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

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.

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.

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.

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 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.

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.

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.

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.

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.