33 results about "Aviation medicine" patented technology

The invention discloses a method for controlling the laser shot peening shape correction quality for aviation engine supports. The method includes steps of creating corresponding relational databases of laser shot peening shape correction parameters and welding deformation amounts by the aid of big data platforms; refining structures of the aviation engine supports; welding the refined structures and correcting the shapes of the refined structures by means of laser shot peening; welding support assemblies and correcting the shapes of the support assemblies by means of laser shot peening; detecting shape correction effects. According to the scheme, the method has the advantages that the complicated aviation engine supports are refined to obtain three types of simple refined structures, and processing sequences of progressive welding, progressive laser shot peening shape correcting, assembly welding and assembly laser shot peening shape correcting are adopted, the shapes of the various refined structures are corrected by means of laser shot peening before the assemblies are welded, accordingly, welding deformation of overall structures of the supports can be reduced, and the overall structures of the supports are easy to correct during laser shot peening shape correction; the problem of deformation of existing aviation engine supports in welding procedures can be solved by the aid of the method, the dimension precision and the shape precision of the supports can be accurately controlled by the aid of the method, and good correction effects can be realized.

An electronic control device is provided for an aviation engine. Each cylinder of the engine is equipped with main ignition plugs and back-up ignition plugs. Lane A including a first CPU and lane B including a second CPU are included in an ECU. The ignition control system is multiplexed by the two lanes A, B. The first and second CPU independently calculate ignition timing for each cylinder based on each sensor signal, and then exchange the results of these calculations with each other. At each cylinder, ignition timing is synchronized in such a manner that ignition timing of the main ignition plugs and ignition timing of the back-up ignition plugs match. The electronic control device so configured has a high level of redundancy with a small number of CPU's. Thus, electronic control device can be provided for the aviation engine with few limitations placed in relation to installation location.

The invention discloses a method for detecting the diameter of an outer wall of a tapered case of an aviation engine on line. According to the method, a five-coordinate numerical control milling center with a Renishaw MP10 trigger-type measuring head is equipped, tapered case parts and a mounting seat on the surface of a tapered case are equipped; a fine adjustment ring gauge of the used measuring head is measured on line; a point contact-type measurement mode is adopted; a machine tool siemens control system Sinumeric 840 D on-line measurement technology is adopted; and an on-line measurement quick tool path amendment and error compensation generation technology is adopted. The method has a broad application prospect; and by the on-line measurement technology, a numerically-controlled machine tool is impelled to form a machining and detecting integrated numerical control machining unit. By the method, the traditional manufacturing mode that a design characteristic is equipped with a set of measurement tool in the current industry is changed, the manufacturing cost of the tool is saved, repair labor-hour is saved, and first-pass yield of product processing is improved, so that the development period and the production cost of new products are reduced.

The invention provides a 3D imaging system and method of an industrial CT. The imaging system comprises an X-ray generator, an arc-shaped detector, a primary conveyer belt and a secondary conveyer belt, wherein the X-ray generator and the arc-shaped detector are opposite to each other; the primary conveyer belt and the secondary conveyer belt are arranged on the same axis; a gap is formed between the opposite ends of the primary conveyer belt and the secondary conveyer belt; the X-ray generator and the arc-shaped detector are arranged in a manner of rotating around the primary conveyer belt and the secondary conveyer belt by taking the gas as the circle center. Through longitudinal section type scanning of the 3D imaging system, relatively long objects such as long-columnar objects of dozens of centimeters to dozens of meters as well as internal materials, meters and elements such as water suction pumps, water conservancy generators, aviation undercarriages, aviation engines, diving gears, underwater searching and rescuing devices, bridge components, aerospace vehicles and underwater moving devices can be relatively easily checked by using the 3D imaging method.

The invention discloses a method and device for detecting the fastening force of a low-pressure turbine shaft disk of an aero-engine based on an eddy current sensor group. relationship; test the relative displacement of the upper and lower surfaces of the low-pressure turbine shaft-disc structure during or after assembly; determine whether the pre-tightening force is insufficient or too large for each bolt to be tested or adjacent bolts; determine unreasonable pre-tightening force bolts, and pre-tightening Tightness deviation value. The invention measures the relative displacement of the upper and lower disk surfaces of the low-pressure turbine shaft disk of the aero-engine, quickly and accurately judges the pre-tightening state of the bolts, does not need to destroy the bolt structure during the measurement process, and has higher precision than the current method of directly measuring the length of short bolts, and measures the relative displacement of the upper and lower disk surfaces , and the relative displacement deviation of the disk surface caused by the pretightening force deviation relative to the expected value, avoiding the influence of the basic coordinate deviation of the disk surface on the measurement data during the preloading process.

The invention discloses a bearing supporting device applied to an aero-engine. The bearing supporting device comprises a bearing; the bearing comprises an inner ring body; a plurality of balls are installed at the outer wall of the inner ring body; a clamping plate is installed in an inner chamber of a clamping slot; an inserting rod is installed at the upper surface of the clamping plate; the topend of the inserting rod is connected with a second upright post; and a second spring is installed at the bottom of the clamping plate and is connected with the inner wall of the clamping slot. According to the bearing supporting device applied to the aero-engine, a first clamping ring and a second clamping ring are used for clamping the bearing at the middle; a nut is tightened and the clampingplate is pressed tightly in a way of twisting a bolt so that the bearing can be clamped by the first clamping ring and the second clamping ring; when shock occurs, the first spring supports the secondupright post so that the shock is alleviated, and the clamping plate is used for limiting the relative positions of a first upright post and the second upright post; and the second spring positionedat the bottom of the clamping plate can also be used for reducing an impact force when shock occurs, so the safety of people is guaranteed.