1008 results about "Pilot system" patented technology

Method and apparatus for OFDM synchronization and channel estimation. In a temporal embodiment, received embedded system pilot symbols are inverse Fourier transformed at expected index locations and correlated with computed complex conjugates of inverse Fourier transforms of pilot symbols for providing a correlation function for the channel impulse response. In a frequency domain embodiment, embedded system pilot symbols are augmented with pilot-spaced inferred guard band symbols, multiplied by scaled complex conjugates of computed pilot systems, and inverse Fourier transformed into the channel impulse response. Time and frequency are synchronized in feedback loops from information in the channel impulse response. The channel impulse response is filtered, interpolated, and then Fourier transformed for determining channel estimates for equalization.

Pilot error is reduced and auto pilot operation is improved by the addition of capture information to the information provided on a cockpit display. The capture information, such as, for example, capture start point, last point to initiate capture, trajectory during capture, and capture overshoot region provide information to the pilot regarding the correct initiation of capture. Pilots are therefore better able to evaluate the ongoing performance of the automation or auto pilot systems and to trust that the auto pilot is functioning as desired. Furthermore, the pilot operating the aircraft in manual mode receives guidance based on this information to better know when to initiate capture of the assigned altitude or vertical path.

The invention provides a three-way loading mechanical property test system of a multifunctional lining segment joint, which mainly comprises a self-balancing frame sub-system, a loading sub-system, a test-piece support sub-system, a test-piece transporting sub-system, a loading control sub-system and a data acquisition sub-system. The loading sub-system adopts a modular design and can finish a shield tunneling lining segment inter-ring shearing test, a bending moment transferring test, a longitudinal joint corner rigidity test, a longitudinal joint radial shearing test and the like by different combinations. The system of the invention can preferably imitate three-way stress states of the shield tunneling lining segment joint in actual conditions and can finish various different loading modes to obtain mechanical parameters of the shield tunneling lining segment joint and mechanical properties of other similar structures.

This invention relates to an automatic driving system of a road vehicle, especially to a system which providing automatic driving information indication for traveling vehicles and realizing vehicle automatic driving through the vehicle automatic control system, which is characterized by comprising: fixing markers at interval along a road travelling line, receiving information feedback by the fixed markers through a set relay information station and forming the vehicle and road information on the road, and constantly supplying the road and vehicle information of the road where the vehicle is to a vehicle automatic receiving processor after the received GPS(Global Position System) information and the vehicle and road information on the road are overall treated, installing an automatic driving software in a vehicle-mounted computer which can receive and treat relevant information of the relay information station at any time, constantly sending operation instructions to a vehicle automatic controller so as to keep the vehicle travelling information direction line consistent with the vehicle driving speed direction line, and sending instructions to the vehicle automatic controller according to the selected mode by a driver so as to realize vehicle automatic driving.

The invention provides a test system and method for a single event effect of an SRAM (System Random Access Memory) type FPGA (Field Programmable Gate Array). The test system comprises a single chip microcomputer processor, an RS232 interface circuit, a USB (Universal Serial Bus) interface circuit, a test FPGA and a storage unit. The test system and method can be used for fault injection tests of a configuration memory and a BRAM (Battery Random Access Memory) of the SRAM type FPGA, and single event function interrupting detection, single event locking detection and single event turning detection including single event turning detection for a configuration storage region, the BRAM and a trigger of the SRAM type FPGA are realized. The invention has the advantages of simplicity in operation, entirety in detection, high accuracy, good real-time property and strong universality.

The invention relates to a multifunctional model test system for tunnel and underground engineering. The test system comprises a rail, a model box, a servo-controlled test loading device, a rotating seat, rotating shafts and a bracket, wherein the rail is arranged on the upper part of the test system; the model box is arranged on the middle part of the test system and comprises an outer frame, an inner frame and an organic glass plate; the servo-controlled test loading device comprises a horizontal loading jack and a vertical loading jack; the rotating shafts are arranged on the two sides of the middle part of the test system; and the rotating seat is arranged on the back surface of the upper part of the test system and is connected with the bracket through a rotating loading cylinder. The system can perform a model test on a block system, rock tunnel excavation, a tunnel chamber, a tunnel group, a side slope, shield excavation and building traversing, has a facade rotating loading function, effectively solves the technical problem that a strain field is required to have a wide uniformity range and a high uniformity degree in the model test, and can well simulate the stress environment of tunnels existing in a rock-soil body.

The invention discloses a gas explosion simulation test system and method and belongs to the technical field of explosion tests. The test method comprises the following steps: checking the connecting integrity of a sensor, and starting a data acquisition unit; starting a high-speed camera and computer software, and adjusting the shooting angle of the high-speed camera; opening an air outlet valve, and vacuumizing a simulated roadway by using a vacuum pump; opening an air inlet valve, a methane gas cylinder, an air bottle, a reducing valve, a solenoid valve and a flowmeter, and regulating to obtain the test premix gas under different gas concentrations; igniting through an igniter, triggering the data acquisition unit to acquire pressure and temperature data, and starting the high-speed camera to shoot the gas explosion process through externally triggering; analyzing and processing the acquired data and image, and finding the gas explosion rule. The method has the advantages that the explosion stress wave propagation rule, temperature change rule and smoke and flame change rule in the gas explosion process can be obtained, and quantified and refined description in the gas explosion process is realized.

The invention discloses a multi-working-condition comprehensive simulation test system for reciprocating seal of an aviation actuator. The multi-working-condition comprehensive simulation test system comprises a test actuator, a reciprocating driving loading system and a hydraulic system, wherein the reciprocating driving loading system is connected with a piston rod of the test actuator; the hydraulic system is connected to an oil inlet/outlet of a cylinder body; the test actuator comprises an end cover, the piston rod and the cylinder body; the reciprocating driving loading system comprises an electric cylinder, a transmission shaft, a transmission vibration isolating device, a force sensor and an LVDT sensor, and the transmission shaft is connected with the force sensor through the transmission vibration isolating device; and the hydraulic system comprises a pump source module, a pressurization module, a pressure maintaining module and a pipeline heater. By using the multi-working-condition comprehensive simulation test system, multi-working-condition comprehensive conditions such as high pressure, wide temperature range, variable speed and airborne vibration of the aviation actuator can be effectively simulated, and the friction force character of multi-type shaft seal of single piston rod and the leakage rate obtained after repeated reciprocation can be accurately measured under various working conditions; and the multi-working-condition comprehensive simulation test system has the characteristics of convenience in use, operation stability, test accuracy, long service life and the like.

The invention discloses an indoor test system and a test method for seepage characteristics of jointed rock mass. Through carrying out seepage, deformation and stress coupling tests of seepage performance for a large scale jointed rock mass test piece under high pressure water to a given jointed rock mass, the test pressure, flow and displacement can be simultaneously displayed and collected in real time, and the test data can be stored. The test method comprises the following steps: a test rock piece with a fissure surface is placed into a mould, the mould is placed into water, and the fissure surface inclination of the rock is adjusted; a water filling pipe is installed on the fissure surface of the rock, the water filling pipe is connected with a high pressure pump, and pressure cells are installed on an upper plate and a lower plate of the fissure surface of the rock; anchorage points are arranged on the upper side and the lower side of the fissure surface, and the anchorage points are connected with a displacement meter; high flow and high pressure hydraulic test is carried out by the high pressure pump to the fissure surface through the water filling pipe, the collected data is transferred to a collector by a pressure sensor on the water filling pipe, a flow sensor, the press cells and the displacement meter respectively and then accesses to a computer, and the real-time pressure, flow, relative displacement of the fissure and coupling relationship are continuously recorded and displayed.

The invention discloses a vehicle automatic pilot system and a method based on various sensors, the method includes: combining the electronic map, laser radar, GPS location and gyroscope for obtaining the real-time information of the vehicle and the road, obtaining the initial road information through the running route offered by the electronic map, obtaining the real-time road state and vehicle state through the laser radar and GPS during the vehicle running process, correcting through the gyroscope by combining the data of the electronic map, laser radar and GPS and obtaining the final automatic pilot strategy. The method is low in complexity, the radar strategy and the GPS strategy can be executed in a parallel mode and the real-time performance is high; various sensors are used and the data of various sensors is used for correcting and checking for having high algorithm reliability; a small amount of road information offered by the electronic map is used not collecting the data on the spot and the system and the method are suitable for the complex environment.

The invention discloses a turning cutter wear state monitoring system. The turning cutter wear state monitoring system comprises a signal collecting system and a cutter wear state identifying system; the signal collecting system comprises a temperature collecting system and a vibration signal collecting system, wherein the temperature collecting system collects temperature of a cutter point of a rake face of the cutter, and the vibration signal collecting system collects a three-dimensional vibrating signal at the lower surface of a cutter handle corresponding to the utter point of the rake face of the cutter; after pretreating the signal collected by the signal collecting system, the sensitive characteristic of the cutter wear state is obtained and transmitted to the well-trained cutter wear state identifying system; thus the wear state of the cutter is judged through the cutter wear state identifying system. The turning cutter wear state monitoring system is simple and applicable, and is convenient to operate; moreover, the sensor in use is relatively universal in use, moderate in cost, and easy to build up a testing system; the turning cutter wear state monitoring system can largely reduce the monitoring cost, effectively identify the wear state of the cutter and reduce the cutter waste.

The invention relates to a low-voltage electric wire carrier communication test method and a testing system thereof. The testing method comprises the following testing methods: I, a carrier transmitting PWL online testing method; II, a carrier receiving sensitivity online testing method; III, a carrier communication anti-interference online testing method; IV, a low-voltage circuit impedance change online testing method. The testing system comprises a carrier transmitting device, a program control attenuating device, a tested carrier receiving device, a manual power network, a frequency spectrograph receiver, a computer, a frequency spectrograph, a noise simulator, an impedance simulator and a purifying power. The invention has the advantages of adopting a manual power network parameter model regulated in GB/T 6113 F2, thus having a high standardization degree and comparable testing data; avoiding the testing problems brought by adopting different carrier communication schemes; realizing the online sensitivity testing; carrying out the test at any time and being not affected by the external environment factors like the weather; besides, the invention can simulate the impedance change environment of a real circuit, thus leading the analyzing of the carrier communication on the impedance change of the circuit to be feasible.

The invention discloses a hardware-in-loop test bed of a hybrid car brake coordination control system, which comprises a driver operation test system (1), a hydraulic brake test system (48), a data processing module (46) a model simulation test system and a motor brake test system (19), wherein, a hydraulic control valve (58) in the hydraulic brake test system (48) is a test object and can be replaced by other hydraulic valves to be tested for testing hydraulic work characteristic. A permanent magnet synchronous motor (34) in the motor brake test system (19) is the test object and can be replaced by other motors to be tested for testing energy recycling characteristic. A brake operation mechanism in the driver operation test system (1) is the test object and can be replaced by other operation mechanisms to be tested for testing the relation of master cylinder pressure, footplate stroke and footplate force. The hardware-in-loop test bed of the hybrid car brake coordination control system can carry out the integral performance test of the hybrid car brake control system which comprises hardware and control strategy.

The invention relates to a system for testing heat-transfer performance of a gas-water-oil heat interchanger, and is composed of a steady air system, a cold water system, a hot water system and a oil system. The steady air system: a voltage-stabilizing case output end is connected with inlets between the first steady air flow gauge and the first steady air pneumatic butterfly valve or the second flow gauge and the second steady air pneumatic butterfly valve and high-pressure centrifugal fan, wherein, steady air bypass electric control valve is connected between the inlet and the outlet of the high-pressure centrifugal fan; the hot water system: an expansion water tank, an electric heater water tank and an outlet are connected to the water pump, and water enters into the heat interchanger to be measured through the bypass of the electric three-way valve, the water flow gauge and the electromagnetic valve, thereby forming a closed loop system; the cold water system: compared with the hot water system, the system does not have an expansion water tank; the oil loop system is a open and close type circulating system: the outlets of the expansion fuel tank and the fuel-tank are connected to the oil pump, oil enters into the heat interchanger to be measured through the bypass of the electric three-way valve, the oil flow gauge and the electromagnetic valve, thereby forming a closed circulation for testing the heat exchange performance of the oil-water, oil-gas heat interchanger.

The invention provides a multifunctional bearing test device, which comprises a rotation driving system unit, a loading system unit, a high and low temperature environment box, a lubrication cooling system unit and a measurement control system unit, and is characterized in that the loading system unit can control the loading force and the loading waveform of loading heads on an axial loading unit and a radial loading unit, and the high and low temperature environment box can realistically simulate a real temperature environment of a test. The multifunctional bearing test device can simulate service conditions of a test bearing in a test room, realizes performance testing for the test bearing under conditions of given rotating speed, lubrication, temperature, axial load, radial load and circumferential unbalanced impact load and the like, and analyzes influences imposed on the bearing performance by misalignment, poor lubrication, uneven stress and the like through data such as vibration acceleration, abrasive dust amount and the like acquired in the testing process, thereby being capable of more authentically simulating actual conditions of a rolling bearing when being subjected to the radial load, the axial load and the like, and being more reliable, systematic and scientific in service life and reliability evaluation for the test bearing.

The invention discloses a multi-field coupling coal bed methane extraction physical simulation testing system. The system comprises a test piece box (1), wherein a step-shaped protruding mouth (9) is formed in a front box plate of the test piece box (1), a protruding sleeve (10) is fixedly connected with the inner side of the protruding mouth (9) through a bolt, an outer pipe fixing seat (11) is arranged inside the protruding sleeve (10), an outer pipe (12) is in threaded connection with an inner hole of the outer pipe fixing seat (11), an extraction outer region (12a) is arranged on the outer pipe (12), a plurality of extraction outer holes (14a) are formed in the extraction outer region (12a), and an inner pipe (15) is arranged on the outer pipe (12). According to the multi-field coupling coal bed methane extraction physical simulation testing system, coal bed methane extraction under the working condition at site can be simulated in a laboratory, changing of coal bed parameters in the actual working condition can be reproduced, and therefore changing of the stress field, the fracture field, the transfusion field and the temperature field can be studied, and spatial-temporal evolution and the distribution rule of coal bed gas migration and coal and rock mass fracture coupling can be analyzed.

The invention discloses a hydrogen container hydrogen environment fatigue test system. One end of a high pressure hydrogen container is respectively communicated with a test container and a low pressure hydrogen container through an explosion protection pressure reducing valve, a flow regulating control valve, a first normal open stop valve and a test container depressurizing valve; the low pressure hydrogen container is communicated with the other end of the high pressure hydrogen container through a booster pump; a pressure sensor and a cycle recording device are arranged between the first normal open stop valve and an atmospheric valve; the normal open stop valve, a pressure display and a standard pressure gauge are arranged between the test container and the normal open stop valve; one path of an automatic control system operation console is respectively electrically connected with the booster pump and the pressure gauge through an excessive pressure controller; the other path of the automatic control system operation console is electrically connected with the atmospheric valve and the test container depressurizing valve. The high pressure hydrogen in the high pressure container is charged into the test container through the explosion protection pressure reducing valve and the flow regulating control valve, the explosion protection pressure reducing valve is closed when a set pressure is reached, the test container depressurizing valve is opened after maintaining the pressure for a while, and the hydrogen is depressurized into the low pressure container to complete a fatigue test cycle.

The invention discloses a test system for deformation measurement of a large spacecraft structure under a vacuum and low-temperature environment. The test system includes a vacuum and low-temperature container, a portal supporting mechanism, a low-temperature cantilever moving mechanism, photogrammetry CCD camera and protection cabin assemblies, a test piece supporting mechanism, a low-temperature reference meter, a temperature and air pressure control system, a motion control system, and a measurement data acquisition and processing system; two sets of photogrammetry CCD camera and protection cabin assemblies are symmetrically hung at two ends of the low-temperature cantilever moving mechanism, and 3m-rotation radius and +/-360-degree-reciprocating rotary movement photographing can be realized under the vacuum and low-temperature environment so as to realize the deformation measurement of the large spacecraft structure. With the test system of the invention adopted, the thermal deformation measurement of a certain 5m large umbrella antenna can be completed under a simulated space environment by using photogrammetric techniques, and the repeatability precision of the measurement of spatial point positions can achieve 20 microns.

The invention provides an aircraft aero-servo-elasticity (ASE) ground simulating test system which is applied to an aircraft capable of generating the ASE stability loss problem. The whole system comprises a test object aircraft (comprising a control and stability augmentation system), and a motion signal sensor, a central control computer, an aircraft pneumatic force number calculating model, a pneumatic force simulating loading device and the like which are arranged on the aircraft structure. The system carries out real-time measurement and processing on a motion signal of the aircraft, calculates the normal-stationary pneumatic force of the aircraft through a special algorithm on the basis of relevant theory, and realizes the pneumatic force simulating loading through a vibrator. The system is connected with the test aircraft to evaluate the ASE of the aircraft, and can be used for the improvement design of the control and stability augmentation system of the original aircraft and the verification research of the advanced control method.

The invention provides a semi-physical simulation testing system for a deep space autonomous navigation star sensor and a method thereof. A star sensor simulator is placed on a similar support frame, and an autonomous navigation star sensor is fixed on a three-axis rate rotating table; the center of an entrance pupil of the autonomous navigation star sensor is arranged on a horizontal rotation central axis of the three-axis rate rotating table; an emergent pupil of the star sensor simulator is in butt joint with the entrance pupil of the autonomous navigation star sensor, and an optical axis of the star sensor simulator is superposed with the optical axis of the autonomous navigation star sensor; and the autonomous navigation star sensor, the three-axis rate rotating table and the star sensor simulator are all connected with a control and information processing computer. By adopting the system and the method, star simulation for the very high-precision star sensor for autonomous navigation of a minor planet can be solved, and the measurement precision of the star sensor and the autonomous navigation positioning precision are verified, thereby having broad application prospects for developing the deep space autonomous navigation sensors.

The invention discloses a three-dimensional visible testing system of a dynamic water grouting model. The testing system comprises a test bench, a grouting system, a water supply tank and a water receiving tank. The test bench is composed of six side walls connected by modular bolts, a toughened glass box is placed in the test bench and clings to the inner wall of the test bench, and the diffusion state of slurry can be dynamically observed through the toughened glass; the grouting system is composed of an air compressor, a pressure bearing cylinder and a grouting pipe, and stable grouting pressure is provided by air pressure; the water supply tank is used for providing a dynamic water environment for the model test. Meanwhile, the invention also discloses a testing method of the system. The three-dimensional visible testing system and method of the dynamic water grouting model researched in the invention can be used for simulating grouting in a dynamic water environment under a visible condition. Compared with previous research, the system is used for successfully simulating the grouting in the dynamic water environment under the visible condition, thereby obtaining relative conclusions more conforming to engineering practice.

The invention provides an autonomous navigation simulation test system based on an earth-sun-moon integrated sensor. The earth-sun-moon integrated sensor is installed on a second single-axle rotary table to acquire measuring signals of the earth, the sun and the moon and send the signals to a navigation computer; a first single-axle rotary table drives an earth simulator, the second single-axle rotary table and the earth-sun-moon integrated sensor to rotate at a satellite track speed so as to simulate the self-rotation movement of a satellite; the second single-axle rotary table drives the earth-sun-moon integrated sensor to rotate so as to simulate the star rolling gesture; a gesture track simulator calculates the satellite gesture track and sends satellite reference track gesture data to a control computer; the control computer generates a track angular speed instruction according to the reference gesture track data to drive the first single-axle rotary table, generates a string width instruction to control the string width of the earth simulator and generates a rolling angle instruction to drive the second single-axle rotary table top rotate; and the navigation computer carries out navigation filter calculation according to the measuring signals, acquires the satellite position estimated value and the speed estimated value, and acquires the navigation precision by comparing the values with the reference data.

The present invention discloses a parking pilot system and method. The system of the present invention comprises a display, at least one image sensor, at least one speed sensor and an ECU. The ECU uses the images captured by the image sensor to calculate an intended parking position and uses the captured images and the detected speed to work out the coordinates of the current position and the intended parking position. The ECU also works out an initial parking position. According to the adopted parking mode, the ECU presents on the display a forward pilot track extending from the current position through the initial parking position to the intended parking position, or a forward pilot track extending from the current position to the initial parking position. Then, the driver can easily park his vehicle and effectively avoid collision via the pilot instructions presented on the display.

An energy conversion system is provided for converting heat energy from a variety of heat sources to electric power for operating electrical appliances. The system may be incorporated in a power on demand pilot system of a gas operated equipment to provide the sole electric power for operating the equipment. Thermoelectric modules provide the basic transducer for converting the heat energy to electric power and a heat pipe is employed for conducting the heat energy from a heat source to the conversion system.

An ultrahigh pressure true three-dimensional non-uniform loading/unloading and steady pressure model test system in which an ultrahigh pressure true three-dimensional non-uniform loading/unloading device is arranged in a combined bench counterforce device and used for carrying out ultrahigh pressure true three-dimensional loading/unloading on a test model, and an intelligent hydraulic loading/unloading and steady pressure numerical control system is connected with the ultrahigh pressure true three-dimensional non-uniform loading/unloading device via a high-pressure oil pipe; the ultrahigh pressure true three-dimensional non-uniform loading/unloading device is controlled in a digital servo manner via an input instruction of the intelligent hydraulic loading/unloading and steady pressure numerical control system to carry out ultrahigh pressure true three-dimensional gradient non-uniform loading/unloading and steady pressure control; an automatic model displacement test system automatically acquires the displacement of any part inside the model; and a high-definition multi-probe peeping system observes a cavern excavation deformation and failure process dynamically in real time.