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34results about How to "Does not affect aerodynamic shape" patented technology
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Ice formation condition detector
ActiveCN102407942ADoes not affect aerodynamic shapeThere is no critical temperature differenceDe-icing equipmentsElectrical resistance and conductanceThermal insulation
The invention provides an ice formation condition detector, which comprises a sensing element, a temperature sensor and a controller, wherein the sensing element comprises a temperature sensing layer and a thermal insulation layer; a resistance wire is embedded into the temperature sensing layer; the thermal insulation layer is fixed on the inner surface of the temperature sensing layer; the temperature sensor is used for measuring real-time temperatures of the sensing element; the controller comprises a heating control module, a data storage module and a processor; the heating control module is used for heating the resistance wire by using constant electric power to ensure that the temperature of the sensing element is kept to be more than 0 DEG C; the data storage module is used for storing temperature target values of the sensing element under different flight conditions and acquiring real-time temperature values, which are measured by the temperature sensor, of the sensing element; and the processor is used for retrieving the temperature target values of the sensing element from the data storage module under a certain flight condition, comparing the temperature target values with the real-time temperature values and determining that an airplane runs into an ice formation condition if the real-time temperature values are less than the temperature target values.
Owner:COMAC +1
Thermotropic type shape memory composite material
InactiveCN105802188ASmall mechanical propertiesImprove mechanical propertiesWoven fabricsCarbon nanotubeDual function
The invention belongs to the field of shape memory functionalized application technology of high performance polymer matrix composite materials, and provides a thermotropic type shape memory composite material. The material comprises the following components: a shape memory polymer and carbon nanotube, wherein the content of the shape memory polymer is 15-85wt%, and the content of the carbon nanotube is 85-15wt%. The carbon nanotube has excellent mechanical properties, electrical property and thermal conductance performance; the carbon nanotube can be used as an enhancer of the polymer matrix composite material, and can be used as a heating element of the thermotropic type shape memory composite material. The thermotropic type shape memory composite material needs to be heated to a certain temperature in order to realize the function thereof, the carbon nanotube of the carbon nanotube enhanced polymer matrix shape memory composite material can be directly electrified for heating, so that dual functions for enhancing and heating the shape memory composite material are realized.
Owner:AVIC COMPOSITES
Airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device
The invention discloses an airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device which comprises an airfoil outer skin, a hot air ice preventing and removing system, an ultrasonic high-frequency oscillating auxiliary device, a program controller, an atmosphere temperature sensor and an icing strength annunciator, wherein the atmosphere temperature sensor is used for detecting external atmosphere temperature; the icing strength annunciator is used for detecting the outer surface ice layer thickness of the airfoil outer skin; the hot air ice preventing and removing system comprises an engine gas compressor, an airfoil ice preventing cavity, an empennage ice preventing cavity and an ice preventing and removing hot air delivery device; the ultrasonic high-frequency oscillating auxiliary device comprises an ultrasonic generator and an ultrasonic energy converter unit which is connected with the output end of the ultrasonic generator by a connecting cable; and the program controller is used for automatically controlling connection and disconnection of the ice preventing and removing hot air delivery device and starting and closing of the ultrasonic generator according to a temperature signal and an icing strength signal. Accordingly, the airplane airfoil ultrasonic-assistant hot air combined ice preventing and removing device can be used for effectively removing the ice layers of middle airplane body and empennage front edges of an airplane during flight in real time and has the advantages of short ice removing time, low energy consumption, safe and reliable system and thorough ice removal.
Owner:SOUTHEAST UNIV
Patching and repairing method for local damage of carbon-fiber reinforced resin base laminating plate
InactiveCN102649342ASmall weight gainDoes not affect aerodynamic shapeLayered productsLaminationEngineeringFiber
The invention discloses a patching and repairing method for the local damage of a carbon-fiber reinforced resin base laminating plate, which is characterized in that the patching and repairing method comprises the following steps of: excavating damaged positions from a carbon-fiber reinforced resin base laminating plate (1) by layers to form a hollow area (2) to be repaired; cleaning to remove dust and greasy dirt on the surface of the hollow area (2) to be repaired; preparing a prepreg patch (4) corresponding to the boundary of damaged positions on each layer; overlaying one layer of plate glue film (3) on the surface of the hollow area (2) to be repaired; successively overlaying the prepreg patch (4) by layers; and then, co-curing the laminating plate (1) to be repaired. Because the hollow area (2) to be repaired, which is formed by excavating damaged positions by layers, is provided with a wedge-shaped angle theta of 1-3 degrees, the strength recovery value of the repaired laminating plate (1) reaches 90-120%; the upmost layer of the surface of the hollow area (2) to be repaired is overlaid with one layering patch (5) with a big boundary; and after the layering patch (5) is co-cured, the appearance of the layering patch (5) is smooth without affecting the pneumatic appearance of a construction member. Compared with a patching and repairing method on the damaged position, the patching and repairing method for the local damage of the carbon-fiber reinforced resin base laminating plate has the characteristics that growth increment in weight is small.
Owner:CHENGDU AIRCRAFT INDUSTRY GROUP
Novel anti-icing and deicing device for airfoils of airplane
InactiveCN102490905AEfficient removalOvercoming Adhesive StrengthDe-icing equipmentsElectricityLeading edge
The invention discloses a novel anti-icing and deicing device for airfoils of an airplane. The device comprises skin, a program controller, an atmospheric temperature sensor and an icing strength annunciator, wherein ultrasonic deicing unit modules are fixedly arranged on the inner surface of the skin, and each ultrasonic deicing unit module comprises a plurality of piezoelectric ceramic transducers; each piezoelectric ceramic transducer is connected with an ultrasonic generator by a connecting cable; the ultrasonic generator is connected with a power supply; and the program controller controls the ultrasonic generator to start and stop according to temperature signals fed back by the atmospheric temperature sensor and controls the power of the ultrasonic generator and the number of the operating ultrasonic deicing unit modules according to ice layer thickness signals fed back by the icing strength annunciator. Therefore, by using the novel anti-icing and deicing device for the airfoils of the airplane, ice layers on the surfaces of the airfoils and the leading edge of an empennage can be effectively removed in real time during the flight of the airplane; the device is efficient, energy-saving, safe and reliable; ice can be thoroughly removed; and the flight safety of the airplane is ensured.
Owner:SOUTHEAST UNIV
Heat pipe and ultrasonic wave combined ice preventing and removing device and method utilizing waste heat of aircraft engine
InactiveCN105691620APrevent freezingStable anti-icing temperatureDe-icing equipmentsEvaporationAtmospheric temperature
The invention provides a heat pipe and ultrasonic wave combined ice preventing and removing device and method utilizing waste heat of an aircraft engine. The device comprises a heat pipe ice-preventing system, an ultrasonic oscillation ice removing system, a program control system, an atmospheric temperature sensor and an icing strength annunciator. The heat pipe ice-preventing system comprises a communicating pipe installed at the tail portion of the engine to absorb exhaust waste heat and a heat pipe bank bundle with an evaporation section connected with the communicating pipe. The ultrasonic oscillation ice removing system comprises an ultrasonic generator and an ultrasonic transducer unit connected with the output end of the ultrasonic generator through a connecting cable. The program control system automatically controls on and off between the heat pipe bank bundle and the communicating pipe and starting or stopping of the ultrasonic generator according to a temperature signal and an icing strength signal. By means of the synergistic effect of heat pipes and ultrasonic waves, preventing and removing can be combined, compared with a method for removing ice simply through ultrasonic waves, the icing phenomenon of wings is greatly reduced, the flying stability of an aircraft is ensured, and a system is safe and reliable.
Owner:NANJING NORMAL UNIVERSITY
Apparatus for measuring height of aircraft, and method thereof
InactiveCN104165618AImprove signal-to-noise ratioDoes not affect aerodynamic shapeHeight/levelling measurementInstrumentation amplifierMeasurement cost
The invention discloses an apparatus for measuring the height of an aircraft, and a method thereof. The apparatus includes a baroceptor, an instrument amplifier, a digital-to-analog conversion circuit, a filter circuit, a microprocessor and a power module; instrument amplifier is connected to the output end of the baroceptor, the filter circuit is connected to the output end of the baroceptor, and the baroceptor acquires change information of the pressure with the height and outputs a first voltage; the first voltage is amplified by the instrument amplifier, the amplified first voltage is filtered by the filter circuit, and the filtered amplified first voltage is output; the digital-to-analog conversion circuit converts a digital voltage value corresponding to the current pressure plane height of the aircraft to a reference voltage; the instrument amplifier amplifies a difference between the first voltage and the reference voltage and then outputs a second voltage; and the microprocessor processes the filtered first voltage and the filtered second voltage, and then outputs the current height of the aircraft. The apparatus and the method have the advantages of reduction of the height measurement cost of a missile flight control process,, improvement of the height measuring resolution and accuracy, simple circuit and low power consumption.
Owner:HUBEI SANJIANG AEROSPACE HONGFENG CONTROL
Reusable carrier rocket vertical landing recovery support mechanism
InactiveCN109911252ADoes not affect aerodynamic shapeFrom ablationSystems for re-entry to earthCosmonautic landing devicesRecovery supportRocket
The invention relates to a reusable carrier rocket vertical landing recovery support mechanism which can ensure that an aerodynamic shape of a reusable carrier rocket at an ascending stage is not affected, and the carrying performance of the reusable carrier rocket is improved. The support mechanism comprises four groups of vertical landing support structures; each group of vertical landing support structure comprises a detached rocket housing, landing legs, telescopic poles, supporting feet, hydraulic control devices, a guide rail and a locking mechanism. At the ascending stage of the reusable carrier rocket, the landing legs, the telescopic poles, the supporting feet and the hydraulic control devices are folded into the detached rocket housing. In the recovery landing process, the detached rocket housing and the landing legs are unfolded downwards under the action of the hydraulic control devices; therefore, the stable support of vertical landing of the carrier rocket is realized. The invention provides a novel reusable carrier rocket vertical landing recovery support structure design scheme, by adopting the support mechanism, stable and reliable vertical landing support of a rocket body of the carrier rocket is realized under the condition that the aerodynamic shape of an original carrier rocket is not affected, and the support mechanism can be used for multiple times, and has a certain practical value.
Owner:PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
Deicing and lightning protection device for unmanned aerial vehicle
PendingCN106697299ADoes not affect aerodynamic shapeGood deicing effectAircraft lighting protectorsDe-icing equipmentsElastomerElectricity
The invention provides a deicing and lightning protection device for an unmanned aerial vehicle, which is suitable for flying safety devices for the unmanned aerial vehicles. According to the deicing and lightning protection device for the unmanned aerial vehicle, an ultrasonic controller (2) applies an alternating current voltage to a piezoelectric ceramic piece (5) through a lead; through inverse piezoelectric effects of the piezoelectric ceramic pieces (5), oscillation elastomers (4) generate standing wave or travelling wave oscillations; and the deformation applies an ultrasonic mechanical acting force to a freezing layer on the unmanned aerial vehicle so that the freezing layer is broken and falls off under an effect of wind power. The oscillation elastomers (4), which are connected section by section, are connected with pointed dischaging brushes (9); and a good conductive passage is provided to a lightning current so that great damage caused to the unmanned aerial vehicle can be avoided. The deicing and lightning protection device for the unmanned aerial vehicle has the advantages of good deicing effect, lightning protection, simple and compact structural design, light weight and so on and has no influence on the aerodynamic shape of the unmanned aerial vehicle.
Owner:洛阳翰翔航空科技有限公司
Improved Z-pin method for two-dimensional ceramic matrix composite
ActiveCN103274714ATo overcome the shortcomings of the limited strength effect in the Z directionReduce breakageCarbon fibersUltimate tensile strength
The invention provides an improved Z-pin method for a two-dimensional ceramic matrix composite. The improved Z-pin method comprises the following steps of (1) preparing a two-dimensional carbon fiber plain woven preform; (2) preparing carbon fiber Z-pin members by using a pultrusion process; (3) drilling inclined holes in the two-dimensional carbon fiber plain woven preform according to a certain distribution rule; (4) embedding the carbon fiber Z-pin members in the inclined holes of the two-dimensional carbon fiber plain woven perform; (5) depositing the two-dimensional carbon fiber plain woven perform with the carbon fiber Z-pin members to densify the same, and thus a two-dimensional ceramic matrix composite plate is obtained; and (6) trimming the parts of the carbon fiber Z-pin members. The Z-pin members are inclinedly embedded according to a certain distribution rule, thereby transferring connection shear loading into a combination of extrusion loading and shear loading, more effectively enhancing Z-direction strength of the two-dimensional ceramic matrix composite and inhibiting stratified damages.
Owner:SOUTHEAST UNIV
High-speed train and emergency braking method and system for high-speed train
ActiveCN112498406AImprove operational safetyDoes not affect aerodynamic shapeRailway braking systemsAutomatic brakingMechanical wear
The invention provides a high-speed train and an emergency braking method and system for the high-speed train. On the basis of conventional braking, a main umbrella device and an air injection deviceare additionally arranged, the main umbrella device is not opened in the normal state, the air injection device is not started, and the aerodynamic configuration of the train is not affected; when anemergency situation occurs, different braking modes are correspondingly started according to different levels of the emergency situation, the wind resistance is greatly increased through the main umbrella device and the air injection device, the braking distance is greatly shortened, the braking effect and the train operation safety are greatly improved, the wind resistance braking mode saves energy and is environmentally friendly, and the mechanical wear of the train and rails is reduced. Obstacles are recognized and obstacle distances are detected based on a visual unit, different braking modes are started according to the obstacle distances, and intelligent and automatic braking under emergency conditions is achieved.
Owner:ZHUZHOU ELECTRIC LOCOMOTIVE CO
Deicing device, system and method for aircraft wing
InactiveCN111792039AOvercome bond strengthPrevent ice tumorDe-icing equipmentsMechanical engineeringEnergy consumption
The invention discloses a deicing device, system and method for an aircraft wing. According to the technical scheme, the deicing device comprises at least one deicing unit; the deicing unit comprisesa plurality of groups of transducers, and each group comprises two transducers; an electromagnetic coil sleeves the outer side of each group of transducers, the electromagnetic coils are connected inparallel and are connected with a precision pulse generator, and the precision pulse generator is connected with a controller; the controller is further connected with a temperature sensor and a thickness detector. By means of high-frequency oscillation of the giant magnetostrictive material and generated instant high-heat-density anti-icing and de-icing, an ice layer at a specific part of a wingin the flying process of an airplane can be effectively removed in real time; and the deicing time is shortened and the energy consumption is greatly reduced while the flight safety of the aircraft iseffectively ensured.
Owner:SHANDONG UNIV
Liquid cooling system for avionic device
InactiveCN105636404ANo stamping requiredDoes not affect aerodynamic shapeCooling/ventilation/heating modificationsJet aeroplaneAviation
The invention relates to a liquid cooling system for an avionic device, and the system is sequentially connected with a liquid pump (1), a liquid-liquid heat radiator (2), a gas-liquid separator (3) and electronic equipment (5) through a pipe (6). A conduit at the downstream side of the electronic equipment (5) is provided with a temperature sensor (4), and a controller (7) is enabled to be connected with the temperature sensor (4) and the liquid pump (1) through a control line. The gas-liquid separator (3) is disposed at the upstream side of the liquid pump (1). Compared with the prior art, the system is simple in construction, is stable and reliable in operation, does not need to punch an air inlet, and does not affect the pneumatic shape of an airplane. A conventional fuel oil system of an airplane serves as a heat sink, and the heat sink carries out heat exchange with the cooling liquid, thereby bringing away the heat generated by airborne electronic equipment. Meanwhile, a variable-frequency liquid pump is employed, and the rotating speed of the pump is automatically adjusted according to the liquid temperature of a pump inlet, so as to control the liquid supply temperature of the system, thereby achieving the optimal management of heat energy, and reducing the cost and loss of the airplane.
Owner:XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
Plug-type helicopter maintenance pedal
ActiveCN108058804AConvenient maintenance channelOvercome deficienciesFuselagesBlock and tackleFootplate
The invention relates to a plug-type helicopter maintenance pedal and belongs to helicopter structural designs. The plug-type helicopter maintenance pedal comprises a first slide rail, a second sliderail and a supporting footboard, wherein the first slide rail is provided with a first track consisting a first limiting rib and a second limiting rib that are mutually parallel, and a first limitingpart is arranged at one end part of the first limiting rib to restrict rollers from sliding; the second slide rail is provided with a second track consisting of a third limiting rib and a fourth limiting rib that are mutually parallel, a second limiting part is arranged at one end part of the third limiting rib to restrict the rollers from sliding, and the second slide rail and the first slide rail are symmetrical; and the supporting footboard is of an arc-shaped structure, a skin is arranged on an arc-shaped side, a diametral plane is a pedal face, not less than two roller sets are arranged on two sides of the pedal face, a certain distance is kept between the roller sets, and axes of the rollers are parallel to the pedal face. The internal space is fully utilized, the pedal is plugged and maintained according to maintenance requirements, defects of a conventional fixed pedal are avoided, and aerodynamic configuration is not influenced.
Owner:CHINA HELICOPTER RES & DEV INST
Aircraft anti-icing fuel system suitable for high-altitude low temperature environment
InactiveCN101580130ANot easy to accumulateAvoid accessPower plant fuel tanksMachines/enginesFuel tankCarburetor
The invention discloses an aircraft anti-icing fuel system suitable for high-altitude low temperature environment. A fuel filter in the fuel system is an irregular rectangular structure with top being a bevel of 45 degrees, adopts aluminum alloy framework and is welded by externally covered filter screens with filter fineness of 50mu; the fuel in a fuel tanker enters a consumption tank after being filtered by the fuel filter; return fuel in an engine evenly flows down through the fuel filter from the top of the fuel filter by passing through a horizontal pipe which is installed at the top of the fuel filter and is provided with small holes; the heat of the return fuel is adopted to melt ice crystals which probably remain on the surface of the fuel filter; impurities such as gum formed by moisture, ice crystals or oxide in the fuel flow to a consumption tank sump along the surface of the fuel filter. By adopting such a special system, impurities such as ice crystals, moisture and the like in the fuel can be effectively stopped from entering a feedline of the engine, impurities such as ice crystals and the like in the fuel can be prevented in real time from blocking the fuel pump and carburetor of the engine, and the engine can be ensured to work safely under high-altitude low temperature environment for long time.
Owner:BEIHANG UNIV
Supporting structure for fairing of oil-driven unmanned aerial vehicle
ActiveCN109484636ADoes not affect aerodynamic shapeAerodynamic shape does not breakRotocraftCantileverHelicopter rotor
The invention provides a supporting structure of a fairing for an oil-driven unmanned aerial vehicle. The supporting structure comprises a first supporting rod, a second supporting rod and a third supporting rod which extend outwards from a transmission seat of a rotor wing of the unmanned aerial vehicle radioactively, wherein the first supporting rod is arranged along the extending direction of acantilever; the second supporting rod and the third supporting rod are respectively arranged in a manner of being vertical to the first supporting rod; the first supporting rod, the second supportingrod, the third supporting rod and the cantilever are arranged to support the fairing from the bottom part of the fairing. The supporting structure provided by the invention has the beneficial effectsthat the supporting structure of the fairing supports the fairing from the bottom part of the fairing, the supporting point of the supporting structure is positioned under the fairing, so that the opening of the connecting part is positioned under the fairing and can not cause interference with the flow field in the fairing basically, the adverse influence of the supporting structure on the airflow efficiency of the rotor wing is reduced, the pneumatic structure of the flow guiding channel can not be damaged and the flow guiding effect is better.
Owner:沈阳旋飞航空技术有限公司
Adjustable helicopter front center-of-gravity counterweight device
InactiveCN109229401ADoes not affect aerodynamic shapeSolve the low efficiency of counterweightAircraft componentsRotocraftStatic strengthUltimate tensile strength
The invention belongs to the technical field of helicopter structures and relates to an adjustable helicopter front center-of-gravity counterweight device, which comprises a fixed counterweight plate,a long bolt, a groove counterweight plate and a movable counterweight plate; As that helicopter head equipment rack is used as a structural support and is installed inside the helicopter, the helicopter head equipment rack occupies a relatively forward position under the condition that the aerodynamic shape of the helicopter is not affected, and the helicopter head equipment rack has high counterweight effect on the front center of gravity of the helicopter; Adopting machined steel counterweight plate and steel adjusting sleeve as main weight adjusting components, the flexible adjustment of counterweight can be realized by adjusting the number of assembled heavy plate and adjusting sleeve. The components of the device are connected by threads, which is convenient to disassemble and assemble. The design of the device and connection scheme can meet the requirements of static strength under flight load.
Owner:HARBIN
A high-speed train, a high-speed train emergency braking method and system
ActiveCN112498406BDoes not affect aerodynamic shapeReduce mechanical wearRailway braking systemsAutomatic brakingMechanical wear
The invention discloses a high-speed train and a high-speed train emergency braking method and system. On the basis of conventional braking, a main umbrella device and an air injection device are added. Under normal conditions, the main umbrella device does not open, the air injection device does not start, and the Affects the aerodynamic shape of the train; when an emergency occurs, different braking modes are activated according to the different levels of the emergency, and the wind resistance is greatly increased through the main parachute device and the air jet device, the braking distance is greatly shortened, and the braking distance is greatly improved. The effect and the safety of train operation, and this wind resistance braking method is energy-saving and environmentally friendly, and reduces the mechanical wear on the train and rails. Based on the visual unit to identify obstacles and detect the distance of obstacles, different braking modes are activated according to the distance of obstacles, realizing intelligent and automatic braking in emergency situations.
Owner:ZHUZHOU ELECTRIC LOCOMOTIVE CO LTD
A method for repairing aircraft pressurized cockpit skin
ActiveCN106143945BDoes not affect aerodynamic shapeAvoid negative effectsFuselage bulkheadsAircraft maintainancePurlinJet aeroplane
The invention provides an airplane pressurized cabin skin repairing method. The method is characterized by including the following steps that firstly, a reinforcing cushion plate is manufactured and provided with lugs connected with a long purlin in a matched manner; secondly, rivets connecting the the damaged position of the long purlin with a skin are decomposed; thirdly, an interlayer sealing material is laid on the region of the damage position; fourthly, the reinforcing cushion plate is placed on the interlayer sealing material between the skin and the long purlin; fifthly, installation holes are drilled in the positions, corresponding to rivet holes in the long purlin, in the reinforcing cushion plate, the positions of the lugs are included, and the reinforcing cushion plate, the interlayer sealing material, the skin and the long purlin are riveted into a whole; and sixthly, the rivets are coated with sealing glue.
Owner:SHAANXI AIRCRAFT CORPORATION
A kind of icing detecting device and icing detecting method
ActiveCN114162331BDoes not affect aerodynamic shapeSmall structure sizeDe-icing equipmentsFlight vehicleEngineering
The present invention is applicable to the technical field of aircraft icing detection, and provides an icing detection device and an icing detection method, including: a detection part, the detection part is installed on the skin surface of the aircraft; an optical sensor, the optical sensor is arranged on In the lower area covered by the detection part; the light sensor includes a substrate, a light emitting module and a light receiving module, the light emitting module and the light receiving module are installed on the substrate, and the light emitting module includes a light emitting circuit And a semiconductor light emitting unit, the light receiving module includes a photosensitive unit; the photosensitive unit is arranged around the semiconductor light emitting unit in an array; a signal processing unit, the signal processing unit is connected to the light sensor. The structural size of the photosensitive unit can be made smaller. Each photosensitive unit will process the received incident light, convert the optical signal into an electrical signal, and finally obtain the ice type, ice structure and ice thickness on the surface of the detection part. information.
Owner:LOW SPEED AERODYNAMIC INST OF CHINESE AERODYNAMIC RES & DEV CENT
Ultrasonic-assisted hot air combined anti-icing device for aircraft airfoil
Owner:SOUTHEAST UNIV
Novel electric heating ice shape regulation and control method and anti-icing aircraft
InactiveCN110481793AGuaranteed normal flightReduced impact on aerodynamic performanceDe-icing equipmentsControl systemFlight vehicle
The invention discloses a novel electric heating ice shape regulation and control method and an anti-icing type aircraft. The anti-icing aircraft comprises a wing main body with a surface skin, wherein a novel electric heating ice shape regulation and control system is arranged between the wing main body and the skin and comprises a plurality of electric heating units arranged and displayed alongthe wing, the electric heating units are the electric heating films, cover the front edge of the wing main body, are arranged in parallel are connected with an airborne power supply. According to theanti-icing aircraft, the whole wing can be prevented from icing, the severe ice shapes (claw ice) can be prevented, the influence of icing on the aerodynamic performance is reduced, and energy consumption is lower.
Owner:AIR FORCE UNIV PLA
Gas Flow Field Measurement System Based on AC Discharge Plasma Sensor
ActiveCN104251767BImprove spatial resolutionFine measurementAerodynamic testingHigh pressurePlasma Gases
The invention provides a gas flow field measurement system based on an AC discharge plasma sensor. The gas flow field measurement system includes: a substrate, attached to the surface of the object to be measured; several plasma sensing units, respectively used to measure the flow conditions in the area where each plasma sensing unit includes: a plasma sensor , including a high-voltage electrode and a ground electrode oppositely arranged on the surface of the substrate; an AC power supply, one end of which is connected to the high-voltage electrode and the other end is connected to the ground electrode, for providing an operating voltage for the plasma sensor; and determining The device is connected with the plurality of plasma sensing units, and is used for judging the gas flow condition at the position where the plasma sensor is located by using the voltage signal output by the plasma sensor. Compared with the existing gas flow field measurement system, the gas flow field measurement system of the present invention has simple structure, low cost and high precision.
Owner:INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
Aircraft anti-icing fuel system suitable for high-altitude low temperature environment
InactiveCN101580130BSafe and reliable workWork lessPower plant fuel tanksMachines/enginesFuel tankAlloy
The invention discloses an aircraft anti-icing fuel system suitable for high-altitude low temperature environment. A fuel filter in the fuel system is an irregular rectangular structure with top beinga bevel of 45 degrees, adopts aluminum alloy framework and is welded by externally covered filter screens with filter fineness of 50mu; the fuel in a fuel tanker enters a consumption tank after beingfiltered by the fuel filter; return fuel in an engine evenly flows down through the fuel filter from the top of the fuel filter by passing through a horizontal pipe which is installed at the top of the fuel filter and is provided with small holes; the heat of the return fuel is adopted to melt ice crystals which probably remain on the surface of the fuel filter; impurities such as gum formed by moisture, ice crystals or oxide in the fuel flow to a consumption tank sump along the surface of the fuel filter. By adopting such a special system, impurities such as ice crystals, moisture and the like in the fuel can be effectively stopped from entering a feedline of the engine, impurities such as ice crystals and the like in the fuel can be prevented in real time from blocking the fuel pump andcarburetor of the engine, and the engine can be ensured to work safely under high-altitude low temperature environment for long time.
Owner:BEIHANG UNIV
Neighbor discharging and dissipating aircraft skin heat dissipation system based on wind-liquid comprehensive heat dissipation structure
PendingCN114435582AReduce weightReduce power consumptionAir-treatment apparatus arrangementsFuselage bulkheadsHeat fluxHeat flow
The invention discloses a nearby discharging aircraft skin radiator based on a wind-liquid comprehensive heat dissipation structure. The aircraft skin radiator comprises an airborne equipment liquid cooling pipeline, a wind-liquid comprehensive heat dissipation conversion pipeline and an in-cabin air cooling regeneration pipeline. Waste heat generated in the working process of the airborne equipment is absorbed by a liquid-phase refrigerant in the liquid cooling pipeline of the airborne equipment, then is transmitted to air in a cabin through the wind-liquid comprehensive heat dissipation conversion pipeline, is transmitted to an aircraft skin through the air cooling regeneration pipeline in the cabin, and is finally discharged to ambient air. Two heat dissipation modes of liquid cooling heat dissipation and air cooling heat dissipation exist in the aircraft skin heat dissipation device at the same time, the requirement for high heat dissipation heat flux density of the surface of airborne equipment can be met under low power consumption, and the reliability of the aircraft skin heat dissipation device is remarkably improved.
Owner:NANJING UNIV OF SCI & TECH
A uniaxial wing folding mechanism
ActiveCN109606633BDoes not affect aerodynamic shapeReduce weightWing adjustmentsStructural engineeringRotary actuator
The invention discloses a uniaxial wing folding mechanism, which is installed between the inner wing and the outer wing, comprising a folding shaft on which the inner wing joint lugs and the outer wing joint lugs are installed, and a folding shaft rotatably mounted on the folding shaft. mechanism; the folding mechanism includes a rotary actuator that is rotationally connected to the folding shaft, an outer wing folding link that is rotatably mounted on the output shaft of the rotary actuator, and an inner wing that is fixedly mounted on the output shaft of the rotary actuator Folding connecting rod; the outer wing folding connecting rod and outer wing joint lugs are respectively connected to the outer wing; the inner wing folding connecting rod and inner wing joint ear are respectively connected to the inner wing. The beneficial effects of the present invention are: the present invention takes up little space, does not affect the aerodynamic profile of the wing, has a large folding angle, light mechanism structure, is easy to maintain, and is easy to implement, and is suitable for carrier-based aircraft wing folding engineering applications; the present invention does not require design The envelope is bulging, so that the wing folding mechanism can fold at a large angle without affecting the aerodynamic shape of the wing.
Owner:CHENGDU AIRCRAFT INDUSTRY GROUP
Aircraft surface humidity online monitoring sensing probe
The invention belongs to the field of aircraft structure corrosion environment element monitoring, and particularly relates to an aircraft surface humidity online monitoring sensing probe. The probe comprises a first line electrode, a second line electrode and an insulating carrier plate, the first line electrode and the second line electrode are made of the same material and are arranged on the carrier plate in parallel, and the distance between the first line electrode and the second line electrode is smaller than the line width of the first line electrode and the line width of the second line electrode. The probe monitors the impedance between the electrodes, can quickly reflect whether a liquid film or moisture exists on the surface of a structure or not, is light in weight and small in size, can be directly attached to the surface of an airplane structure for in-situ monitoring, does not damage the original structure, and does not influence the weight and aerodynamic configurationof the airplane.
Owner:CHINA SPECIAL TYPE FLIER RES INST
Anti-icing wind power generation blade
ActiveCN110259650ADoes not affect aerodynamic shapeHigh fever rateMachines/enginesWind energy generationCarbon nanotubeEngineering
The invention discloses an anti-icing wind power generation blade. The anti-icing wind power generation blade comprises a blade body, deicing devices capable of preventing the wind power generation blade from icing are densely distributed on the surface of the blade body, and the deicing devices are carbon nanotube heating wires; a cavity is formed in a blade root position of the blade body, and an electrifying device connected to the carbon nanotube heating wires for electrifying is arranged in the cavity; and a moving device capable of driving the electrifying device to move outwards from the cavity is arranged on the electrifying device, and an electromagnetic seat capable of enabling the moving device to move through magnetic adsorption is arranged on one side of the moving device. According to the anti-icing wind power generation blade, deicing can be realized by coating the carbon nanotube heating wires or carbon nanotube heating coating material on the blade body, micro size does not influence the aerodynamic shape of the blade, heating and deicing can be carried out without shutdown, electrifying can be realized through using electromagnetic connection, the complexity of construction can be further reduced, and a more convenient and reliable solution is provided for the deicing problem of the whole wind power generation field.
Owner:中山宝立得高分子材料有限公司
Heat pipe ultrasonic combined anti-icing and de-icing device and method using waste heat of aircraft engine
InactiveCN105691620BPrevent freezingStable anti-icing temperatureDe-icing equipmentsAtmospheric temperatureEvaporation
The invention provides a heat pipe and ultrasonic wave combined ice preventing and removing device and method utilizing waste heat of an aircraft engine. The device comprises a heat pipe ice-preventing system, an ultrasonic oscillation ice removing system, a program control system, an atmospheric temperature sensor and an icing strength annunciator. The heat pipe ice-preventing system comprises a communicating pipe installed at the tail portion of the engine to absorb exhaust waste heat and a heat pipe bank bundle with an evaporation section connected with the communicating pipe. The ultrasonic oscillation ice removing system comprises an ultrasonic generator and an ultrasonic transducer unit connected with the output end of the ultrasonic generator through a connecting cable. The program control system automatically controls on and off between the heat pipe bank bundle and the communicating pipe and starting or stopping of the ultrasonic generator according to a temperature signal and an icing strength signal. By means of the synergistic effect of heat pipes and ultrasonic waves, preventing and removing can be combined, compared with a method for removing ice simply through ultrasonic waves, the icing phenomenon of wings is greatly reduced, the flying stability of an aircraft is ensured, and a system is safe and reliable.
Owner:NANJING NORMAL UNIVERSITY
A plug-in helicopter maintenance pedal
The invention relates to a plug-type helicopter maintenance pedal and belongs to helicopter structural designs. The plug-type helicopter maintenance pedal comprises a first slide rail, a second sliderail and a supporting footboard, wherein the first slide rail is provided with a first track consisting a first limiting rib and a second limiting rib that are mutually parallel, and a first limitingpart is arranged at one end part of the first limiting rib to restrict rollers from sliding; the second slide rail is provided with a second track consisting of a third limiting rib and a fourth limiting rib that are mutually parallel, a second limiting part is arranged at one end part of the third limiting rib to restrict the rollers from sliding, and the second slide rail and the first slide rail are symmetrical; and the supporting footboard is of an arc-shaped structure, a skin is arranged on an arc-shaped side, a diametral plane is a pedal face, not less than two roller sets are arranged on two sides of the pedal face, a certain distance is kept between the roller sets, and axes of the rollers are parallel to the pedal face. The internal space is fully utilized, the pedal is plugged and maintained according to maintenance requirements, defects of a conventional fixed pedal are avoided, and aerodynamic configuration is not influenced.
Owner:CHINA HELICOPTER RES & DEV INST
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