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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 23. Отображено 23.
15-08-2023 дата публикации

Cross-generation development small bypass ratio turbofan engine main engine and stress application matching method

Номер: CN116595680A
Автор: CHENG RONGHUI, CAO MAOGUO, HAOBISI GALATU, CHEN ZHONGGUANG, XU XINGPING, ZHANG ZHISHU, YUAN JILAI, JIANG YU, XUE HAIBO, CHEN DI, JIANG FANSHENG, CHEN ZEHUA, RUAN WENBO, ZHANG XUEDONG, ZHU ZHENKUN
Принадлежит:

The invention belongs to the field of aero-engine design, and relates to a cross-generation development small-bypass-ratio turbofan engine main engine and afterburner matching method, which comprises the following steps: preliminarily determining a main engine and afterburner design criterion, and then carrying out main engine and afterburner matching work preliminary scheme design; and processing hardware until the engine performance or the main engine and thrust augmentation matching design criterion requirements are met, then carrying out a full-size afterburner test, collecting test data, correcting the working abnormity of the afterburner, putting all parts of the full-size afterburner test into the whole engine, carrying out the whole-process test of the whole engine, and completing the whole-process test of the whole engine. The actual performance of all parts under the overall condition is obtained, after the work matching problem of a main engine and an afterburner is optimized ...

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Номер записи: 1
23-06-2023 дата публикации

Quick warm-up control method and device for ensuring reliable work of aero-engine

Номер: CN116291898A
Автор: CHENG RONGHUI, ZHANG XUEDONG, WANG JINGKE, CAO MAOGUO, JIA LINYUAN, BAI SHUAIYU, ZHAI YINGHAN, ZHU ZHENKUN, BING LIANXI, ZHANG ZHICHENG, LI CHENGLONG, BAI HANSONG, YUAN JILAI, JIANG FANSHENG, ZHANG ZHISHU, ZHANG XICHANG, CHEN ZHONGGUANG, WU YASHUAI
Принадлежит:

The invention belongs to the technical field of engine control, and particularly relates to a rapid warm-up control method and device for ensuring reliable work of an aero-engine. The method comprises the following steps: S1, acquiring a use mode of an engine, wherein the use mode comprises a combat mode or a training mode; s2, the starting state of the engine is obtained, wherein the starting state comprises a cold starting state or a hot starting state; and S3, four engine warming strategies are formed according to the combination of the use mode and the starting state of the engine, engine warming is carried out according to the different slow rotating speed staying time and the set rotating speed staying time at the set rotating speed higher than the slow rotating speed according to the engine warming strategies, and under the engine warming strategy with the combat mode and the cold-state starting state combined, engine warming is carried out according to the set rotating speed staying ...

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Номер записи: 2
22-08-2023 дата публикации

Control framework for overall structural design of aero-engine

Номер: CN116628866A
Автор: FAN JIANG, E YUYANG, GUO JIAWEI, DING XI, CAO MAOGUO
Принадлежит:

The invention relates to the technical field of aero-generator design, in particular to a control framework for aero-engine overall structure design, which comprises an overall structure design control framework and an engine overall design control framework, a control framework layer with a mutual dependency relationship is established, a control framework of the current layer in the control framework layer is composed of geometric elements and corresponding control parameters, a lower-layer control framework in the control framework layer depends on an upper-layer control framework, and the control frameworks in the same layer do not have a dependency relationship; the dependency relationships among the control framework layers comprise parameter correlation relationships, geometric correlation relationships and constraint correlation relationships, compared with the prior art, the engine overall structure control framework is utilized, design key points are easy to grasp, complex dependency ...

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Номер записи: 3
23-06-2023 дата публикации

Novel integrated high-strength bearing cavity oil supply and heat insulation structure

Номер: CN116291884A
Автор: LENG ZIHAO, CHENG RONGHUI, CAO MAOGUO, SU ZHUANG, GUO SONG, ZHANG JIEYI, ZHENG KAI, LI GUOQUAN
Принадлежит:

The invention belongs to the technical field of aero-engines, and particularly relates to a novel integrated high-strength bearing cavity oil supply and heat insulation structure, through an integrated rear cover assembly structure, an oil supply pipe assembly and a skin heat insulation assembly structure are integrated, the assembly work of a rotor and a stator can be completed under the visual condition, and meanwhile through the design of a jackscrew hole structure, the assembly efficiency is improved. The disassembly work of the rear cover assembly can be very conveniently completed, structures such as a sealing device are prevented from being damaged, and the assembly and disassembly reliability of the bearing cavity oil supply and heat insulation structure is greatly improved; through the inner skin structure with the reinforcing ribs, the skin heat insulation assembly structure is optimized, under the condition of high pressure difference, the outer skin stress and the skin heat ...

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Номер записи: 4
15-08-2023 дата публикации

Accurate determination method for low-conduction capacity requirement of whole engine

Номер: CN116595790A
Автор: CHENG RONGHUI, HAOBISI GALATU, CHEN ZEHUA, YANG LONGLONG, CHEN ZHONGGUANG, ZHANG ZHISHU, CAO MAOGUO, HUANG YUJUAN, YU MING, RUAN WENBO, ZHANG XUEDONG, ZHU ZHENKUN, JIANG FANSHENG, XUE HAIBO, WU YASHUAI
Принадлежит:

The invention belongs to the field of aero-engine design, and relates to a method for accurately determining the low conduction capacity requirement of a complete engine, which comprises the following steps of: firstly, respectively carrying out part test, core engine and complete engine test on the engine by adopting the same set of hardware and the same set of test scheme to obtain the actual performance of each part under the overall condition; then, the high-pressure turbine expansion ratio and the external and internal culvert outlet pressure ratio are determined, the subsequent design direction is determined by judging the high-pressure turbine expansion ratio and the expansion ratio design value and the external and internal culvert outlet pressure ratio and the pressure ratio design value respectively, and then the influence of low-pressure turbine guider area adjustment on adjustable parameters is scored, so that the design direction is determined. According to the method, the ...

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Номер записи: 5
07-04-2023 дата публикации

Aerial turbofan engine shaft component cyclic fatigue life load spectrum compilation method

Номер: CN115935523A
Автор: ZHENG MAOJUN, CHENG RONGHUI, ZHANG YONG, YANG CHANGQI, CONG PEIHONG, CAO MAOGUO, WANG HAIXU, GUO YONG
Принадлежит:

The invention provides an aviation turbofan engine shaft component cycle fatigue life load spectrum compilation method comprising the following steps: 1, collecting an engine typical mission profile and mixing frequency data thereof, and combining the height, the Mach number and the engine working state to form an engine typical working point; 2, corresponding overall performance parameters are collected according to typical working points of the engine and converted into torque characteristic values, and a graphic format of a typical task section is established with the torque characteristic values as ordinates and task section serial numbers as abscissas; 3, performing statistics on each typical mission profile according to the torque characteristic value by adopting a rain flow counting method to obtain all peak/valley value points of a plurality of cycle pairs and corresponding typical working points of the engine; and 4, selecting or clustering peak/valley value points from the typical ...

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Номер записи: 6
21-04-2023 дата публикации

Engine turbine rear thrust increasing component

Номер: CN115992776A
Автор: CHENG RONGHUI, LIU BAO, SUN XIAOFENG, CAO MAOGUO, XU XINGPING, YOU QINGJIANG, MA HONGYU, ZHU JIAN, LIU WEICHEN, JIANG YU, BAO ZHANYANG, CHEN DI, ZHANG ZHIXUE, LI JIANGNING, ZHOU CHUNYANG, GUO HONGTAO, ZHANG XIAOYU, MA YU, PAN XINZHENG, YAN JINSHENG
Принадлежит:

The invention belongs to the technical field of design of non-variable-capacity engine components, and particularly relates to an engine turbine rear thrust increasing component which comprises an annular outer wall, an inner wall and an outer wall. The confluence ring is arranged in the annular outer wall, and an outer culvert is formed between the confluence ring and the annular outer wall; the inner cone is arranged in the confluence ring, and an inner connotation is formed between the inner cone and the confluence ring; the annular heat insulation screen is arranged in the annular outer wall, is located at the outlet part of the annular outer wall and is corrugated, and a plurality of rows of air film holes are formed in each windward side of the corrugation; the outer side air entraining cylinders are arranged between the annular outer wall and the annular heat insulation screen, and the rear ends of the outer side air entraining cylinders are connected to crest positions of the corrugations ...

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Номер записи: 7
07-04-2023 дата публикации

Method for rapidly and accurately evaluating roundness through variable step size fast iteration of runout measurement value

Номер: CN115930877A
Автор: LI QIJIAN, ZHAO DANDAN, WANG DONG, CAO MAOGUO, HONG HAORAN, WANG CHUJUN
Принадлежит:

The invention belongs to the field of roundness evaluation of rotary body parts, and particularly relates to a method for rapidly and accurately evaluating roundness through variable step size rapid iteration of a runout measurement value. Comprising the steps that a two-dimensional coordinate system is established based on the plane where the rotary body part is located, and any point in the rotary body part serves as the original point of the coordinate system; a plurality of data points are determined on the rotary body part, and a roundness evaluation area containing all the data points is obtained; averagely dividing the roundness evaluation area into N * M rectangular areas through segmentation lines, calculating the distance between the intersection of the segmentation lines and each data point, obtaining the maximum distance Rmax and the minimum distance Rmin from each intersection to the data point, and determining the intersection with the minimum Rmax-Rmin; the area defined by ...

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Номер записи: 8
27-06-2023 дата публикации

Aero-engine lubricating oil ventilation system with high sealing reliability

Номер: CN116335827A
Автор: LENG ZIHAO, CHENG RONGHUI, CAO MAOGUO, SU ZHUANG, HOU HONGJIAN, HU XINGLONG, GU ZHIYING, SONG GUANLIN, LI GUOQUAN
Принадлежит:

The invention belongs to the field of aero-engines, and particularly relates to a high-sealing-reliability aero-engine lubricating oil ventilation system which improves the oil return effect of a bearing cavity and avoids lubricating oil leakage by increasing the thickness of front and middle cavity oil return stage rotors in an oil return pump set and increasing the oil return capacity of front and middle cavities. Controllable ventilation electromagnetic valves are arranged on ventilation pipelines of a front bearing cavity and a middle bearing cavity, when an engine is at a low rotating speed, ventilation of the front cavity and the middle cavity is closed, and under the suction effect of an oil scavenging pump set, the cavity pressure of the front cavity and the middle cavity is reduced, the sealing pressure difference is increased, the sealing reliability is improved, and lubricating oil leakage of the front cavity and the middle cavity is avoided.

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Номер записи: 9
11-08-2023 дата публикации

Method for rapidly determining infrared stealth performance of aero-engine

Номер: CN116579135A
Автор: CHEN HANZE, CHENG RONGHUI, SHANG SHOUTANG, CAO MAOGUO, DENG HONGWEI, LU HAOHAO, WANG DIANLEI
Принадлежит:

The invention relates to a method for rapidly determining the infrared stealth performance of an aero-engine, and the method comprises the steps: carrying out the simulation calculation on an infrared stealth material on each backward visual part on the basis of setting that the infrared stealth material has a plurality of different damage areas; the infrared stealth performance of the aero-engine under the combination of different damage areas of the infrared stealth material on each backward visual part is obtained, so that a regression equation associated between the infrared stealth performance of the aero-engine and the damage area of the infrared stealth material on each backward visual part is trained, and a regression coefficient is obtained; selecting the aero-engine, measuring the damage area of each backward visual component, obtaining the infrared stealth performance of the aero-engine through simulation calculation, checking the accuracy of a regression equation, and quickly ...

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Номер записи: 10
18-07-2023 дата публикации

Bearing cavity oil return and ventilation structure with low lubricating oil consumption

Номер: CN116447013A
Автор: LENG ZIHAO, CHENG RONGHUI, CAO MAOGUO, SU ZHUANG, SONG GUANLIN, HU XINGLONG, HAN JINZAI, GUO SONG, ZHANG JIEYI, YU LI, CHEN XUEQI, MAO HONGTU
Принадлежит:

The invention belongs to the field of aero-engines, and particularly relates to a bearing cavity oil return and ventilation structure with low lubricating oil consumption, by designing a bearing cavity oil return oil-gas separation structure, a high-speed rotating gas cavity and a lubricating oil return cavity are isolated, oil and gas in an oil collection cavity are effectively separated, interference of high-speed flowing gas on flowing of lubricating oil in the oil return cavity is reduced, and the lubricating oil in the lubricating oil return cavity is effectively separated. By designing a ventilation oil-gas separation structure of the bearing cavity, oil gas near the ventilation hole is effectively separated, the amount of the lubricating oil entering the ventilation cavity is reduced, the oil return efficiency is improved, and the lubricating oil consumption is reduced.

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Номер записи: 11
23-06-2023 дата публикации

Aero-engine slide rail assembly system

Номер: CN116280241A
Автор: LI JIAN, CAO MAOGUO, JIA ZHIYUAN, YANG RANSHENG, LIANG JING, SUN JIAWEI, YANG YONGHUA, LU WENRUI, DENG RUTAN, DING SONG
Принадлежит:

The invention provides an aero-engine sliding rail assembling system. The aero-engine sliding rail assembling system comprises an engine mounting rack car, a sliding rail assembly and a sliding rail assembly, the engine hanging system is formed by a double-lug structure above the engine; the sliding rail is installed in an engine compartment of the aircraft and is of a rectangular opening structure, and the opening is located on the lower side of the rectangular section; the pulley assembly comprises a pulley mounting seat, a plurality of groups of pulleys are distributed on two sides of the pulley mounting seat, a single-lug structure is formed on one side, opposite to the pulleys, of the pulley mounting seat, and a bearing is mounted in the single-lug structure; when the engine is mounted, firstly, the engine is lifted behind the engine through the engine mounting rack car, the engine is lifted in front of the engine, the engine hanging system is fixedly connected with the pulley assembly ...

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Номер записи: 12
21-07-2023 дата публикации

Sawtooth crown blade and blade crown tightness design method thereof

Номер: CN116467804A
Автор: CHENG RONGHUI, GUO RUI, CAO MAOGUO, MA SHIYAN, WEI WENTAO, YANG YANGHUA, YU RONGBIN
Принадлежит:

The invention provides a sawtooth crown blade shroud tightness design method which comprises the following steps: constructing a relation between blade shroud torsional mechanics and a geometric position according to a blade shroud stress condition of a turbine blade in an assembly state; introducing a tightness change rate, and constructing a relational expression between the shroud tightness function and the shroud meshing angle, the tightness change rate and the shroud pre-torsion angle; drawing a plurality of curves with equal pre-torsion angles and equal meshing angles by taking the tightness change rate as an abscissa and the shroud tightness function as an ordinate to obtain a shroud tightness extrusion force function curve; determining a shroud tightness function, a tightness change rate and a shroud meshing angle range, drawing a maximum straight line and a minimum straight line of the shroud tightness function on a shroud tightness function curve, and drawing a maximum curve and ...

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Номер записи: 13
09-06-2023 дата публикации

Self-adaptive rear bearing casing outer ring rectification heat shield structure

Номер: CN116241345A
Автор: SUN GUOZHI, LIU MEI, CAO MAOGUO, LIU YUNLONG, YUAN CHANG, XIE LIJUAN, CUI YAN, ZHUO WENJING, DONG YUE
Принадлежит:

The invention belongs to the design field of aero-engines and gas turbines, and relates to a self-adaptive rear bearing casing outer ring rectification heat shield structure which comprises a second front mounting edge, a cylinder and a second rear mounting edge, and the cylinder is divided into a plurality of split bodies with the same size in the circumferential direction; each split body is integrally connected with the second front mounting edge and the second rear mounting edge, so that a connecting structure does not need to be arranged between any split bodies, a connecting bolt of the middle mounting edge is omitted, the radial space is saved, the diameter of the outer culvert of the bearing case is reduced, and the weight is reduced; meanwhile, the flow channel molded surface has no height difference in the axial direction, the smoothness is improved, and the pneumatic loss is reduced; according to the outer ring rectification heat shield structure, the plurality of split bodies ...

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Номер записи: 14
04-08-2023 дата публикации

Method for improving cleanliness of lubricating oil system of aero-engine

Номер: CN116537947A
Автор: HOU HONGJIAN, SU ZHUANG, CAI CHENGYANG, HU XINGLONG, CAO MAOGUO, GU ZHIYING
Принадлежит:

The invention belongs to the technical field of engine maintenance, and particularly relates to a method for improving the cleanliness of a lubricating oil system of an aero-engine. The method comprises the steps that S1, an oil supply pipeline between a lubricating oil filter (3) and a radiator (4) is decomposed, and an extracorporeal circulation oil filter (5) with the filtering precision higher than that of the lubricating oil filter (3) is externally connected; s2, detaching a filter element of the oil filter (3), and replacing the filter element with a process filter element framework (6) without a filter screen; and S3, engine lubricating oil is filtered based on the extracorporeal circulation oil filter (5), after the engine lubricating oil is controlled to run along with the engine for a set time, the extracorporeal circulation oil filter (5) is detached, and assembly of the engine oil supply pipeline and the lubricating oil filter element is restored. Foreign matters mingled in ...

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Номер записи: 15
04-04-2023 дата публикации

Fan-shaped on-duty stabilizer and oil supply method thereof

Номер: CN115899762A
Автор: CHENG RONGHUI, JIANG YU, CAO MAOGUO, XU XINGPING, LIU BAO, CHEN DI, BAO ZHANYANG, YOU QINGJIANG, ZHANG XIAOYU, MA YU, KANG BOFENG
Принадлежит:

The invention belongs to the field of aero-engine design, and particularly relates to a fan-shaped on-duty stabilizer and an oil supply method thereof. The radial stabilizers are installed on the inner wall of the afterburner casing in the circumferential direction, the roots of the radial stabilizers are installed on the inner wall face of the afterburner casing, and the tips of the radial stabilizers point to the center line of the afterburner casing; wherein each radial stabilizer is provided with a cavity, each cavity is provided with a main spray rod and an auxiliary spray rod, and the main spray rods and the auxiliary spray rods spray oil through nozzles on the side walls of the radial stabilizers; the main spraying rod is connected with a main pipe for supplying oil; the auxiliary spraying rod comprises a first group of auxiliary spraying rods and a second auxiliary spraying rod, the first group of auxiliary spraying rods are connected with a first auxiliary pipe for supplying oil ...

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Номер записи: 16
06-06-2023 дата публикации

Method for constructing maneuvering overload spectrum of aero-engine

Номер: CN116227148A
Автор: ZHENG MAOJUN, ZHANG YONG, CHENG RONGHUI, CONG PEIHONG, CAO MAOGUO, BAI HANSONG
Принадлежит:

The invention provides an aero-engine maneuvering overload spectrum construction method, which is used for constructing a maneuvering load spectrum of a new trans-generation research model, and takes demand analysis as a starting point, based on analysis of a design usage of the new trans-generation research model, various existing limitation data conditions are collected, analyzed, absorbed and integrated, and the maneuvering overload spectrum of the aero-engine is constructed. According to the method, the problem that the maneuvering overload spectrum of the aero-engine cannot be directly obtained through out-field use data statistics due to the fact that the maneuvering overload spectrum of the aero-engine has no direct design input and the difference between active service model usage is large is solved, and a basis is provided for life design and test of an important force bearing structure of the engine; due to the fact that the method is closely attached to a cross-generation model ...

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Номер записи: 17
16-05-2023 дата публикации

Rotor assembly process and evaluation method

Номер: CN116131559A
Автор: LIU JIANXIAN, CAO MAOGUO, FENG SHAOBAO, WANG DONG, LI MENG, YANG FALI
Принадлежит:

The invention belongs to the technical field of aero-engine rotor assembly, and relates to a rotor assembly process and an evaluation method, the rotor assembly quality is judged by measuring the coaxiality of the mounting position, the assembly quality can be directly determined by the assembly phase at the assembly position, and for two rotor parts adopting arc end tooth structures, the assembly quality can be directly determined by the assembly phase at the assembly position. The method comprises the following steps: firstly setting a mark, then carrying out primary assembly on a part I and a part II, measuring the coaxiality in a primary assembly state by taking the mark as a reference, then exchanging the part I and the part II by 180 degrees, then carrying out primary measurement, then calculating the coaxiality, and calculating the vector difference between the two coaxiality measurements. Therefore, the minimum coaxiality position under the combination of the two parts can be obtained ...

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Номер записи: 18
04-04-2023 дата публикации

Method for accurately acquiring total pressure loss coefficient of combustion chamber on engine

Номер: CN115901268A
Автор: WANG DONG, CAO MAOGUO, RUAN WENBO, CHEN ZHONGGUANG, ZHANG JIANGUO, TIAN JING, HONG HAORAN
Принадлежит:

The invention belongs to the field of aero-engine design, and relates to a method for accurately acquiring a total pressure loss coefficient of a combustion chamber on an engine, which adopts a numerical value replacement mode to find out a total pressure loss coefficient of a combustion chamber, which is the same as a main combustion chamber diffusion section outlet total pressure numerical value and a main combustion chamber flame tube outlet total pressure numerical value. However, the measurement is more convenient, two accurate data can be used for replacing the main combustion chamber diffusion section outlet total pressure value and the main combustion chamber flame tube outlet total pressure, and the direct measurement of the main combustion chamber diffusion section and combustion section total pressure recovery coefficient can be directly carried out on the whole machine; errors between numerical simulation and part test results and whole machine working conditions can be reduced ...

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Номер записи: 19
02-05-2023 дата публикации

Turbine rear casing structure part fatigue test loading determination and test method

Номер: CN116046408A
Автор: XIE LIJUAN, BAI HANSONG, CONG PEIHONG, CAO MAOGUO, CHENG RONGHUI, LYU TIANBO, SONG YANG
Принадлежит:

The invention relates to a turbine rear casing structure part fatigue test loading determination and test method, and the method comprises the steps: carrying out the fatigue simulation analysis of a turbine rear casing structure in a design state, and obtaining the stress distribution of the turbine rear casing structure in the design state; determining a fatigue key examination part of the turbine rear casing structure according to the stress distribution of the turbine rear casing structure in the design state; in the part test state, fatigue simulation analysis is conducted on the turbine rear casing structure, and stress distribution of the turbine rear casing structure in the part test state is obtained; adjusting the magnitude of the loading load of each test load loading point on the turbine rear casing structure in the part test state, so that the stress distribution of the fatigue key examination part of the turbine rear casing structure in the part test state and the stress distribution ...

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Номер записи: 20
30-05-2023 дата публикации

Combustion chamber of gas turbine

Номер: CN116182195A
Автор: CHENG RONGHUI, LIU BAO, SUN XIAOFENG, QIN LEI, ZHANG GUANGYU, LI LEI, WANG XIAOYU, CAO MAOGUO, XU XINGPING, MA HONGYU, CONG PEIHONG, ZHANG ZHIXUE
Принадлежит:

The invention belongs to the technical field of gas turbine combustion chamber design, and particularly relates to a gas turbine combustion chamber which comprises an annular combustion chamber outer wall. The combustion chamber inner wall is annular and is arranged in the outer wall; the combustion chamber heads are circumferentially distributed at the inlet part between the combustion chamber outer wall and the combustion chamber inner wall, and the peripheries of the combustion chamber heads are provided with annular switching sections; each switching section is connected between the combustion chamber outer wall and the combustion chamber inner wall, a plurality of cooling holes are formed in each switching section, and the cooling holes close to the combustion chamber outer wall have relatively large density and/or radius.

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Номер записи: 21
28-04-2023 дата публикации

Afterburner of aero-engine

Номер: CN116025926A
Автор: CHENG RONGHUI, LIU BAO, LIU SHENG, SUN XIAOFENG, XU XINGPING, CAO MAOGUO, LI LEI, MA HONGYU, CONG PEIHONG, ZHANG ZHIXUE, YOU QINGJIANG, BAO ZHANYANG, CHEN DI, JIANG YU, LIU WEICHEN, ZHOU CHUNYANG, GUO HONGTAO, ZHANG XIAOYU, PAN XINZHENG, YAN JINSHENG
Принадлежит:

The invention belongs to the technical field of general combustion engines and aero-engines, and particularly relates to an afterburner of an aero-engine. The confluence ring is arranged in the outer casing, an outer culvert is formed between the confluence ring and the outer casing, and a plurality of cooling air inlets distributed in the circumferential direction are formed in the side wall of the tail edge of the confluence ring; the inner cone is arranged in the confluence ring, and an inner connotation is formed between the inner cone and the confluence ring; the radial stabilizer outer walls are connected into the confluence ring and point to the inner cone, the cross sections of the radial stabilizer outer walls are V-shaped, openings of the radial stabilizer outer walls face backwards, and tooth grooves distributed in a staggered mode are formed in the tail edges of the two side walls; the radial stabilizer inner walls are connected into the confluence ring and correspondingly connected ...

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Номер записи: 22
04-07-2023 дата публикации

Method for determining radar stealth performance after damage of aero-engine radar stealth material

Номер: CN116381640A
Автор: CHEN HANZE, CHENG RONGHUI, SHANG SHOUTANG, CAO MAOGUO, YANG SHENGNAN, WANG QUN, SUN XU, WU FEI
Принадлежит:

The invention relates to a method for determining radar stealth performance after damage of an aero-engine radar stealth material, and the method comprises the steps: carrying out the simulation calculation on the basis of setting that the radar stealth material on each part has a plurality of different damage areas; the radar stealth performance of the aero-engine under the combination of different damage areas of the radar stealth material on each component is obtained, a regression equation associated between the radar stealth performance of the aero-engine and the damage area of the radar stealth material on each component is trained, a regression coefficient is obtained, and the aero-engine is selected; according to the method, the damage area of each part is measured, the radar stealth performance is obtained through simulation calculation, the accuracy of a regression equation is checked, and after the check is passed, the radar stealth performance of a target aero-engine is quickly ...

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Номер записи: 23