention discloses a method for preparing a high-strength and high-conductivity copper-based alloy coating by means of laser-induction hybrid cladding, which is characterized by comprising the following steps of: firstly, performing chemical nickel-plating treatment on a special copper-based alloy powder to form a nickel-coated copper-based alloy powder with a core-shell structure; secondly, performing oil removal, rust removal, surface activation and chemical nickel-plating treatment on the surface of a matrix; and finally, preparing the high-conductivity copper-based alloy coating on the surface of the matrix by means of laser-induction hybrid cladding. The method disclosed by the invention has the advantages of being high in machining efficiency, low in cost, good in technical and economic benefits, and has a wide application prospect in the surface reinforcement and repair of fields of aeronautics, astronautics, automobile, metallurgy, electricity and the like, in which aluminium and aluminium alloy, magnesium and magnesium alloy, and copper and copper alloy are widely used.

The invention discloses a cross-correlation eddy current thermal imaging defect detection and tomography method and a cross-correlation eddy current thermal imaging defect detection system. The system can work in the pulse mode, phase-lock mode, frequency modulating mode, phase modulating mode and other modes to generate different modulation signals, a high-frequency AC signal is modulated to generate different excitation signals so as to realize induction heating of a detected object, and at the same time, the time-dependent temperature information on the surface of the detected object is recorded to serve as detection data. A specific signal is adopted or is generated to serve as a reference signal, and the detection data and the reference signal are subjected to cross-correlation algorithm to realize pulse compression so as to obtain matching information such as phase coincidence, orthogonality, amplitude value and phase position of the detection data and the reference signal at different moments. Characteristic values are extracted from the matching information, the detection signal-to-noise ratio is enhanced, the internal defect detection capability is improved, change of surface emissivity is inhibited, and tomography of the detected object is realized. The method and the system can be applied to equipment nondestructive detection, material representation evaluation, product quality control and structural health monitoring in the fields of aeronautics and astronautics, new materials, petrochemical engineering, nuclear power, railways, automobiles, special equipment, machinery, metallurgy, civil construction and the like.

The invention relates to a non-cooperative target docking mechanism with a peripheral swing-rod-type expansion joint, which aims to solve the problems of the complex structure, large size, heavy weight, and limitation on the application in the missions of 'GEO (geostationary orbit) protection' and 'in-orbit maintenance' of the present non-cooperative target docking mechanism. The mechanism realizes the rotation around a rotary shaft via the contact and the interaction of a swing rod, a slide surface and a conical inclined surface to finish the expansion and folding functions of a swing rod and realize docking and docking unlocking. An expansion mechanism is used for docking a throat structure of the inner surface of a spray tube, and after the swing rod is expanded, the docking rigidity is ensured by virtue of the compression surfaces of a locking slider and a shell, thereby realizing a docking function. The mechanism performs stepping by virtue of the expansion of the swing rod caused by a return spring and the locking movement of the locking slider, so that the control on the locking movement is simple. The mechanism disclosed by the invention is used for the field of aeronautics and astronautics.

The invention relates to a wireless passive high-temperature pressure sensor, in particular to a wireless passive high-temperature pressure sensor with temperature compensation and a temperature compensation algorithm thereof. The invention solves the problem that the conventional wireless passive high-temperature pressure sensor cannot measure pressure under the environment in which temperature constantly changes. The wireless passive high-temperature pressure sensor with temperature compensation comprises a first green ceramic plate, a second green ceramic plate, a third green ceramic plate, a fourth green ceramic plate and a fifth green ceramic plate; a lower polar plate of a first flat capacitor is arranged on the left part of the top surface of the first green ceramic plate; a lower polar plate of a second flat capacitor is arranged on the right part of the top surface of the first green ceramic plate; a first induction coil and the first flat capacitor are jointly formed into a temperature-compensating sensitive LC loop; a second induction coil and the second flat capacitor are jointly formed into a main sensitive LC loop. The invention is applicable to pressure measurement under high-temperature environments in the fields of automation, astronautics, aeronautics and national defense industry.

The invention discloses a preparation method for a perfluor polyether oil-based magnetic liquid. The magnetic liquid is formed by bare Fe[3]O[4] magnetic nano-particles, a perfluor polyether carboxylic acid surface active agent and a perfluor polyether oil-based carrier liquid in a prepared mode. The bare Fe[3]O[4] nano-particles with the average particle diameter of 10 nanometers are firstly prepared by the adoption of a chemical coprecipitation method; the perfluor polyether carboxylic acid surface active agent is then adopted for modifying the bare Fe[3]O[4] nano-particles; finally, the modified Fe[3]O[4] magnetic nano-particles and the perfluor polyether oil-based carrier liquid are blended through a high-energy ball milling or ultrasonic shaking method to form the uniform and stable perfluor polyether oil-based magnetic liquid, and the saturation magnetization of the perfluor polyether oil-based magnetic liquid is 14-600 Gs. The magnetic liquid has the excellent special performance of resisting to chemical corrosion, high temperature, low temperature resistance and radiation and never burning, can work stably for a long time at the temperature of 40 DEG C below zero-200 DEG C at the pH value of 1-14, and is particularly suitable for space stations, aeronautics and astronautics and other military industry fields.

The invention discloses polyimide with low dielectric properties, and a preparation method and an application thereof. The polyimide provided by the invention is prepared through an imidization method by using the raw materials of aromatic diamine comprising triphenylamine and with large side group comprising triphenylethylene/tetraphenylethylene, and various tetra-dianhydrides. The polyimide provided by the invention has ultra-low dielectric constant, relatively low dielectric loss, excellent solubility, relatively high glass transition temperature, relatively high thermal stability, excellent mechanical performances, excellent photo-luminescent performance, and the like. The synthesis method of the polyimide is simple and diverse, and is suitable for industrial productions. The polyimide provided by the invention can be used for preparing low dielectric materials, and can be widely applied in high-tech industry fields such as electronics, microelectronics, information, luminescent materials, aeronautics and astronautics, and specially very large scale integrated circuits.

The invention discloses a numerically controlled method for adjusting the forming die of a bent pipe with thin wall. The forming die of the bent pipe comprises a bending die (1) fixed and coupled with a machine tool, a lock block (2), a fixture block (3), a mandrel (5) and a crease resistant block (4) with six degrees of freedom. The method for adjusting the forming die gradually adjusts and installs the die according to the destructiveness of each defect of the bent pipe and the effect of forming parameters on each quality parameter so as to acquire the qualified bent pipe which does not crease and has thinned wall and section distortion satisfying the requirements. The method can ensure the smooth process of the bending forming experiment of pipes with thin wall, and is used for guiding the forming of the bend of the pipe with thin wall and small bending radius in practical engineering, so as to reduce the die adjusting times, lower the production cost and satisfy the requirements of high-tech industries such as aeronautics and astronautics and the like.

The invention relates to the technical field of aeronautics and astronautics, and discloses a different-body isomorphic connection and separation device and system. The different-body isomorphic connection and separation device comprises a driving assembly, a connection and separation executing assembly and a supporting assembly, wherein the driving assembly and the connection and separation executing assembly are arranged through the supporting assembly in a supported mode; and the connection and separation executing assembly comprises a sliding pin, a fixed guide ring, a coupling ring, a driving ring, a bolt driving ring and a bolt ring, wherein the fixed guide ring, the coupling ring, the driving ring, the bolt driving ring and the bolt ring are sequentially arranged from inside to outside in a sleeved mode. The different-body isomorphic connection and separation device and system have universality, the child-mother docking of tiny modular satellites can be realized, the child-childdocking and mother-child docking can be further realized, and the docking reconfigurability and expandability among the multiple tiny modular satellites are increased.

The invention discloses a free-form surface imaging optical system. The free-form surface imaging optical system comprises a first reflector, a second reflector, a third reflector, a fourth reflector, an aperture diaphragm and a detector. A target is irradiated on the second reflector after being reflected by the first reflector, is irradiated on the third reflector after being reflected by the second reflector, is irradiated on the fourth reflector after being reflected by the third reflector, and finally is irradiated on the image plane of the detector after being reflected by the fourth reflector. The aperture diaphragm coincides with the third reflector in position. The first reflector is a long-strip-shaped spherical reflector of which the focal power is negative. The second reflector is a free-form surface reflector of which the focal power is positive. The third reflector is a free-form surface reflector of which the focal power is negative. The fourth reflector is a free-form surface reflector of which the focal power is positive. A camera with the free-form surface imaging optical system adopted is huge in view field and small in distortion, and can achieve multi-spectrum imaging. The free-form surface imaging optical system can be applied to the field of aeronautics and astronautics photo-electronic imaging.

The invention relates to a multi-degree-of-freedom bionic piezoelectric driver, which belongs to the field of precision machining. The multi-degree-of-freedom bionic piezoelectric driver comprises a case, a stator and a rotor, and is based on a stepping operation mode, the stator does not have embedded elements, and by utilizing the combined action of the forward thrust of piezoelectric stacks and the backward resilient force of flexible hinges, the multi-degree-of-freedom bionic piezoelectric driver realizes the forward and backward motion and axial linear motion of the rotor of the driver. In addition, in terms of the tests of micro-characteristics of materials, the driver can simultaneously carry out the nano-level elongation and torsion tests of fine materials. Based on inchworm type piezoelectric drive, the multi-degree-of-freedom bionic piezoelectric driver has high-precision positioning and repetitive positioning capability, and can be applied in the fields of ultraprecision machining machine tools, the testing of nano mechanical properties of material test specimens, microelectromechanical systems, precision optics, aeronautics and astronautics, robots and the like. The driving precision of ordinary drivers can be greatly increased, and the multi-degree-of-freedom bionic piezoelectric driver has the advantages of high displacement control precision, quick response, high driving force, low driving power, wide operating frequency, low cost, little investment, quick return, high benefit and the like.

The invention relates to a misaligned spline vibration wear experimental device and belongs to the aeronautics and astronautics vibration field. The misaligned spline vibration wear experimental device is characterized in that the misaligned spline vibration wear experimental device is composed of temperature sensors, constant-temperature covers, ball bearings, vibration displacement sensors, wheel discs, a rotor 1, bearing seats, grease collecting covers, spline jackets, splines, a rotor 2, double-row bearings, a motor, a frequency converter, a synchronizing belt, a synchronizing wheel, a driven wheel, a preamplifier, a signal acquisition device, an industrial personal computer, a rotor 3, a rotation speed sensor, electric heating wires, bearing elevation adjusting devices, an integrated bearing seat, a basic platform, infrared thermometers, flexible couplings and magnetic powder brakes. The misaligned spline vibration wear experimental device of the invention has a spline comprehensive condition contrast test function, a spline lubricating oil temperature and temperature rise research function, a spline/bearing misalignment research function, a spline engaging torque loading function and a comprehensive data online monitoring function. The misaligned spline vibration wear experimental device is advantageous in multiple experiment functions, strong comparability, excellent repeatability, stable operation, convenience in assembly and disassembly.

The invention belongs to the field of metal amorphous composite materials, and discloses amorphous composite materials, and a preparation method and applications thereof. The amorphous composite materials comprise nickel, zirconium, titanium, niobium, aluminum and copper with a nickel-based amorphous phase as a matrix phase and beta-Ti and (Cu,Ni) Ti2 as reinforcing phases, and comprise the specific components according to the atomic percentage: 30-59 at.% of Ni, 10-24 at.% of Zr, 10-35 at.% of Ti, 7-10 at.% of Nb, 3-7 at.% of Al, 1-3 at.% of Cu, and the balance being inevitable trace impurities. The amorphous composite materials are prepared by rapidly sintering a nickel-based amorphous powder and a titanium-based amorphous powder. With control of the addition amount of the nickel-based amorphous powder, the amorphous composite materials with different amorphous phase content can be obtained. The amorphous composite materials are nearly fully dense, and can be applied in the fields of aeronautics and astronautics, military industry and the like.

The invention relates to a calibration method of a quartz crystal microbalance, belonging to the technical field of aeronautics and astronautics. The method comprises depositing heavy metal gold at the surface of the quartz crystal microbalance by using a magnetron sputtering device; injecting an inert gas in a vacuum system; observing and recording the vacuum degree of a vacuum chamber; monitoring and storing the frequency value and the temperature value of the quartz crystal microbalance; monitoring and storing the S polarized light current and P polarized light current of ellipsometry system, and finally closing the testing system, closing the gas charging system of inert gas, and closing the vacuum system. The method improves the sensibility of precision measurement of the quartz crystal microbalance; the test procedure is stable and reliable, and has good replicability; an ellipsometry film thickness measuring apparatus is used for providing direct film thickness measuring method for the quartz crystal microbalance; and the method has high measuring accuracy, stable test procedure and good replicability.