405 results about "Ullage" patented technology

A fuel system for a hydrogen fueled gas turbine engine comprises a main hydrogen fuel storage unit configured to store liquid hydrogen. The main fuel storage unit comprises an ullage space configured to store ullage fluid comprising gaseous or supercritical hydrogen. The system further comprises a liquid hydrogen drain line configured to provide liquid hydrogen from the main hydrogen fuel storage unit to a fuel conduit, the fuel conduit being configured to supply hydrogen fuel to a combustor of the gas turbine engine. A priming line is provided, which is configured to provide ullage fluid to the fuel conduit, and a priming valve is configured to selectively control flow through the priming line.

The invention relates to the technical field of aviation, and discloses a gas compressor and an engine, and the gas compressor comprises a casing, a rotor blade and an adjusting unit. By arranging the adjusting unit, the adjusting unit can control switching between the communicating state and the non-communicating state between the first cavity and the second cavity in the casing, that is, when the rotating speed of the gas compressor is the medium-low rotating speed, the adjusting unit controls the second cavity to be in the first state, and the adjusting unit controls the second cavity to be in the non-communicating state; and the air flow blocked between the blade tip part and the inner wall of the casing flows into the second cavity, so that the surge phenomenon of the air compressor is avoided, and the technical effect of improving the working performance of the air compressor is achieved. When the rotating speed of the gas compressor is high, the adjusting unit controls the second cavity to be in the second state, the second cavity is closed, and the situation that friction between gas flows is increased due to existence of the second cavity can be avoided, so that energy loss in the gas compressor is reduced, and heat insulation efficiency of the gas compressor is prevented from being reduced; and therefore, the technical effect of reducing the oil consumption of the engine and the oil consumption of the engine is achieved.

The invention belongs to the technical field of aviation equipment industry, and particularly relates to an electric power inspection unmanned aerial vehicle which comprises an unmanned aerial vehicle body, a high-definition camera, a temperature sensing variable resistance plate, a flaming foreign matter removing mechanism, a load reduction feedback mechanism, a rotor rotating speed self-adjusting compensation mechanism, a lubricating state visual display mechanism and a PLC. The rotor speed of the unmanned aerial vehicle can be automatically adjusted based on the environment temperature and the condition that the load of the unmanned aerial vehicle is reduced due to fuel consumption in the use of the flaming mechanism, the flight stability of the unmanned aerial vehicle is ensured, and the situation that the unmanned aerial vehicle is more sensitive to airflow and wind direction changes due to excessive lift force can be avoided; according to the method, the problem that the flight stability is influenced due to the fact that the lubricating oil loss condition in the flight process of the unmanned aerial vehicle can be automatically calculated is solved, so that workers can arrange the maintenance time more reasonably, and unnecessary premature maintenance or too late maintenance is avoided.

The invention relates to the technical field of sealing test, in particular to a sealed cabin heating system for high-temperature rotary dynamic sealing test and a test device. The device comprises a sealed cabin, a circulating pipeline is connected between a liquid inlet and a liquid outlet of the sealed cabin, and a circulating pump and a heater are mounted on the circulating pipeline; a high-level tank is further connected to the circulating pipeline so as to supplement liquid into the circulating pipeline when the liquid in the circulating pipeline is lost; the circulation pipeline or the sealed cabin is connected with a pressure relief pipeline, and a sealing valve is installed on the pressure relief pipeline. According to the invention, the burden and energy consumption of the heater are reduced, and the method also has the advantages of high medium temperature rise rate, short regulation time efficiency and high precision.

The invention relates to a wheel and paddle coaxial amphibious robot and a using method thereof, and belongs to the technical field of robot aircrafts. Comprising a fuselage, four deformation modules, connecting rods and an air-ground execution mechanism, the four deformation modules are evenly arranged on the fuselage, the deformation modules are connected with the air-ground execution mechanism through the connecting rods, and the deformation modules are used for controlling position change of the air-ground execution mechanism, so that conversion between a land mode and an unmanned aerial vehicle mode is achieved. The coaxial design that the wheel motor directly drives the wheel is adopted, compared with other gear transmission and synchronous belt transmission for driving the wheel, errors and friction loss caused by transmission are avoided, and meanwhile the situation that the mass is reduced due to the use of a bearing is avoided; the design of the channel in the center of the sleeve further provides convenience for line arrangement of the blade motor, and the problem of line winding is effectively solved through the fixing mode of the blade motor base.

The disclosure relates to a system that includes a vehicle, a cryogenic container mounted on the vehicle, and an ancillary system for filling the cryogenic container with cryogenic fluid. The ancillary system includes a filling line routed into the cryogenic container and a filling coupling. The cryogenic container is fillable via the filling line. The system may also include a ullage tank for setting a hold time more precisely.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a fuel cell stack auxiliary power unit (APU) and a first tank arranged to store liquid hydrogen with an ullage. A first fuel line includes a first pump and a first vaporiser and transports hydrogen from the first tank to combustion apparatus of the engine during operation of the propulsion system. A second fuel line includes a second fuel pump and a second vaporiser and transports hydrogen from the first tank to the fuel cell stack APU. A duct connects the second fuel line at a position thereon between the second vaporiser and the fuel cell stack to the ullage of the first tank, providing for pressure in the first tank to be maintained therein as liquid hydrogen within the first tank is depleted, thus avoiding cavitation of liquid hydrogen within the first fuel pump.

The retracting and releasing mechanism comprises a retracting and releasing bin, a propeller body is connected to the interior of the left side of the retracting and releasing bin, a propeller is connected to the bottom of the propeller body, and a bin door is rotationally arranged at the bottom of the right side of the retracting and releasing bin through a rotating shaft; the fixed column is installed on the inner wall of the rear side of the collecting and releasing bin, the outer side of the fixed column is sleeved with a circular plate, and the circular plate is slidably connected with spray pipes used for cleaning at equal angles; and the rotary cleaning mechanism is arranged on the rear side of the collecting and releasing bin and on the circular plate, and the rotary cleaning mechanism cleans the propeller by driving a spray pipe to move and rotate, so that corrosion loss caused by seawater and attached microorganisms is reduced. According to the retracting and releasing mechanism for the lifting type thruster, after the thruster is retracted, the spraying pipe can be driven to blow air to remove water from a propeller of the thruster in a rotary opening and closing mode, and then corrosion loss of the thruster caused by seawater and attached microorganisms is reduced.

The invention belongs to the field of aero-engines, and discloses a low-pressure casting process design method for a fuel regulator and the fuel regulator. According to the method, modeling is conducted on the fuel regulator to obtain a three-dimensional model of the fuel regulator; based on the three-dimensional model of the fuel regulator, numerical simulation is conducted on the liquid lifting, mold filling and cooling solidification processes of the casting to predict metallurgical defects of the casting, the metallurgical defects of the casting are analyzed, and a simulation result is obtained; and optimizing low-pressure casting process parameters or / and a process based on an analog simulation result to finally obtain a low-pressure casting process optimization scheme of the fuel regulator. By adopting the method, the forming quality of the complex casting is improved, the blindness of trial-manufacturing depending on experience in the traditional process is reduced, and the product percent of pass is improved while the research and development period is shortened; and the cost loss caused by defect repair is greatly reduced, and a systematic process guarantee is provided for efficient and precise manufacturing of the aero-engine fuel regulator.

The invention relates to the technical field of undercarriages, in particular to a folding undercarriage device of a low-altitude aircraft, which comprises an aircraft body, a pesticide spraying mechanism for crop fertilization is arranged on the aircraft body, a height-adjustable undercarriage mechanism is arranged at the lower end of the aircraft body, and a landing buffer mechanism is arranged on the undercarriage mechanism. The landing buffering mechanism is used for reducing impact on the undercarriage mechanism at the moment of landing, a linkage auxiliary mechanism is arranged on the aircraft body, the undercarriage mechanism comprises a fixing plate body, and the fixing plate body is detachably installed on the aircraft body. By arranging the undercarriage mechanism and adopting a dynamic folding design, after taking off, the second-stage frame body retracts to drive the telescopic joint to be shortened, so that the overall height is reduced, air turbulence during flight can be effectively reduced, meanwhile, the first-stage frame body rotates to be parallel to the fuselage, the cross sectional area of the undercarriage mechanism is greatly reduced, and the overall height is reduced. And the wind resistance loss during high-speed flight can be obviously reduced.

The utility model provides an evaporator heat pump direct expansion dehumidification device, which relates to the technical field of industrial dehumidification, a dehumidification component, which includes at least two stages of wheels connected by cavities and an air inlet duct connecting the moisture absorption areas of the multi-stage wheels and an exhaust duct connecting the dehumidification areas required by the wheels; and a heat recovery component, which includes an evaporator installed in the corresponding wheel front air inlet cavity and a condenser installed in the last stage and away from the remaining wheel cavities, a pipe loop with built-in refrigerant is formed between the condenser and the corresponding evaporators of each stage, and the refrigerant absorbing heat in the pipe refluxes to heat the condenser; the refrigerant absorbs the heat of the first-stage evaporator and the second-stage evaporator and flows to the condenser in the form of gas, the condenser transfers heat to the exhaust air, and the refrigerant flows to the first-stage evaporator and the second-stage evaporator again to absorb heat, so that the heat of the fresh air and the return air is fully utilized to dehumidify the regeneration area of ​​the wheel, and the energy loss required for heating the regeneration area of ​​the wheel is greatly reduced.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

The present application discloses a planar transformer, which relates to the technical field of transformers, and includes a magnetic core and a plurality of PCB boards; the magnetic core includes a base, a column and a cover; both ends of the top of the base have vertical plates, and an installation space is formed between the two vertical plates; the column is fixedly installed on the top of the base, the axis of the column is vertical, and the column is centered in the installation space; the cover is arranged on the top of the base, and the cover and the base are detachably connected; after the cover is connected to the base, the cover contacts and abuts against the top of the column; a clearance opening is opened at the center of the PCB board, and after the PCB board is installed on the magnetic core, the two ends of the PCB board extend out of the outside of the two openings of the installation space respectively. The present application has a small space occupancy rate, a low heat exchange loss and a good secondary leakage inductance, thereby making the application of planar transformers more extensive.

The invention discloses a low-resistance bonding ceramic tube coating material and a coating method thereof, and relates to the field of steel tube coatings, and the low-resistance bonding ceramic tube coating material comprises a bottom layer material, a ceramic hybrid layer material and a hydrophobic functional material. According to the low-resistance bonding ceramic tube coating material and the coating method thereof, through coating of the bottom layer material, the ceramic hybrid layer material and the hydrophobic functional material, a coated steel tube can have natural resistance to corrosive media such as acid, alkali and salts, and even under the long-term complex working condition, the corrosion resistance of the steel tube is greatly improved. The roughness of the inner wall of the pipe can still be stably maintained within the range of 20-100 microns, the surface smoothness is 5-20 times that of a traditional pipe in the initial service stage, the friction coefficient of fluid and the pipe wall can be greatly reduced, the fluid can more easily form a laminar flow state, energy loss is effectively reduced, and the service life of the pipe is prolonged. And the composite material can be applied to the fields with extremely high requirements on energy consumption and stability, such as ships, airplanes, high-speed rails, ocean engineering, petrochemical engineering, sewage treatment, long-distance water delivery and the like.

A propulsion system comprises a propulsive hydrogen-burning gas turbine engine, a first tank storing liquid hydrogen with an ullage and a first fuel line including a fuel pump and a vaporiser, the first fuel line providing gaseous hydrogen to the engine during operation of the system. A second tank storing gaseous hydrogen is coupled by a second fuel line to the first fuel line at a position thereon between the vaporiser and the engine, providing for engine start-up (when the vaporiser is inoperative) and power-boosting during operation of the system. A duct connects gaseous hydrogen within the second tank to the ullage in the first tank in order maintain pressure in the first tank as liquid hydrogen within it is depleted, preventing cavitation of liquid hydrogen within the fuel pump.

The invention relates to the technical field of control boxes, and discloses a main control box based on industrial control, which comprises a box body, an aviation socket arranged on one side of the box body, jacks annularly formed in the aviation socket, contacts arranged in the jacks, mounting seats arranged in the jacks, contacts arranged at the top of the mounting seats, and plugs arranged on the aviation socket, the plug is arranged in the box body, the contact pins are arranged on the plug, the devices are arranged in the box body, and the cleaning component is arranged in the jack. When the cleaning part works, extra power is not needed, the contact pin cleaning part is driven to rotate along the spiral hole through mechanical thrust generated when the plug is plugged in and pulled out, linear motion is converted into rotary scraping, cleaning while plugging is achieved, and the problems of energy consumption and structure complexity of a traditional active cleaning scheme are solved. By scraping dust and an oxide layer in real time, the fluctuation of contact resistance can be effectively controlled, and compared with a traditional aviation socket, the electric conduction loss and the heating risk are remarkably reduced.

The invention relates to the technical field of mooring unmanned aerial vehicles, in particular to a hydrogen power mooring unmanned aerial vehicle which comprises a sky end and a ground end, a pipeline is arranged between the sky end and the ground end, and the pipeline is used for conveying fuel at the ground end to the sky end; the sky end comprises an aircraft, a fuel cell stack is fixedly mounted at the lower end of the aircraft, an avionics bin is fixedly mounted at the position, located at the lower end of the aircraft, of one side of the fuel cell stack, and a hydrogen receiving opening is formed in the lower portion of the fuel cell stack. The high-pressure hydrogen in the hydrogen cylinder just reaches the working pressure when reaching the fuel cell stack after passing through the pressure reducer at the ground end and the on-way pressure drop of the pipeline; the problems that a traditional mooring unmanned aerial vehicle with a hydrogen fuel cell energy storage system and an electric pile at the ground end is powered by a high-voltage direct-current or alternating-current cable, so that power transmission loss is large, and the weight of the cable is high are solved.

The invention relates to the technical field of gas storage, in particular to a storage device. The storage device comprises a storage tank used for storing low-temperature liquefied gas; the shell part comprises a shell body and a connecting piece, a containing space is formed in the shell body, the saving box is located in the containing space, one end of the connecting piece is connected to the shell body, and the other end of the connecting piece is connected to the saving box; and the cooling part comprises a cooling pipeline, the cooling pipeline is wound around the exterior of the storage tank and the connecting piece, and a cooling medium is contained in the cooling pipeline. Based on the setting, the storage device provided by the embodiment of the invention can reduce the temperature influence of the external environment on the storage tank, prolongs the storage time of the storage tank for the low-temperature liquid gas, and is beneficial to reducing the loss of the low-temperature liquid gas.

The invention discloses an airfoil aerodynamic configuration adjusting method and device and a medium. Relates to the field of airfoil design, and solves the problems of high experiment cost and long iteration period caused by airfoil design optimization through a wind tunnel experiment. Geometric characteristics of the airfoil profile are converted into mathematical parameters through CST parameterization, airfoil profile performance data are rapidly obtained in combination with a preset selective neural network model, and the processes of physical model manufacturing, repeated blowing testing, CFD simulation, finite element analysis and the like in a traditional wind tunnel test are replaced. Hardware cost of wind tunnel equipment operation and maintenance, model processing and the like does not need to be invested, and material loss and time waste caused by physical model modification are also avoided. Besides, parameter disturbance, gradient optimization and geometric screening based on normal distribution are all realized through a computer algorithm, single-group parameter optimization can be quickly realized, and airfoil performance requirements under different working conditions can be quickly responded, while a traditional wind tunnel test needs several hours to several days for a single test, and the test needs to be rearranged after model modification.

The invention discloses an electromechanical multi-professional module integral lifting device and a construction method, and belongs to the field of lifting devices. The electromechanical multi-professional module integral lifting device comprises a moving seat, positioning frames are fixedly connected to the two sides of the top of the moving seat, the electromechanical multi-professional module integral lifting device further comprises a bearing bracket vertically sliding along the positioning frames, a lifting assembly is arranged on the moving seat, and the lifting assembly is used for pulling the bearing bracket to vertically slide along the positioning frames; the positioning block is fixed at the bottom of the movable seat, and the two sides of the positioning block are rotationally connected with movable wheels; through the repulsion effect of a magnetic plate and a piston plate and the arrangement of a first spring, circulating spraying of a lubricating agent is achieved, the friction effect borne by the lifting cable is reduced, the durability of the lifting cable is improved, the lifting safety is ensured, meanwhile, the situation that pollution is caused by dripping of excessive lubricating agent is avoided, recycling of the excessive lubricating agent is achieved, and the cost is reduced. The loss of the lubricant is effectively reduced, and the energy-saving effect is improved.

A system and method for warehousing barrels for maturing a spirit, comprising the application of a film layer to cover a first (e.g. upper) portion of the barrel, while leaving a second (e.g. lower) portion exposed. Such a configuration allows drainage / evaporation of liquid leaks from the barrel while inhibiting leakage and evaporation from the headspace, thereby reducing ullage. In one form a pallet having a solid / gapless deck is contacted with an end of an upright barrel. Weight from the pallet and / or a barrel stacked thereon creates a seal and further inhibition of vapour loss from the headspace while the spirit is matured over an extended time period.

The utility model relates to a high-strength stable type gear which comprises a gear body, air bags are fixedly connected in tooth grooves of the gear body, exhaust holes are formed in the side of the gear, air outlet holes are formed in the sides, close to the axis of the gear body, of the air bags, and sealing plates are connected to the sides, close to the outer portion of the gear body, of the exhaust holes. The side, away from the exhaust hole, of the sealing plate is connected with a ventilation pipe. The utility model relates to the technical field of gears. When the high-strength stable gear is used, the gear body is continuously meshed with the corresponding gear, so that the air bag is extruded, air flow can be quickly blown to a tooth groove, to be meshed, of the gear body, and then centrifugal force of the gear body is matched; and dust impurity particles and metal particles in the tooth grooves in the gear body are separated from the tooth grooves, so that the loss during meshing of the gear body and the gear is reduced, and the service life of the gear body is prolonged.

The eVTOL aircraft tail thrust motor connecting structure is characterized in that a motor support comprises a motor base of an annular structure, a motor is arranged on the motor base, and a propeller is arranged on the motor; the motor base comprises a first step, a second step is arranged at the front end of the first step, the thickness of the first step is larger than that of the second step, and a motor connecting edge connected with a motor is arranged at the rear end of the first step. Two receding grooves are formed in the inner wall of the motor base, a plurality of connecting ribs connected with the first step and the second step at the same time are arranged on the outer wall of the motor base, the rear half sections of the connecting stringers correspond to the connecting ribs in a one-to-one mode and are connected with the connecting ribs and the second step at the same time, and the front half sections of the connecting stringers are connected with a horizontal tail on the machine body. The invention has the beneficial effects of improving the damage safety, ensuring the stability of the thrust line, reducing the flight attitude fluctuation, reducing the maintenance cost, reducing the power loss of the motor, improving the cruising ability, reducing the stress of the connecting part, prolonging the service life of the structure and the like.

The invention discloses an adjustable assembly type geosyncline device which comprises a fixed support, a mounting table located above the fixed support, a lifting structure used for adjusting the distance between the mounting table and the fixed support and a driving mechanism used for driving the lifting structure to conduct adjustment. The lifting structure comprises an inserting groove formed in the upper portion of the fixed support and an inserting rod which is rotatably connected to the lower portion of the mounting table and inserted into the inserting groove with the inserting depth adjustable, the height adjusting device can meet the requirements of different ground environments, height adjustment is conducted according to the mounting heights of different wallboards, the requirements of various supporting heights are met, and the practicability is high. And on-site secondary adjustment can be carried out, so that the purposes of reducing the assembly time and reducing the loss of assembly materials are achieved, and high popularization value is achieved.

The invention relates to the technical field of aero-engine gas flow path sealing, and discloses a labyrinth type multi-stage brush type sealing device which comprises a rotor runway and a multi-stage brush type sealing structure. The rotor runway comprises a plurality of convex parts and a plurality of concave parts, and the convex parts and the concave parts are sequentially and alternately connected in the first direction to form a concave-convex structure; the multi-stage brush type sealing structure comprises a plurality of brush type sealing units, part of the brush type sealing units abut against the protruding parts, and part of the brush type sealing units abut against the concave parts. The multi-stage brush type sealing is arranged, so that the pressure resistance of the sealing device is improved; and meanwhile, the rotor runway forms a concave-convex structure through sequentially and alternately connecting a plurality of convex parts and a plurality of concave parts, and is matched with a multi-stage brush type sealing structure to form a labyrinth sealing effect, so that double sealing is formed, a leakage flow path is increased, leakage energy loss is effectively increased, the leakage amount is greatly reduced, and the sealing performance of the whole device is improved.

The application belongs to the technical field of aircraft deicing, and discloses a reconfigurable intelligent aircraft deicing system and method. The hidden deicing liquid nozzle unit sprays deicing liquid on different deicing yard areas divided by different pressure nozzle assemblies to perform aircraft engine deicing operation; the deicing detection unit adopts image recognition technology to collect the ice and snow coverage area, thickness and type of the aircraft body in real time, and determines the aircraft model and parking position; the deicing waste liquid detection unit detects the physical property parameters of the deicing waste liquid during deicing operation in real time; the intelligent control unit controls the flow, temperature, pressure and angle of the nozzle assembly with the same pressure in real time, so as to optimize the deicing efficiency; the deicing liquid supply unit, deicing liquid conveying unit and deicing liquid recovery unit jointly supply and recycle the deicing liquid without interruption. The application greatly improves the deicing efficiency of the aircraft, greatly avoids the possibility of secondary icing of the aircraft, and maximally avoids the invalid energy loss.

The present invention discloses a portable switch vibration dryer, which belongs to the technical field of vibration dryers. The key points of the technical solution are that it includes a base, a vibration seat, a lower material bin, a plurality of movable material bins and an upper material bin in sequence from bottom to top; the lower material bin is provided with a discharge port and an air inlet; the movable material bin includes an outer frame and a material tray arranged in the outer frame, the material tray is provided with a material discharge mechanism and a plurality of air vents, two vertical shafts are symmetrically arranged on both sides of the movable material bin, and a plurality of movable material bins are alternately rotated and connected to the two vertical shafts in sequence; the upper material bin is provided with a discharge port and an air outlet; the upper and lower ends of each outer frame are respectively provided with an upper sealing ring and a lower sealing ring. The portable switch vibration dryer has high discharge quality, low energy efficiency loss and is easy to be thoroughly cleaned.

The utility model relates to the technical field of fans, in particular to a fan balancing structure, which is characterized in that counter weight is adjusted through the design of circular array balancing columns on a disc, so that when an impeller rotates, dynamic balance can be ensured, the balancing precision is improved, and through the design of an arc-shaped gradually-expanded blocking wall along the disc, the balancing precision is improved. The width of the blocking wall is gradually increased in the rotating direction of the impeller, airflow can be guided to be smoothly transited to the air guide cavity from the containing cavity, impact between the airflow and the wall face of the volute and generation of local vortexes are reduced, turbulence noise is lowered, the airflow is prevented from flowing backwards into the containing cavity, vibration caused by collision between the impeller and the airflow is avoided, and dynamic balance of the impeller is guaranteed. Meanwhile, the divergent structure is matched with the airflow diffusion rule under the centrifugal force effect of the impeller, energy loss is reduced, and the fan efficiency is improved.

A multi-angle oil stirring loss test system for an aviation oil-cooled high-power high-rotating-speed motor comprises a pitch angle overturning test board, an upper computer control table, a cooling and lubricating system, a frequency conversion cabinet, a lubricating oil circulating system and a measurement and control cabinet, and the pitch angle overturning test board comprises an overturning angle control system, a bearing seat, a dragging system and a supporting frame. The system can accurately simulate the pitching flight attitude of an aircraft, exposes the heat dissipation and lubrication failure risk of the motor in advance, and guarantees the flight safety. The device has good vibration resistance and accurate angle control capability, and is adaptive to various motor cooling modes and types; and by adopting a modular design, the structure is simple, the maintenance is convenient, and data support can be provided for optimization and improvement of the aviation oil-cooled motor.

The present application discloses a steering device and its design method, a liquid level measurement system and method, relating to the technical field of liquid level measurement. The steering device includes a plane reflecting surface and a parabolic reflecting surface. The present application utilizes the combined technology of the plane reflecting surface and the parabolic reflecting surface to extend the parabolic focusing steering device technology that could only be used on vertical tanks to spherical tanks, sausage tanks and other special-shaped tanks, so that the main beam of the mechanical vibration wave emitted by the probe installed at any position and at any angle on the tank body all becomes a parallel beam without divergence loss and vertically shoots upward to the liquid surface in the tank, and focuses and reflects the liquid surface echo to the probe, increasing the intensity of the echo signal, achieving the effects of stable and accurate measurement of the liquid level in the tank, and moreover, the volume of the steering device can be reduced.