34results about How to "Does not affect aerodynamic shape" patented technology

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.