33 results about "Aerospace systems" patented technology

A system and method that determines whether a heat exchanger within a complex networked system is fouling is provided. The system and method includes training classifiers indicative of a plurality of fouling conditions associated with the heat exchanger and testing the classifiers with optimal sensor data from optimal sensors to determine whether the fouling is being experienced by the heat exchanger.

An aerospace system includes a leveling device defining two plane levels (yz-plane and xz-plane). The plane levels are included within an inertial measurement unit and each of the plane levels includes two capacitance controlled oscillators. Each of the capacitance controlled oscillators includes a quad capacitor bubble sensor.

The invention relates to a superconductive and energy-storage magnetic suspension flywheel with a high energy density, which can be used as energy storage equipment of electric power systems, vehicles and aviation and aerospace systems. The superconductive and energy-storage magnetic suspension flywheel mainly comprises a base, a sealing cover, a stator shaft mounting frame, a main shaft, an axial magnetic bearing, radial magnetic bearings, a motor, a wheel body assembly and a superconductive magnetic bearing, wherein the main shaft is fixed in the center of an inner cavity of the base through the stator shaft mounting frame; the axial magnetic bearing, the radial magnetic bearing, the motor, the radial magnetic bearing and the superconductive magnetic bearing are mounted from top to bottom; and the wheel body assembly is located in the center of the main shaft and is connected with the main shaft through the axial magnetic bearing and the radial magnetic bearings. All assemblies are reasonable and compact in layout, non-contact suspension of a flywheel wheel body is realized by using combined actions of the superconductive magnetic bearing and the common magnetic bearings, and the high energy density is realized by using high-speed rotation of the carbon fiber wheel body.

The invention discloses a novel composite film preparation method with high light transmittance and excellent electromagnetic shielding effectiveness, which comprises the following steps: step 1, substrate surface treatment; 2, preparation of silver nanowire and preparing silver nanowire dispersion; 3, preparation of a silver nanowire transparent conductive film by a wire rod scrape coating method; 4, acid treat that surface of the silver nanowire film; 5, firstly placement of the substrate obtained in the step 4 on a glue homogenizer, uniformly coating PEDOT: PSS on the surface of the substrate, post-treating the dried composite film with DBSA, and spin-washing and drying the DBSA on the surface of the composite film with deionized water for many times to obtain silver nanowires; and 5, wherein the silver nanowires are coated on the surface of the substrate uniformly with PEDOT: PSS, and the silver nanowires are deposited on the surface of the composite film; and the silver nanowiresare deposited on the surface of the composite film. (PEDOT: PSS) composite film. A silver nanowire is prepared by the method of the invention (PEDOT: PSS) composite film has the characteristics of high light transmittance, outstanding electromagnetic shielding effectiveness and good conformability, which solves the problems of electromagnetic compatibility and protection application of traditionalshielding materials in aerospace system.

The invention relates generally to a novel cooling system and fuel preheating system for use in an advanced, high speed aerospace vehicle. A hydrocarbon fluid, such as fuel is accelerated to supersonic conditions within a cooling channel located proximate a high-temperature flight surface. The hydrocarbon fuel absorbs a heat load as it passes through the cooling channel in the flight control surface prior to the fuel being directed into the aircraft engine.

The invention provides a device for mechanically controlling exposure time, which comprises a disc-like shutter with a fan-shaped hole, a direct current brushless motor for controlling the rotation of the disc-like shutter, and a control circuit for controlling the rotational speed of the direct current brushless motor, wherein the control circuit is used for computing the rotational speed of the direct current brushless motor according to the currently-required exposure time and the current position of the disc-like shutter, and controlling the direct current brushless motor to work at the rotational speed. The invention simultaneously provides a corresponding method for controlling the exposure time. The device and the method utilize a speed modulation and large-hole residing mode to realize the exposure time, and can realize 27 segments of exposure time, wherein the minimum accurate exposure time can reach 2 ms and the maximum accurate exposure time can be infinitely extended upwards, thus the dynamic range is wide; the consistency, the uniformity and the reliability are all good; the accuracy is high; and the device and the method can be applied to aerospace systems and ground systems.

A self-managing system that uses autonomy and autonomicity is provided with the self-* property of autopoiesis (self-creation). In the event of an agent in the system self-destructing, autopoiesis auto-generates a replacement. A self-esteem reward scheme is also provided and can be used for autonomic agents, based on their performance and trust. Art agent with greater self-esteem may clone at a greater rate compared to the rate of an agent with lower self-esteem. A self-managing system is provided for a high volume of distributed autonomic / self-managing mobile agents, and autonomic adhesion is used to attract similar agents together or to repel dissimilar agents from an event horizon. An apoptotic system is also provided that accords an “expiry date” to data and digital objects, for example, that are available on the internet, which finds usefulness not only in general but also for controlling the loaning and use of space scientific data.

The invention belongs to the technical field of aerospace system data communication. and discloses a configuration processing method of a data message in a 1553B bus BC mode based on a management table. The method comprises the following steps: a structure is defined to describe the use state of a message space, in the initialization process, a bus memory area is registered in a message managementtable, data transmission from a BC to an RT is managed based on the message management table, data transmission from the RT to the BC is managed based on the message management table, and the messagemanagement table is cancelled in data transmission dynamic management. According to the invention, the defects of a data message configuration processing method in a BC mode of the existing 1553B busare overcome; a method based on a management table is provided, a structure is designed to describe the state of a 1553B message space, the message management table is adopted to manage receiving andsending of data between a BC and an RT, and the problem of efficient message management in the process of processing a large number of messages at high frequency through a 1553B bus is solved.

An Intelligent Modular Aerospace System (IMAS) is a paradigm shift in the architecture, utility, efficiency, operation, test / checkout, qualification testing and adaptability of an aerospace application system that provides Time / Space / Position Information, Data Acquisition / Processing / Relay, Power Generation / Distribution, avionic solutions, navigation, and command / data handling. IMAS (10) as shown in FIG. 1 is comprised of open architecture stackable modules (12) which are interchangeable and connectable in any order, internally interconnected in a plug and play fashion with an internal raceway (14) containing an input access (16) and output access (18). The resultant IMAS is capable of ingesting any type of external power or data source such as GPS, IMU, communications, command functions and databases such as targeting information. IMAS output includes capabilities such navigation / control logic, avionics steering commands, autonomous flight and flight termination system commands, satellite inter-communications and power from within the modules.

The invention provides a reliability analyzing method of an initiating explosive device testing system, and relates to the field of quality detection of initiating explosive devices in aerospace systems. The reliability analyzing method comprises the following step ofproviding a reliability evaluation method based on a dynamic bayes network for the reliability of a flexible testing system of an initiating explosive device in an aerospace system. The aerospace-stage initiating explosive device has extreme requirements forthe reliability, and the reliability has to reach 100%. The quality of theinitiating explosive device is determined by adopting an ignition test, the initiating explosive device belongs to a disposable product, only a limited sampling ignition test is performed on each batch of initiating explosive devices to evaluate the overall quality characteristics of the initiating explosive device, and a testing system is an important guarantee to accurately evaluate the qualityreliability of the initiating explosive device. Since the varieties of theaerospace initiating explosive devices are large, and initiating explosive devices of different varieties are equipped with different testing instruments and different testing channels and have different parameter configurations. The reliability of the testing system is related to time and product task batches, a dynamic bayes network structure chart of the testing system is established by using the dynamic bayes network evaluation method, the timing sequence causality relationship between different time slices is combined with the causality relationship in time slices, and dynamic analysis and prediction are performed through quantitative reasoning.

The invention relates to a low-voltage direct-current constant-power load stabilization method dedicated for aviation. The low-voltage direct-current constant-power load of the aviation is taken as a control object, a double-closed-loop control structure is adopted, backward-stage capacitance energy (outer ring) and forward-stage inductance current (inner ring) are collected to design a method for directly injecting a duty cycle on the basis of the high-frequency component of filter inductance current, a capacitor with small voltage and weight can be used to make a system stable under the same constant-power load condition, and the requirements of light weight and small volume of an aerospace system can be favorably met. The low-voltage direct-current constant-power load stabilization method improves a stable situation of the system during constant-power load and inhibits system vibration. LC filter capacitance is obviously reduced, the requirements of light weight and small volume of the aerospace system can be met, the cruising ability of an airplane is improved, and the consumption of aviation fuel is lightened. The low-voltage direct-current constant-power load stabilization method is high in practical value.

The invention discloses a surface modification technique for magnesium alloy used for parts such as engine cases of aerospace systems. The surface modification technique specifically comprises the step of degreasing, pickling, surface conditioning, plasma surface ceramization and secondary organic spraying are sequentially conducted on the magnesium alloy; and the emissivity of a finally-obtainedplasma oxidized ceramic layer / organic coating composite treatment film reaches 0.88 and is reduced by six levels under the corrosion current density, the weight loss ratio caused by abrasion is reduced by one level, and the friction coefficient is reduced by one time. According to the surface modification technique for the magnesium alloy, the plasma oxidization technique is adopted for basic treatment of a matrix, so that the corrosion-resistant ceramic cylinder with good binding force is formed to support an organic coating; and the surface of the ceramic layer is of a porous structure, so that the specific surface area of a whole workpiece is enlarged, and the binding force of the organic coating is improved. Through the black coating formed through organic spraying, the corrosion resistance of the workpiece is further improved, the friction coefficient is decreased, and the using requirement for high emissivity is met.

The invention relates to a superconductive and energy-storage magnetic suspension flywheel with a high energy density, which can be used as energy storage equipment of electric power systems, vehicles and aviation and aerospace systems. The superconductive and energy-storage magnetic suspension flywheel mainly comprises a base, a sealing cover, a stator shaft mounting frame, a main shaft, an axial magnetic bearing, radial magnetic bearings, a motor, a wheel body assembly and a superconductive magnetic bearing, wherein the main shaft is fixed in the center of an inner cavity of the base through the stator shaft mounting frame; the axial magnetic bearing, the radial magnetic bearing, the motor, the radial magnetic bearing and the superconductive magnetic bearing are mounted from top to bottom; and the wheel body assembly is located in the center of the main shaft and is connected with the main shaft through the axial magnetic bearing and the radial magnetic bearings. All assemblies are reasonable and compact in layout, non-contact suspension of a flywheel wheel body is realized by using combined actions of the superconductive magnetic bearing and the common magnetic bearings, and the high energy density is realized by using high-speed rotation of the carbon fiber wheel body.

The invention provides an airflow-induced acoustic piezoelectric power generation forced vibration device, which comprises a vibration structure and a piezoelectric transducer, wherein the vibration structure comprises an air inlet, a nozzle and an acoustic pipe; the piezoelectric transducer is fixed at the bottom part of the acoustic pipe; one end of a housing and a plug form the air inlet; an inner hole of the nozzle is a variable-section contracting airway; the acoustic pipe and a piezoelectric plate are sequentially arranged at the other end of the housing and are fixedly connected with the housing through an outer end cover board; the piezoelectric plate is pressed at the tail end of the acoustic pipe; and a hollow cavity is reserved between the nozzle and the acoustic pipe. By the change characteristic generated by airflow after flowing through a pipeline and the characteristic of structure vibration caused by acoustic wave propagation in the hollow cavity and a pipe hole, the novel airflow-induced acoustic piezoelectric power generation forced vibration device free of a moving part provided by the invention comprises a forced vibrating mechanical system for mechanically self-modulating an airflow-excited fluid power sound source, meets the self-powered requirements of application systems in various fields of automobiles, unmanned vehicles, weapon application systems, aerospace systems, robots, urban or residential lighting and the like, improves clean renewable energy sources and has important theoretical value and guidance significance for engineering.

The invention provides an airflow-induced acoustic piezoelectric power generation forced vibration device, which comprises a vibration structure and a piezoelectric transducer, wherein the vibration structure comprises an air inlet, a nozzle and an acoustic pipe; the piezoelectric transducer is fixed at the bottom part of the acoustic pipe; one end of a housing and a plug form the air inlet; an inner hole of the nozzle is a variable-section contracting airway; the acoustic pipe and a piezoelectric plate are sequentially arranged at the other end of the housing and are fixedly connected with the housing through an outer end cover board; the piezoelectric plate is pressed at the tail end of the acoustic pipe; and a hollow cavity is reserved between the nozzle and the acoustic pipe. By the change characteristic generated by airflow after flowing through a pipeline and the characteristic of structure vibration caused by acoustic wave propagation in the hollow cavity and a pipe hole, the novel airflow-induced acoustic piezoelectric power generation forced vibration device free of a moving part provided by the invention comprises a forced vibrating mechanical system for mechanically self-modulating an airflow-excited fluid power sound source, meets the self-powered requirements of application systems in various fields of automobiles, unmanned vehicles, weapon application systems, aerospace systems, robots, urban or residential lighting and the like, improves clean renewable energy sources and has important theoretical value and guidance significance for engineering.

The invention discloses a metal bellows welding structure with long fatigue life. The metal bellows welding structure comprises metal bellows, a transition ring for fixing the metal bellows, compression rings for eliminating the contact gaps between the metal bellows and the transition ring and a screw for connecting the metal bellows, the transition ring and the compression rings, wherein one end of the metal bellows is provided with a stress release ring of a semicircular flanging structure, the transition ring is in assembling connection with the stress release ring and used for providing a support structure for the metal bellows and serves as the flanging female die of the stress release ring, and the two compression rings are matched during use and respectively connected with the stress release ring and the transition ring. The metal bellows welding structure has the advantages that the repeated discharge times of the metal bellows are increased, the work reliability of the metal bellows is increased, the application range of the metal bellows in aerospace systems is expanded, and the metal bellows welding structure is high in reliability, high in safety, long in fatigue life, widely applicable to military and civil fields with high repeated discharge times requirements, and the like.

The invention belongs to the field of hybrid integrated optical transmit-receive design, and discloses an optical transmit-receive circuit and an optical transmit-receive device. The optical transmit-receive circuit comprises a driver, a laser array, a detector array, a TIA amplifier, an MTFA jumper fiber and a control circuit; the driver is sequentially connected with the laser array, the MT-FA jumper fiber, the detector array and the TIA amplifier; the MT-FA jumper fiber is provided with a light receiving end and a light transmitting end, and the control circuit is connected with the driverand the amplifier; the optical transceiving device comprises an optical transceiving circuit, a high-speed differential line, and a bottom plate, a substrate, a frame and a cover plate which are sequentially connected from bottom to top. The adopted device is simple in structure, capable of being well compatible with a modern microelectronic process and a hybrid integration process, low in deviceand assembly cost, small in size, and capable of effectively replacing an existing electric transmission mode and being applied to broadband data and image transmission in radar and aerospace systems;the bottleneck problems of large signal capacity, large data transmission loss and the like in the system are solved.

The invention belongs to the field of manufacturing of rare earth permanent magnet materials, and particularly relates to a high-working temperature low-magnetic variation rare earth-cobalt permanentmagnet material and a preparation method. In order to solve the problems that in the prior art, the working temperature of a permanent magnet material is not higher than 500 DEG C, and practical application is influenced due to the fact that the permanent magnet material has a great magnetic performance difference under the room temperature working condition and the high temperature working condition, the rare earth-cobalt permanent magnet material is prepared from alloys including the A component and the B component, and the chemical formula of the material is A1-xBx, wherein in the chemicalformula, x=0-1; the chemical formula of the A component is Sm(Co1-u-v-wCuuFevZrw)Z, wherein in the chemical formula, Z-6.5-7.5, u=0.08-0.13, v=0.09-0.22, and w=0.027-0.033; and the chemical formula ofthe B component is HRE(Co1-u'-v'-w'Cuu'Fev'Zrw')Z', wherein in the chemical formula, HRE is one or more heavy rare earth elements in Gd, Er, Tb and Ho, Z'=6.8-7.8, u'=0.08-0.13, v'=0.09-0.22, and w'=0.027-0.033. The invention further provides the preparation method of the material. The material is applied to high-working temperature application occasions such as aviation and aerospace systems andthe like.

The invention discloses an oil well oil-gas-water three-phase gas lift production process simulation device, which includes an oil-water power system, an air power system, a plurality of simulated well shafts and a gas-liquid separation system. The oil-water power system includes a pure oil system, a pure water system, and an oil-water mixing system. Tank, oil-water steady flow system and liquid flowmeter calibration device; air power system includes cooling water system, air compressor, air steady flow system, air heating tank and gas flowmeter calibration device; simulated wellbore is set on the horizontal platform frame, horizontal The two ends of the platform are slidingly arranged on the horizontal track and the vertical track respectively, and the simulated shaft is provided with an oil-water inlet, a gas inlet and an oil-water-gas outlet. The invention can realize the real simulation of the fluid flow state in the actual oil and gas wellbore, provide basic test data for the gas lift production theory and technology, and has the advantages of simple principle, complete functions, convenient use, safety and reliability, and low cost.

Provided are methods and systems for a modular multi-stage aerospace system having a first-stage vehicle that lifts and accelerates and is capable of achieving velocities of Mach 2.5, the first-stage vehicle powered by at least one turbine engine, and capable of autonomous and remote control; and a second-stage atmospheric flight vehicle capable of velocities of Mach 5.0, the second-stage atmospheric flight vehicle powered by at least one hydrogen-fueled turboramjet engine, and capable of carrying an internal payload; wherein the first-stage vehicle is adapted to support the second-stage atmospheric flight vehicle, as the first-stage vehicle reaches velocities sufficient to launch the second-stage atmospheric flight vehicle, and the second-stage atmospheric flight vehicle is capable of travel 12,000 miles.

The invention belongs to the technical field of manned aerospace systems, and particularly relates to a circumferential illumination measurement system and a measurement method. The system comprises a control device, a linear servo system, a moving guide rail, a circumferential servo system, a circumferential slide rail, and an illumination measurement device. The circumferential slide rail is fixedly arranged on the moving guide rail, and the normal direction of the rotating surface of the circumferential slide rail is parallel to the linear motion direction of the moving guide rail; the illumination measurement device is fixedly arranged on the circumferential slide rail and is used for measuring illumination data of a measured light source; the circumferential slide rail rotates to drive the illumination measurement device to rotate; and the control device is used for collecting illumination data measured by the illumination measuring device and judging whether the illumination data is qualified or not. According to the measurement system and the measurement method provided by the invention, by adopting a mode of combining the linear servo system and the circumferential servo system, the position precision of illumination measurement is improved, and the measurement precision of the illumination is further increased.

The invention relates to a method for stabilizing an aviation-specific low-voltage direct current constant power load, which takes the aviation low-voltage direct current constant power load as the control object, adopts a double closed-loop control structure, and collects the capacitor energy of the rear stage (outer loop) and the inductor current of the front stage (inner loop) ), designed a method based on the direct injection of the high-frequency components of the filter inductor current into the duty cycle, so that under the same constant power load conditions, the system can be stabilized by using capacitors with smaller volume and weight, which can well meet the For the requirements of light weight and small volume of aerospace systems. The invention improves the stability of the system under constant power load and suppresses the vibration of the system. Significantly reducing the capacitance of the LC filter satisfies the requirements of light weight and small size of the aerospace system, increases the endurance of the aircraft and reduces the consumption of aviation fuel by the aircraft. It has strong practical value.

The invention discloses a novel composite film preparation method with high light transmittance and excellent electromagnetic shielding effectiveness, which comprises the following steps: step 1, substrate surface treatment; 2, preparation of silver nanowire and preparing silver nanowire dispersion; 3, preparation of a silver nanowire transparent conductive film by a wire rod scrape coating method; 4, acid treat that surface of the silver nanowire film; 5, firstly placement of the substrate obtained in the step 4 on a glue homogenizer, uniformly coating PEDOT: PSS on the surface of the substrate, post-treating the dried composite film with DBSA, and spin-washing and drying the DBSA on the surface of the composite film with deionized water for many times to obtain silver nanowires; and 5, wherein the silver nanowires are coated on the surface of the substrate uniformly with PEDOT: PSS, and the silver nanowires are deposited on the surface of the composite film; and the silver nanowiresare deposited on the surface of the composite film. (PEDOT: PSS) composite film. A silver nanowire is prepared by the method of the invention (PEDOT: PSS) composite film has the characteristics of high light transmittance, outstanding electromagnetic shielding effectiveness and good conformability, which solves the problems of electromagnetic compatibility and protection application of traditionalshielding materials in aerospace system.

The invention belongs to the field of hybrid integrated optical transceiver design, and discloses an optical transceiver circuit and an optical transceiver device. The optical transceiver circuit includes a driver, a laser array, a detector array, a TIA amplifier, an MT-FA fiber jumper, and a control circuit; the driver is sequentially connected Laser array, MT-FA fiber jumper, detector array and TIA amplifier, optical receiving end and optical transmitting end are set on MT-FA fiber jumper, control circuit is connected with driver and amplifier; optical transceiver device includes optical transceiver circuit, high-speed differential line And a base plate, a base plate, a frame and a cover plate which are sequentially connected from bottom to top. The structure of the device used is simple, and it can be better compatible with modern microelectronics technology and hybrid integration technology. The cost of devices and assembly is low, and the volume is small. It can effectively replace the existing electrical transmission mode and be applied to broadband data in radar and aerospace systems. And image transmission, and then solve the bottleneck problems such as large signal capacity and large data transmission loss in the system.