RU2664982C1 - Stand for tests of helicopter elements with coaxial screws - Google Patents

Abstract

FIELD: testing equipment; aviation.

SUBSTANCE: invention relates to aviation test equipment, namely to test stands for helicopter elements with coaxial screws. Device contains the foundation of the stand, the power frame, clamping devices, mounting frame, fuselage frame, shock absorbers, motoram, internal combustion engine, gearbox, gearbox, output coaxial shafts, skew machine, coaxial screws, clutch, levers, rocker arms, load device, piloting device with control drives for the automatic skew, fuel system, lubricants, cooling systems, engine management system, fire extinguishing system, supply and exhaust ventilation system, control panel, pilot controls, electric drive of the rotor screws, protection and switching unit, electrochemical recuperator, current source analyzer, high-speed video cameras, thermal imagers, spectrum analyzer, system of noise analysis, means of technological control of electret microphones, a parametric tester of serial communication channels, an optical control system for bodies of revolution, means of interface with the system for ensuring the operation of the helicopter, autonomous uninterruptible power supplies.

EFFECT: technical result is to expand the functionality and increase security.

1 cl, 20 dwg

Description

The invention relates to aeronautical testing equipment, namely, to stands for testing elements of a helicopter with coaxial rotors, for example, rotors, main shafts, swashplate, rotor drive, power plant, power supply system, prognostic and diagnostic system of technical condition, monitoring system and registration of flight information, electronic equipment from the flight complex.

A device is known - a stand for life tests of the elements of a power plant of a helicopter with coaxial screws (IPC G01M 7/06, G01M15 / 00, RF patent No. 2091739, publ. 09/27/1997).

The disadvantages of this device are:

- limited functionality when performing tests of elements of the power supply system, prognostic and diagnostic system of the technical condition, control system and registration of flight information, the flight complex of the helicopter;

- low degree of safety for staff, for example, in the destruction of coaxial screws, ignition of fuel, a dangerous concentration of exhaust gases.

There is also known a device - a stand for testing the drive system of coaxial rotors of a helicopter (IPC G01M 7/00, G01N 3/32, RF patent No. 59251, publ. 10.12.2006).

This device contains drive machines, input shafts, a test sample, multipliers, connecting shafts, torque meters, intermediate bearings, plate couplings, output coaxial shafts, a loading machine, a transfer gearbox, an intermediate shaft, a splined ferrule, horizontal levers, a rocker arm, a cylindrical insert with pin, thrust bearing, mounting plate, bushings, two shoulders levers, vertical load hydraulic cylinders, horizontal load hydraulic cylinder, housing, rods, force sensor, struts, support rollers and, leashes, helical shaft, drive handle, screw coupling, equal arms horizontal levers, articulated rods, supports, sub-gear plate, support brackets, bed, power frame, movable truss, wheels, guide rails, stand foundation, coaxial rocking, horizontal rods, parallel levers, handle and stops.

The device has:

- limited functionality that does not allow it to be used when performing autonomous and complex tests of elements of a power plant, power supply system, system for predicting and diagnosing the technical condition, flight information monitoring and recording system, helicopter flight complex with coaxial screws;

- a low degree of safety for operators, maintenance personnel and the device itself during testing of elements of the helicopter with coaxial screws, for example, during the destruction of component parts of the device or fire.

The closest analogue, selected as a prototype, is a device - a stand for testing the elements of an unmanned helicopter with coaxial screws (IPC G01M 7/00, G01N 3/32, RF patent No. 2628873, publ. 08/22/2017).

электровентиляторов, устройство пожаротушения, систему управления двигателя в составе привода дроссельной заслонки, блока управления привода дроссельной заслонки, реле стартера, стартера, первого и второго датчиков давления воздуха, первого и второго датчиков температуры воздуха, первого и второго датчиков положения коленвала, от одного до

датчиков температуры выхлопных газов, датчика температуры охлаждающей жидкости, датчика температуры масла, датчика давления масла, датчика давления и температуры воздуха на входе двигателя, датчика положения заслонки, датчика детонации, датчика температуры подредукторного пространства, датчика температуры на входе радиатора охлаждения, датчика температуры на выходе радиатора охлаждения, датчика давления в сливной топливной магистрали, датчика оборотов несущего винта, от одной до

катушек зажигания,

инжекторов и

свечей зажигания, систему электроснабжения в составе от одного до n генераторов, блока цифрового регулятора, блока предохранителей, устройств аварийного питания и разъема аэродромного питания, систему выхлопную в составе глушителя и выхлопных труб, устройство измерения вибрации, защитные экраны, устройство отвода отработавших газов в составе гибкого трубопровода и вытяжного вентилятора с электроприводом и частотным регулятором, систему приточно-вытяжной вентиляции, элементы освещения, от одной до k видеокамер, пульт управления, оснащенный первым и вторым вычислительными комплексами (электронными вычислительными машинами), первой и второй клавиатурами, первым и вторым манипуляторами типа «мышь», первым и вторым устройствами документирования, первым и вторым мониторами, комплектом органов управления и индикации, устройством видеонаблюдения и регистрации, устройством индикации и регистрации, устройством согласования дискретных сигналов, средствами аварийного отключения, первый и второй каналы информационного обмена с оборудованием стенда, от одного до k каналов информационного обмена с видеокамерами, устройство электропитания, состоящее из устройства бесперебойного питания, коммутатора, устройства вторичных источников питания, устройства преобразования интерфейсов и устройства аварийного отключения, устройство программирования, средства пожаротушения.This device contains the stand foundation, power frame, clamping devices, mounting frame, fuselage frame, shock absorbers, motor mount, internal combustion engine, sub gear frame, gearbox, output coaxial shafts, swash plate, coaxial screws, clutch, levers, rocker arms, load device, pilot device with swash plate control drives, fuel system as part of a fuel tank, coarse filter, fine filters, first and second fuel pumps, fuel lines, ur sensor vnya fuel pressure sensor in the fuel lines, consisting of a system of lubrication oil cooler, the oil tank and oil feed lines, water cooling system consisting of water radiator, an expansion tank, a tank overflow and coolant lines, air cooling system composed of from one to

electric fans, fire extinguishing device, engine control system as part of a throttle actuator, throttle actuator control unit, starter relay, starter, first and second air pressure sensors, first and second air temperature sensors, first and second crankshaft position sensors, from one to

exhaust gas temperature sensors, coolant temperature sensor, oil temperature sensor, oil pressure sensor, engine air pressure and air temperature sensor, damper position sensor, knock sensor, sub gearbox temperature sensor, cooling radiator inlet temperature sensor, outlet temperature sensor cooling radiator, pressure sensor in the drain fuel line, rotor speed sensor, from one to

ignition coils

injectors and

spark plugs, power supply system consisting of from one to n generators, a digital regulator unit, a fuse box, emergency power devices and an airfield power connector, an exhaust system consisting of a muffler and exhaust pipes, a vibration measuring device, protective shields, an exhaust gas device as a part a flexible pipeline and an exhaust fan with an electric drive and a frequency controller, a supply and exhaust ventilation system, lighting elements, from one to k video cameras, a control panel, the first and second computing complexes (electronic computers), the first and second keyboards, the first and second manipulators of the “mouse” type, the first and second documenting devices, the first and second monitors, the set of control and display devices, the video surveillance and registration device, the indicating device and registration, a device for matching discrete signals, emergency shutdown means, the first and second channels of information exchange with the equipment of the stand, from one to k channels inf interchange with video cameras, a power supply device consisting of an uninterruptible power supply device, a switch, a secondary power supply device, an interface conversion device and an emergency shutdown device, a programming device, fire extinguishing equipment.

This device solves the problem of carrying out autonomous and complex tests of the elements of the helicopter support system with coaxial screws, a power plant, power supply system and the helicopter flight system, but its disadvantages are:

- limited functionality that does not allow the device to be used when performing autonomous and complex tests of helicopter elements with a mechanical control system for the position of the blades, electric rotors and a hybrid power plant;

- limited functionality that does not allow using the device to control the position of the rotor blades, the geometric parameters of the output coaxial shafts, the thermal stress of the structural elements of the helicopter, the operating conditions of the onboard emergency power sources, the electromagnetic radiation of the onboard electronic equipment, the values of the acoustic noise generated by the helicopter, the signal quality in serial channels of information exchange between elements of on-board equipment, work aids electret microphones;

- limited functionality of the device to prevent emergencies that could lead to a disruption of the state of the helicopter elements with coaxial screws due to mechanical failure and / or overheating of the structural elements of the helicopter carrier system, a short-term reduction or exceeding the limit parameters of the onboard electrical network, manufacturing defects output coaxial shafts;

- limited functionality of the device for ongoing maintenance, diagnostics of components and the implementation of repair work when signs of failure occur;

- limited functionality of the device for integration with the helicopter operation support system when forming a database (electronic passport) about the initial technical parameters of the helicopter at the stage of its testing;

- insufficient degree of safety for operators, maintenance personnel and the device itself during testing of elements of a helicopter with coaxial screws in case of a sudden interruption in the supply of electricity to the components of the device.

The technical task of the invention is the creation of a device - a stand for testing elements of a helicopter with coaxial screws, which allows you to expand the functionality and improve the safety of the stand for testing elements of a helicopter with coaxial screws.

The problem is solved as follows.

электровентиляторов, устройство пожаротушения, систему управления двигателя в составе привода дроссельной заслонки, блока управления привода дроссельной заслонки, реле стартера, стартера, первого и второго датчиков давления воздуха, первого и второго датчиков температуры воздуха, первого и второго датчиков положения коленвала, от одного до p датчиков температуры выхлопных газов, датчика температуры охлаждающей жидкости, датчика температуры масла, датчика давления масла, датчика давления и температуры воздуха на входе двигателя, датчика положения заслонки, датчика детонации, датчика температуры электрического привода несущих винтов, датчика температуры на входе радиатора охлаждения, датчика температуры на выходе радиатора охлаждения, датчика давления в сливной топливной магистрали, датчика оборотов несущих винтов, от одной до

катушек зажигания,

инжекторов и

свечей зажигания, систему электроснабжения в составе от одного до n генераторов, блока цифрового регулятора, устройств аварийного питания и разъема аэродромного питания, систему выхлопную в составе глушителя и выхлопных труб, устройство измерения вибрации, защитные экраны, устройство отвода отработавших газов в составе гибкого трубопровода и вытяжного вентилятора с электроприводом и частотным регулятором, систему приточно-вытяжной вентиляции, элементы освещения, от одной до k видеокамер, первый, второй и третий пульты управления, каждый из которых оснащен первым и вторым вычислительными комплексами, первой и второй клавиатурами, первым и вторым манипуляторами типа «мышь», первым и вторым устройствами документирования, первым и вторым мониторами, комплектом органов управления и индикации, устройством индикации и регистрации, устройством видеонаблюдения и регистрации, устройством согласования дискретных сигналов, средствами аварийного отключения, первый и второй каналы информационного обмена с оборудованием стенда, от одного до k каналов информационного обмена с видеокамерами, устройство электропитания, состоящее из устройства бесперебойного питания, коммутатора, устройства вторичных источников питания, устройства преобразования интерфейсов и устройства аварийного отключения, устройство программирования, средства пожаротушения дополнительно введены органы управления пилота, электрический привод несущих винтов, блок защиты и коммутации, электрохимический рекуператор, анализатор источников тока, первая и вторая высокоскоростные видеокамеры, первый и второй тепловизоры, анализатор спектра с функцией измерения прямых и отраженных сигналов, от одного до s антенн, система шумоанализа, от одного до t микрофонов, средства технологического контроля электретных микрофонов, параметрический тестер последовательных каналов информационного обмена, оптическая система контроля тел вращения, средства сопряжения с системой обеспечения эксплуатации вертолета, в каждый пульт управления первый и второй автономные источники бесперебойного питания, осциллограф, комплект инструментов и принадлежностей, причем фундамент стенда представляет собой монолитную железобетонную плиту с металлическим силовым каркасом, на котором зажимными приспособлениями закреплена рама монтажная с жестко присоединенным к ней, с помощью болтов, каркасом фюзеляжа, на который, в свою очередь, крепятся: на амортизаторах моторама с установленным на ней двигателем внутреннего сгорания, причем двигатель внутреннего сгорания соединен с глушителем с помощью выхлопных труб, а на выходном вале двигателя внутреннего сгорания размещаются от одного до n генераторов из состава системы электроснабжения; рама для крепления электрического привода несущих винтов с установленной на ней конструкцией из электрического привода несущих винтов, выходных соосных валов, автомата перекоса, соосных винтов и приводов управления автоматом перекоса из устройства пилотирования с приводами управления автоматом перекоса, причем электрический привод несущих винтов имеет механическую связь с выходными соосными валами соединенными в свою очередь с соосными винтами, устройство пилотирования с приводами управления автоматом перекоса через рычаги, автомат перекоса и коромысла соединены с соосными винтами, приводы управления автоматом перекоса и другие составные элементы устройства пилотирования с приводами управления автоматом перекоса имеют между собой электрические и информационные связи; органы управления пилота, причем органы управления пилота через рычаги, автомат перекоса и коромысла соединены с соосными винтами; на амортизаторах топливный бак и другие элементы системы топливной: фильтр грубой очистки, фильтры тонкой очистки, первый и второй топливные насосы, причем топливный бак, с установленным в нем датчиком уровня топлива, с помощью топливных магистралей, с подключенным датчиком давления в топливных магистралях, через фильтр грубой очистки, фильтры тонкой очистки, первый и второй топливные насосы соединен с инжекторами из состава системы управления двигателя, первый и второй топливные насосы находятся в общем корпусе; масляный радиатор и маслобак из состава системы смазки, причем масляный радиатор и маслобак с помощью магистралей подачи масла соединены с двигателем внутреннего сгорания; водяной радиатор, бачок расширительный и бачок переливной из состава системы водяного охлаждения с помощью магистралей подачи охлаждающей жидкости соединены с двигателем внутреннего сгорания; электровентиляторы из состава системы воздушного охлаждения, причем электровентиляторы размещены на каркасе фюзеляжа так, чтобы обеспечить оптимальное охлаждение двигателя внутреннего сгорания и электрического привода несущих винтов, масляного радиатора из состава системы смазки и водяного радиатора из состава системы водяного охлаждения; устройство пожаротушения; привод дроссельной заслонки и блок управления привода дроссельной заслонки из состава системы управления двигателя, причем блок управления привода дроссельной заслонки соединен с приводом дроссельной заслонки информационными и электрическими связями, а привод дроссельной заслонки с дроссельной заслонкой двигателя внутреннего сгорания - механической связью; блок цифрового регулятора, блок защиты и коммутации, электрохимический рекуператор, анализатор источников тока, устройства аварийного питания и разъем аэродромного питания, причем блок цифрового регулятора с помощью первой группы входов-выходов соединен с реле стартера, первым и вторым датчиками давления воздуха, первым и вторым датчиками температуры воздуха, первым и вторым датчиками положения коленвала, датчиками температуры выхлопных газов, датчиком температуры охлаждающей жидкости, датчиком температуры масла, датчиком давления масла, датчиком давления и температуры воздуха на входе двигателя, датчиком положения заслонки, датчиком детонации, датчиком температуры электрического привода несущих винтов, датчиком температуры на входе радиатора охлаждения, датчиком температуры на выходе радиатора охлаждения, датчиком давления в сливной топливной магистрали, датчиком оборотов несущих винтов, катушками зажигания, инжекторами из состава системы управления двигателя, а через четвертую группу входов-выходов - с блоком защиты и коммутации, устройства аварийного питания подключены через блок защиты и коммутации к потребителям электроэнергии, размещенным на каркасе фюзеляжа, генераторам, электрохимическому рекуператору и разъему аэродромного питания, разъем аэродромного питания через блок защиты и коммутации связан с электрическим приводом несущих винтов, электрохимическим рекуператором, потребителями электроэнергии, размещенными на каркасе фюзеляжа, и устройствами аварийного питания, генераторы, размещенные на выходном вале двигателя внутреннего сгорания, через блок защиты и коммутации связаны с электрическим приводом несущих винтов, электрохимическим рекуператором, потребителями электроэнергии, размещенными на каркасе фюзеляжа, и устройствами аварийного питания, стартер, размещенный на двигателе внутреннего сгорания, соединен с реле стартера, свечи зажигания, попарно размещенные на двигателе внутреннего сгорания, соединены с соответствующими катушками зажигания, электрохимический рекуператор подключен к анализатору источников тока и через блок защиты и коммутации к потребителям электроэнергии, размещенным на каркасе фюзеляжа; устройство измерения вибрации, по периметру фундамента стенда расположены защитные экраны, с внутренней стороны которых установлены первая и вторая высокоскоростные видеокамеры, первый и второй тепловизоры, от одной до s антенн, от одного до t микрофонов, к выхлопным трубам из состава системы выхлопной подведен гибкий трубопровод, соединенный с вытяжным вентилятором с электроприводом и частотным регулятором из состава устройства отвода отработавших газов, помещение в котором располагается фундамент стенда оборудовано системой приточно-вытяжной вентиляции, элементами освещения и видеокамерами, с внешней стороны защитных экранов размещаются средства технологического контроля электретных микрофонов, параметрический тестер последовательных каналов информационного обмена, анализатор спектра с функцией измерения прямых и отраженных сигналов, система шумоанализа, оптическая система контроля тел вращения, устройство электропитания, первый и второй пульты управления, причем к первому вычислительному комплексу из состава первого пульта управления подключены первый автономный источник бесперебойного питания, первая клавиатура, первый манипулятор типа «мышь», первое устройство документирования, первый монитор и через первый канал информационного обмена с оборудованием стенда устройство индикации и регистрации, осциллограф, устройство пилотирования с приводами управления автоматом перекоса и второй вход-выход блока цифрового регулятора из состава системы электроснабжения, к второму вычислительному комплексу из состава первого пульта управления подключены второй автономный источник бесперебойного питания, вторая клавиатура, второй манипулятор типа «мышь», второе устройство документирования, второй монитор и через второй канал информационного обмена с оборудованием стенда устройство индикации и регистрации, осциллограф, устройство пилотирования с приводами управления автоматом перекоса и третий вход-выход блока цифрового регулятора из состава системы электроснабжения, к первому вычислительному комплексу из состава второго пульта управления подключены первый автономный источник бесперебойного питания, первая клавиатура, первый манипулятор типа «мышь», первое устройство документирования, первый монитор и через первый канал информационного обмена с оборудованием стенда устройство индикации и регистрации, осциллограф, первая высокоскоростная видеокамера, первый тепловизор, анализатор спектра с функцией измерения прямых и отраженных сигналов с подключенными к нему антеннами, система шумоанализа с подключенными к ней микрофонами, средства технологического контроля электретных микрофонов, параметрический тестер последовательных каналов информационного обмена, оптическая система контроля тел вращения, к второму вычислительному комплексу из состава второго пульта управления подключены второй автономный источник бесперебойного питания, вторая клавиатура, второй манипулятор типа «мышь», второе устройство документирования, второй монитор и через второй канал информационного обмена с оборудованием стенда устройство индикации и регистрации, осциллограф, вторая высокоскоростная видеокамера, второй тепловизор, анализатор спектра с функцией измерения прямых и отраженных сигналов с подключенными к нему антеннами, система шумоанализа с подключенными к ней микрофонами, средства технологического контроля электретных микрофонов, параметрический тестер последовательных каналов информационного обмена, оптическая система контроля тел вращения, к первому вычислительному комплексу из состава третьего пульта управления подключены первый автономный источник бесперебойного питания, первая клавиатура, первый манипулятор типа «мышь», первое устройство документирования, первый монитор и через первый канал информационного обмена с оборудованием стенда устройство индикации и регистрации, осциллограф, средства сопряжения с системой обеспечения эксплуатации вертолета, первые вычислительные комплексы из состава первого и второго пультов управления, к второму вычислительному комплексу из состава третьего пульта управления подключены второй автономный источник бесперебойного питания, вторая клавиатура, второй манипулятор типа «мышь», второе устройство документирования, второй монитор и через второй канал информационного обмена с оборудованием стенда устройство индикации и регистрации, осциллограф, средства сопряжения с системой обеспечения эксплуатации вертолета, вторые вычислительные комплексы из состава первого и второго пультов управления, к комплектам органов управления и индикации из состава первого, второго и третьего пультов управления через устройства согласования дискретных сигналов и устройство преобразования интерфейсов подключен коммутатор из состава устройства электропитания, к устройствам видеонаблюдения и регистрации из состава первого, второго и третьего пультов управления через каналы информационного обмена с видеокамерами подключены видеокамеры, к входам устройства бесперебойного питания из состава устройства электропитания подключены внешние источники электроэнергии, а к выходам - устройство вторичных источников питания, которое в свою очередь соединено через коммутатор с потребителями электроэнергии из состава устройства - стенда, к входу устройства аварийного отключения из состава устройства электропитания подключены средства аварийного отключения из состава первого, второго и третьего пультов управления, а к выходу - коммутатор, устройство программирования может подключаться к первому и/или второму вычислительным комплексам из состава первого, второго и третьего пультов управления, и/или устройству преобразования интерфейсов из состава устройства электропитания, и/или устройству пилотирования с приводами управления автоматом перекоса, и/или блоку цифрового регулятора из состава системы электроснабжения, и/или устройству индикации и регистрации из состава первого, второго и третьего пультов управления, третий пульт управления располагается в отдельном изолированном помещении, все помещения стенда оборудованы средствами пожаротушения, в состав первого, второго и третьего пультов управления включены по одному комплекту инструментов и принадлежностей.The device includes a test bench for testing elements of a helicopter with coaxial screws, containing the test bench foundation, power frame, clamping devices, mounting frame, fuselage frame, shock absorbers, engine mount, internal combustion engine, frame for fastening the rotor electric drive, output coaxial shafts, swashplate , coaxial screws, levers, rocker arms, piloting device with swash plate drives, fuel system as part of a fuel tank, coarse filter, fine filters, first and second fuel pumps, fuel lines, fuel level sensor and pressure sensor in the fuel lines, lubrication system as part of the oil cooler, oil tank and oil supply lines, water cooling system as part of the water radiator, expansion tank, overflow tank and coolant supply lines, system air cooling from one to

electric fans, fire extinguishing device, engine control system as part of a throttle actuator, throttle actuator control unit, starter relay, starter, first and second air pressure sensors, first and second air temperature sensors, first and second crankshaft position sensors, from one to p exhaust gas temperature sensors, coolant temperature sensor, oil temperature sensor, oil pressure sensor, pressure sensor and air temperature at the engine inlet, sensors the position of the damper, knock sensor, temperature sensor of the main rotor electric drive, temperature sensor at the inlet of the cooling radiator, temperature sensor at the outlet of the cooling radiator, pressure sensor in the drain fuel line, rotor speed sensor, from one to

ignition coils

injectors and

spark plugs, power supply system consisting of from one to n generators, a digital regulator unit, emergency power supply devices and an airfield power supply connector, an exhaust system consisting of a muffler and exhaust pipes, a vibration measuring device, protective shields, an exhaust gas removal device as part of a flexible pipeline and exhaust fan with electric drive and frequency regulator, supply and exhaust ventilation system, lighting elements, from one to k cameras, the first, second and third control panels, each the first of which is equipped with the first and second computer systems, the first and second keyboards, the first and second manipulators of the “mouse” type, the first and second documentation devices, the first and second monitors, the set of controls and indicators, the indicator and registration device, the video surveillance and registration device , a device for matching discrete signals, emergency shutdown means, the first and second channels of information exchange with the equipment of the stand, from one to k channels of information exchange with Wi e-cameras, a power supply device consisting of an uninterruptible power supply device, a switch, a secondary power supply device, an interface conversion device and an emergency shutdown device, a programming device, fire extinguishing means, pilot controls, an electric rotor drive, a protection and switching unit, an electrochemical recuperator, analyzer of current sources, the first and second high-speed cameras, the first and second thermal imagers, a spectrum analyzer with the function of measuring direct and reflected signals, from one to s antennas, a noise analysis system, from one to t microphones, technological monitoring tools for electret microphones, a parametric tester for serial communication channels, an optical system for monitoring rotation bodies, means for interfacing with a helicopter operation support system, each control panel is the first and second autonomous uninterruptible power supplies, an oscilloscope, a set of tools and accessories, and the stand’s foundation is a monolithic reinforced concrete slab with a metal power frame, on which the mounting frame is fixed with clamping devices with a fuselage frame rigidly attached to it, using bolts, which, in turn, are mounted on: motor shock absorbers with an internal combustion engine installed on it, and the internal combustion engine is connected to the muffler using exhaust pipes, and from one to n generators from the power supply system are placed on the output shaft of the internal combustion engine; a frame for attaching an electric rotor drive with a structure of an electric rotor drive, coaxial output shafts, a swashplate, coaxial screws and a swashplate control actuators from a piloting device with a swashplate control drives, and the rotor electric drive is mechanically connected to output coaxial shafts connected in turn with coaxial screws, piloting device with control drives of the swash plate through levers, automatic t skew and the rocker are connected with coaxial screws, automatic skew control actuators and other constituent elements of automatic control devices with actuators piloting skew are electrically interconnected and informational communications; pilot controls, and pilot controls through levers, swash plate and rocker arm connected to coaxial screws; on shock absorbers, a fuel tank and other elements of the fuel system: a coarse filter, fine filters, first and second fuel pumps, the fuel tank, with a fuel level sensor installed in it, using fuel lines, with a pressure sensor in the fuel lines connected coarse filter, fine filters, the first and second fuel pumps are connected to injectors from the engine control system, the first and second fuel pumps are in a common housing; an oil cooler and oil tank from the lubrication system, the oil cooler and oil tank using the oil supply lines connected to an internal combustion engine; a water radiator, an expansion tank and an overflow tank from the composition of the water cooling system are connected to the internal combustion engine using the coolant supply lines; electric fans from the air cooling system, and electric fans are placed on the fuselage frame so as to provide optimal cooling of the internal combustion engine and electric drive of the rotors, oil cooler from the lubrication system and water radiator from the water cooling system; fire extinguishing device; the throttle actuator and the throttle actuator control unit from the engine management system, the throttle actuator control unit being connected to the throttle actuator by information and electrical connections, and the throttle actuator with the throttle of the internal combustion engine by mechanical coupling; a digital controller unit, a protection and switching unit, an electrochemical recuperator, a current source analyzer, emergency power devices and an aerodrome power connector, the digital controller unit using the first group of inputs and outputs connected to the starter relay, the first and second air pressure sensors, the first and second air temperature sensors, first and second crankshaft position sensors, exhaust gas temperature sensors, coolant temperature sensor, oil temperature sensor, m pressure sensor asla, a pressure sensor and air temperature at the engine inlet, a damper position sensor, a knock sensor, a temperature sensor for the electric drive of the main rotors, a temperature sensor at the inlet of the cooling radiator, a temperature sensor at the outlet of the cooling radiator, a pressure sensor in the drain fuel line, a rotor speed sensor , ignition coils, injectors from the engine control system, and through the fourth group of inputs and outputs - with a protection and switching unit, emergency power devices connected through a protection and switching unit to electric consumers located on the fuselage frame, generators, an electrochemical recuperator and an aerodrome power connector, an aerodrome power connector through a protection and switching unit is connected to an electric rotor drive, an electrochemical recuperator, electric consumers placed on the fuselage frame, and emergency power devices, generators located on the output shaft of the internal combustion engine, through the protection and switching unit are connected electric rotor drive, electrochemical recuperator, power consumers located on the fuselage frame, and emergency power devices, a starter placed on an internal combustion engine, connected to a starter relay, spark plugs placed in pairs on an internal combustion engine, connected to corresponding ignition coils, the electrochemical recuperator is connected to the analyzer of current sources and through the protection and switching unit to electricity consumers placed on the fu frame potion; a vibration measuring device, along the perimeter of the stand foundation there are protective screens, on the inside of which are installed the first and second high-speed cameras, the first and second thermal imagers, from one to s antennas, from one to t microphones, a flexible pipe is connected to the exhaust pipes from the exhaust system connected to an exhaust fan with an electric drive and a frequency regulator from the exhaust gas device, the room in which the stand foundation is located is equipped with a supply system o-exhaust ventilation, lighting elements and video cameras, from the outside of the protective screens are placed the means of technological control of electret microphones, a parametric tester of serial channels of information exchange, a spectrum analyzer with the function of measuring direct and reflected signals, a noise analysis system, an optical control system of rotation bodies, an electrical power device , the first and second control panels, and the first and connected to the first computing complex from the first control panel tone uninterruptible power supply, first keyboard, first mouse-type manipulator, first documenting device, first monitor and, through the first channel of information exchange with the stand equipment, an indication and registration device, an oscilloscope, a piloting device with skew control drives and a second input-output unit digital controller from the power supply system, the second stand-alone source is connected to the second computer complex from the first control panel power supply, a second keyboard, a second mouse-type manipulator, a second documentation device, a second monitor, and through a second channel of information exchange with the stand equipment, an indicating and recording device, an oscilloscope, a piloting device with skew control drives and a third input-output of a digital controller block from the power supply system, the first stand-alone uninterruptible power supply, the first keyboard, are connected to the first computer complex from the second control panel the first mouse-type manipulator, the first documentation device, the first monitor and, through the first channel of information exchange with the equipment of the stand, the indicating and recording device, an oscilloscope, the first high-speed video camera, the first thermal imager, a spectrum analyzer with the function of measuring direct and reflected signals with antennas connected to it , noise analysis system with microphones connected to it, means of technological control of electret microphones, parametric tester of serial channels of information exchange, optical system for controlling the bodies of revolution, a second autonomous uninterruptible power supply, a second keyboard, a second mouse-type manipulator, a second documentation device, a second monitor and a second channel of information exchange with the equipment of the stand are connected to the second computer complex from the second control panel indicating and recording device, oscilloscope, second high-speed video camera, second thermal imager, spectrum analyzer with the function of measuring direct and reflected signals from under antennas connected to it, a noise analysis system with microphones connected to it, means of technological control of electret microphones, a parametric tester of serial communication channels, an optical system for monitoring bodies of revolution, the first stand-alone uninterruptible power supply, the first keyboard are connected to the first computer complex from the third control panel , the first mouse-type manipulator, the first documentation device, the first monitor and through the first channel of information about exchange with stand equipment, indicating and registering device, oscilloscope, means of interfacing with a helicopter operation support system, first computer systems from the first and second control panels, a second stand-alone uninterruptible power supply, a second keyboard, and a second keyboard are connected to the second computer complex from the third control panel a mouse-type manipulator, a second documentation device, a second monitor, and through a second channel of information exchange with the equipment of the device stand indicating and registering equipment, an oscilloscope, means of interfacing with a helicopter operation support system, second computer systems from the first and second control panels, to control and indication sets from the first, second and third control panels through discrete signal matching devices and an interface conversion device a switch is connected from the power supply device to the video surveillance and registration devices from the first, second and third consoles control cameras through the information exchange channels with video cameras are connected video cameras, external power sources are connected to the inputs of an uninterruptible power supply device from the power supply device, and secondary power supply devices are connected to the outputs, which, in turn, is connected via a switch to electricity consumers from the device-stand, to emergency shutdown devices from the first, second and third are connected to the input of the emergency shutdown device from the power supply device its control panels, and to the output is a switch, the programming device can be connected to the first and / or second computer systems from the first, second and third control panels, and / or the interface conversion device from the power supply device, and / or the pilot device with drives control the swashplate, and / or the digital controller unit from the power supply system, and / or the display and registration device from the first, second and third control panels, the third lt controls located in a separate, isolated room, all rooms are equipped with fire extinguishing agents stand, in the first, second and third control units included one set of tools and accessories.

The set of distinctive features of the claimed invention ensures the implementation of the technical task.

From the studied scientific, technical and patent information, the authors do not know the device with the distinguishing features indicated in the claims, this gives reason to conclude that the claimed object meets the criteria of the invention.

The invention is illustrated by drawings, where in FIG. 1 shows a general view of the device, FIG. 2 is a plan view of FIG. 3 shows the fuselage frame; FIG. 4 - fuel tank, in FIG. 5 - power unit, in FIG. 6 is an external view of the engine mount, in FIG. 7 shows a carrier system; FIG. 8 shows an engine control system; FIG. 9 shows a side view with a load module, FIG. 10 shows a fuel system; FIG. 11 - lubrication system, in FIG. 12 is a water cooling system; FIG. 13 is an air cooling system; FIG. 1 4 is an exhaust system; FIG. 15 shows the sensors, in FIG. 16, 17, 18 show various parts of the structure of the device, in FIG. 19 shows an exhaust system; FIG. 20 - exhaust gas device.

катушек зажигания

,

инжекторов

и

свечей зажигания

систему электроснабжения 66 в составе от одного до n генераторов 67₁÷67_n, блока цифрового регулятора 68, блока защиты и коммутации 69, устройств аварийного питания 70, электрохимического рекуператора 71 и разъема аэродромного питания 72, систему выхлопную 73 в составе глушителя 74 и выхлопных труб 75, устройство измерения вибрации 76, защитные экраны 77, устройство отвода отработавших газов 78 в составе гибкого трубопровода 79 и вытяжного вентилятора с электроприводом и частотным регулятором 80, систему приточно-вытяжной вентиляции 81, элементы освещения 82, от одной до k видеокамер 83₁÷83_k первый 84, второй 85 и третий 86 пульты управления, каждый из которых оснащен первым 87 и вторым 88 вычислительными комплексами, первой 89 и второй 90 клавиатурами, первым 91 и вторым 92 манипуляторами типа «мышь», первым 93 и вторым 94 устройствами документирования, первым 95 и вторым 96 мониторами, первым 97 и вторым 98 автономными источниками бесперебойного питания, осциллографом 99, комплектом органов управления и индикации 100, устройством видеонаблюдения и регистрации 101, устройством индикации и регистрации 102, устройством согласования дискретных сигналов 103, средствами аварийного отключения 104, комплектом инструментов и принадлежностей 105, первый 106 и второй 107 каналы информационного обмена с оборудованием стенда, от одного до к каналов информационного обмена с видеокамерами 108₁÷108_k, устройство электропитания 109, состоящее из устройства бесперебойного питания 110, коммутатора 111, устройства вторичных источников питания 112, устройства преобразования интерфейсов 113 и устройства аварийного отключения 114, устройство программирования 115, средства пожаротушения 116, первую 117 и вторую 118 высокоскоростные видеокамеры, первый 119 и второй 120 тепловизоры, анализатор спектра с функцией измерения прямых и отраженных сигналов 121, от одной до s антенн 122₁÷122_s, систему шумоанализа 123, от одного до t микрофонов 124₁÷124_t, средства технологического контроля электретных микрофонов 125, параметрический тестер последовательных каналов информационного обмена 126, оптическую систему контроля тел вращения 127, средства сопряжения с системой обеспечения эксплуатации вертолета 128.The device is a stand for testing elements of a helicopter with coaxial screws; it contains the foundation of stand 1, a power frame 2, clamping devices 3, an assembly frame 4, a fuselage frame 5, shock absorbers 6, an engine mount 7, an internal combustion engine 8, a frame for attaching an electric drive of the rotors 9 , electric drive of rotors 10, output coaxial shafts And, swashplate 12, coaxial screws 13, pilot controls 14, levers 15, rocker arms 16, current source analyzer 17, pilot device with gearbox control drives CA 18, a fuel system 19 comprising a fuel tank 20, a coarse filter 21, fine filters 22, a first 23 and a second 24 fuel pumps, fuel lines 25, a fuel level sensor 26 and a pressure sensor in the fuel lines 27, a lubrication system 28 the composition of the oil radiator 29, the oil tank 30 and the oil supply lines 31, the water cooling system 32 as part of the water radiator 33, the expansion tank 34, the overflow tank 35 and the coolant supply lines 36, the air cooling system 37 consisting of one to m ele fan fans 38 ₁ ÷ 38 _m , fire extinguishing device 39, engine control system 40 comprising throttle actuator 41, throttle actuator control unit 42, starter relay 43, starter 44, first 45 and second 46 air pressure sensors, first 47 and second 48 air temperature sensors, first 49 and second 50 crankshaft position sensors, from one to p exhaust temperature sensors 51 ₁ ÷ 51 _r , coolant temperature sensor 52, oil temperature sensor 53, oil pressure sensor 54, pressure and temperature sensor air at the inlet of the engine 55, the position sensor of the damper 56, the knock sensor 57, the temperature sensor of the electric drive rotors 58, the temperature sensor at the inlet of the cooling radiator 59, the temperature sensor at the output of the cooling radiator 60, the pressure sensor in the drain fuel line 61, the speed sensor rotors 62, from one to

ignition coils

,

injectors

and

spark plugs

power supply system 66 consisting of one to n generators 67 ₁ ÷ 67 _n , a digital controller block 68, a protection and switching unit 69, emergency power supply devices 70, an electrochemical recuperator 71 and an airfield power supply connector 72, an exhaust system 73 comprising a silencer 74 and exhaust pipes 75, a vibration measuring device 76, protective shields 77, an exhaust gas device 78 as part of a flexible pipe 79 and an exhaust fan with an electric drive and a frequency controller 80, a supply and exhaust ventilation system 81, lighting elements I am 82, from one to k video cameras 83 ₁ ÷ 83 _k first 84, second 85 and third 86 control panels, each of which is equipped with the first 87 and second 88 computer systems, the first 89 and second 90 keyboards, the first 91 and second 92 manipulators of the type “Mouse”, the first 93 and second 94 documenting devices, the first 95 and second 96 monitors, the first 97 and second 98 autonomous uninterruptible power supplies, an oscilloscope 99, a set of controls and indicators 100, a video surveillance and registration device 101, an indication and registration device 102 device coordination of discrete signals 103, emergency shutdown means 104, a set of tools and accessories 105, the first 106 and second 107 channels of information exchange with the equipment of the stand, from one to the channels of information exchange with video cameras 108 ₁ ÷ 108 _k , power supply device 109, consisting of uninterruptible power supply 110, switch 111, secondary power supply device 112, interface conversion device 113 and emergency shutdown device 114, programming device 115, fire extinguishing means Nia 116, first 117 and second 118 high-speed video camera, the first 119 and second 120 thermal imagers, the spectrum analyzer with the function of measuring the direct and the reflected signals 121 from one to s antennas 122 ₁ ÷ 122 _s, shumoanaliza 123 system from one to t microphones 124 ₁ ÷ 124 _t , means of technological control of electret microphones 125, parametric tester of serial channels of information exchange 126, optical control system of rotation bodies 127, means of interfacing with a support system for operating a helicopter 128.

из состава системы управления двигателя 40, первый 23 и второй 24 топливные насосы находятся в общем корпусе; масляный радиатор 29 и маслобак 30 из состава системы смазки 28, причем масляный радиатор 29 и маслобак 30 с помощью магистралей подачи масла 31 соединены с двигателем внутреннего сгорания 8; водяной радиатор 33, бачок расширительный 34 и бачок переливной 35 из состава системы водяного охлаждения 32 с помощью магистралей подачи охлаждающей жидкости 36 соединены с двигателем внутреннего сгорания 8; электровентиляторы 38₁÷38_m из состава системы воздушного охлаждения 37, причем электровентиляторы 38₁÷38_m размещены на каркасе фюзеляжа 5 так, чтобы обеспечить оптимальное охлаждение двигателя внутреннего сгорания 8 и электрического привода несущих винтов 10, масляного радиатора 29 из состава системы смазки 28 и водяного радиатора 33 из состава системы водяного охлаждения 32; устройство пожаротушения 39; привод дроссельной заслонки 41 и блок управления привода дроссельной заслонки 42 из состава системы управления двигателя 40, причем блок управления привода дроссельной заслонки 42 соединен с приводом дроссельной заслонки 41 информационными и электрическими связями, а привод дроссельной заслонки 41 с дроссельной заслонкой двигателя внутреннего сгорания 8 - механической связью; блок цифрового регулятора 68, блок защиты и коммутации 69, электрохимический рекуператор 71, анализатор источников тока 17, устройства аварийного питания 70 и разъем аэродромного питания 72, причем блок цифрового регулятора 68 с помощью первой группы входов-выходов соединен с реле стартера 43, первым 45 и вторым 46 датчиками давления воздуха, первым 47 и вторым 48 датчиками температуры воздуха, первым 49 и вторым 50 датчиками положения коленвала, датчиками температуры выхлопных газов

датчиком температуры охлаждающей жидкости 52, датчиком температуры масла 53, датчиком давления масла 54, датчиком давления и температуры воздуха на входе двигателя 55, датчиком положения заслонки 56, датчиком детонации 57, датчиком температуры электрического привода несущих винтов 58, датчиком температуры на входе радиатора охлаждения 59, датчиком температуры на выходе радиатора охлаждения 60, датчиком давления в сливной топливной магистрали 61, датчиком оборотов несущих винтов 62, катушками зажигания

инжекторами

из состава системы управления двигателя 40, а через четвертую группу входов-выходов - с блоком защиты и коммутации 69, устройства аварийного питания 70 подключены через блок защиты и коммутации 69 к потребителям электроэнергии, размещенным на каркасе фюзеляжа 5, генераторам 67₁÷61_n, электрохимическому рекуператору 71 и разъему аэродромного питания 72, разъем аэродромного питания 72 через блок защиты и коммутации 69 связан с электрическим приводом несущих винтов 10, электрохимическим рекуператором 71, потребителями электроэнергии, размещенными на каркасе фюзеляжа 5, и устройствами аварийного питания 70, генераторы 67₁÷67_n, размещенные на выходном вале двигателя внутреннего сгорания 8, через блок защиты и коммутации 69 связаны с электрическим приводом несущих винтов 10, электрохимическим рекуператором 71, потребителями электроэнергии, размещенными на каркасе фюзеляжа 5, и устройствами аварийного питания 70, стартер 44, размещенный на двигателе внутреннего сгорания 8, соединен с реле стартера 43, свечи зажигания (65_1-1, 65_2-1),…,

попарно размещенные на двигателе внутреннего сгорания 8, соединены с соответствующими катушками зажигания

электрохимический рекуператор 71 подключен к анализатору источников тока 17 и через блок защиты и коммутации 69 к потребителям электроэнергии, размещенным на каркасе фюзеляжа 5; устройство измерения вибрации 76, по периметру фундамента стенда 1 расположены защитные экраны 77, с внутренней стороны которых установлены первая 117 и вторая 118 высокоскоростные видеокамеры, первый 119 и второй 120 тепловизоры, от одной до s антенн 122₁÷122_s, от одного до t микрофонов 124₁÷124_t, к выхлопным трубам 75 из состава системы выхлопной 73 подведен гибкий трубопровод 79, соединенный с вытяжным вентилятором с электроприводом и частотным регулятором 80 из состава устройства отвода отработавших газов 78, помещение в котором располагается фундамент стенда 1 оборудовано системой приточно-вытяжной вентиляции 81, элементами освещения 82 и видеокамерами 83₁÷83_k, с внешней стороны защитных экранов 77 размещаются средства технологического контроля электретных микрофонов 125, параметрический тестер последовательных каналов информационного обмена 126, анализатор спектра с функцией измерения прямых и отраженных сигналов 121, система шумоанализа 123, оптическая система контроля тел вращения 127, устройство электропитания 109, первый 84 и второй 85 пульты управления, причем к первому вычислительному комплексу 87 из состава первого пульта управления 84 подключены первый автономный источник бесперебойного питания 97, первая клавиатура 89, первый манипулятор типа «мышь» 91, первое устройство документирования 93, первый монитор 95 и через первый канал информационного обмена с оборудованием стенда 106 устройство индикации и регистрации 102, осциллограф 99, устройство пилотирования с приводами управления автоматом перекоса 18 и второй вход-выход блока цифрового регулятора 68 из состава системы электроснабжения 66, к второму вычислительному комплексу 88 из состава первого пульта управления 84 подключены второй автономный источник бесперебойного питания 98, вторая клавиатура 90, второй манипулятор типа «мышь» 92, второе устройство документирования 94, второй монитор 96 и через второй канал информационного обмена с оборудованием стенда 107 устройство индикации и регистрации 102, осциллограф 99, устройство пилотирования с приводами управления автоматом перекоса 18 и третий вход-выход блока цифрового регулятора 68 из состава системы электроснабжения 66, к первому вычислительному комплексу 87 из состава второго пульта управления 85 подключены первый автономный источник бесперебойного питания 97, первая клавиатура 89, первый манипулятор типа «мышь» 91, первое устройство документирования 93, первый монитор 95 и через первый канал информационного обмена с оборудованием стенда 106 устройство индикации и регистрации 102, осциллограф 99, первая высокоскоростная видеокамера 117, первый тепловизор 119, анализатор спектра с функцией измерения прямых и отраженных сигналов 121 с подключенными к нему антеннами 122₁÷122_s, система шумоа-нализа 123 с подключенными к ней микрофонами 124₁÷124_t, средства технологического контроля электретных микрофонов 125, параметрический тестер последовательных каналов информационного обмена 126, оптическая система контроля тел вращения 127, к второму вычислительному комплексу 88 из состава второго пульта управления 85 подключены второй автономный источник бесперебойного питания 98, вторая клавиатура 90, второй манипулятор типа «мышь» 92, второе устройство документирования 94, второй монитор 96 и через второй канал информационного обмена с оборудованием стенда 107 устройство индикации и регистрации 102, осциллограф 99, вторая высокоскоростная видеокамера 118, второй тепловизор 120, анализатор спектра с функцией измерения прямых и отраженных сигналов 121 с подключенными к нему антеннами 122₁÷122_s, система шумоанализа 123 с подключенными к ней микрофонами 124₁÷124_t, средства технологического контроля электретных микрофонов 125, параметрический тестер последовательных каналов информационного обмена 126, оптическая система контроля тел вращения 127, к первому вычислительному комплексу 87 из состава третьего пульта управления 86 подключены первый автономный источник бесперебойного питания 97, первая клавиатура 89, первый манипулятор типа «мышь» 91, первое устройство документирования 93, первый монитор 95 и через первый канал информационного обмена с оборудованием стенда 106 устройство индикации и регистрации 102, осциллограф 99, средства сопряжения с системой обеспечения эксплуатации вертолета 128, первые вычислительные комплексы 87 из состава первого 84 и второго 85 пультов управления, к второму вычислительному комплексу 88 из состава третьего пульта управления 86 подключены второй автономный источник бесперебойного питания 98, вторая клавиатура 90, второй манипулятор типа «мышь» 92, второе устройство документирования 94, второй монитор 96 и через второй канал информационного обмена с оборудованием стенда 107 устройство индикации и регистрации 102, осциллограф 99, средства сопряжения с системой обеспечения эксплуатации вертолета 128, вторые вычислительные комплексы 88 из состава первого 84 и второго 85 пультов управления, к комплектам органов управления и индикации 100 из состава первого 84, второго 85 и третьего 86 пультов управления через устройства согласования дискретных сигналов 103 и устройство преобразования интерфейсов 113 подключен коммутатор 111 из состава устройства электропитания 109, к устройствам видеонаблюдения и регистрации 101 из состава первого 84, второго 85 и третьего 86 пультов управления через каналы информационного обмена с видеокамерами 108₁÷108_k подключены видеокамеры 83₁÷83_k, к входам устройства бесперебойного питания 110 из состава устройства электропитания 109 подключены внешние источники электроэнергии, а к выходам - устройство вторичных источников питания 112, которое в свою очередь соединено через коммутатор 111 с потребителями электроэнергии из состава устройства - стенда, к входу устройства аварийного отключения 114 из состава устройства электропитания 109 подключены средства аварийного отключения 104 из состава первого 84, второго 85 и третьего 86 пультов управления, а к выходу - коммутатор 111, устройство программирования 115 может подключаться к первому 87 и/или второму 88 вычислительным комплексам из состава первого 84, второго 85 и третьего 86 пультов управления, и/или устройству преобразования интерфейсов 113 из состава устройства электропитания 109, и/или устройству пилотирования с приводами управления автоматом перекоса 18, и/или блоку цифрового регулятора 68 из состава системы электроснабжения 66, и/или устройству индикации и регистрации 102 из состава первого 84, второго 85 и третьего 86 пультов управления, третий пульт управления 86 располагается в отдельном изолированном помещении, все помещения устройства - стенда оборудованы средствами пожаротушения 116, в состав первого 84, второго 85 и третьего 86 пультов управления включены по одному комплекту инструментов и принадлежностей 105.At the same time, the foundation of stand 1 is located in an isolated room and is a monolithic reinforced concrete slab with a metal power frame 2, on which the mounting frame 4 is mounted with clamping devices 3 with the fuselage frame 5 rigidly attached to it, using bolts, which, in turn, are attached: on the shock absorbers 6 of the engine 7 with the internal combustion engine 8 installed on it, and the internal combustion engine 8 is connected to the muffler 74 using the exhaust pipes 75, and on the output shaft of the engine, inside of combustion 8 are placed from one to n generators 67 ₁ ÷ 67 _n from the composition of the power supply system 66; a frame for mounting an electric drive of rotors 9 with a structure made of an electric drive of rotors 10, output coaxial shafts 11, swash plate 12, coaxial screws 13 and drives of the swashplate control from the piloting device with swashplate control drives 18, and the electric drive rotors 10 has a mechanical connection with the output coaxial shafts 11 connected in turn with the coaxial screws 13, a piloting device with actuators for controlling the swash plate 18 of levers 15, swash plate 12 and the rocker 16 connected with coaxial screws 13, automatic skew control actuators and other constituent elements with automatic piloting device control actuators 18 have a skew between a power and data communication; the pilot controls 14, and the pilot controls 14 through levers 15, the swashplate 12 and the rocker 16 are connected to the coaxial screws 13; on the shock absorbers 6, the fuel tank 20 and other elements of the fuel system 19: the coarse filter 21, the fine filters 22, the first 23 and the second 24 fuel pumps, and the fuel tank 20, with the fuel level sensor 26 installed in it, using the fuel lines 25 , with a connected pressure sensor in the fuel lines 27, through the coarse filter 21, fine filters 22, the first 23 and second 24 fuel pumps are connected to the injectors

from the engine control system 40, the first 23 and second 24 fuel pumps are in a common housing; an oil cooler 29 and an oil tank 30 from the composition of the lubrication system 28, the oil cooler 29 and the oil tank 30 are connected to an internal combustion engine 8 via oil supply lines 31; a water radiator 33, an expansion tank 34 and an overflow tank 35 from the composition of the water cooling system 32 are connected to the internal combustion engine 8 using the coolant supply lines 36; electric fans 38 ₁ ÷ 38 _m from the air cooling system 37, and electric fans 38 ₁ ÷ 38 _m are placed on the fuselage frame 5 so as to provide optimal cooling of the internal combustion engine 8 and the electric drive of the rotors 10, oil cooler 29 from the composition of the lubrication system 28 and a water radiator 33 from the composition of the water cooling system 32; fire extinguishing device 39; the throttle actuator 41 and the throttle actuator control unit 42 from the engine control system 40, wherein the throttle actuator control unit 42 is connected to the throttle actuator 41 by information and electrical connections, and the throttle actuator 41 with the throttle of an internal combustion engine 8 is mechanical communication; the digital controller unit 68, the protection and switching unit 69, the electrochemical recuperator 71, the current source analyzer 17, the emergency power supply device 70 and the airfield power connector 72, the digital controller unit 68 being connected to the starter relay 43 using the first group of inputs and outputs, the first 45 and the second 46 air pressure sensors, the first 47 and second 48 air temperature sensors, the first 49 and second 50 crankshaft position sensors, exhaust gas temperature sensors

coolant temperature sensor 52, oil temperature sensor 53, oil pressure sensor 54, pressure and air temperature sensor at the engine inlet 55, damper position sensor 56, knock sensor 57, temperature of the rotor drive electric drive 58, temperature sensor at the inlet of the cooling radiator 59 , a temperature sensor at the outlet of the cooling radiator 60, a pressure sensor in the drain fuel line 61, a rotor speed sensor 62, ignition coils

injectors

from the control system of the engine 40, and through the fourth group of inputs and outputs - with the protection and switching unit 69, emergency power supply devices 70 are connected through the protection and switching unit 69 to electricity consumers located on the fuselage frame 5, generators 67 ₁ ÷ 61 _n , to the electrochemical recuperator 71 and the terminal of the airfield power 72, the terminal of the airfield power 72 through the protection and switching unit 69 is connected to the electric drive of the rotors 10, the electrochemical recuperator 71, power consumers located on Arkása fuselage 5, and the emergency power supply units 70, generators 67 ₁ ÷ 67 _n, placed on the output shaft of the internal combustion engine 8 via the UPC 69 associated with the power rotor 10, the electrochemical recuperator 71, consumers of electricity placed on the frame the fuselage 5, and emergency power supply devices 70, the starter 44, located on the internal combustion engine 8, is connected to the relay of the starter 43, the spark plug (65 _1-1 , 65 _2-1 ), ...,

pairwise placed on the internal combustion engine 8, connected to the respective ignition coils

an electrochemical recuperator 71 is connected to the analyzer of current sources 17 and through the protection and switching unit 69 to electricity consumers placed on the fuselage frame 5; vibration measurement device 76, along the perimeter of the foundation of stand 1 there are protective screens 77, on the inside of which are installed the first 117 and second 118 high-speed cameras, the first 119 and second 120 thermal imagers, from one to s antennas 122 ₁ ÷ 122 _s , from one to t microphones 124 ₁ ÷ 124 _t , a flexible conduit 79 connected to the exhaust pipes 75 from the exhaust system 73 is connected to an exhaust fan with an electric drive and a frequency regulator 80 from the exhaust gas device 78, the room in which the foundation is located t of stand 1 is equipped with a supply and exhaust ventilation system 81, lighting elements 82 and video cameras 83 ₁ ÷ 83 _k , technological monitoring of electret microphones 125, a parametric tester of serial communication channels 126, a spectrum analyzer with direct measurement and reflected signals 121, a noise analysis system 123, an optical system for monitoring bodies of revolution 127, a power supply device 109, the first 84 and second 85 control panels, and to the first computing The complex 87 of the first control panel 84 is connected to the first stand-alone uninterruptible power supply 97, the first keyboard 89, the first mouse-type manipulator 91, the first documentation device 93, the first monitor 95, and the display and registration device through the first channel of information exchange with the equipment of the stand 106 102, an oscilloscope 99, a piloting device with control drives of the swashplate 18 and a second input-output of a block of a digital controller 68 from the power supply system 66, to a second computing complex 88 of the first control panel 84, a second autonomous uninterruptible power supply 98, a second keyboard 90, a second mouse-type manipulator 92, a second documentation device 94, a second monitor 96, and an indication and recording device 102 , an oscilloscope 99, a piloting device with control drives of the swashplate 18 and a third input-output of the digital controller block 68 from the power supply system 66, to the first computing complex 87 from the Ava second control panel 85 connected the first stand-alone uninterruptible power supply 97, the first keyboard 89, the first manipulator type “mouse” 91, the first documenting device 93, the first monitor 95 and through the first channel of information exchange with the equipment of the stand 106, the indicating and recording device 102, an oscilloscope 99, the first high-speed video camera 117, the first thermal imager 119, a spectrum analyzer with the function of measuring direct and reflected signals 121 with antennas connected to it 122 ₁ ÷ 122 _s , the noise analysis system 123 s connected with microphones 124 ₁ ÷ 124 _t , means of technological control of electret microphones 125, parametric tester of serial communication channels 126, optical control system of rotation bodies 127, the second autonomous uninterruptible power supply 98 is connected to the second computer complex 88 from the second control panel 85 , a second keyboard 90, a second mouse-type manipulator 92, a second documenting device 94, a second monitor 96, and through a second information exchange channel with the equipment of the stand 107 GUT indicating and registering 102, the oscilloscope 99, the second high-speed video camera 118, a second imager 120, a spectrum analyzer with the function of measuring the direct and the reflected signals 121 from the connected antennas 122 ₁ ÷ 122 _s, shumoanaliza system 123 connected thereto microphones 124 ₁ ÷ 124 _t, the process control means electret microphone 125, a parametric tester successive traffic channels 126, the optical monitoring system of rotation bodies 127, the first computer complex 87 from the third remote councils 86, the first stand-alone uninterruptible power supply 97 is connected, the first keyboard 89, the first mouse-type manipulator 91, the first documentation device 93, the first monitor 95 and, through the first channel of information exchange with the equipment of the stand 106, the indicating and recording device 102, the oscilloscope 99, means interfacing with the support system for the operation of the helicopter 128, the first computing systems 87 from the first 84 and second 85 control panels, to the second computing complex 88 from the third control panel 86 p a second stand-alone uninterruptible power supply 98, a second keyboard 90, a second mouse-type manipulator 92, a second documenting device 94, a second monitor 96, and an indication and recording device 102, an oscilloscope 99, means for interfacing with support system for the operation of the helicopter 128, the second computer systems 88 from the first 84 and second 85 control panels, to the sets of control and display 100 from the first 84, second 85 and third 8 6 control panels through a device for matching discrete signals 103 and a device for converting interfaces 113 connected to the switch 111 of the power supply device 109, to the video surveillance and registration devices 101 of the first 84, second 85 and third 86 control panels through communication channels with video cameras 108 ₁ ÷ 108 _k connected camcorder ₁ 83 ÷ 83 _k, to the inputs of an uninterruptible power supply device 110 from the power supply device 109 connected external power sources, and the outputs - the device original power supplies 112, which in turn is connected through a switch 111 to consumers of electricity from the device-stand, emergency shutdown means 104 from the first 84, second 85 and third 86 control panels are connected to the input of the emergency shutdown device 114 from the power supply device 109 and the output is a switch 111, the programming device 115 can be connected to the first 87 and / or second 88 computing complexes from the first 84, second 85 and third 86 control panels, and / or the interface conversion property 113 of the power supply device 109, and / or the pilot device with the swashplate control drives 18, and / or the digital controller block 68 of the power supply system 66, and / or the display and registration device 102 of the first 84, second 85 and the third 86 control panels, the third control panel 86 is located in a separate isolated room, all rooms of the device stand are equipped with fire extinguishing means 116, the first 84, the second 85 and the third 86 control panels Features are included with one set of tools and accessories 105.

The operating procedure of the device is divided into stages:

- preparatory;

- main;

- emergency.

Preparatory stage

When power is supplied from external power sources to the uninterruptible power supply device 110 through the secondary power supply device 112 and the switch 111 from the power supply device 109, the operating voltage is supplied to the electricity consumers from the first 84, second 85 and third 86 control panels. The device of secondary power sources 112 provides the conversion of primary electricity (AC voltage) from external sources of electricity into DC and AC voltage with the characteristics necessary to ensure the operability of electricity consumers from the device-stand. The switch 111 carries out switching - closing / opening the electric power transmission circuits from the device of secondary power supplies 112 to the consumers of electric power from the device - the stand by commands from the interface conversion device 113 and the emergency shutdown device 114. Moreover, the commands from the interface conversion device 113 are used to control the circuits that in the initial position are open, and from the emergency shutdown device 114 - closed.

When power is supplied through closed circuits of switch 111 to the analyzer of current sources 17, first 117 and second 118 high-speed cameras, first 119 and second 120 thermal imagers, a spectrum analyzer with the function of measuring direct and reflected signals 121, a noise analysis system 123, a parametric tester of serial communication channels 126, the optical system for monitoring the bodies of revolution 127, initialization of the software preinstalled on them and autonomous preparation for their intended use are performed.

When power is supplied through closed circuits of the switch 111 to the first 87 and second 88 computing complexes, the first 93 and second 94 documenting devices, the first 95 and second 96 monitors, video surveillance and recording devices 101, indicating and recording devices 102 from the first 84, second 85 and the third 86 control panels are initialized pre-installed on them software. In this case, it is carried out:

a) automatic testing and preparation for operation of hardware and software of the first 84, second 85 and third 86 control panels:

- the first 87 and second 88 computing complexes, the first 89 and second 90 keyboards, the first 91 and second 92 mouse-type manipulators, the first 93 and second 94 documentation devices, the first 95 and second 96 monitors;

- oscilloscopes 99;

- video surveillance and registration devices 101;

- indicating and recording devices 102;

b) under the control of functional or system software of the first 87 and second 88 computing complexes of the first 84, second 85 and third 86 control panels, automatic testing of the first 106 and second 107 channels of information exchange with the equipment of the stand, respectively;

c) display of information about the sequence, content and initialization results of functional software:

- the first 87 and second 88 computing complexes of the first 84, second 85 and third 86 control panels respectively on the first 95 and second 96 monitors;

- on the information display elements from the composition of video surveillance and registration devices 101 and display and registration devices 102 of the first 84, second 85 and third 86 control panels;

d) automatic or at the command of operators (in the “operator-computer complex” dialog using the first 89 and second 90 keyboards, or the first 91 and second 92 manipulators of the “mouse” type) paper-based documentation of the results of initialization of functional software using the first 93 and second 94 documentation devices.

When power is supplied through closed circuits of switch 111 to video cameras 83 ₁ ÷ 83 _k through information exchange channels with video cameras 108 ₁ ÷ 108 _k to the video surveillance and registration devices 101 of the first 84, second 85 and third 86 control panels, video information about the state of the device elements starts to be transmitted - stand located in the room where the foundation of stand 1 is located. Video surveillance and registration devices 101 after initializing the pre-installed software provide reception, storage and display information obtained with reference to the astronomical time scale constantly at all subsequent stages of the operation of the device - the stand.

Indication and registration devices 102 of the first 84, second 85 and third 86 control panels after initializing the pre-installed software and testing the first 106 and second 107 channels of information exchange with the equipment of the stand, receive, store and display information received through the first 106 and second 107 channels of information exchange with the equipment of the stand, with reference to the astronomical time scale, constantly at all subsequent stages of the operation of the device.

When power is supplied through the closed circuits of the switch 111 to the sets of controls and indicators 100 and emergency shutdown means 104 of the first 84, second 85 and third 86 control panels, preparations are made for the operation of command transmission chains in the “operator-switch” dialogue mode:

- from the sets of controls and indicators 100 through the device matching discrete signals 103 and a device for converting interfaces 113 to the switch 111;

- from the emergency shutdown means 104 through the emergency shutdown device 114 to the switch 111.

Information about the state of the electrical circuits of the switch 111 through the interface conversion device 113 and the discrete signal matching device 103 is transmitted to the control and indication sets 100, where it is displayed to operators by means of light information boards, backlit buttons, light bulbs, etc.

It is allowed to supply electric power from the device of secondary power sources 112 through closed circuits of the switch 111 and the terminal of the airfield power supply 72 to the protection and switching unit 69 from the power supply system 66.

Oscilloscopes 99, sets of tools and accessories 105 from the first 84, second 85 and third 86 control panels are used to perform maintenance and repair of the device - stand.

Main stage

The preparatory phase of the device is completed.

In accordance with the methods and algorithms of operation of the device - the stand in series or in parallel for the first 87 and second 88 computing complexes from the first 84, second 85 and third 86 control panels automatically, under the control of functional software, or manually by operators, in the dialogue mode "operator -computing complex ”using the first 89 and second 90 keyboards, first 91 and second 92 mouse-type manipulators, sets of controls and displays 100, respectively carried out:

- inclusion of lighting elements 82;

- inclusion of a system of supply and exhaust ventilation 81;

- inclusion of the exhaust gas device 78;

- pre-launch control of the elements of the device - stand;

- starting and operation of the internal combustion engine 8;

- promotion of coaxial screws 13;

- ground-stand autonomous or complex tests of helicopter elements with coaxial screws;

- stop the internal combustion engine 8;

- bringing the elements of the device - stand to its original state. At the same time, the operation of the device - stand is:

- transceiving signals between the first computer complex 87 of the first control panel 84 and the digital controller 68 and / or the second computer complex 88 of the first control 84 and the digital controller 68 through the first 106 and second 107 communication channels with the equipment of the stand;

- operators that act on the buttons and switches from the set of controls and indications 100 of the first control panel 84. This causes the closure / opening of the electrical circuits that transmit the input DC voltage supplied through closed circuits of the switch 111 to the set of controls and indications 100, further to the device for matching discrete signals 103. The device for matching discrete signals 103 in turn converts the signals from a set of controls 100 signals into a serial code, which is transmitted to the interface conversion device 113, where the signals are converted back from the serial code to discrete signals — DC voltage and their subsequent transmission to the switch 111. The switch 111 uses the signals from the device to convert the interfaces 113 the opening of the electric power transmission circuits from the device of the secondary power sources 112 to the consumers of electric power from the device-stand, thereby forming the necessary control actions on the elements of the device - the stand.

The inclusion of lighting elements 82 is performed by a command generated manually by operators. Upon receipt of the control action from the output of the switch 111 to the lighting elements 82 in the rooms where the base of the stand 1 and the third operator panel 86 are located, the light comes on. In the future, the light is constantly on at all subsequent stages of the operation of the device - the stand and turns off at the input of bringing the elements of the device - stand to its original state.

The inclusion of the supply and exhaust ventilation system 81 is performed according to a command manually generated by the operators. Upon receipt of the control action from the output of the switch 111 to the supply and exhaust ventilation system 81 in the room where the base of the stand 1 is located, the forced supply and exhaust ventilation system 81 is provided with forced air supply and forced air exhaust that does not contain exhaust gases from the operation of the internal combustion engine 8. In the future, forced supply and forced air removal is provided continuously at all subsequent stages of the operation of the device - the stand and the input of the element is stopped in the device - stand in its original state.

The inclusion of the exhaust gas device 78 is performed by a command manually generated by the operators. Upon receipt of the control action from the output of the switch 111 to an exhaust fan with an electric drive and a frequency regulator 80 through a flexible conduit 79, a forced exhaust gas from the exhaust pipes 75 from the exhaust system 73 with the internal combustion engine 8. is provided. Further, the forced exhaust of gases is provided constantly at all the subsequent stages of the operation of the device - the stand and stops entering the bringing the elements of the device - stand to its original state.

Pre-start control of the elements of the device-stand is performed according to the commands generated by the first 87 and / or second 88 computing complexes of the first control panel 84, in the following sequence:

a) checks the health of the throttle actuator 41 of the engine control system 40:

- the control unit of the throttle actuator 42 is issued a command from the digital controller 68 to move the throttle actuator 41 from the current position to the position corresponding to its first extreme position;

- means of the control unit of the throttle actuator 42 checks the execution of the command to move the throttle actuator 41 to the first extreme position. If the test is successful, then the throttle actuator control unit 42 generates a message to the digital controller unit 68 about the successful completion of the throttle actuator test 41, otherwise a message is generated indicating a sign of failure of the throttle actuator 41;

- if no signs of failure were detected during the previous steps, a command is issued to the throttle actuator control unit 42 from the digital controller 68 to move the throttle actuator 41 from the first extreme position to the position corresponding to its second extreme position;

- means of the control unit of the throttle actuator 42 checks the execution of the command to move the throttle actuator 41 to the second extreme position. If the test is successful, then the throttle actuator control unit 42 generates a message to the digital controller unit 68 about the successful completion of the throttle actuator test 41, otherwise a message is generated indicating a sign of failure of the throttle actuator 41;

- a command is issued to the throttle actuator control unit 42 from the digital controller 68 to move the throttle actuator 41 from the second extreme position to the initial position that it had before the start of the test;

- if all checks of the throttle actuator 41 are successful, then in the block of the digital controller 68 a sign of successful completion of the check of the throttle actuator 41 is generated, otherwise a sign of the presence of a failure of the throttle actuator 41 is generated;

b) the health of the air cooling system 37 is checked:

- sequentially from the block of the digital controller 68 through the protection and switching unit 69 commands are issued to turn on the electric fans 38 ₁ ÷ 38 _m ;

- sequentially, by means of the block of the digital controller 68, a check is carried out on the execution of commands to turn on electric fans 38 ₁ ÷ 38 _m . If the check is successful, then in the block of the digital controller 68, a sign of successful completion of the check of the air cooling system 37 is generated, otherwise a sign of the failure of the air cooling system 37 is formed;

C) checks the health of the engine control system 40:

, датчика температуры охлаждающей жидкости 52, датчика температуры масла 53, датчика давления масла 54, датчика давления и температуры воздуха на входе двигателя 55, датчика положения заслонки 56, датчика детонации 57, датчика температуры электрического привода несущих винтов 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущих винтов 62;- sequentially, the digital controller 68 performs reading of the first 45 and second 46 air pressure sensors, the first 47 and second 48 air temperature sensors, the first 49 and second 50 crankshaft position sensors, exhaust temperature sensors

, coolant temperature sensor 52, oil temperature sensor 53, oil pressure sensor 54, pressure and air temperature sensor at the engine inlet 55, damper position sensor 56, knock sensor 57, temperature sensor of the electric drive rotors 58, temperature sensor at the inlet of the cooling radiator 59, the temperature sensor at the outlet of the cooling radiator 60, the pressure sensor in the drain fuel line 61, the rotor speed sensor 62;

, датчика температуры охлаждающей жидкости 52, датчика температуры масла 53, датчика давления масла 54, датчика давления и температуры воздуха на входе двигателя 55, датчика положения заслонки 56, датчика детонации 57, датчика температуры электрического привода несущих винтов 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущих винтов 62. Если проверка выполнена успешно, то в блоке цифрового регулятора 68 формируется признак успешного завершения проверки системы управления двигателя 40, иначе формируется признак наличия отказа системы управления двигателя 40;- sequentially by means of the digital controller unit 68, the readings of the first 45 and second 46 air pressure sensors, the first 47 and second 48 air temperature sensors, the first 49 and second 50 crankshaft position sensors, exhaust temperature sensors are checked

, coolant temperature sensor 52, oil temperature sensor 53, oil pressure sensor 54, pressure and air temperature sensor at the engine inlet 55, damper position sensor 56, knock sensor 57, temperature sensor of the electric drive rotors 58, temperature sensor at the inlet of the cooling radiator 59, the temperature sensor at the outlet of the cooling radiator 60, the pressure sensor in the drain fuel line 61, the rotor speed sensor 62. If the test is successful, then in the block of the digital controller 68 forms there is a sign of successful completion of the check of the engine control system 40, otherwise a sign of the failure of the engine control system 40 is formed;

g) checks the serviceability of the piloting device with actuators control the swashplate 18:

- by means of technological control of electret microphones 125, the health of electret microphones from the pilot device with control drives of the swashplate 18 is monitored;

- a self-test of the piloting device with the swashplate control actuators is performed 18. If the self-test successfully completes to the digital controller 68 from the piloting device with the swashplate control drives 18, the device is ready to work, otherwise a sign of a failure in the piloting device with the swashplate control drives is generated eighteen;

- if a message about readiness for operation is received from the piloting device with the swashplate control actuators 18 by the digital controller 68, the sign of the successful completion of the test of the piloting device with the swashplate control actuators 18 is generated in the digital controller 68, otherwise the pilot device with drives control swashplate 18;

d) the health of the power supply system 66 is checked:

- sequentially, by means of the digital controller unit 68, the analog signals from the protection and switching unit 69 and generated by emergency power supply devices 70 are measured to the fourth group of inputs and outputs by the digital controller unit 68;

- sequentially by means of the block of the digital controller 68, the measured analog signals are checked. If the check is successful, then in the block of the digital controller 68, a sign of successful completion of the check of the power supply system 66 is generated, otherwise a sign of the failure of the power supply system 66 is generated.

Pre-start control of the elements of the device - stand is considered completed successfully if the digital controller 68 does not show signs of failure in the tested systems and devices, which allows you to start starting the internal combustion engine 8.

Starting the internal combustion engine 8 is performed by a command that is generated by means of the first 87 or second 88 computing complexes of the first control panel 84 and transmitted respectively through the first channel of information exchange with the equipment of the stand 106 to the second input-output block of the digital controller 68 or through the second channel of information exchange with the equipment of stand 107 to the third input-output unit of the digital controller 68. The block of the digital controller 68, after receiving a start command, performs start-up and operation cyclograms vigatelya internal combustion engine 8, are implemented in its functional software:

a) issuing signals from the first group of inputs and outputs:

- to the control unit of the throttle actuator 42 to change the position of the throttle actuator 41;

- on the first 23 and second 24 fuel pumps;

- to the starter relay 43 and further to the starter 44;

и далее на свечи зажигания

,

;- to ignition coils

on to the spark plugs

,

;

;- to injectors

;

b) reception from the first group of inputs and outputs and signal processing:

- from the fuel level sensor 26 and the pressure sensor in the fuel lines 27;

, датчика температуры охлаждающей жидкости 52, датчика температуры масла 53, датчика давления масла 54, датчика давления и температуры воздуха на входе двигателя 55, датчика положения заслонки 56, датчика детонации 57, датчика температуры электрического привода несущих винтов 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущих винтов 62;- from the first 45 and second 46 air pressure sensors, the first 47 and second 48 air temperature sensors, the first 49 and second 50 crankshaft position sensors, exhaust temperature sensors

, coolant temperature sensor 52, oil temperature sensor 53, oil pressure sensor 54, pressure and air temperature sensor at the engine inlet 55, damper position sensor 56, knock sensor 57, temperature sensor of the electric drive rotors 58, temperature sensor at the inlet of the cooling radiator 59, the temperature sensor at the outlet of the cooling radiator 60, the pressure sensor in the drain fuel line 61, the rotor speed sensor 62;

c) receiving / issuing from the fourth group of inputs and outputs and processing signals of the protection and switching unit 69. Moreover:

- fuel from the fuel tank 20 through the coarse filter 21, fine filters 22, the first 23 and second 24 fuel pumps through the fuel lines 25 enters the internal combustion engine 8;

- oil circulates between the oil cooler 29 and the internal combustion engine 8 through the oil tank 30 along the oil supply lines 31;

- coolant circulates between the water radiator 33 and the internal combustion engine 8 through the expansion tank 34, the overflow tank 35 along the coolant supply lines 36;

- air by electric fans 38 ₁ ÷ 38 _{m is} distributed on hot surfaces by an internal combustion engine 8, an electric rotor drive 10, an oil cooler 29 and a water radiator 33;

- electricity from the outputs of the generators 67 ₂ ÷ 67 _n is supplied to the protection and switching unit 69 and then to the consumers of electricity placed on the frame of the fuselage 5;

- exhaust gases through a muffler 74, exhaust pipes 75, a flexible pipe 79 and an exhaust fan with an electric drive and a frequency controller 80 are removed from the room where the foundation of stand 1 is located;

- atmospheric air through the supply and exhaust ventilation system 81 is supplied to the room where the foundation of stand 1 is located;

- information on the operation of the piloting device with drives for controlling the swash plate 18, fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 73 along the first 106 and second 107 channels information exchange with the equipment of the stand is transmitted to the display and registration device 102 of the first control panel 84, where it is displayed, recorded in a long-term memory and stored;

- information on the operation of the piloting device with drives for controlling the swash plate 18, fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 73 along the first 106 and second 107 channels information exchange with the equipment of the stand is transmitted respectively to the first 87 and second 88 computing complexes of the first control panel 84, where it is recorded in long-term memory, stored, processed, transmitted on the display, respectively, on the first 95 and second 96 monitors, transmission for documentation to the first 93 and second 94 of the documentation device of the first control panel 84.

If the engine output shaft speed exceeds a certain value, 69 generators 67 ₁ ÷ 67 _n are connected to the electric drive of the rotors 10 using the protection and switching unit. The electric drive of the rotors 10 provides rotation of the coaxial screws 13. Electricity from the outputs of the generators 67 ₁ ÷ 67 _n is supplied to the protection and switching unit 69 and then to electricity consumers placed on the fuselage frame 5.

Ground-stand autonomous or complex tests of helicopter elements with coaxial propellers are carried out by the operator acting on the pilot controls 14 and / or by commands that are generated by means of the first 87 and / or second 88 computer systems of the first control panel 84 and transmitted respectively through the first information exchange channel with the equipment of the stand 106 to the second input-output of the block of the digital controller 68 and the piloting device with drives for controlling the swashplate 18 and / or through the second channel in formation exchange with the equipment of the stand 107 to the third input-output unit of the digital controller 68 and the piloting device with drives for controlling the swashplate 18.

The impact of the operator on the pilot controls 14 imitate various operating modes of the helicopter carrier system with coaxial screws by controlling the position of the coaxial screws 13 by changing the position of the swashplate 12, levers 15, rocker 16.

The digital controller block 68, after receiving commands, by means of pre-installed functional software implements a simulation of various operating modes of the helicopter carrier system with coaxial screws:

a) issuing signals from the first group of inputs and outputs:

- to the control unit of the throttle actuator 42 to change the position of the throttle actuator 41;

и далее на свечи зажигания

,

;- to ignition coils

on to the spark plugs

,

;

;- to injectors

;

b) reception from the first group of inputs and outputs and signal processing:

- from the fuel level sensor 26 and the pressure sensor in the fuel lines 27;

датчика температуры охлаждающей жидкости 52, датчика температуры масла 53, датчика давления масла 54, датчика давления и температуры воздуха на входе двигателя 55, датчика положения заслонки 56, датчика детонации 57, датчика температуры электрического привода несущих винтов 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущих винтов 62;- from the first 45 and second 46 air pressure sensors, the first 47 and second 48 air temperature sensors, the first 49 and second 50 crankshaft position sensors, exhaust temperature sensors

coolant temperature sensor 52, oil temperature sensor 53, oil pressure sensor 54, pressure and air temperature sensor at the engine inlet 55, damper position sensor 56, knock sensor 57, temperature sensor of the electric drive rotors 58, temperature sensor at the inlet of the cooling radiator 59 , a temperature sensor at the outlet of the cooling radiator 60, a pressure sensor in the drain fuel line 61, a rotor speed sensor 62;

c) receiving / issuing from the fourth group of inputs and outputs and signal processing of the protection and switching unit 69.

If the generators 67 ₁ ÷ 67 _n from the power supply system 66 are connected through the protection and switching unit 69 to the rotor electric drive 10, the pilot device with the swashplate control drives 18 using the pre-installed functional software imitates various operating modes of the helicopter carrier system with coaxial screws by controlling the position of the coaxial screws 13 by changing the position of the swashplate 12, levers 15, rocker 16.

Wherein:

- the internal combustion engine 8, the fuel system 19, the lubrication system 28, the water cooling system 32, the air cooling system 37, the engine control system 40, the power supply system 66, the exhaust system 73, the exhaust gas extraction device 78, the supply and exhaust ventilation system 81 continue function in the same way as when starting up and ensuring the operation of the internal combustion engine 8;

- the electrochemical recuperator 71 ensures the maintenance of the required quality of electricity in the power supply system 66 during short-term surges or voltage dips due to dynamic changes in the load on the power supply system 66;

- the analyzer of current sources 17 analyzes, writes to long-term memory and stores information about the quality of electricity in the power supply system 66;

- the first 117 and second 118 high-speed video cameras carry out high-speed shooting and transmission, respectively, through the first 106 and second 107 channels of information exchange with the equipment of the video information stand about the operation of the coaxial screws 13 to the first 87 and second 88 computing complexes of the second control panel 85, where it is processed, output on indication, it is recorded in long-term memory and stored;

- the first 119 and second 120 thermal imagers shoot and transmit, respectively, through the first 106 and second 107 channels of information exchange with the equipment of the information stand on the temperature of the internal combustion engine 8, the electric drive of the rotors 10, the output coaxial shafts 11, the swashplate 12, the fuel system 19, lubrication systems 28, water cooling systems 32, air cooling systems 37, engine control systems 40, power supply systems 66, exhaust systems 73 to the first 87 and second 88 computer systems s of the second control unit 85, where it is processed, displayed on the display is recorded in non-volatile memory and is stored;

- a spectrum analyzer with the function of measuring direct and reflected signals 121 measures through antennas 122 ₁ ÷ 122 _s , and transmits, respectively, through the first 106 and second 107 channels of information exchange with the equipment of the stand information about the electromagnetic radiation of the equipment of the device - the stand located inside the shields 77 , on the first 87 and second 88 computing complexes of the second control panel 85, where it is processed, displayed, displayed in long-term memory and stored;

- the noise analysis system 123 measures through microphones 124 ₁ ÷ 124 _t , and transmits, respectively, through the first 106 and second 107 channels of information exchange with the equipment of the stand information about the acoustic noise of the device equipment — the stand located inside the shields 77, to the first 87 and second 88 computing complexes of the second control panel 85, where it is processed, displayed, displayed in long-term memory and stored;

- a parametric tester of consecutive channels of information exchange 126 measures and transfers, respectively, through the first 106 and second 107 channels of information exchange with the equipment of the stand information on the operation of the channels of information exchange of the equipment of the device - the stand located inside the protective screens 77, to the first 87 and second 88 computing complexes the second control panel 85, where it is processed, displayed, recorded in a long-term memory and stored;

- the optical control system of bodies of revolution 127 carries out measurement and transmission, respectively, through the first 106 and second 107 channels of information exchange with the equipment of the stand information about the operation parameters of the output coaxial shafts 11, where it is processed, displayed, recorded in a long-term memory and stored;

- information on the operation of the piloting device with drives for controlling the swash plate 18, fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 73 along the first 106 and second 107 channels information exchange with the equipment of the stand is transmitted to the display and registration device 102 of the first control panel 84, where it is displayed, recorded in a long-term memory and stored;

- information on the operation of the piloting device with drives for controlling the swash plate 18, fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 73 along the first 106 and second 107 channels information exchange with the equipment of the stand is transmitted respectively to the first 87 and second 88 computing complexes of the first control panel 84, where it is recorded in long-term memory, stored, processed, transmitted on the display, respectively, on the first 95 and second 96 monitors, transmission for documentation to the first 93 and second 94 of the documentation device of the first control panel 84.

The stop of the internal combustion engine 8 is carried out by a command that is generated by means of the first 87 or second 88 computer systems of the first control panel 84 and is transmitted respectively through the first channel of information exchange with equipment of the stand 106 to the second input-output block of the digital controller 68 or through the second channel of information exchange with the equipment of the stand 107 to the third input-output block of the digital controller 68. The block of the digital controller 68 after receiving a command using the predefined functionality noy software provides the implementation of the shutdown diagram of the internal combustion engine 8:

a) issuing signals from the first group of inputs and outputs:

- to the control unit of the throttle actuator 42 to change the position of the throttle actuator 41;

и далее на свечи зажигания

- to ignition coils

on to the spark plugs

- to injectors

b) reception from the first group of inputs and outputs and signal processing:

- from the fuel level sensor 26 and the pressure sensor in the fuel lines 27;

датчика температуры охлаждающей жидкости 52, датчика температуры масла 53, датчика давления масла 54, датчика давления и температуры воздуха на входе двигателя 55, датчика положения заслонки 56, датчика детонации 57, датчика температуры электрического привода несущих винтов 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущих винтов 62;- from the first 45 and second 46 air pressure sensors, the first 47 and second 48 air temperature sensors, the first 49 and second 50 crankshaft position sensors, exhaust temperature sensors

coolant temperature sensor 52, oil temperature sensor 53, oil pressure sensor 54, pressure and air temperature sensor at the engine inlet 55, damper position sensor 56, knock sensor 57, temperature sensor of the electric drive rotors 58, temperature sensor at the inlet of the cooling radiator 59 , a temperature sensor at the outlet of the cooling radiator 60, a pressure sensor in the drain fuel line 61, a rotor speed sensor 62;

c) receiving / issuing from the fourth group of inputs and outputs and signal processing of the protection and switching unit 69.

Wherein:

- the internal combustion engine 8, the fuel system 19, the lubrication system 28, the water cooling system 32, the air cooling system 37, the engine control system 40, the power supply system 66, the exhaust system 73, the exhaust system 78, the supply and exhaust ventilation system 81 are stopped function;

- information on the operation of the fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 73 through the first 106 and second 107 channels of information exchange with the equipment of the stand is transmitted to the display device and registration 102 of the first control panel 84, where it is displayed, is recorded in a long-term memory and stored;

- information on the operation of the fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 73 through the first 106 and second 107 channels of information exchange with the equipment of the stand is transmitted respectively to the first 87 and second 88 computing complexes of the first control panel 84, where it is recorded in long-term memory, stored, processed, transmitted to the display, respectively, on the first 95 and second 96 monitors, transmitted and documentation on the first 93 and second 94 documenting devices.

When bringing the elements of the device to its original state:

- by a command formed manually by the operators, the exhaust gas removal device 78 is turned off. Forced exhaust gases from the exhaust pipes 75 from the exhaust system 73 are stopped;

- by a command formed manually by operators, the supply and exhaust ventilation system is turned off 81. Forced air supply and forced air removal in the room where the foundation of stand 1 is located are stopped;

- by a command formed manually by operators, the lighting elements 82 are turned off. The light in the rooms where the stand of the stand 1 and the operator panel 86 are located is turned off.

During the main stage of operation of the device - stand:

- indication of the content and results of the functional software of the first 87 and second 88 computing complexes of the first 84, second 85 and third 86 control panels is carried out respectively on the first 95 and second 96 monitors, respectively, of the first 84, second 85 and third 86 control panels;

- paper-based documentation of the content and results of the functional software of the first 87 and second 88 computing complexes of the first 84, second 85 and third 86 control panels is carried out respectively using the first 93 and second 94 documenting devices from the first 84, second 85 and third 86 control panels;

- the measurement of vibration of the constituent elements of the device located on the frame of the fuselage 5, is carried out using a vibration measuring device 76;

- measurement and indication of the parameters of the electrical signals of the devices from the first 84, second 85 and third 86 control panels is carried out using the corresponding oscilloscopes 99;

- the results of the operation of the device - the stand are transferred to the means of interfacing with the helicopter operation support system 128 to generate electronic passports of the helicopter elements with coaxial screws.

Emergency phase

At the preparatory and main stages, operators use an analyzer of current sources 17, first 117 and second 118 high-speed cameras, first 119 and second 120 thermal imagers, a spectrum analyzer with the function of measuring direct and reflected signals 121, a noise analysis system 123, a parametric tester of serial communication channels 126, optical control system of bodies of revolution 127 monitor the operation of the device - stand. If signs of abnormal work are detected that adversely affect the safety of the device-stand:

a) fire extinguishing device 39 performs actions that prevent the occurrence and maintenance of burning in the room where the foundation of stand 1 is located;

b) the functional software of the first 87 and / or second 88 computer systems from the first control panel 84 performs actions to stop the internal combustion engine 8 in the amount provided for at the main stage of operation of the device;

c) by operators, in the “operator-computer complex” dialogue mode, using the first 89 and second 90 keyboards, the first 91 and second 92 mouse-type manipulators, the set of control and indication elements 100 of the first control panel 84, actions are taken to stop the internal engine combustion 8 and bringing the elements of the device - stand to its original state in the volume provided for at the main stage of operation of the device;

d) operators by means of an emergency shutdown 104 of the first control panel 84 issue a command for an emergency power off of the device through the emergency shutdown device 114 to the switch 111, which opens the electrical circuits of power supply to consumers of electricity from the device;

e) firefighting operators or fire fighting personnel use fire extinguishing means 116;

f) the uninterruptible power supply 110 is supplied with electric energy to the stand in the absence of power from external sources of electricity;

g) the first 97 and / or second 98 autonomous uninterruptible power supplies supply electric energy to the first 87 and second 88 computing complexes, respectively, of the first 84, second 85 and third 86 control panels in the absence of power from external sources of electricity;

h) the protection and switching unit 69 disables faulty sources of electricity: generators 67 ₁ ÷ 67 _n , emergency power supply devices 70, airfield power supply connectors 72 from electricity consumers placed on the fuselage frame;

i) the block of protection and switching 69 disconnects the faulty consumers of electricity, located on the frame of the fuselage 5, from electric power sources: generators 67 ₁ ÷ 67 _n , emergency power supply devices 70, airfield power supply connector 72.

At all stages of the operation of the device, the protection of the operators or staff of the stand from accidental or accidental expansion of the elements of the device located on the frame of the fuselage 5, carry protective screens 77.

To perform fault diagnostics, update functional software and copy information to the first 87 and / or second 88 computing complexes from the first 84, second 85 and third 86 control panels, and / or interface conversion device 113 from the power supply device 109, and / or a piloting device with drives for controlling the swashplate 18, and / or a digital controller unit 68 from the power supply system 66, and / or an indication and registration device 102 from the first 84, the second 8 5 and the third 86 control panels can connect the programming device 115.

This device compared with the prototype allows you to:

- to carry out autonomous and comprehensive tests of the elements of the helicopter with a mechanical control system for the position of the blades, electric drive rotors and a hybrid power plant, which extends the functionality of the device;

- control the position of the rotor blades, the geometrical parameters of the output coaxial shafts, the thermal stress of the helicopter structural components, the operating modes of the emergency emergency power supplies, the electromagnetic radiation of the electronic avionics, the values of the acoustic noise generated by the helicopter, the quality of the signals in the serial communication channels between the onboard equipment the performance of electret microphones, which extends the functionality of the mouth oystva;

- to prevent emergencies that may lead to a disruption of the state of the helicopter elements with coaxial screws due to mechanical failure and / or overheating of the structural elements of the helicopter carrier system, a short-term decrease or exceeding the limit parameters of the onboard electrical network, production defects of the output coaxial shafts, which expands the functionality of the device;

- conduct ongoing maintenance, diagnostics of components and repair work when signs of failure appear, which extends the functionality of the device;

- transmit information to the helicopter operation support system to form a database (electronic passport) about the initial technical parameters of the helicopter at the stage of its testing;

- protect operators, maintenance personnel and the device itself from the consequences of emergency situations that may occur during testing of elements of an unmanned helicopter with coaxial screws in the event of a sudden interruption in the supply of electricity to the components of the device, which increases the safety of the device.

The use of the invention in aviation test equipment can reduce the time and cost of ground-bench tests of helicopter elements with coaxial screws, due to the lack of the need to create and operate separate devices - stands to provide autonomous testing of each helicopter component. In addition, it is possible to identify the structural imperfections of the helicopter in the early stages of its design, due to the integration and integrated testing (testing) of the main helicopter systems as part of a single device.

Claims (1)

Helicopter element test bench with coaxial screws, containing the stand base, power cage, clamping devices, mounting frame, fuselage frame, shock absorbers, motor mount, internal combustion engine, frame for mounting the rotor electric drive, output coaxial shafts, swash plate, coaxial screws , levers, rocker arms, piloting device with drives for controlling the swash plate, fuel system as a part of the fuel tank, coarse filter, fine filters, first and second fuel pumps, fuel lines, fuel level sensor and pressure sensor in the fuel lines, lubrication system as part of the oil cooler, oil tank and oil supply lines, water cooling system as part of the water radiator, expansion tank, overflow tank and coolant supply pipes, air cooling system consisting of one to m electric fans, fire extinguishing device, engine control system as part of a throttle actuator, throttle actuator control unit Onki, starter relay, starter, first and second air pressure sensors, first and second air temperature sensors, first and second crankshaft position sensors, one to p exhaust gas temperature sensors, coolant temperature sensor, oil temperature sensor, oil pressure sensor, pressure sensor and air temperature at the engine inlet, damper position sensor, knock sensor, temperature sensor of the main rotor drive, temperature sensor at the inlet of the cooling radiator, sensor and the temperature at the outlet of the cooling radiator, pressure sensor in the drain fuel line, rotor speed sensor, from one to l ignition coils, 2l injectors and 2l spark plugs, power supply system consisting of one to n generators, a digital controller block, emergency power devices and airfield power connector, exhaust system consisting of a muffler and exhaust pipes, a vibration measuring device, protective shields, an exhaust gas device as part of a flexible pipe and exhaust fan and with an electric drive and a frequency regulator, a supply and exhaust ventilation system, lighting elements, from one to k video cameras, the first, second and third control panels, each of which is equipped with the first and second computer systems, the first and second keyboards, the first and second manipulators of the type “Mouse”, the first and second documentation devices, the first and second monitors, a set of controls and indicators, an indication and registration device, a video surveillance and registration device, a matching device discrete signals, emergency shutdown means, the first and second channels of information exchange with the equipment of the stand, from one to k channels of information exchange with video cameras, a power supply device, consisting of an uninterruptible power supply device, a switch, a secondary power supply device, an interface conversion device and an emergency shutdown device , programming devices, fire extinguishing means, characterized in that the pilot controls are additionally introduced, electric when rotors, protection and switching unit, electrochemical recuperator, current source analyzer, first and second high-speed cameras, first and second thermal imagers, spectrum analyzer with direct and reflected signal measurement, from one to s antennas, noise analysis system, from one to t microphones, means of technological control of electret microphones, parametric tester of serial channels of information exchange, optical system for monitoring bodies of revolution, means of interfacing with an electronic support system helicopter operations, in each control panel, the first and second autonomous uninterruptible power supplies, an oscilloscope, a set of tools and accessories, the stand foundation being a monolithic reinforced concrete slab with a metal power frame, on which a mounting frame is fixed with clamping devices, with it rigidly attached to it, using bolts, the fuselage frame, which, in turn, are mounted: on the shock absorbers of the engine mount with an internal combustion engine installed on it, and the engine s combustion is connected with the muffler via the exhaust pipe, and on the output shaft of the internal combustion engine are arranged from one to n generators from the power supply system; a frame for attaching an electric rotor drive with a structure of an electric rotor drive, coaxial output shafts, a swashplate, coaxial screws and a swashplate control actuators from a piloting device with a swashplate control drives, and the rotor electric drive is mechanically connected to output coaxial shafts, connected in turn with coaxial screws, a piloting device with control drives of the swash plate through levers, automatic The skew and rocker arms are connected to the coaxial screws, the swashplate control drives and other components of the piloting device with the swashplate control drives have electrical and information connections between each other; pilot controls, and pilot controls through levers, swash plate and rocker arm connected to coaxial screws; on shock absorbers, a fuel tank and other elements of the fuel system: a coarse filter, fine filters, first and second fuel pumps, the fuel tank, with a fuel level sensor installed in it, using fuel lines, with a pressure sensor in the fuel lines connected coarse filter, fine filters, the first and second fuel pumps are connected to injectors from the engine control system, the first and second fuel pumps are in a common housing; an oil cooler and oil tank from the lubrication system, the oil cooler and oil tank using the oil supply lines connected to an internal combustion engine; a water radiator, an expansion tank and an overflow tank from the composition of the water cooling system are connected to the internal combustion engine using the coolant supply lines; electric fans from the air cooling system, and electric fans are placed on the fuselage frame so as to provide optimal cooling of the internal combustion engine and electric drive of the rotors, oil cooler from the lubrication system and water radiator from the water cooling system; fire extinguishing device; the throttle actuator and the throttle actuator control unit from the engine management system, the throttle actuator control unit being connected to the throttle actuator by information and electrical connections, and the throttle actuator with the throttle of the internal combustion engine by mechanical coupling; a digital controller unit, a protection and switching unit, an electrochemical recuperator, a current source analyzer, emergency power devices and an aerodrome power connector, the digital controller unit using the first group of inputs and outputs connected to the starter relay, the first and second air pressure sensors, the first and second air temperature sensors, first and second crankshaft position sensors, exhaust gas temperature sensors, coolant temperature sensor, oil temperature sensor, m pressure sensor asla, a pressure sensor and air temperature at the engine inlet, a damper position sensor, a knock sensor, a temperature sensor for the electric drive of the main rotors, a temperature sensor at the inlet of the cooling radiator, a temperature sensor at the outlet of the cooling radiator, a pressure sensor in the drain fuel line, a rotor speed sensor , ignition coils, injectors from the engine control system, and through the fourth group of inputs and outputs - with a protection and switching unit, emergency power devices connected through a protection and switching unit to electric consumers located on the fuselage frame, generators, an electrochemical recuperator and an aerodrome power connector, an aerodrome power connector through a protection and switching unit connected to an electric rotor drive, an electrochemical recuperator, electric consumers placed on the fuselage frame, and emergency power devices, generators located on the output shaft of the internal combustion engine, through the protection and switching unit are connected electric rotor drive, electrochemical recuperator, power consumers located on the fuselage frame, and emergency power devices, a starter placed on an internal combustion engine, connected to a starter relay, spark plugs placed in pairs on an internal combustion engine, connected to corresponding ignition coils, the electrochemical recuperator is connected to the analyzer of current sources and through the protection and switching unit to electricity consumers placed on the fu frame potion; a vibration measuring device, along the perimeter of the stand foundation there are protective screens, on the inside of which are installed the first and second high-speed cameras, the first and second thermal imagers, from one to s antennas, from one to t microphones, a flexible pipe is connected to the exhaust pipes from the exhaust system connected to an exhaust fan with an electric drive and a frequency regulator from the exhaust gas device, the room in which the stand foundation is located is equipped with a supply system No-exhaust ventilation, lighting elements and video cameras, from the outside of the protective screens are placed the means of technological control of electret microphones, a parametric tester of serial channels of information exchange, a spectrum analyzer with a function for measuring direct and reflected signals, a noise analysis system, an optical control system for rotation bodies, an electrical power device , the first and second control panels, and the first computer complex of the first control panel connected to the first a stand-alone uninterruptible power supply, the first keyboard, the first mouse-type manipulator, the first documentation device, the first monitor and, through the first channel of information exchange with the stand equipment, an indication and registration device, an oscilloscope, a piloting device with skew control drives and a second input-output unit a digital controller from the power supply system, a second autonomous uninterruptible source is connected to the second computer complex from the first control panel power supply, a second keyboard, a second mouse-type manipulator, a second documentation device, a second monitor, and through a second channel of information exchange with the equipment of the stand, an indication and recording device, an oscilloscope, a piloting device with skew control drives and a third input-output of a digital controller block from the power supply system, the first autonomous uninterruptible power supply, the first keyboards are connected to the first computer complex from the second control panel , the first mouse-type manipulator, the first documenting device, the first monitor and, through the first channel of information exchange with the equipment of the stand, the indicating and recording device, an oscilloscope, the first high-speed video camera, the first thermal imager, a spectrum analyzer with the function of measuring direct and reflected signals connected to it antennas, noise analysis system with microphones connected to it, means of technological control of electret microphones, parametric tester of serial channels of information the second exchange, an optical system for controlling the bodies of revolution, a second autonomous uninterruptible power supply, a second keyboard, a second mouse-type manipulator, a second documentation device, a second monitor and a second channel of information exchange with the equipment of the stand are connected to the second computer complex from the second control panel indicating and recording device, oscilloscope, second high-speed video camera, second thermal imager, spectrum analyzer with the function of measuring direct and reflected signals with antennas connected to it, a noise analysis system with microphones connected to it, means of technological control of electret microphones, a parametric tester of serial communication channels, an optical system for monitoring rotation bodies, the first stand-alone uninterruptible power supply, the first keyboard are connected to the first computer complex from the third control panel , the first mouse-type manipulator, the first documentation device, the first monitor and through the first channel of information exchange with the stand equipment, an indication and registration device, an oscilloscope, means of interfacing with a helicopter operation support system, the first computer systems from the first and second control panels, the second stand-alone uninterruptible power supply, the second keyboard, and the second are connected to the second computer complex from the third control panel a mouse-type manipulator, a second documentation device, a second monitor, and through the second channel of information exchange with the equipment of the stand indication and registration system, oscilloscope, means of interfacing with a helicopter operation support system, second computer systems from the first and second control panels, to control and indication sets from the first, second and third control panels through discrete signal matching devices and interface conversion device a switch is connected from the power supply device to the video surveillance and registration devices from the first, second and third panels control cameras through the information exchange channels with video cameras are connected video cameras, external power sources are connected to the inputs of an uninterruptible power supply device from the power supply device, and secondary power supply devices are connected to the outputs, which, in turn, is connected via a switch to electricity consumers from the device-stand, to emergency shutdown devices from the first, second and third are connected to the input of the emergency shutdown device from the power supply device control panels, and the output is a switch, the programming device can be connected to the first and / or second computer systems from the first, second and third control panels, and / or the interface conversion device from the power supply device, and / or the pilot device with drives control the swashplate, and / or the digital controller unit from the power supply system, and / or the display and registration device from the first, second and third control panels, the third Ultimate control is located in a separate, isolated room, all rooms are equipped with fire extinguishing agents stand, in the first, second and third control units included one set of tools and accessories.

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