33 results about "Aerospace systems" patented technology

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 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.

A launch vehicle having an annular outer element and related systems and methods are disclosed herein. An aerospace system according to certain embodiments includes a launch vehicle having a first end and a second end substantially opposite the first end, the launch vehicle extending along a vehicle axis between the first end and the second end and having The outer surface facing outward. The system also includes an annular element carried by the carrier vehicle, the annular element having radially spaced apart inwardly facing outer surfaces and extending at least partially circumferentially about the vehicle axis, the annular element having a A first edge face in a first direction of the axis and a second edge face facing in a second direction along the axis of the aircraft, the second direction being opposite to the first direction. A propulsion system may be carried by the launch vehicle and may have at least one nozzle positioned toward the first end of the vehicle for launching the vehicle.

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 C / C-SiC composite material of a sandwich structure and a preparation method thereof, belonging to the technical field of carbon fiber reinforced ceramic-based composite materials. The composite material is specifically as follows: a novel sandwich structure composite material of which the middle is provided with high-density C / C and two sides are respectively provided with C / C-SiC and C / SiC in symmetrical distribution is designed. The invention further discloses a novel process for rapidly preparing the C / C-SiC composite material of the sandwich structure. The material is low in density and excellent in oxidation resistance and high-temperature mechanical property. The process has the characteristics of short preparation cycle, low cost, low energy consumption andthe like. According to the implementation, the application range of the C / C-SiC composite material in an aerospace system can be widened.

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.

The invention provides a system-level reinforcement method and circuit for high-voltage diodes used in aerospace to resist single-event burning, aiming at realizing the high-voltage diode anti-single-event burning reinforcement design more simply and at low cost, and providing component protection for aerospace systems. This method is aimed at multiple high-voltage fast recovery rectifier diodes D used in aerospace systems. i , each high voltage fast recovery rectifier diode D i Replace it with at least two high-voltage fast-recovery rectifier diodes in series with the same specification; correspondingly, for the screen-grid power output rectifier filter circuit, the original high-voltage fast-recovery rectifier diode D 1 、D 2 、D 3 、D 4 Constitute a bridge rectifier circuit, high voltage fast recovery rectifier diode D 5 、D 6 As the clamping diode and the freewheeling diode in the CDD snubber network, they are replaced by at least two high-voltage fast-recovery rectifier diodes in series with the same specification. The invention has the advantages of simple and convenient realization, low process implementation difficulty, low cost and high application value.

The invention discloses a surface modification technology suitable for magnesium alloys used in components such as engine casings of aerospace systems, specifically: degreasing, pickling, surface conditioning, plasma surface ceramization, and two Sub-organic spraying, the emissivity of the finally obtained plasma oxidation ceramic layer / organic coating composite treatment film reaches 0.88, the corrosion current density decreases by 6 orders of magnitude, the wear weight loss rate decreases by 1 order of magnitude and the friction coefficient is doubled. In the present invention, the substrate is primed by using plasma oxidation technology to form a ceramic layer with good bonding force, corrosion resistance and wear resistance, which plays a supporting role for the organic coating; and the porous structure on the surface of the ceramic layer increases the size of the entire workpiece. The specific surface area improves the binding force of the organic coating. The black coating formed by organic spraying further improves the corrosion resistance of the workpiece, reduces the coefficient of friction, and meets the requirements of high emissivity.

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.