47 results about "Ground start" patented technology

A hybrid surge protector for a network interface device (NID) is disclosed. The hybrid surge protector includes a fail-safe spring connected to the ground electrode of a three-electrode gas tube. Tabs on the fail-safe spring are held away from the gas-tube end electrodes by a fusible element. The hybrid surge protector also includes metal-oxide varistor elements (“MOVs”) in contact with the gas-tube end electrodes and with the ground electrode via an MOV spring. This arrangement provides for two initial paths to ground-one path from the gas-tube end electrodes to the ground electrode through the gas tube, and another from the gas-tube end electrodes to the ground electrode through the MOVs and the MOV spring. The dominant path to ground starts as the MOV ground path but switches to the gas-tube path as the gas tube becomes activated. Another path to ground via the fail-safe spring is also available should the gas tube overheat. A surge protection module that includes the hybrid surge protector is also disclosed.

An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages.

The invention discloses a method and device for controlling flat ground starting of a vehicle and the vehicle. The method includes the steps that accelerator pedal signals, brake pedal signals, the current engine rotating speed and hill signals of the vehicle are obtained; the target axle speed of a clutch is determined according to the accelerator pedal signals, the brake pedal signals, the current engine rotating speed and the hill signals, and the current axle speed of the clutch is further obtained; a target axle speed processing mode of the vehicle is determined according to the current axle speed of the clutch and the target axle speed of the clutch, and the target engine rotating speed corresponding to the target axle speed processing mode of the vehicle is obtained; and the increment of torque transmission of the clutch is worked out according to the current axle speed of the clutch, the target axle speed of the clutch, the accelerator pedal signals, the current engine rotating speed and the target engine rotating speed, and the clutch engaging position is determined according to the increment of torque transmission of the clutch. By means of the method, starting smoothness is improved, starting impact is reduced, abrasion to the clutch is lowered, and therefore user experience is improved.

The invention relates to a starting control method for a driverless caterpillar. The method comprises the steps that driving parameters of the driverless caterpillar are collected, the ramp slope and real-time ramp heading of the caterpillar on a ramp are calculated, and planning parameters of an upper computer planning system are obtained; on the basis of the collected driving parameters and the obtained planning parameters in the last step, autonomous recognition of starting working conditions is conducted; according to the autonomously recognized starting working conditions, corresponding starting control strategies are adopted for conducting starting of the caterpillar. An autonomous recognition method for the three working conditions of flat ground starting, in-situ steering starting and ramp starting is provided, starting control strategies corresponding to the three working conditions are provided, the slipping frictional power of a clutch is reduced in the control method, and the service life is prolonged. Accordingly, the starting problem of the driverless caterpillar is solved, the driverless demand of the caterpillar can be met, and the maneuverability of the caterpillar is brought into full play.

The invention relates to a dual-mode gas generating device and a dual-mode gas generating method. The device comprises a gas cylinder assembly, an air stop and pressure reducing valve, a fuel oil storage tank, a fuel oil stop and control valve, an air control valve, a gas generator and a control system; gas in the gas cylinder assembly is output in two paths through the air stop and pressure reducing valve, one path of gas is output to the fuel oil storage tank, and the other path of gas is output to the gas generating device through the air control valve; and the fuel oil storage tank is communicated with the gas generator through the fuel oil stop and control valve. The device solves the technical problems that the conventional gas generating device can only be used once, has high cost and is complex to maintain; and when the device is used as a flight emergency power source, the device provides power for ground start of an auxiliary system, so that the system is simplified.

The invention relates to a fully automatic biomass gasification boiler indoor constant temperature system with reasonable structure, energy saving and environmental protection. Set the indoor temperature and the system can detect the set temperature and automatically start and shut down the boiler. The indoor constant temperature system solar water heater and the fully automatic biomass gasification boiler complement each other. When the solar water temperature reaches the set temperature, the fully automatic gasification boiler automatically shuts down and uses solar energy for heating. When the solar water temperature is lower than the set temperature, the boiler automatically starts Combustion supplements the temperature of solar energy. When the indoor temperature is higher than the set temperature, the indoor constant temperature system automatically shuts down the solar energy and gasification boiler, starts the underground water cooling system, and installs a floor-temperature air conditioner. The water is circulated during heating and does not need to be discharged. There are conditions for cooling. The water can be treated and used as domestic water or industrial water. It does not occupy underground water resources. The circulating water in the ground temperature air conditioner is not polluted. It just uses the temperature of the water to reduce the indoor temperature.

An engine starting apparatus and method may allow for two methods of engine start where only one engine gearbox accessory pad exists off the aircraft engine. A gearbox lubricating apparatus may also be provided to lubricate the gearbox at altitude without added complexity. Two engine starting inputs (for example, one input for ground start and one input for in-flight engine start) are provided while avoiding complex gearbox designs. Clutches may also be used to prevent the starter gearbox from continuous operation (rotation) after the engine has started. Apparatus and methods are also provided for improving the air-fuel combustion of the hot-gas turbine start input (for in-flight engine start) to minimize the build-up of solid carbon (soot) in and around the combustor and turbine nozzle flow passages.

The invention provides a landing automatic flameout system for an unmanned helicopter, belonging to the technical field of the unmanned plane. The system is characterized by comprising a contact switch, a safety switch, an insulating strip and a weight, wherein the contact switch and the safety switch are connected in series with a flameout wire of an engine of the unmanned helicopter; the contact switch is used for detecting a landing state of the unmanned helicopter; the safety switch is used for ensuring that the system just starts to work after the unmanned helicopter takes off; and when the unmanned helicopter lands, the contact switch is closed due to pressure, the engine automatically flames out instantly because of short circuit of a flameout circuit. The landing automatic flameout system simultaneously considers the problems of engine ground start and landing automatic flameout of the unmanned helicopter, and can realize automatic flameout of the unmanned helicopter safely, simply and reliably.

The invention relates to an automatic flameout system of an unmanned helicopter after landing, belonging to the technical field of unmanned aerial vehicles. The automatic flameout system of the unmanned helicopter after landing is characterized in that the system comprises pressing contact switches, a safety switch, an insulating strip and a weight, wherein the safety switch consists of a base and two metal reeds, the pressing contact switches are used for detecting the landing state of the unmanned helicopter and comprise a left front side pressing contact switch, a left rear side pressing contact switch, a right front side pressing contact switch and a right rear side pressing contact switch, and after the pressing contact switches are connected in series, in parallel or in series parallel, the pressing contact switches are connected with the safety switch and an engine flameout line; when the unmanned helicopter takes off, the insulating strip is drawn out by the weight from the safety switch, the safety switch is turned on, the pressing contact switches are turned off and the system is started; and when the unmanned helicopter is landed, the pressing contact switches are pressed and are turned on, and an engine is flamed out immediately because the entire flameout line is short-circuited to the ground. The automatic flameout system of the unmanned helicopter after landing simultaneously considers the engine ground startup, the air flight and the landing of the unmanned helicopter and can simply and reliably realize the automatic flameout of the unmanned helicopter after landing.

Described is a method for the trenchless underground laying of pipes. According to said method, a shield tunnel boring machine and then subsequently pipes are driven through the ground starting from a starting shaft. The shield tunnel boring machine produces a borehole whose diameter is slightly greater than the outer diameter of the pipes. The annular space between the borehole wall and the pipes thereby obtained is filled with a supporting and lubricating agent. During advance, a continuous and periodical examination of the composition of the ground is carried out in the area of the shield tunnel boring machine or the first pipe following the shield tunnel boring machine or the first lubricating point. Depending on the result of the examination, the ground in the examined area is sealed off and / or solidified by a sealing and / or solidifying agent and / or the composition of the supporting and lubricating agent is adjusted.

The invention provides an inspection instrument for a ground starting system of a plane engine and comprises a self-checking module, a liquid crystal module, a keyboard module, a communication module, a micro-processor, an isolation module, a DDS module, a conditioning module, an amplitude control module, a power module, an output module, a switching value input module, a switching value isolation module and a LED indication module. The DDS technology can be adopted to produce frequency source, the frequency and the amplitude of which can be adjusted continuously; with the control of each module and connection with crystal display, keyboard input, etc., a menu-type man-machine dialog interface can be realized; therefore, the signal quality can be improved and the operation of the instrument can be simplified.

The invention discloses a hydraulic jacking inverted-installing device for a reducing tower and a hoisting method thereof. The hydraulic jacking inverted-installing device for the reducing tower and the hoisting method thereof comprises a tower foundation, wherein a tower base plate is arranged on the tower foundation, a hydraulic station is arranged on the side edge of the tower foundation, an oil circuit distributor is arranged on the upper portion of the tower base plate, and a plurality of lifting devices are arranged around the oil circuit distributor. The hydraulic station is connected with the oil circuit distributor through an oil tube, the oil circuit distributor is connected with the lifting devices through an oil distributing pipe, and the side edges of the lifting devices are connected with expansion rings. The outside of the expansion rings are connected with wall plates, and wall plates to be welded are arranged on the wall plates. A hydraulic jacking inverted-installingmethod is adopted for installation, assembly is carried out on the ground starting from the top of the tower, assembly of a section then lifting, assembly of next section is carried out on the ground,so circular, the operation is easy, the use is convenient, and the good using effect is obtained.

A hybrid surge protector for a network interface device (NID) is disclosed. The hybrid surge protector includes a fail-safe spring connected to the ground electrode of a three-electrode gas tube. Tabs on the fail-safe spring are held away from the gas-tube end electrodes by a fusible element. The hybrid surge protector also includes metal-oxide varistor elements (“MOVs”) in contact with the gas-tube end electrodes and with the ground electrode via an MOV spring. This arrangement provides for two initial paths to ground-one path from the gas-tube end electrodes to the ground electrode through the gas tube, and another from the gas-tube end electrodes to the ground electrode through the MOVs and the MOV spring. The dominant path to ground starts as the MOV ground path but switches to the gas-tube path as the gas tube becomes activated. Another path to ground via the fail-safe spring is also available should the gas tube overheat. A surge protection module that includes the hybrid surge protector is also disclosed.

The invention belongs to the technical field of design of aircraft engines, and provides a method for controlling ground start of an engine under oil-rich state by using a temperature control system. The method comprises the following steps of controlling oil combustion and ignition of the engine, then continuously monitoring the indication temperature and HPC (high performance computing) rotating speed of a temperature indicator, when exhaust gas temperature of a turbine is indicated to reach 380-400 DEG C, limiting oil supply of an oil supply pipeline of the engine for one minute, then normally supplying oil for one second, and repeating for three to four times; and (2) carrying out the repeated oil supply operation of the oil supply pipeline of the engine in a pulse mode of 'limiting-normal operating'by using the method if the exhaust gas temperature of the turbine still increases after the work is completed till observing the decreasing state of the exhaust gas temperature. When the engine is subjected to ground start under specific environment condition, with the adoption of the method, the exhaust gas temperature of the turbine of the engine can be effectively inhibited, and thus the effects of normally starting the engine and protecting the engine are achieved.

Stair elements installed on sloped ground starting bottom up and using a riser reversibly secured with a clamping mechanism. Each riser is attached to a corresponding tread at the time of installation. The manner of fixing the riser to the tread permits the relationship between the two to be adjusted for angle and position.

Dampers for bearing assemblies of gas turbine engines are provided. For example, a damper comprises a damper housing, a lubricant passage defined in the damper housing, and a valve positioned within the lubricant passage. The lubricant passage includes an inlet and an outlet. In one embodiment, the valve is configured to restrict a flow of lubricant from the inlet into the damper when a reference temperature is below a threshold temperature. In another embodiment, the valve is configured to increase leakage of a lubricant through the outlet when a reference temperature is below a threshold temperature. In other embodiments, the valve is passively actuated and is configured to move within the lubricant passage to control a flow of lubricant from the inlet to the outlet based on a reference temperature.

The invention discloses a giant plane ground starting device which comprises a turboshaft engine, a centrifugal compressor and an alternating-current generator, wherein the turboshaft engine is used for outputting power; the centrifugal compressor is connected with the turboshaft engine and is used for supercharging the input air under the driving of the power output by the turboshaft engine and supplying the supercharged air to giant planes so as to realize multiple synchronous starting of the giant planes; the alternating-current generator is connected with the turboshaft engine and is used for converting the power output by the turboshaft engine into electricity and supplying the electricity to the giant planes for charging. According to the giant plane ground starting device, an airborne auxiliary power plant is removed, and thus the multiple starting of the giant planes is realized; the structure of the starting system of the giant plane is simplified, and thus the cost is reduced; airborne fuel is saved, the service life is long, and the economical efficiency is good; the maintenance is convenient, the giant plane ground starting device can be maintained on the ground or in a room and does not need to be disassembled and assembled or maintained on the giant plane; the range of application is wide, the giant plane ground starting device can start a carrier-borne aircraft and can also start a combustion gas turbine on a warship; the dead weight during the flight is reduced, and the tactical and technical index is improved.

The invention relates to a multistage amplification swinging type omnidirectional impending earthquake alarm, which can generate an alarm in the situation that the ground starts to slightly swing before the impending earthquake in a mechanical multistage amplification manner. The alarm is composed of a machine outer casing and a lower base seat, a machine internal part device frame, a X-shaped base seat connected under the device frame and used for increasing the swinging, a plurality of groups of two-stage amplification swinging soft spring supporting frames and soft spring swinging contact head balls arranged on the device frame, a plurality of groups of circuit contact heads, a plurality of groups of circuit contractors, an alarm generator, a battery pack and a transformer, etc. The device is characterized in that the stratum slightly swings when a large earthquake impends, the alarm enables the swinging to be increased through three-stage physical transfer, automatic alarm is realized through closing a swing triggering alarm circuit after being enlarged, so as to remind the people to avoid immediately. The alarm has the advantages that the alarm is amplified by adopting the physical principle, and is fearless of being moistened; the service life of the alarm is longer; an amplification swing device is arranged aiming at five directions of left, right, front, rear and underground; an impending earthquake slight swinging wave from different directions can be detected; and the alarm scope of slight swinging can be adjusted, etc. The alarm is applied to families, schools, enterprises and institutions, and can form an impending earthquake automatic alarm system in a county town or an area through combing a plurality of alarms.

The invention relates to an arc suppression coil control method and system. The method comprises the following steps of sampling a neutral point voltage of an arc suppression coil with a certain frequency to acquire the neutral point voltage; judging that a grounding fault occurs if the neutral point voltage conforms to a preset numerical value constraint condition and the duration of conforming to the preset numerical value constraint condition reaches a preset time threshold value, wherein the preset numerical value constraint condition is set according to the maximum value of a grounding starting voltage and the neutral point voltage; and outputting a control signal to a silicon controlled control circuit to start the arc suppression coil for compensation when the grounding fault occurs.

Stair elements installed on sloped ground starting bottom up and using a riser reversibly secured with a clamping mechanism. Each riser is attached to a corresponding tread at the time of installation. The manner of fixing the riser to the tread permits the relationship between the two to be adjusted for angle and position.

The invention discloses a gas generator for a military aircraft. The gas generator comprises a gas cylinder, an air combined reducing valve, an air control valve, a fuel oil bottle, an exciting device, a gas generator, an ignition plug, a fuel oil control valve, a high-pressure sensor, a temperature sensor, a low-pressure sensor and the like. The gas generator can achieve two functions, working media are easily accessible air and aircraft fuel, two required working-condition gases can be output, a ground starting auxiliary power system of the military aircraft is realized, stable gas output is provided, and 'Bang-Bang' pulsed gas output is provided in case of a flight emergency.

A comparator-based switchmode power converter monitors the most negative of the tip and ring line voltages, to control the supply voltage to a SLIC. The voltage applied to the SLIC's power terminals is slightly higher than the sensed voltage for different loop signaling conditions, including loop start, ground start balanced ringing. The switchmode converter includes a comparator coupled to a DC-DC output node downstream of a MOSFET switch installed in a DC supply rail of a source of DC supply voltage, and coupled to a power supply terminal of the SLIC. The comparator is also coupled to a set point node, which is coupled through a voltage offset path to each of tip and ring portions of the telephone line. The comparator functions to control the conductivity of the MOSFET to provide a modulated DC voltage to the SLIC, in accordance with that one of tip and ring loop voltages having the largest magnitude, so as to provide power supply tracking during loop current, superimposed voice signals, loop start, ground start and balanced ringing.

A communication card including a card substrate, a power interface adapted to receive power from a power source and distribute it to elements mounted on the card substrate and a ground start detection circuit on the card substrate. The card additionally includes an active current regulating circuit adapted to receive electrical power through the power interface, regulate a provided current responsive to the received electrical power and provide the regulated current to the ground start detection circuit.

The invention discloses a data wireless replacement method based on a train operation monitoring and recording device, which reduces manual participation in LKJ data replacement, improves data replacement efficiency, reduces work intensity, and prevents wrong replacement, missed replacement, and early replacement. The technical solution is as follows: the on-board data file is transmitted to the cache of the on-board data replacement module through the wireless network; the on-board data replacement module simultaneously sends the ready status to the ground system and the on-board display to request online update of the on-board data; manually starts on the on-board display The online update process or the ground change control personnel use the ground to start the online update; the wireless communication module obtains the identification number of the vehicle-mounted host plug-in configured on the ground, and automatically compares it with the number of the vehicle-mounted host plug-in. Only when the comparison is consistent can the process continue Online update process until the update is complete.

The invention discloses a reverse charging resisting device for an aircraft ground starting power supply. The reverse charging resisting device consists of an aerospace ground power supply, a reverse charge resisting device and an aircraft, wherein the reverse charge resisting device consists of a spiral diode, an aircraft end connecting device, a ground power supply end connecting device and a radiator. The reverse charging resisting device has the beneficial effects that 1, the reverse charging resisting device is small in size, simple in structure, and convenient to detach and maintain; 2, no movable electric contact component is adopted, so that the working reliability of a system is enhanced greatly, the service life of the system is prolonged greatly, the service lives of an airborne generator and an airborne storage battery are prolonged, and the flight safety is ensured at the same time; and 3, damage to the airborne generator caused by a voltage difference during startup operation of the aircraft is avoided, the defects of high cost, low reliability and short service life in an original differential under-voltage relay are overcome, and the reverse charging resisting device is mainly applied to charging operations of large-sized aircrafts. Through adoption of the reverse charging resisting device, the equipment cost of the aircraft ground starting power supply is reduced greatly. The reverse charging resisting device is suitable for starting and ground power-on checking operations of various helicopters and small and medium-sized fixed wing aircrafts.

A ground mobile direct strike lightning protection system, including lightning monitoring and early warning system, lightning receiving device, lifting system, grounding system and automatic control system; the lightning monitoring and early warning system monitors the atmospheric electric field environment around special vehicles in real time; the automatic control system is based on The monitoring data of the lightning monitoring and early warning system activates the corresponding level of early warning; according to the situation, it sends a rising or falling signal to the lifting system and the lightning receiving device, and sends a grounding start signal or an end grounding signal to the grounding system; Stand upright to enter the direct lightning lightning receiving mode or fold down to put it away; the lifting system rises or falls according to the received signal; the grounding system quickly and reliably grounds or withdraws special vehicles that are in the process of moving or temporarily parked in the field. The invention can provide effective direct lightning protection for special vehicles in the process of moving or under the condition of temporary parking in the field.