49 results about "High rail" patented technology

An automated tribometer for measuring the coefficient of friction of the tread and gauge surfaces of railroad rail is disclosed. A tribometer is provided that is pushed in front of a high-rail vehicle, wherein during operation, the tribometer extends a rail test assembly to contact the surfaces of the rail. The rail test assembly has a rail testing wheel that is urged towards contact with the rail to be tested, and eventually contacts the rail, and lastly applies a known load to the rail. The testing wheel is then dynamically braked to slow the testing wheel to the point of creepage. The automated tribometer then can calculate the coefficient of friction of the rail.

A tie plate slide structure comprises a tie plate slide frame having a first frame member and a second opposed frame member, the first frame member and the second frame member extending substantially parallel from a first upper end to a second lower end, a substantially central support structure extending from the first upper end to the second lower end, the substantially central support disposed between the first frame member and the second frame member, a support assembly having first and second rail wheels depending from a lower side of the tie plate frame, a gate assembly disposed near the lower end of the tie plate slide frame to discharge tie plates slidably moving downwardly along the first and second frame members and the central support structure.

The invention discloses a parameter optimization-based spacecraft single-pulse drop-shaped fly-around track hover control method, belongs to the technical field of spacecraft track control, and aims to solve the problems that the existing fixed point hover method requires the control quantity to be continuous and the existing single-pulse drop-shaped fly-around method realizes hovering without considering the fuel consumption of a tracking spacecraft hovering on the track plane of a target spacecraft due to long hovering time. According to the technical scheme, the target spacecraft is positioned on a circular high-orbit track, the relative position range has upper and lower boundaries, the single-pulse drop-shaped fly-around track scheme with parameter optimization is adopted for implementation, and the scheme with the least performance index value, namely fuel consumption, is discovered on the basis that the entire drop-shaped track meets the position range requirement of hovering in consideration of the relative motion coordinate system based on a hill equation. The method is mainly used for track control of the spacecraft.

The invention relates to a space application communication platform based on a rail retaining last stage of a carrier rocket. The space application communication platform comprises a satellite adapter, an instrument mounting plate, an attitude control system sensor, an actuator, a storage battery, a power control unit, a task manager, a communication relay load and a solar panel, wherein the communication relay load comprises an antenna and an information processing device, the actuator comprises a counterforce flywheel, a magnetic torque and an attitude control exhaust pipe, the satellite adapter is of a hollow circular truncated cone structure with two open ends, and the instrument mounting plate is mounted at a bottom end of the circular truncated cone structure. According to the communication platform provided by the invention, the surplus carrying capacity of the carrier rocket is fully excavated, any necessary devices necessary for realizing an expansion task are deployed in the structural cabin segment of the satellite adapter by the ideas of loading and restructuring, the communication relay load is loaded, high-rail, middle-rail and low-rail space cloud communication service systems for commercial aerospace are constructed to realize measurement and control, communication and other directional services without secondary launching costs, thereby having the advantages of low-cost operation.

The invention provides a high precision propellant filling method for a high orbit satellite with parallel-connection flat-laid storage tanks. The high precision propellant filling method comprises the steps that before test, a standard weight is used for calibrating a barycenter test board; the satellite is directly mounted on the barycenter test board, and before a propellant is filled, influence, of tools on the periphery of the satellite, on the test is eliminated; in the filling process, the mass and the barycenter of the satellite are directly measured; and after filling, the creeping effect of the barycenter test board is calibrated, and test is conducted again. By adoption of the filling method provided by the invention, the precision of mass test is smaller than 0.6 kg, the precision of barycenter test is smaller than 0.5 mm, the error of satellite filling is decreased, the determination precision, of the transverse barycenter of the satellite, on the ground is increased, a direct basis is provided for determination of the transverse barycenter position of the satellite at the ignition time of an orbit transfer section apogee engine, control over disturbance torque is facilitated, and safe orbit transfer can be ensured.

A high-orbit optical remote sensor vacuum hot test external heat flow simulation method comprises the steps of firstly determining solar radiation heat flow according to on-orbit solar absorptance of an optical remote sensor (3), secondarily arranging the optical remote sensor (3) in a vacuum environment simulation chamber (1), then determining a 'sun outage' time period by judging whether the solar radiation heat flow Q1 (t) absorbed by an optical system within a orbit period is 0 or not, determining the time period of the Q1 (t) unequal to 0 as the 'sun outage' time period, adopting a solar simulator (2) and electric heater combined simulation scheme to perform outer heat flow simulation, determining that the time period of the Q1 (t) equal to 0 is a 'non-sun outage' time period, and adopting an independent electric heater simulation scheme to perform outer heat flow simulation. The problem that an existing non-contact space optical remote sensor outer heat flow simulation method does not have a solar spectral energy spectrum characteristic and directionality is solved, energy distribution of solar spectrum of the remote sensor on orbit can be accurately simulated, simulation accuracy is high, and project realization is promoted.

The invention proposes a pulse density modulator used for a TD-SCDMA terminal, a Beyond 3G terminal and a 4G terminal. The pulse density modulator (PDM) comprises a DSP interface, a clock gate control unit, a clock frequency divider, an accumulator, an OR gate, an output register, a reset circuit and an output control circuit. The output of the pulse density modulator is a simulation value generated by a simulation low-pass plate external filter. When the PDM outputs a high level signal, the voltage is very close to the source voltage Vcc; when the PDM outputs a low level signal, the voltage is very close to the ground voltage GND. The pulse density modulator (PDM) can have high resolution expressed by the multi-bit and output all voltage values in the range from the logic low level to the logic high level. The output of the pulse density modulator (PDM) can be set to be in a high resistance state; the refresh speed of the pulse density modulator (PDM) can be set by a DSP or a DSP software / firmware. When a plurality of pulse density modulators (PDM) are in use, all pulse density modulators (PDM) can be divided into groups; each group can include a plurality of pulse density modulators; each group of PDM can be enabled separately; the groups are controlled by the PDM clock enabling signal; each group of PDM is provided with a reset circuit; the PDM is reset and initialized to be in the high resistance state when the pulse density modulator (PDM) receives the reset signal of the DSP each time. When the pulse density modulator (PDM) is set to be the high rail level output or in the high resistance state, the internal clock frequency divider in the pulse density modulator (PDM) stops operating.

The invention discloses a high-accuracy micro deformation star sensor mounting bracket. A star sensor mounting plate is connected to the outer surface of a thin-wall shell structure; a heat pipe is positioned inside the thin-wall shell structure; one end of the heat pipe is connected to the star sensor mounting plate; the other end of the heat pipe is connected with a heat collecting plate; the heat collecting plate is connected to the inner side of the top of the thin-wall shell structure and partially extends out of the top of the thin-wall shell structure; a first insulation mat is mounted between the heat collecting plate and the thin-wall shell structure; a rear cover board is connected to the back of the thin-wall shell structure so as to form a mounting bracket head; one end of a strut assembly is connected with the mounting bracket head; the other end of the strut assembly is used for mounting a spacecraft optical imaging effective load structure body. The high-accuracy micro deformation star sensor mounting bracket solves the technical difficult problem of harsh thermal deformation of a high-orbit spacecraft star sensor mounting bracket so as to meet the requirements on high-accuracy attitude determination of a spacecraft and image navigation registration, and meanwhile, has the advantages of novel structural form, light weight and the like.

The invention discloses a method for locating a non-cooperative wireless signal source based on a high-rail three-satellite time-difference system. The method for locating the non-cooperative wireless signal source based on the high-rail three-satellite time-difference system is achieved through a high-rail signal detecting-receiving locating constellation and a ground system, wherein the high-rail signal detecting-receiving locating constellation is deployed above a particular region and is composed of three satellites which run in an inclined geosynchronous small-eccentricity elliptical orbit, the three satellites have the same circular ground track, the constellation is provided with an equilateral stable triangular configuration and thousands of kilometers of inter-satellite baselines which are even and stable, each satellite conducts real-time and continuous detection and receiving on radar signals or communication signals transmitted by the ground non-cooperative wireless signal source, signal detection and parameter measurement are respectively finished, a satellite-ground link arranged on each satellite so that measurement information can be transmitted downward to the ground system in real time, and the ground system conducts processing and resolving according to the time difference of signal detection and receiving among the three satellites. The high-rail three-satellite time-difference system is adopted so that locating of the non-cooperative wireless signal source can be achieved. The method for locating the non-cooperative wireless signal source based on the high-rail three-satellite time-difference system has the remarkable advantages of being large in coverage area, strong in real-time performance, stable in locating precision and the like.

The invention discloses a high-orbit area array staring infrared camera imaging circuit system comprising an area array infrared detector, a bias driving module, a signal processing module, a data storage module, a locking and current limiting monitoring module and a high-speed clock management module. In the bias driving module and the signal processing module, a device having high performance and high radiation resistance is used for generating a bias driving voltage and a timing sequence necessary for the work of the area array infrared detector; in the data storage module, a magnetic memory array having flexible reading and writing control and single event upset immunity is used for storing large-scale non-uniform correction coefficients of the area array infrared detector so as to effectively prevent the occurrence of the single event upset effect; for the device sensitive to single event locking in the system, the locking and current limiting technology is used for protecting and locking the device from being burnt by large current and improving the single event upset locking resistance of the device; and the high-speed clock management module provides a high-quality clock for the modules. The high-orbit area array staring infrared camera imaging circuit system provided by the invention has the characteristics of high speed, high reliability and high radiation resistance.

A mixed-signal integrator, having an analog input and a digital output, is adapted to perform an integration operation partially in the analog domain and partially in the digital domain while eliminating the limitations of a conventional analog integrator. The integrator also digitizes a signal of interest without the use of a conventional sampling operation followed by a conventional analog-to-digital converter. The analog integrator portion generates an analog integration signal limited between low and high rail voltages defined by two comparators with corresponding threshold voltages. When either rail voltage is reached, the polarity of the input signal is reversed to prevent the integration result from exceeding that rail. Each such event is also tracked in digital logic, which provides a count whenever two consecutive such events correspond to the two different rails. At the end of the integration duration this count serves as the digital representation of the integration result.

The invention discloses a communication method and system based on high and low orbit satellites. High orbit satellites and N low orbit satellites are included; the N low orbit satellites are used foracquiring and receiving event information in respective coverage areas, and reporting the service information of the event information to the high orbit satellites; and the high orbit satellites areused for distributing and matching the service information to the low orbit satellites in the management domain of the high orbit satellites or the high orbit satellites outside the management domainof the high orbit satellites. According to the communication method and system based on the high and low orbit satellites disclosed by the invention, due to an inter-satellite communication resource collaborative management mode, the acquisition and distribution collaborative operation of wide-area information is realized among the high and low orbit satellites; the storage and unlocking mode of inter-satellite resources is provided; collaborative storage and distributed unloading of communication resources among the high and low orbit satellites can be realized; the inter-satellite resource scheduling efficiency and the utilization rate are increased; and the calculation delay of inter-satellite resources is reduced.

The invention discloses a matrix-type electroplating production line. Multiple tanks of the matrix-type electroplating production line are arranged in a matrix way. The multiple rows of the tanks are tightly arranged side by side. A bridge crane for conveying workpieces can walk forwards, backwards and sideways on the production line. A frame of the production line has an assembled structure, the tanks are arranged on the frame, the bridge crane is installed in a high rail way and a guide rail is supported by stand columns at two sides of the production line. The bridge crane is provided with a gear motor, a suspension hook, a plurality of machines and an electric appliance protection device. A rotary encoder and a rack-and-pinion structure are used for bridge crane positioning. A tank chain-type structure is used for bridge crane walking. A tank cover is provided with a horizontal movement seal cover plate.

The invention discloses a construction setting out method for high speed rotary road curved surface spreading, and belongs to the technical field of building construction. The method comprises the steps of using GPS to set out the positions of reference points on the inner side of a high speed rotary road curved surface, arranging control piles according to the positions of the reference points, and measuring the elevations and plane positions of the control piles; performing low track point setting out, arranging low track support piles at low track points, and erecting low track guide beamson the low track support piles; performing high track point setting out, arranging high track support at high track points, erecting high track guide beams on the high track support piles, and using abridge spreading machine to walk on the high track guide beams and low track guide beams for spreading work to meet the planes and elevations required for the bridge spreading machine to control spreading. When the method is used for curved surface spreading, it is not necessary to repeat the setting out, and the spreading precision is high.

The embodiment of the invention discloses a control method and device for airless injection of a leak-tightness oil injector. The control method comprises the steps that after an engine shuts down, when the rail pressure of the interior of a common rail pipe is excessively high, dynamic leakage, that is an airless injection method of the leak-tightness oil injector is used for discharging high rail pressure of the interior of the common rail pipe, specifically, a shut-down signal of the engine is responded, and whether the rail pressure of the interior of the common rail pipe is greater than apreset threshold value or not is judged according to a rail pressure signal; if yes, the condition that the rail pressure of the interior of the common rail pipe is excessively high is illustrated; and in order to prevent the influence brought by the excessively high rail pressure of the interior of the common rail pipe, the oil injector is controlled to conduct airless injection for pressure discharging, the oil injector is controlled to stop airless injection pressure discharging until a preset stopping condition is achieved, the purpose that after the engine shuts down, the excessively high rail pressure of the interior of the common rail pipe is discharged is achieved, when the engine is started again, the condition that impact of the excessively high rail pressure of the interior ofthe common rail pipe on parts and components of a fuel system influences the service life of the parts and the components is prevented, and meanwhile, high risks for halt maintenance brought by the excessively high rail pressure are avoided.

There is described a hi-rail device for mounting on a vehicle, comprising a linkage between an axle assembly for holding wheels and a mounting assembly. The linkage, pivotally connected to an upper pivot connection thereof, is foldable and unfoldable to translate the axle assembly relative to the upper pivot connection. An active suspension between the linkage and the mounting assembly is provided and comprises a suspension body to swivel about the mounting assembly, actuated by a spring proximally urging on the suspension body to provide the swivel. The suspension body comprising the upper connection to the linkage, which can move along with the suspension body to provide active suspension. Also, a locking pin, extending through the linkage, can be locked in a slot using a hydraulic cylinder, distinct from a hydraulic cylinder for deployment, and which comprises a spring for default locking not involving hydraulic power.

The invention provides main architecture of a small-type high-orbit satellite common platform. The main architecture of the small-type high-orbit satellite common platform comprises a shell, an intermediate baffle, a platform cabin main bearing truss set and a load cabin bearing truss, wherein the shell forms a holding space, and the intermediate baffle divides the holding space into a platform cabin and a load cabin; the platform cabin main bearing truss set applies supporting force on the partial outer shell and the intermediate baffle which form the platform cabin; and the load cabin bearing truss applies supporting force on the partial shell and the intermediate partition which form the load cabin. According to the main architecture of the small-type high-orbit satellite common platform, a bearing structure is composed of the platform cabin main bearing truss set, the load cabin bearing truss, a bottom plate inner embedded frame, and a baffle inner embedded frame.

The invention provides a satellite navigation signal simulation method specific to a terminal carrier used as a high rail satellite. On the basis of the existing satellite navigation signal simulation, a navigation satellite shielding angle is calculated by adopting a way of an earth tangential line specific to the feature that the elevating angle of the navigation satellite relative to a high track GNSS receiver is less than 0 degree, so as to judge the visibility of the navigation satellite; specific to the feature of weak strength of signals received by the high track GNSS receiver, simulation of a satellite emitting antenna direction graph is added, the power simulation function is improved and the satellite is selected upon power; specific to the feature that a part of signal crossesthrough an atmospheric layer twice, the dual-atmospheric effect simulation is added. Through the method, analogue simulation of the satellite navigation signal received by the high track satellite isrealized, and the testing tool is provided for the GNSS receiver and related system loaded on the high track satellite.

The invention discloses a power transmission line forest fire monitoring method and device based on high-orbit and low-orbit satellite data. The method comprises the following steps of determining coordinates and the fire range of a fire point according to image data shot by a high-orbit satellite in a monitoring period; when the fire point is in the coverage area of a current power transmission line, calling a low-orbit satellite to monitor the fire point, and determining a target position, the fire area and a fire development direction of the fire point; and when the fire development of thefire point is deduced to endanger the current power transmission line by utilizing a simulation result of a fire deduction model, judging the danger level of the fire point as a dangerous situation, and giving out early warning. Therefore, the method and the device provided by the invention have the advantages that the time resolution of the high-orbit satellite and the spatial resolution of the low-orbit satellite are considered, so that fire monitoring and early warning of the power transmission line can be realized through fusion of the high-orbit satellite data and the low-orbit satellitedata, the requirements for the time resolution and the spatial resolution of fire monitoring of the power transmission line can be met at the same time, and forest fire monitoring can be carried out timely and accurately.

A satellite track analog test system includes an analog optical terminal, a master control computer, a tested laser communication terminal charactering in constituting a control test drive system and a universal swing table, among which,, the cross point of the tested laser communication terminal vertical shaft and a horizontal shaft is coincident with the cross point of a mechanical structure vertical shaft and horizontal shaft of the universal swing table to be passed by the analog optical terminal light shaft. In the master control computer, a database is set storing data of a pitch angle and azimuth angle of the satellite track by driving the universal swing table accurately.

The invention discloses a two-dimensional directional antenna with an initial directing function and applicable to a high-orbit satellite. The two-dimensional directional antenna comprises an antennabody, an X-Y two-dimensional directing mechanism, a locking and releasing device, a waveguide feeder and a frame. The antenna body and the waveguide feeder are mainly used for receiving radio-frequency signals transmitted by a transmitter and radiating outwards. The X-Y two-dimensional directing mechanism is used for realizing contraction of the antenna in launching and expansion of the antenna after orbit injection and has a function of two-dimensional free rotation. The locking and releasing device is used for realizing contraction and locking of the antenna in a launching stage and capableof directing a set ground station after orbit injection at a fixed point, and the antenna is unlocked and released after orbit injection without affecting the two-dimensional rotation function of theantenna. A thermal control component is mainly used for guaranteeing a great operating temperature environment for moving parts in an in-orbit period, and a motion function of the two-dimensional mechanism is unaffected. The two-dimensional directional antenna is capable of directing a target after orbit injection and capable of rotating two-dimensionally for directional communication after unlocking.

A kind of high-rail traffic of the present invention is to set up a track line on a subgrade line, wherein a track line includes two rails and two anti-derailment, and the distance between the rails and the anti-derailment is equal; run on this line The rail car is equipped with rail wheels and anti-derailment wheels. The rail wheels and anti-derailment wheels are controlled by the rails on the track line and the anti-derailment control and cannot be derailed. When the rail car is gradually speeding up at high speed, don't worry Derailment accidents will happen.

The present disclosure generally relates to a road rail stoneblower vehicle for carrying out rail maintenance operations near fixed structures such as bridges and overpasses. The road rail stoneblower includes a hi-rail chassis having a first set of wheels configured to engage a road surface and a second set of wheels configured to engage surfaces of substantially parallel rails of a railroad track. The road rail stoneblower further includes a plurality of workheads that are capable of dispensing ballast stones into a bed of ballast underlying the railroad track to adjust the height of the rails. The road rail stoneblower further includes a leveling system detachedly coupled to the hi-rail chassis that is configured to transmit a detectable signal that defines a reference plane with which the rails are to be aligned. Related methods of operation of the road rail stoneblower vehicle and associated maintenance of ballast beds underlying railroad tracks are also described.

The invention relates to a low-rail large-dip-angle reciprocating feeder. The reciprocating feeder is mainly used in an intermediate transfer process of coal mine bin materials and particularly applicable to high-yield and high-efficiency production systems. Reciprocating feeders in the prior art are low in production capacity and cannot meet requirements for the high feeding capacity of high-production systems of coal mines. The reciprocating feeder is composed of a hopper, a trough and a movable base plate which is driven by a motor, a decelerator and a crank connecting-rod mechanism. The movable base plate is composed of a small-dip-angle base plate and a large-dip-angel base plate. The small-dip-angle base plate moves on a roller of a high-rail hanger, and the large-dip-angel base plate moves on a roller of a low-rail hanger. According to the reciprocating feeder, the inclined angle of the base plate is large, so that the sliding force of materials during moving is increased, the material operation speed is accelerated, and materials in a bin falls rapidly for feeding, accordingly, the feeding capacity is improved greatly. The reciprocating feeder has the advantages of being high in production efficiency, small in operation power, uniform in feeding, low in noise, small in maintenance amount, high in part universality and the like.

An oscillator architecture with pulse-edge tuning to control the pulse rising and falling edges (such as for duty cycle correction), including a signal generator with a pull-up PMOS transistor coupled to a high rail, and a pull-down NMOS transistor coupled to a low rail. Pulse-edge tuning circuitry includes a high-side tuning PMOS transistor between the high rail and a source terminal of the pull-up PMOS transistor, and a low-side tuning NMOS transistor between the low rail and a source terminal of the pull-down NMOS transistor. Both tuning FETs are controlled for operation as a variable resistor by respective high-side and low-side DACs to provide tuning control signals to the tuning FETs. In an example application, the oscillator design is adapted for a direct conversion RF signal chain (TX and / or RX) including an I-Path and a Q-Path: the signal generator generates ±I and ±Q differential signal frequencies.

The invention discloses a fully-automatic high rail type ABS automobile part production line which comprises a production line of a U-shaped structure, wherein a loading device, a transfer device and an unloading device are arranged on the production line; the production line comprises a rack; a transverse moving rail is arranged in the rack; a plurality of mechanical suspension arm lifting vehicles are arranged on the transverse moving rail in the rack; and a plurality of stations are further arranged in the rack. The fully-automatic high rail type ABS automobile part production line implements a functional unit assembly, so that one step is needed for obtaining a product from raw materials, and use of manpower and material resources is reduced. According to the fully-automatic high rail type ABS automobile part production line, the unit fit is optimized, the degree of automation is high, the occupied factory space is small, the pollution source is less, the power consumption is low, the cost is low and the maintenance is easy; the unit adopts transmission of a servo motor for precisely controlling and reducing starting-up and position-covering time, so that the product waste length is shortened; and communication of a human-computer interface is operated by one person, so that unit fit can be completed.

The invention discloses a high-rail and low-rail universal type window cleaning machine. The high-rail and low-rail universal type window cleaning machine comprises a high-area window cleaning machine rail and a window cleaning machine body; the window cleaning machine body is arranged on the high-area window cleaning machine rail; the high-rail and low-rail universal type window cleaning machine also comprises a low-area transfer trolley rail and a transfer trolley; the transfer trolley is arranged on the low-area transfer trolley rail; a transfer window cleaning machine rail is arranged at the top of the transfer trolley; the transfer window cleaning machine rail and the high-area window cleaning machine rail have the same structure and consistent height; a rail abutting positioning pin is arranged on one side, facing the high-area window cleaning machine rail, of the transfer window cleaning machine rail; a transfer trolley positioning pin is arranged on a wheel of the transfer trolley; and a detachable stop block is arranged on the transfer window cleaning machine rail. Through the transfer trolley, the whole building can be cleaned only by one window cleaning machine when the heights of the rail mounting surfaces of the building are different, so the engineering cost is greatly reduced.

The invention relates to a ball-type guiding damping mechanism suitable for a general cone rod capturing mechanism of a high-orbit satellite, which comprises a rocker arm mounting seat (2), roller rocker arm structures and the like, wherein one end of a guide cylinder (9) is provided with the rocker mounting seat (2), and a sliding seat (4) is arranged on the guide cylinder (9) and slides along an outer wall of the guide cylinder (9); an annular damping rod supporting seat (8) is arranged on a flange plate at the other end of the guide cylinder (9); the roller rocker arm structures are uniformly distributed around a central axis of the guide cylinder (9), the one end of each roller rocker arm structure is rotationally connected with the rocker arm mounting seat (2), and the other end of the each roller rocker arm structure is rotationally connected with an end part of a damping rod (6); the one end of the damping rod (6) connected with the roller rocker arm structure is fixed on the flange plate at the end part of the sliding seat (4), and the other end of the damping rod (6) extends into a damping rod mounting seat (8) and slides along an inner wall of the damping rod mounting seat (8). The ball-type guiding damping mechanism suitable for the general cone rod capturing mechanism of the high-orbit satellite can adapt to a rolling target capture under a condition of weak impactand can provide larger relative speed and angular velocity tolerance for the cone rod capturing mechanism.