73results about How to "Increase functional density" patented technology

Devices utilize elements carried by a fluid in a microchannel toswitch, attenuate, shutter, filter, or phase shift optical signals. In certain embodiments, a microchannel carries a gaseous or liquid slug that interacts with at least a portion of the optical power of an optical signal traveling through a waveguide. The microchannel may form part of the cladding of the waveguide, part of the core and the cladding, or part of the core only. The microchannel may also have ends or may be configured as a loop or continuous channel. The fluid devices may be self-latching or may be semi-latching. The fluid in the microchannel is moved using e.g., e.g., electrocapillarity, differential-pressure electrocapillarity, electrowetting, continuous electrowetting, electrophoresis, electroosmosis, dielectrophoresis, electro-hydrodynamic electrohydrodynamic pumping, magneto-hydrodynamic magnetohydrodynamic pumping, thermocapillarity, thermal expansion, dielectric pumping, and / or variable dielectric pumping.

The invention discloses a satellite and launch vehicle integrated aerospace system, and relates to a satellite and rocket integrated aerospace system. The system aims to solve the problems that a small satellite is difficult to flexibly adapt to the requirements of different loads of emergency disaster monitoring and that the maximum capability of a small space launch vehicle is restricted in terms of the orbit injection quality of the launched satellite. The system comprises a mission payload bay and a launch vehicle. A high-resolution camera and a data measurement and control module are arranged in the mission payload bay. The launch vehicle comprises a first-stage launch rocket, a second-stage launch rocket and a third-stage launch rocket. The system further comprises a shared service capsule and a controller area network (CAN) bus. A data acquisition and control instruction module, a propelling module, a posture and orbit control module, a power module, an apparatus mounting module and a thermal control module are arranged in the shared service capsule. The data acquisition and control instruction module controls the mission payload bay and the launch vehicle through the CAN bus. The system is applied in the field of aerospace.

Provided is a semiconductor device and methods of forming the same. The semiconductor device includes a substrate having source / drain regions and a channel region between the source / drain regions; a gate structure over the substrate and adjacent to the channel region; source / drain contacts over the source / drain regions and electrically connecting to the source / drain regions; and a contact protection layer over the source / drain contacts. The gate structure includes a gate stack and a spacer. A top surface of the source / drain contacts is lower than a top surface of the spacer, which is substantially co-planar with a top surface of the contact protection layer. The contact protection layer prevents accidental shorts between the gate stack and the source / drain regions when gate vias are formed over the gate stack. Therefore, gate vias may be formed over any portion of the gate stack, even in areas that overlap the channel region from a top view.

The invention discloses an intelligent thermal control device. The intelligent thermal control device adopts the multi-layer composite structure comprising a reflecting layer, a dielectric layer, a phase change layer and an absorptivity adjusting and controlling layer sequentially from bottom to top; and the multi-layer composite structure is located on a base layer. A preparation method of the intelligent thermal control device includes steps as follows: (1) the reflecting layer is prepared on a base with the physical vapor deposition method; (2) the dielectric layer is prepared on the surface of the reflecting layer with the physical vapor deposition method; (3) the vanadium dioxide thin-film phase change layer is prepared on the surface of the dielectric layer with the magnetron sputtering method; (4) the phase change layer is covered with the absorptivity adjusting and controlling layer, and then the intelligent thermal control device is obtained. The prepared intelligent thermal control device has the large emissivity change range and has the good temperature adjusting and controlling effects, the corresponding high emissivity at the high temperature is higher than 0.8, the area of the thermal control device is reduced favorably, and the function density is increased; and meanwhile, the sunlight absorptivity is lower than 0.3, the intelligent adjusting ability of the device can be guaranteed, and the actual demand for thermal control of a space vehicle can be basically satisfied.

The invention discloses a braking sail derailment device for a cube satellite. The braking sail derailment device comprises a locking device, a storage mechanism, a mounting panel, a conical spring, an unfolding mechanism and a diaphragm sail. The locking device is fixed on the top face of the mounting panel. The storage mechanism is fixed on the bottom face of the mounting panel. The conical spring, the unfolding mechanism and the diaphragm sail are arranged in the storage mechanism. The large-diameter end of the conical spring is fixedly connected with the mounting panel, and the small-diameter end of the conical spring is fixedly connected with the unfolding mechanism. The diaphragm sail is tied to the unfolding mechanism. The braking sail derailment device is fixedly connected to the bottom of the satellite through the mounting panel at the top, so that the space inside the satellite is not occupied. After receiving a command from the ground, the locking device releases a central shaft in the unfolding mechanism, and a strap elastic mast wound on the central shaft drives the diaphragm sail fixed on the mast to be unfolded by releasing elastic potential stored in the mast. According to the invention, the diaphragm sail is unfolded to increase the cross-sectional area in the flight direction of the cube satellite, and the atmospheric resistance of the cube satellite is increased, so that the cube satellite derails quickly.

The invention discloses a cubesat brake sail de-orbit device. The cubesat brake sail de-orbit device is composed of two completely identical cubesat brake sail de-orbit sub-devices. Each cubesat brake sail de-orbit sub-device comprises a de-orbit device body and a partition board arranged on the top of the de-orbit device body, wherein the de-orbit device body is of a central symmetry structure and comprises a main frame, an upper end cover, a sail storage chamber guide rail, a Hall sensor, a base plate and two expanding mechanisms, the main frame is Z-shaped, the main frame is divided into two identical chambers with the center of the main frame as the symmetry center, and the two expanding mechanisms are arranged in the two chambers respectively. Four film sails are expanded in four directions by means of tape spring masts to increase the normal sectional area of satellite movement, so as to successfully solve the problem that a cubesat stays on the original track for a long time after fulfilling a task and becomes space debris.

The invention discloses a deorbiting device for a micro / nano satellite. The deorbiting device for the micro / nano satellite comprises a sail storing device, a sail unfolding device and an unlocking device, wherein the sail unfolding device is of a centrosymmetric structure, and comprises an upper end cover, a lower end cover, a clack-shaped central shaft, two ring flanges, two strip elastic masts, four supporting prisms, four pairs of pilot sleeves, four hold-down mechanisms and four leaf springs. After a ground command is received, the unlocking device releases the clack-shaped central shaft of the sail unfolding device; the strip elastic masts wound on the clack-shaped central shaft drive a thin-film sail, which is stored in a sail storing chamber, to unfold through releasing elastic potential energy stored by the strip elastic masts. According to the deorbiting device for the micro / nano satellite, the normal sectional area, in which a satellite moves, is increased by utilizing the unfolding of the thin-film sail, the effect of atmospheric drag perturbation on the micro / nano satellite is enhanced, and thus, the passive deorbiting of the micro / nano satellite is prompted.

The embodiments of the invention disclose a navigation apparatus and a method for the surface inspection of a spacecraft and relates to the technical field of the aerospace on-orbit-servicing technology, wherein the relative navigation of an inspection device and the surface structure detection of a target spacecraft are multiplexed. According to the invention, the orbital coordinate system of the target spacecraft is adopted as a navigation coordinate system. The acceleration and angular velocity information outputted by an inertial measurement unit is adopted for the pure inertial navigation integral calculation, so that the navigation parameters of the target spacecraft relative to the navigation coordinate system, including the attitude, the position, the speed and the like, are calculated. Moreover, the point cloud data of the profile of the spacecraft are measured based on the triangle method. The obtained point cloud data of the profile of the spacecraft are converted to be data in a geodetic coordinate system based on the short-time and high-accuracy features of the inertial navigation and the installation parameters of a linear laser triangulation survey meter. In addition, the known structural data of the profile of the target spacecraft is rectified according to the actually measured point cloud data of the profile of the spacecraft, so that the attitude and the position of the inspection device relative to the navigation coordinate system are calculated. Meanwhile, the attitude and the position, measured by a Kalman filter, are integrated with the navigation information calculated by the inertial navigation system. As a result, accurate navigation parameters can be obtained.

The present invention provides a single-Board satellite borne integrated electronic system. The single-Board satellite borne integrated electronic system comprises a refresh arbitration module, a data processing module, a satellite service interface module, a satellite service CPU module and an inter-board connector; the refresh arbitration module is connected with a first external device and a second external device through the inter-board connector so as to receive stored data and telemetry data; the data processing module is connected with a third external device through the inter-board connector so as to receive remote control commands; the satellite service interface module is connected with a fourth external device through the inter-board connector so as to receive satellite service data; and the satellite service CPU module is connected with the refresh arbitration module, the data processing module and the satellite service interface module through the inter-board connector so as to receive satellite service data, remote control commands and telemetry data. The system of the present invention has the advantages of high expansibility and high integration.

A coupler-multiplexer permutation switch (CMPS) integrates multiplexng and switching functions on a single substrate. It has a single-mode / multi-mode backward coupler followed by a digital optical switch (DOS). In the CMPS, the single-mode waveguide channels are phase-matched through a grating with the corresponding, backward-propagating modes of a multi-mode waveguide. The different modes are subsequently separated in a digital optical switch. Different permutations are obtained by electronically controlling an effective-index distribution of DOS output waveguides.

The invention provides an FPGA-based embedded dual-core relay protecting system. The FPGA-based embedded dual-core relay protecting system comprises a first NIOS II soft-core processor, a second NIOS II soft-core processor, an Avalon bus module and a mailbox module. The mailbox module is connected with the first NIOS II soft-core processor, the second NIOS II soft-core processor and the Avalon bus module. The FPGA-based embedded dual-core relay protecting system integrates the digital system onto one chip and accordingly is high in function density, small in size, low in power consumption and high in reliability; compared with a special ASIC (application specific integrated circuit), FPGA is low in cost and flexible in design and is the development tendency of integrated circuit design of future microcomputer relay protecting products; the FPGA-based embedded dual-core relay protecting system comprises data collection, logic processing and a variety of peripheral systems and can meet the requirements of hardware interfaces on diversification and customization.

The invention relates to a programmable logic device (7) comprising several logic blocks (3A to 3D) with configurable characteristics, elements for linking the logic blocks to one another and a processing unit (4) and an input / output unit (5). In addition, the linking elements have at least one configurable changeover logic block, enabling the logic blocks (3A to 3D) to be re-configured during the operation of the logic device (7). Said changeover logic block is used for the configuration of at least one of the re-configurable logic blocks (3A to 3D) and its connection to other blocks and / or its connection to the processing unit (4) and / or to the input / output unit (5).

The invention discloses a six-unit cubesat main force bearing structure. The six-unit cubesat main force bearing structure is formed by means of the method that two three-unit cubesat main frames cooperate with each other through a connecting frame. The main frames are each of a cuboid frame structure, end covers are arranged at the two ends of each main frame in the direction of the long edge, and middle frameworks are arranged in the middles of the main frames. Four screws are arranged in each main frame and penetrate through the corresponding middle framework to be fixed to the end covers of the two ends of the corresponding main frame, and six hinges are arranged on the connecting frame and the two main frames. The assembly difficulty of a cubesat is lowered, and the integrity of innerlayout is improved. According to the six-unit cubesat main force bearing structure, the main frames are of an integrated structure and connected through the connecting frame making contact with the main frames in a large area so that the parallelism between guiding rails can be ensured, the six-unit cubesat main force bearing structure and a cubesat-rocket separating device are not jammed in launching, and successful launching is ensured.

The invention discloses a paper money sorting machine based on expansion by spiral air. A core mechanism is a paper money expansion mechanism. The paper money expansion mechanism comprises an inner barrel. The inner barrel comprises a barrel wall and a barrel bottom which is connected with the barrel wall. The barrel bottom is provided with a closable opening. The barrel wall and / or barrel bottom is provided with a plurality of steam inlets and an air inlet. An outer barrel which sleeves the inner barrel is provided with a barrel wall, and two ends of the outer barrel are open. The inner surface of the wall of the outer barrel is provided with a material which rubs with the inner barrel for generating static. Furthermore the material clings to the outer wall of the inner barrel. The outer barrel can drive the material to perform movement relative to the inner barrel, thereby generating static on the inner barrel. A paper money separating mechanism is connected with the inner barrel. According to the paper money sorting machine, the paper money expansion mechanism is used as a core module, and integration of paper money expansion, sorting, counting and packaging can be realized. The paper money sorting machine has advantages of high response speed, flexible structure, high rigidity-to-weight ratio, low cost, etc.

The invention discloses a siloxane modified urethane acrylate hyperbranched oligomer and a preparation method thereof and a multi-curing coating obtained therefrom. The siloxane modified urethane acrylate hyperbranched oligomer is short for Si-PUA aligomer and the weight percentage composition thereof is as follows: 20 wt percent to 50 wt percent of vulcabond, 5 wt percent to 40 wt percent of polylol, 20 wt percent to 50 wt percent of hydroxyl acrylate, 1 wt percent to 20 wt percent of heperbranched polyester, 0.5 wt percent to 10 wt percent of diamino siloxane, 0.001 wt percent to 1 wt percent of catalyst, 0.001 wt percent to 1 wt percent of inhibitor and 5 wt percent to 50 wt percent of reactive diluent. The multi-curing coating containing such Si-PUA aligomer can not only realize ultraviolet light-heat dual curing but also realize moisture curing, thus improving the hardness and enhancing adhesive force of the film thereof and having better properties of water resistance, chemical agent resistance and friction resistance.

The invention relates to transgenic mammals characterized by 5-HT3 receptor over-expression in the central nervous system (CNS) . The mammals have particular utility as models for studying the role of 5-HT3 receptors in the CNS, especially for the study of reward pathways for alcohol and other substances of abuse.

The invention discloses a three-unit cube satellite main load bearing structure which is composed of a main frame, end covers, middle frameworks, threaded rods, end nuts and a middle support. The mainframe is of a cubic frame structure, the two end covers are arranged at the two ends of the main frame in the long side direction, the two middle frameworks are arranged in the middle positions of the main frame in parallel in a spaced mode, the middle support is arranged between the middle frameworks in parallel, and the four threaded rods are arranged in the main frame, penetrate through the middle frameworks and the middle support and are fixed to the end covers at the two ends of the main frame. The assembling difficulty of a cube satellite is lowered, and the integrality of an internal layout is improved. Due to the fact that the main frame is of an integrated structure, the parallelism between guide rails can be guaranteed, the structure and a satellite and rocket separation deviceare not locked in the launching process, and the successful launch is guaranteed.

A spacecraft in-orbit multifunctional structure integrated management and control system comprises a multifunctional structure unit, a power management unit, a data processing unit, and a discharge load unit. The multifunctional structure unit integrates the bearing, power supply and vibration reduction functions. The power management unit controls charge / discharge operation, detects and adjusts the electrical performance parameters of power modules in real time, and transmits the parameters to the data processing unit. The data processing unit acquires the mechanical / electrical performance parameters of system operation and submits the parameters to a spacecraft platform through a remote sensing and data transmission interface, and the parameters are finally transmitted back to the ground. The discharge load unit consumes power under control of the power management unit. According to the system, a spacecraft structure and a power source are fused in a multifunctional manner, power source charge / discharge management, structure mechanics / electrical performance monitoring, and data management and transmission are integrated together, and the task process from remote control instruction receiving to multifunction implementation and further to state monitoring and data management and transmission can be executed systematically.

The invention relates to a disk type electric machine which includes a rotary shaft, the first armature, the first magnetic steel ring that can rotate oppositely to the first armature and an external member, wherein the external member is sheathed on the outside of the first magnetic steel ring; the first magnetic gap is reserved between the first magnetic steel ring and the first armature; the inner wall of the first armature is also provided with the second magnetic steel ring; the second armature capable of moving oppositely to the second magnetic steel ring is arranged in the second magnetic steel ring; the second magnetic gap is reserved between the second armature and the second magnetic steel ring. Driven by the rotary shaft, the invention ensures a formation of two oppositely rotating movement series by the first magnetic steel ring and the second armature with the first armature and the second magnetic steel ring; thereby leading the first magnetic steel ring, the first armature, the second magnetic steel ring and the second armature to form two independent magnetoelectric series, namely realizing the goal of mounting two independent magnetoelectric series simultaneously in the same motor. Compared with the prior art, as a magnetoelectric series is added, the function density is increased remarkably.

The invention discloses a cubesat bias momentum attitude control system. The cubesat bias momentum attitude control system comprises a mounting frame, a base, a control module and a measuring and control component; the base is fixed at the bottom of the mounting frame; the control module is fixed at the upper part of the base and positioned in the mounting frame; the measuring and control component comprises two bias momentum wheels, four sun sensors, a three-axis magnetic torquer, a gyroscope, a GPS receiver and two paths of magnetometers; the two bias momentum wheels are fixed in the mounting frame; the four sun sensors are correspondingly fixed at four external side edges of the mounting frame; the gyroscope is fixed in the base; and the GPS receiver and the two-way magnetometer are integrated on the control module. The cubesat bias momentum attitude control system has the advantages that the volume is small; the functional density is high; by reserving four-corner through holes, the system can be fixed in a cubesat through studs; the system is suitable for design standards of an existing cubesat; and moreover, the mounting space for the two bias momentum wheels is reserved in the system; and as the two paths of magnetometers are integrated in a control circuit board, the reliability of the attitude control system can be effectively enhanced.

The invention discloses an optical system based on multispectral imaging, which comprises a white light imaging CCD (15), a laser imaging CCD (16), a laser detector (17), a secondary mirror (3), a primary mirror (2), a first glued lens group and a pendulum lens (7), wherein the middle of the primary mirror (2) is provided with a hole matched with the secondary mirror (3); the path of light reflected by the pendulum lens is provided with a first dispersion prism (8), the path of the light passing through the first dispersion prism (8) is divided to two, one path is received by the white light imaging CCD (15), the other path of light is provided with a mirror (12), and a second dispersion prism (14) is arranged behind the mirror (12); and the laser imaging CCD (16) and the laser detector (17) are arranged on two light paths after light splitting of the second dispersion prism (14). The optical system based on multispectral imaging takes white light imaging, laser imaging and laser detection into consideration, and high imaging quality is ensured.

The invention discloses a robot joint arm and a robot. The robot joint arm comprises a shell, and a motor is arranged in the shell the robot joint arm; further comprises a multiplex encoder, the multiplexing encoder is in an annular shape and the multiplexing encoder is arranged on a rotating shaft of the motor in a sleeved mode, the inner ring part of the multiplex encoder is a photoelectric encoder, and the outer ring part is a magnetic encoder. According to the robot joint arm, the optical encoder and the magnetic encoder which are independently arranged in the prior art are integrated intoa whole, the axial size of the motor can be greatly reduced, and the functional density of the motor can be improved, the axial size of the joint arm of the whole robot can be reduced, and the photoelectric encoder and the magnetic encoder cannot be influenced so that the multiplex encoder can simultaneously have the functions of detecting the rotating speed and position of the rotating shaft andthe phase change point of the motor.

The invention discloses an intelligent core system with measurement and control functions and a center computer function and relates to the field of rapid spacecraft platform designing. The intelligent core system solves the problems that in microsatellite integrated electronic system, a measurement and control transponder and a center computer are large in size, heavy in weight and low in functional density. The intelligent core system with the measurement and control functions and the center computer function comprises two data transmission and processing systems, an interface module and a power supply and distribution module. Each data transmission and processing system comprises an RF channel module and a data management module. The RF channel modules are used for receiving RF signals and processing the received RF signals to generate a baseband data flow, so that conversion between the RF signals and baseband data is achieved. The data management modules are used for remotely controlling telemetric terminals and computers according to the RF signals. The RF channel modules and the data management modules achieve data interaction through the interface module. The power supply and distribution module is used for transmitting power-on / off instructions to the RF channel modules and the data management modules. The intelligent core system is applicable to communication of microsatellite systems.

The invention belongs to the technical field of semiconductor devices, and particularly relates to a three-dimensional capacitor inductor based on a high-functional-density silicon through hole structure and a preparation method. The three-dimensional capacitor inductor comprises a substrate, provided with a silicon through hole; a three-dimensional capacitor, formed on the side wall of the silicon through hole and sequentially comprising a first metal layer, a second insulating layer and a second metal layer; a three-dimensional inductor, formed by rewiring central filling metal and planar thick metal of the silicon through hole. A first insulating layer is arranged between the side wall of the silicon through hole and the three-dimensional capacitor, and a third insulating layer is arranged between the three-dimensional capacitor and the three-dimensional inductor. Values of capacitance and inductance in an integrated system can be effectively increased, capacitance and inductance can be integrated near a chip in three-dimensional integration, the functional density of through silicon vias in three-dimensional integration can be improved, and the utilization rate of silicon in system integration is increased. Compared with discrete capacitors and inductors on other organic substrates, the integration level is greatly improved.

The invention provides a mini high-functional-density integrated satellite electronic system which is high in functional density, expansibility and standard degree. The system is applied to a 10kg, 50kg or 100 kg micro / nano satellite, and comprises a core board card and an expanded board card which communicate with each other via a high-speed interconnection bus. The expanded board card is connected with satellite hardware equipment via interfaces, concretely, connected with a microwave network interface of a satellite antenna, a load interface of a satellite load, an analog collection interface of a satellite single-end analog collector, an instruction interface of instruction reception, a primary bus interface of a satellite storage battery, a power driving interface of a power driver, aheat control loop interface of heat control equipment and a sensor interface of a sensor. The core board card obtains data of the satellite hardware equipment via the expanded board card to realize functions including satellite affair management, attitude and orbit control, measurement and control, navigation, data transmission and power supply management.