692 results about "Inlet channel" patented technology

The invention relates to a propulsion system, in particular to an air-breathing radio frequency ion electric propulsion system with mixed working medium power and a multi-mode working method thereof, and aims to solve the problems that an existing air-breathing electric propulsion system only takes atmosphere as a single working medium, the atmosphere trapping efficiency is low, and the performance of a spacecraft is affected. The device comprises a propelling and gas trapping unit, a radio frequency neutralizer, a power and control unit and a xenon storage and supply unit, the propelling and gas trapping unit comprises a radio frequency ion thruster and an atmosphere trapping gas inlet channel; the power and control unit comprises a direct current module, a control module and a radio frequency module; the xenon storage and supply unit comprises a xenon bottle and a valve and sensor assembly; the control module and the valve are electrically connected with the sensor assembly. The radio frequency ion thruster is electrically connected with the radio frequency neutralizer through the radio frequency module. The first output end of the xenon storage and supply unit is connected with the gas path input end of the radio frequency neutralizer, and the second output end of the xenon storage and supply unit is connected with the gas path input end of the radio frequency ion thruster.

The invention discloses a radial flow field bipolar plate and a fuel cell stack structure, and belongs to the technical field of fuel cells, the radial flow field bipolar plate comprises a bipolar plate body, two sides of the bipolar plate body are respectively provided with an anode side groove and a cathode side groove, the middle part of the bipolar plate body is provided with a cathode air inlet channel, and one side of the cathode air inlet channel is connected with a connecting cylinder; a plurality of anode rib plates which are distributed in a multi-stage arc shape are arranged on the bottom surface of the anode side groove, and two anode air holes are formed in the side wall of the anode side groove; a plurality of cathode rib columns distributed in a multistage radial mode are arranged on the bottom face of the cathode side groove, cathode air inlet holes are formed in the side wall of the connecting cylinder, and cathode air outlet holes are formed in the side wall of the cathode side groove in a penetrating mode. The structure is simple and compact, stacking is convenient, the gas flowing state is effectively improved, more uniform gas distribution is realized, uniform reaction in the whole electric pile is ensured, and the efficiency and performance of the electric pile are improved; and the pressure drop during gas flowing can be reduced, so that the operation of the galvanic pile is more energy-saving and efficient.

The invention provides a turnable helicopter air inlet channel structure, and belongs to the technical field of helicopter structural design, the structure comprises a front support frame, a rear support frame, a left fixed cover, a right fixed cover, a movable cover, a lower air inlet channel, an air inlet channel support assembly and an air inlet net assembly, the air inlet channel is divided into an upper part and a lower part, wherein the upper air inlet channel is integrated on the movable cover, the upper section and the lower section are pressed and sealed through the P-type sealing ring, the air inlet net assembly is connected to the movable cover in a screwed mode, and the left side of the movable cover is connected with the left fixed cover; the right side of the movable cover is connected with the right fixed cover through a front hinge assembly and a rear hinge assembly. The front and the back of the movable cover are connected with the front support frame and the back support frame; the interior of the front side of the movable cover is connected with the front supporting frame; the air inlet channel supporting assembly, the lower air inlet channel, the front supporting frame, the rear supporting frame, the left fixing cover and the right fixing cover are riveted to form a stable frame structure. The device is simple in structure, convenient to mount and maintain, reasonable in stress form, safe, reliable and capable of solving the problems of maintainability and safety of the rear cabin engine of the power cabin.

The invention discloses a bilateral support balance structure for measuring intake and exhaust influence, and belongs to the field of aerodynamics. The device comprises an aircraft fuselage shell, an air inlet channel upper cover, a double-support balance, a corrugated pipe and a fixed support, the double-support balance comprises a front shell matching section, a front air inlet channel, an air inlet channel lower cover, support balances and a rear shell matching section, the aircraft fuselage shell is connected with the double-support balance through the shell matching section, the air inlet channel lower cover is connected with the front shell matching section, and the two sides of the front shell matching section and the two sides of the rear shell matching section are connected through the support balances. The air inlet channel lower cover is provided with an air inlet channel upper cover, the air inlet channel upper cover and the air inlet channel lower cover jointly form a middle air inlet channel, the rear shell matching section is provided with a fixed support, and the rear air inlet channel of the rear shell matching section is communicated with the air inlet passage through a corrugated pipe. The problems that a complete air inlet channel is formed in the middle of an aircraft wing body, the internal space is narrow, a balance cannot be installed, and the six-component load measurement requirement cannot be met are solved.

The utility model discloses humidity monitoring equipment for environmental protection monitoring, which comprises a base, an upper cover is fixedly arranged on the upper surface of the base through bolts, a humidity sensor is fixedly mounted on the upper surface of the base, and air inlet channels are uniformly formed in the side surface of the upper end of the upper cover. A filter screen is fixedly installed at the end, facing the exterior of the upper cover, of the air inlet channel, air outlet channels are evenly formed in the lower end of the upper cover, an air inlet motor is fixedly installed in the upper cover, fan blades are fixedly connected to the lower end of an output shaft of the air inlet motor, and a switching structure is arranged in the upper cover. And monitoring failure caused by blockage of the filter screen is prevented through a multi-channel air inlet mode. According to the humidity monitoring equipment for environmental protection monitoring, due to the arrangement of the multiple air inlet channels, even if part of the air inlet channels are blocked by impurities and dust, the humidity monitoring device can still work normally without maintenance, and therefore the humidity monitoring device can work stably for a long time.

The invention belongs to the technical field of ice prevention and removal, and relates to a combined unmanned aerial vehicle automatic deicing system. The system comprises a deicing controller, and an icing detection subsystem, an engine air inlet channel anti-icing subsystem and a wing empennage airbag deicing subsystem which are connected with the deicing controller, the icing detection subsystem is used for detecting whether the unmanned aerial vehicle is iced or not and the icing degree and outputting an icing signal; the deicing controller controls whether the engine air inlet channel anti-icing subsystem and the wing empennage air bag deicing subsystem work or not according to icing signals output by the icing detection subsystem.

According to the electronic cigarette sensor with the partition wall structure, a partition wall, a step and a Z-shaped air inlet channel are formed in an injection molding cavity of a lead frame, the high step is provided with an air inlet channel penetrating through the high step and the bottom wall of the lead frame, the air inlet channel is in an inverted Z shape, the high step is further provided with a micro-electro-mechanical sensor, and the micro-electro-mechanical sensor is arranged on the bottom wall of the lead frame. A low step is arranged at the position, away from the high step, in the cavity, and protective nets are arranged on the upper cover and the lower cover. The lead frame is provided with a circular cavity, the height of the bottom of the circular cavity is slightly higher than that of the star-shaped bonding pad, the circular cavity is in a concave semi-wrapping state, and good sealing performance and good mounting welding performance during mounting of the formed electronic cigarette sensor are facilitated. A partition wall is further arranged in the cavity, the ASIC chip and the micro-electro-mechanical sensor are isolated through the partition wall, the micro-electro-mechanical sensor is protected from being polluted by manufacturing procedures, tobacco tar and the like, and a sealed oil-proof air channel is provided for the oil-proof cotton.

The invention provides a heat preservation box capable of rapidly replacing a cold source. The heat preservation box comprises a box body and cold storage plates; the box body is provided with a box door, a cold storage area, a control area and a cold source area are arranged in the box body, the cold storage area is separated from the control area and the cold source area through a middle partition board, and the control area and the cold source area are separated through a side partition board; a backflow partition board is arranged in the cold source area, the cold source area is divided into a cold source cavity and a backflow cavity through the backflow partition plate, the cold source cavity communicates with the lower portion of the backflow cavity, a plurality layers of cold sourceframes used for containing the cold storage plates are arranged in the cold source cavity, and the cold source cavity communicates with the cold storage area through an air inlet channel; an exhaustfan is arranged on the air inlet channel, the cold storage area communicates with the backflow cavity through a backflow channel, and an air blower is arranged on the backflow channel; a control module is arranged in the control area, a first temperature sensor is arranged in the cold storage area, the exhaust fan, the air blower, and the first temperature sensor are electrically connected with the control module; and box body, the middle partition plate and the side partition plate are all made of vacuum composite plates. According to the heat preservation box, the replacement efficiency of the cold source is improved.

The invention belongs to the technical field of wind tunnel tests, and discloses a test device and method for a conventional and large-attack-angle and large-sideslip-angle air inlet channel of a temporary-impulse wind tunnel. A model connecting block, a sideslip front shaft, a main support and a machete of a temporary impact type wind tunnel machete mechanism are sequentially connected to the upper back face of the tail of an air inlet duct model of the test device from front to back, and a medium-pressure hose switching section, a medium-pressure hose, a telescopic sleeve, a flow meter and an ejector are sequentially connected to a lower abdomen air outlet of the tail from front to back. The test method comprises the steps of wind tunnel test preparation; carrying out a conventional air inlet channel test; carrying out a large-incidence-angle and large-sideslip-angle air inlet test; and processing test data. According to the test device and method, an incidence angle close-range pre-deflection and sideslip angle secondary deflection mode is adopted, and it is ensured that an air inlet duct model is always located in a core flow field of a wind tunnel test section; the telescopic sleeve adopts a'double-layer different-side 'sealing design, so that'damping' cavity pressure is formed, and shaking of the medium-pressure hose is inhibited; and the test efficiency of the air inlet channel, the data accuracy and the universality of the test system are improved.

The invention discloses a single-action pressure reduction diaphragm type pressure flow amplifier in the field of industrial flow control. The single-action pressure reduction diaphragm type pressure flow amplifier comprises a machine body, a valve core, a flexible diaphragm, an exhaust assembly, a large pressure reduction device and a small pressure reduction device. An adjusting cavity, an air inlet cavity, an air outlet cavity, an air inlet channel and an air outlet channel are formed in the machine body, the air inlet channel is communicated with the air inlet cavity, the air outlet cavity is communicated with the air outlet channel, the valve core is arranged between the air inlet cavity and the air outlet cavity, the valve core is pushed through the flexible diaphragm and the exhaust assembly, and the compressed air flow and pressure intensity between the air inlet cavity and the air outlet cavity can be adjusted; when the pressure intensity of the adjusted air is relatively low, the small pressure reducing device is used for reducing pressure; and when the pressure intensity is high, the large pressure reducing device is used for reducing pressure. The diaphragm structure design is adopted, the flow and the pressure intensity of compressed air are adjusted through reciprocating motion of the flexible diaphragm, the pressure intensity of the adjusted air is reduced through the two pressure reducing devices, and the diaphragm structure can be better suitable for application scenes where the pressure intensity of the adjusted air is high.

The utility model discloses a high-speed large-maneuvering target drone, which relates to the field of unmanned aerial vehicles and comprises a drone body, wings, a horizontal tail, a vertical tail and an air inlet channel. The fuselage can reduce resistance to a great extent to realize high-speed flight; the wings adopt sweepback upper single wings to reduce the resistance during high-speed flight, the problem of overlarge transverse stability caused by sweepback and high placement of the wings can be avoided through the downward reverse design, and meanwhile, the wings can be integrally disassembled and assembled and have better operability and convenience; the control efficiency of a full-motion horizontal tail is high, and the heading stability under a large-angle-of-attack attitude can be improved through the design of the inverted-V-shaped tail; the vertical fin without the control surface can improve the course stability and ensure the matching property of the transverse course stability, and is light in structural weight and small in flight resistance; the bearing separation channel type air inlet channel can avoid landing damage of the air inlet channel in the parachute landing recovery process, and meanwhile the requirements for high total pressure recovery, low air inlet distortion, radar stealth and the like are met.

The invention discloses a section shape control method applied to a three-dimensional inward-turning adjustable air inlet channel, and belongs to the field of air inlet channel molded surface pneumatic design, and the method comprises the following steps: step 1, optimization design of an inward-turning reference flow field; based on a given incoming flow design working condition, a preliminarily optimized inward rotation reference flow field is obtained; 2, optimization design of the profile of the inward-rotation adjustable air inlet channel is carried out; an inlet capture molded line and an adjustable section control constraint of the air inlet are given, and the inward turning air inlet meeting the requirement is obtained through streamline tracking in the inward turning reference flow field in the first step by combining an optimization tool and utilizing an optimization algorithm; 3, profile adjustment design is conducted, specifically, profile adjustment design is conducted at the position of a set rotating shaft straight line on the basis of the inward rotating air inlet channel generated in the step 2; according to the scheme, the inward rotation air inlet channel generated directly through streamline tracking has the characteristic that the section molded line is approximately a straight line at the specified section, and the problem that in the prior art, an original streamline tracking molded surface needs to be changed to be matched with adjustable design is solved.

The invention discloses a forming tool and method for an annular rib co-curing structure of an aircraft air inlet channel, and belongs to the technical field of aviation composite material forming. The manufacturing cost can be effectively reduced, and the weight of the air inlet duct of the aircraft can be reduced. The forming tool comprises a soft mold paving mold, an air inlet channel main body paving mold, a paving platform, a soft mold positioner and an air inlet channel demolding tool. According to the air inlet duct, the nine annular T-shaped reinforcing ribs of the air inlet duct main body piece can be integrally formed, the manufacturing cost can be effectively reduced, and the weight of the air inlet duct of the aircraft can be reduced. By means of the soft mold positioner, the problem that the operation space is limited in the paving process is solved, and meanwhile it is guaranteed that the position tolerance after the nine annular T-shaped reinforcing ribs and the air inlet channel body are integrally formed is within + / -0.5 mm. The paving platform is ingeniously designed to have three functions, namely a rotary paving function, a positioning function of a soft mold by being combined with a soft mold positioner and a bracket function of curing in a tank.

The invention relates to the technical field of auxiliary power systems, in particular to a manufacturing method of an air supply device of an auxiliary power system. The method comprises the steps that a high-pressure air pressure distribution area under the working state of an auxiliary power system air supply device is obtained; determining a positioning surface and a sealing surface of the air supply device of the auxiliary power system according to the distribution area; the assembly tolerance of the auxiliary power system air supply device is determined according to the positioning face and the sealing face; an air inlet channel shell, an air inlet air pocket, an air inlet channel outer ring, an air inlet volute, a labyrinth ring, a locking unit and a rotor are machined according to the assembly tolerance; and an auxiliary power system air supply device is assembled, so that the air inlet channel shell, the air inlet air pocket, the air inlet channel outer ring and the air inlet volute sequentially abut against one another in the axial direction, the labyrinth ring is pressed between the outer side ring face of the outer sealing barrel and the inner side ring face of the volute positioning barrel, and a stepped pressure relief cavity is formed between every two adjacent pressure relief ring gears. Therefore, the problem that the air inlet end shell of the auxiliary power system is very difficult to position and seal well is solved.

The invention belongs to the technical field of airplane two-power systems, and discloses a rotor blade tip clearance measuring method and device, and the method comprises the steps: firstly, measuring the distance a between the outer ring surface of an air inlet channel outer ring support and the end surface of an air inlet channel outer ring, and measuring the height of the end surface of the air inlet channel outer ring on a plane; then directly measuring the distance between the lower end surface of the air inlet bearing end cover of the product and the surface of the air inlet bearing end cover, which is used for assembling the L-shaped sealing gasket, and measuring the distance between the bottom of the air inlet outer ring and the lower end surface of the air inlet bearing end cover; calculating to obtain a distance A from a gap design point on the air inlet channel outer ring to a surface, used for assembling an L-shaped sealing gasket, of the air inlet bearing end cover; measuring the bearing axial clearance f of the product bearing under the pretightening force; measuring the thickness h of the L-shaped sealing gasket, and measuring the distance g from a gap design point on the centrifugal impeller to the bottom of the bearing inner ring; the distance B between the clearance design point on the impeller and the end face of the L-shaped sealing gasket is obtained, wherein B = g + the theoretical distance between the end faces of the inner ring and the outer ring of the bearing-f / 2 + h; and calculating the blade tip clearance C = B-A at the clearance design point on the centrifugal impeller. Compared with an existing measuring method, the method has the advantages that the blade tip clearance is measured in the product assembling process, the whole product does not need to be disassembled and assembled repeatedly, meanwhile, the product does not need to be transferred back and forth between measuring equipment, the product assembling efficiency is improved, and the method is more suitable for batch operation.

The invention provides an air inlet flow pipe and a design method and application method thereof, and belongs to the technical field of aerodynamic acoustic tests. The air inlet flow pipe is used for an aeroacoustic test of an aero-engine and comprises a horn mouth section and a circular pipe section which are communicated, the horn mouth section comprises a similar section, the molded line of the similar section is the same as that of an air inlet channel of the aero-engine, and the circular pipe section is provided with a static pressure measuring section. The distance from the static pressure measurement section to one end of the circular pipe section away from the similar section is greater than or equal to the diameter of the circular pipe section. The similar section of the horn mouth section of the air inlet flow pipe adopts the same molded line as the air inlet channel of the aero-engine, that is, the similar section and the air inlet channel of the aero-engine are the same in design formula, and the similar section is obtained by reducing the proportion, so that the similar section is closer to the actual situation. The test can better simulate and measure far-field acoustic characteristics, and the test precision is further improved.

The invention belongs to the technical field of hypersonic flight vehicle control, and particularly relates to a hypersonic flight vehicle protection control method considering non-starting of an air inlet channel. The method specifically comprises the steps of establishing a quasi-one-dimensional nominal mechanism model to describe flow field changes of an isolation section and a combustion chamber; adopting a physical information neural network to construct a reduced-order model as a real-time agent of the quasi-one-dimensional model; designing a dual extended Kalman filtering algorithm to realize joint online estimation of model parameters and blind area states, and introducing shock wave position pseudo measurement to form multi-loop feedback; a dual-channel fusion early warning system of a model channel and an intelligent sensor channel is constructed, and robust early warning is realized through adaptive weight; and designing a continuous adaptive model prediction controller, and dynamically adjusting a control strategy according to risk indexes and parameter uncertainty to realize active protection control.

The invention discloses a flow field self-adjustment-based inward rotation type air inlet channel design method which comprises the following steps: S1, generating an air inlet channel profile scheme under a given design point incoming flow condition; s2, the molded surface of the air inlet channel is modified under the incoming flow condition of a given starting point, and the molded surface of the air inlet channel with a groove is formed; s3, generating an air inlet channel reference molded surface based on pneumatics; s4, on the basis of the reference molded surface of the air inlet channel, the self-adaptive adjusting capacity of the pneumatic throat channel is checked within the operation range; s5, on the basis of the air inlet channel reference molded surface designed and completed in the step S4, generating the inward rotation type air inlet channel with the pneumatic self-adaptive adjusting capacity; and S6, iteration and optimization are carried out on the inward rotation type air inlet channel formed in the step S5. The flow channel area at the throat of the air inlet channel is controlled through the virtual wall face formed by the separation area, then wide-area operation of the air inlet channel is achieved, and the suction-free air inlet channel with the rectangular section and the fixed geometry and capable of operating within the Mach number range of 3-7 is designed.

The high-position air inlet channel comprises an air inlet channel shell, an air inlet and an air outlet are formed in the air inlet channel shell, the air inlet and the air outlet are communicated to form an airflow channel, and the air inlet and the air outlet face different directions; the channel structure comprises a first-section channel close to the air inlet and a rear-section channel close to the air outlet, the air inlet is formed in one end of the first-section channel, the other end of the first-section channel is communicated with one end of the rear-section channel, the air outlet is formed in the other end of the rear-section channel, and the first-section channel is divided into a plurality of side-by-side channels in the airflow circulation direction; wherein the plurality of channels are suitable for generating reflected sound waves to counteract sound waves transmitted from the rear-section channel to the first-section channel. By the adoption of the high-position air inlet channel, the silencing function of the air inlet of the high-position air inlet channel can be achieved, weight cost increase caused by an external connection structure can be reduced, and the high-position air inlet channel is more attractive.

The utility model discloses a code scanning dust removal assembly and lens assembling equipment, including a linear moving module, a rotating platform, an ion blower gun and a code scanning assembly, the linear moving module is provided with a moving carrier plate, the rotating platform is installed on the moving carrier plate, the rotating platform is provided with a dust removal cavity, and an air inlet channel and an air outlet channel communicated with the dust removal cavity, the ion blower gun is installed on the moving carrier plate, an air outlet of the ion blower gun communicates with the air inlet channel, the code scanning assembly is installed at one end of the linear moving module, and a code scanning area of the code scanning assembly intersects with the moving track of the rotating platform. The linear moving module drives the rotating platform to do linear motion through the moving carrier plate, the lens placed in the dust removal cavity is rotated in the moving process, dust removal is conducted on the lens through the ion blower gun, and when the rotating platform moves to a code scanning area of the code scanning assembly, the code scanning assembly scans codes of the lens, and the lens is subjected to dust removal. Therefore, dust removal and code scanning can be synchronously carried out on the lens, and the production efficiency can be improved.

The invention discloses a rotor type gas energy engine and a working method thereof, and the rotor type gas energy engine comprises a rotor shell which is internally provided with a cylindrical rotor chamber; the rotor is arranged in the rotor chamber and comprises a rotor shaft and at least one rotor wing arranged on the rotor shaft, and the rotor chamber is divided into rotor cavities with the same number as the rotor wings by the rotor; the airflow inlet and outlet channel comprises at least one air inlet channel and at least one air outlet channel which are arranged on the rotor shell and are equal in number; the compressed air source mechanism is connected with the air inlet channel; and the electric control system is used for controlling start and stop of the air inlet valve and the exhaust valve and the air flow provided by the compressed air source mechanism so as to be matched with rotation of the rotor to complete a working cycle through the three processes of air inlet, acting and exhaust. The rotor type gas energy engine is small in vibration, low in noise, selectable in low speed, medium speed and high speed, fast in stepless speed regulation response, and capable of effectively improving work efficiency, meeting the requirements of low rotating speed, high torque and other different rotating speeds and torques, and achieving stable operation of the engine.

The invention belongs to the technical field of wind tunnel tests, and discloses an air inlet balance calibration device and method for simulating a test state. The air inlet balance calibration device comprises a calibration supporting rod, a connecting piece, a balance and a loading head which are sequentially connected from back to front; the rear end of the calibration supporting rod is fixed on the two-degree-of-freedom balance calibration frame; the corrugated pipe connecting piece is clamped on the connecting piece and slides along the connecting piece; the rear end of the corrugated pipe is fixed on the front end face of the corrugated pipe connecting piece, the front end of the corrugated pipe is connected with the air inlet channel, and the air inlet channel is fixed on the lower surface of the front section of the balance through a square boss above the air inlet channel. The air inlet balance calibration method comprises the following steps: carrying out optical balance calibration; carrying out model assembly; adjusting the position of a corrugated pipe connecting piece; carrying out air inlet balance calibration; and performing a wind tunnel test. According to the air inlet balance calibration device and method for simulating the test state, accurate calibration of the balance, the air inlet and a corrugated pipe parallel force measurement system is achieved, and the load of the air inlet can be efficiently and accurately measured.

The present application relates to the technical field of household appliances, and provides a gas water heater, which comprises a bottom shell, the bottom shell being provided with an opening; a burner, the burner being installed on the bottom shell; and a cover plate assembly, the cover plate assembly being installed on the bottom shell and covering the opening, the cover plate assembly comprising a first cover plate and a second cover plate, the second cover plate being located between the burner and the first cover plate, the cover plate assembly being provided with an air inlet channel between the first cover plate and the second cover plate, the first cover plate being provided with a first air inlet opening communicating with the air inlet channel, and the second cover plate being provided with a second air inlet opening at a position away from the first air inlet opening, the second air inlet opening communicating the air inlet channel with an air inlet of the burner. The gas water heater provided by the present application is provided with a multi-layer cover plate structure, each layer of the cover plate can weaken the internal noise, and the cavity between the cover plates forms a long air inlet channel, which can greatly increase the path length of the noise along the air inlet channel to propagate outward, effectively improve the transmission loss of the noise to propagate outward, and greatly reduce the flow channel resistance.

The invention aims to provide a simulated analysis method for bird impact of an air inlet of a turbofan engine, which can reduce the test cost and shorten the test period, and meanwhile, the test has good reliability. In order to achieve the purpose, the bird impact resistance design requirement of the air inlet channel is clarified by interpreting airworthiness terms, an air inlet channel bird impact simulation analysis working process is established, a bird body is simulated by adopting an SPH method, connecting pieces such as rivets and bolts are simulated by adopting an SPOTWELD unit, and a bird impact simulation model reflecting the real structure of the air inlet channel is established. Information such as deformation and damage of components in the impact process is obtained through turbofan aero-engine air inlet bird impact simulation analysis, and air inlet structure optimization design is guided.

The invention relates to the field of aerospace, in particular to an unmanned aerial vehicle rocket boosting takeoff force bearing device with a belly air inlet channel, which comprises an adapter bracket, a separation device, a fuselage longitudinal stringer, a rear air bag box, a boosting reinforcing frame, a thrust seat, an engine left thrust beam, an engine right thrust beam, a boosting reinforcing beam and a rear hanging point frame. The reliability of the unmanned aerial vehicle in the boosting flight process can be improved, the force bearing structure of the unmanned aerial vehicle body is simplified, the body structure is simple, force transmission is direct, the booster rocket installation process is simplified, the reliability of separation of the booster rocket and the unmanned aerial vehicle is improved, and the cost of each flight of the unmanned aerial vehicle is reduced.

The invention relates to the technical field of automobile power systems, in particular to a gas ejector which comprises a shell and a valve element mechanism, the shell is provided with a valve cavity, a gas inlet channel and a gas outlet channel, the gas inlet channel and the gas outlet channel are arranged on the two sides of the valve cavity in the preset direction, and the gas inlet channel and the gas outlet channel communicate with the valve cavity; the valve element mechanism comprises a plunger assembly, a cam and a driver, the plunger assembly can generate elastic deformation in the preset direction, the plunger assembly is slidably arranged in the valve cavity in the preset direction, one end of the plunger assembly abuts against the inner wall of the valve cavity and seals the air inlet channel, and the cam is arranged in the valve cavity and is in running fit with the shell. The peripheral wall of the cam abuts against the other end of the plunger assembly, the driver drives the cam to rotate, and a rotating shaft of the cam is perpendicular to the preset direction. According to the gas ejector, an electromagnetic valve in a gas ejector in the prior art is replaced by the driver and the cam, so that electromagnetic leakage into the environment is avoided, and interference to surrounding electronic equipment is avoided.

The invention provides a concentric circle rotor type internal combustion engine and a design method thereof. One or more air cylinders are arranged on the peripheral side of the rotor shell, a main oil sprayer and a spark plug are arranged in each air cylinder, and a transition air channel is arranged between each air cylinder and the rotor chamber; the rotor is arranged in the rotor chamber; the air inlet channel is arranged on the air cylinder and is used for introducing compressed air into the air cylinder; the fuel cylinder is arranged on the rotor shell and communicates with the transition air channel, and an auxiliary fuel injector is arranged in the fuel cylinder; the transition valve is arranged on the side, close to the air cylinder, of the communicating portion of the transition air channel and the rotor shell. When the transition valve is closed, the combustion chamber is divided into an ignition cylinder and a main combustion space, fuel is constantly supplied in the ignition cylinder according to theoretical mixed gas, fuel is supplied in the main combustion space according to lean mixed gas, and the fuel quantity changes along with working conditions. Various fuels can be used, ignition is stable, the multi-rotor type can achieve torque superposition, the anti-overturning performance is improved, and high power and low oil consumption are achieved under the condition that the height is not increased and the rotating speed of an original single rotor is not changed.

The invention provides an aircraft engine air inlet channel detection method, and belongs to the technical field of aircraft engine air inlet channel detection. In order to solve the problems of low detection efficiency, reliability and safety of an aircraft engine air inlet channel, the invention provides an aircraft engine air inlet channel detection method which comprises the following steps: S1, a control device controls a carrying device to move from one side of an aircraft to an air inlet channel inlet of a corresponding side edge; s2, the control device adjusts the height and the pitching angle of the containing disc by controlling a posture adjusting mechanism till the front contact sensor is extruded to the lower lip edge of the inlet of the air inlet channel to be detected, and then the control device controls the detection robot to enter the air inlet channel for detection and return to the containing disc after detection is completed; s3, the control equipment controls the movable chassis to move backwards, controls the posture adjusting mechanism to restore the initial state, and then controls the movable chassis to horizontally move to an air inlet channel inlet in the other side edge; s4, repeating the step S2; and S5, the control equipment controls the mobile chassis to move backwards, controls the posture adjusting mechanism to recover the initial state, and then controls the mobile chassis to translate to the outer side of the air passage inlet, so that detection is completed. According to the invention, the human input can be greatly reduced, the detection efficiency and reliability are improved, the human error risk is avoided, and the detection safety is improved.

The invention provides an air-breathing aircraft for long-term flight in an upper atmosphere, and relates to the technical field of aircrafts in the upper atmosphere, the air-breathing aircraft comprises an aircraft body, the aircraft body is provided with an air-breathing electric propulsion system, the outer contour of the aircraft body is cylindrical, and an air inlet channel is arranged in the center of the aircraft body; the air inlet channel comprises a gradually-shrinking conical inlet pipeline, an inwards-concave gradually-shrinking compression pipeline, a cylindrical ionization acceleration pipeline and a gradually-expanding conical outlet pipeline which are sequentially arranged from front to back. The solar cell wings are arranged on the outer side of the aircraft body, the solar cell wings are forward-swept trapezoidal wings, and the solar cell wings can supply power to the air suction type electric propulsion system; the problem that in the prior art, technical defects exist in the aerodynamic configuration design of how to achieve thrust and resistance balance of an aircraft flying for a long time in the upper atmosphere is solved.

The invention discloses a gas compressor test device and method, and belongs to the field of gas compressor tests.The gas compressor test device comprises a driver, and a driving shaft of the driver is used for being connected with a main shaft of a gas compressor; the unloading assembly comprises a balance drum, a high-pressure gas supply unit, an exhaust unit and an adjusting valve, the balance drum is used for being connected with a main shaft of the gas compressor and used for being connected with an impeller on the main shaft of the gas compressor, the high-pressure gas supply unit is used for being communicated between the balance drum and the impeller, and the exhaust unit is used for being communicated with the side, away from the impeller, of the balance drum; an inlet temperature sensor, an inlet pressure sensor and a flow sensor are arranged in the double-twisted-wire air inlet channel; an outlet temperature sensor and an outlet pressure sensor are arranged in the annular outlet throttler; and a controller. The technical effects of the invention lie in that the device not only facilitates the independent test of the related gas compressor, but also facilitates the small axial force of the impeller of the gas compressor borne by the thrust bearing.