RU2628873C2 - Stand for testing elements of beliliary helicopter with outside screws - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: device contains the foundation of the stand, the power frame, the clamping devices, the mounting frame, the fuselage frame, the shock absorbers, the engine mounting, the internal combustion engine, the gearbox, the reducer, the output coaxial shafts, the skew machine, the coaxial screws, the clutch, the levers, the rocker arms, the load device, A piloting device with slip control drives, a fuel system, lubricants, cooling systems, an engine management system, a fire extinguishing system, a supply and exhaust ventilation system, Holds the control panel.

EFFECT: enhanced functionality and increased security.

18 dwg

Description

The invention relates to aeronautical testing equipment, and in particular, to stands for testing elements of an unmanned helicopter with coaxial propellers, for example, a rotor, a main gearbox and main shafts, a swashplate, a power plant, an electric power supply system, drives and electronic equipment, from an aerobatic complex.

A device-stand for dynamic testing of elements is known, which contains a frame, end panels, brackets, articulated bearings, lever, hinges, clamping devices, the tested product, drums, cables, tenders, mechanical vibrators, cardan transmission, junction box, electric motor, dynamometer and power exciter (RF patent No. 2028591, IPC G01M 7/00, publ. 09.02.1995).

The disadvantages of this device are the limited functionality when performing tests of the elements of the power plant, power supply system and the flight complex of an unmanned helicopter with coaxial screws.

There is also a device-stand for life tests of the elements of the power plant of a helicopter with coaxial screws (RF patent No. 2091739, IPC G01M 7/06, G01M 15/00, publ. 09/27/1997).

The device comprises a base, a cardan frame, a power unit of the helicopter, hinges, shock absorbers and coaxial screws.

The device has:

- limited functionality when testing the elements of the power supply system and the flight complex of an unmanned helicopter;

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

The closest prototype to the claimed technical solution is a device-stand for testing the drive system of the coaxial rotors of the helicopter (RF patent No. 59251, IPC G01M 7/00, G01N 3/32, 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.

This device solves the problem of testing the elements of the supporting system of the helicopter with coaxial screws, but its disadvantages are:

- limited functionality that does not allow it to be used when performing autonomous and complex tests of the elements of the power plant, power supply system and the flight complex of an unmanned helicopter with coaxial screws;

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

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

The problem is solved as follows.

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, система электроснабжения в составе от одного до n генераторов, блока цифрового регулятора, блока предохранителей, устройств аварийного питания и разъема аэродромного питания, система выхлопная 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, система 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, 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; рама подредукторная с установленной на ней конструкцией из редуктора, выходных соосных валов, автомата перекоса, соосных винтов и приводов управления автоматом перекоса из устройства пилотирования с приводами управления автоматом перекоса, причем выходной вал двигателя внутреннего сгорания через муфту, редуктор и выходные соосные валы соединен с соосными винтами, а приводы устройства 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; на амортизаторах топливный бак и другие элементы системы топливной: фильтр грубой очистки, фильтры тонкой очистки, первый и второй топливные насосы из состава системы топливной, 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, 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; один генератор, блок цифрового регулятора, блок предохранителей, устройства аварийного питания и разъем аэродромного питания из состава системы электроснабжения, причем генератор механически связан с муфтой и подключен через блок предохранителей к устройству аварийного питания и потребителям электроэнергии размещенными на каркасе фюзеляжа, 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 подредукторного пространства, датчиком температуры на входе радиатора охлаждения, датчиком температуры на выходе радиатора охлаждения, датчиком давления в сливной топливной магистрали, датчиком оборотов несущего винта, катушками зажигания, инжекторами из состава системы управления двигателя, а через четвертую группу входов-выходов - с блоком предохранителей, устройства аварийного питания подключены через блок предохранителей к потребителям электроэнергии, размещенным на каркасе фюзеляжа, генераторам и разъему аэродромного питания, разъем аэродромного питания через блок предохранителей связан с потребителями электроэнергии, размещенными на каркасе фюзеляжа и устройствами аварийного питания, генераторы, размещенные на двигателе внутреннего сгорания, через блок предохранителей связаны с 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; устройство измерения вибрации, по периметру фундамента стенда расположены защитные экраны, 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, системой освещения и видеокамерами, в другом изолированном помещении размещается пульт управления и устройство электропитания, причем к первому вычислительному комплексу из состава пульта управления подключены первая клавиатура, первый манипулятор типа «мышь», первое устройство документирования, первый монитор и через первый канал информационного обмена с оборудованием стенда устройство индикации и регистрации, устройство пилотирования с приводами управления автоматом перекоса и второй вход-выход блока цифрового регулятора из состава системы электроснабжения, ко второму вычислительному комплексу из состава пульта управления подключены вторая клавиатура, второй манипулятор типа «мышь», второе устройство документирования, второй монитор и через второй канал информационного обмена с оборудованием стенда устройство индикации и регистрации, устройство пилотирования с приводами управления автоматом перекоса и третий вход-выход блока цифрового регулятора из состава системы электроснабжения, к комплекту органов управления и индикации из состава пульта управления через устройство согласования дискретных сигналов и устройство преобразования интерфейсов подключен коммутатор из состава устройства электропитания, к устройству видеонаблюдения и регистрации из состава пульта 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 пульта управления, а к выходу - коммутатор, устройство программирования может подключаться к первому и/или второму вычислительным комплексам из состава пульта 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 пульта управления, вместо генератора и редуктора с помощью механической передачи к выходному валу двигателя внутреннего сгорания может подключаться нагрузочное устройство, изолированные помещения, в которых располагаются фундамент стенда и пульт управления, оборудованы средствами пожаротушения.Into a device-stand for testing elements of an unmanned helicopter with coaxial screws, containing the stand foundation, power cage, 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 and load device, a piloting device with drives for controlling the swash plate was additionally introduced, the fuel system as a part of the fuel tank, rough 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, air cooling system consisting of one to m electric fans, fire extinguishing device, engine control system as part of the throttle drive minutes damper throttle actuator control unit, starter switch, a starter, the first and second air pressure sensors, the first and second temperature sensors, the first and second position sensors, crankshaft, 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 block, a fuse block, emergency power devices and an aerodrome 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 flexible duct and exhaust fan with electric drive and frequency regulator, supply and exhaust ventilation system, lighting elements, from one to k video cameras, control panel, equipped with 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 means, the stand foundation being a monolithic reinforced concrete slab with a metal power frame on which clamping devices mounted mounting frame with a rigidly attached to it, using bolts, the fuselage frame, on which, in turn, are mounted: on the shock absorbers of the engine mount with an internal combustion engine installed on it, the internal combustion engine being connected to the muffler using exhaust pipes; sub-gear frame with a structure mounted on it from a gearbox, output coaxial shafts, swashplate, coaxial screws and swashplate control drives from a piloting device with swashplate control drives, and the output shaft of the internal combustion engine through a coupling, gearbox and output coaxial shafts connected to coaxial screws, and the pilot device drives with control gears of the swash plate through levers, the swash plate and rocker arms are connected to the coaxial screws, the control drives are Omata skew and other constituent elements of the piloting device swashplate control actuators are electrically interconnected and informational communications; on the shock absorbers, the fuel tank and other elements of the fuel system: a coarse filter, fine filters, the first and second fuel pumps from the fuel system, and the fuel tank, with a fuel level sensor installed in it, using fuel lines, with a pressure sensor connected to fuel lines, through a 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 common puse; 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 the electric fans are placed on the fuselage frame so as to provide optimal cooling of the internal combustion engine, the oil radiator from the lubrication system and the 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; one generator, a digital controller block, a fuse block, emergency power supply devices and an aerodrome power connector from the power supply system, the generator being mechanically connected to the clutch and connected through the fuse block to the emergency power device and power consumers located on the fuselage frame, the digital controller block using the first group of inputs and outputs is connected to the starter relay, the first and second air pressure sensors, the first and second air temperature sensors, the first and second m crankshaft position sensors, 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 , temperature sensor at the outlet of the cooling radiator, pressure sensor in the drain fuel line, rotor speed sensor, ignition coils I, by injectors from the engine control system, and through the fourth group of inputs and outputs - with a fuse box, emergency power devices are connected through a fuse box to electricity consumers located on the fuselage frame, to generators and an aerodrome power connector, the aerodrome power connector is connected through a fuse box with electricity consumers placed on the fuselage frame and emergency power devices, generators placed on the internal combustion engine through the pre keepers are connected with consumers of electric power, arranged on the frame of the fuselage, and the emergency power supply device, starter, arranged on the internal combustion engine, the starter relay is connected to the spark plugs, arranged in pairs on an internal combustion engine connected to the respective ignition coils; vibration measuring device, protective screens are located around the perimeter of the stand foundation, 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 equipped with a supply and exhaust system ventilation, lighting system and video cameras, in another isolated room is a control panel and power supply, and to p The first computer complex from the control panel includes 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, a piloting device with skew control drives and a second input-output of the digital controller unit from the power supply system, a second keyboard is connected to the second computer complex from the control panel, the second ma a mouse-type emulator, a second documentation device, a second monitor, and an indication and registration device, a pilot device with skew control drives and a third input-output of a digital controller block from the power supply system, to the set of controls and indications from the composition of the control panel through a device for matching discrete signals and a device for converting interfaces connected to the switch from the device e power supply, video cameras are connected to the video surveillance and registration device from the control panel through the information exchange channels with video cameras, external power sources are connected to the inputs of the uninterruptible power supply from the power supply device, and the secondary power supply device is connected to the outputs, which in turn is connected via a switch with electricity consumers from the stand device, to the input of the emergency shutdown device from the power device emergency shutdown means from the control panel are connected, and a switch is connected to the output, the programming device can be connected to the first and / or second computer complexes from the control panel, and / or the interface conversion device from the power supply device, and / or the piloting 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 control panel, instead of the generator gear via a mechanical transmission to the output shaft of the internal combustion engine can be connected to the load device, isolated areas, in which the base and stand arranged control panel, equipped with fire extinguishing means.

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 claimed invention is illustrated in FIG. 1-18.

датчиков температуры выхлопных газов

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 подредукторного пространства 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущего винта 62, от одной до

катушек зажигания

инжекторов

и

свечей зажигания

систему электроснабжения 66 в составе от одного до n генераторов 67₁÷67_n, блока цифрового регулятора 68, блока предохранителей 69, устройств аварийного питания 70 и разъема аэродромного питания 71, систему выхлопную 72 в составе глушителя 73 и выхлопных труб 74, устройство измерения вибрации 75, защитные экраны 76, устройство отвода отработавших газов 77 в составе гибкого трубопровода 78 и вытяжного вентилятора с электроприводом и частотным регулятором 79, систему приточно-вытяжной вентиляции 80, элементы освещения 81, от одной до k видеокамер 82₁÷82_k, пульт управления 83, оснащенный первым 84 и вторым 85 вычислительными комплексами (электронными вычислительными машинами), первой 86 и второй 87 клавиатурами, первым 88 и вторым 89 манипуляторами типа «мышь», первым 90 и вторым 91 устройствами документирования, первым 92 и вторым 93 мониторами, комплектом органов управления и индикации 94, устройством видеонаблюдения и регистрации 95, устройством индикации и регистрации 96, устройством согласования дискретных сигналов 97, средствами аварийного отключения 98, первый 99 и второй 100 каналы информационного обмена с оборудованием стенда, от одного до k каналов информационного обмена с видеокамерами 101₁÷101_k, устройство электропитания 102, состоящее из устройства бесперебойного питания 103, коммутатора 104, устройства вторичных источников питания 105, устройства преобразования интерфейсов 106 и устройства аварийного отключения 107, устройство программирования 108, средства пожаротушения 109.The device-stand for testing elements of an unmanned helicopter with coaxial screws contains the foundation of stand 1, power cage 2, clamping devices 3, mounting frame 4, fuselage frame 5, shock absorbers 6, motor frame 7, internal combustion engine 8, sub-gear frame 9, gearbox 10, output coaxial shafts 11, swash plate 12, coaxial screws 13, clutch 14, levers 15, rocker arms 16, loading device 17, piloting device with drives for controlling the swash plate 18, fuel system 19 as part of the fuel tank 20, rough filter 21, fine filters 22, first 23 and second 24 fuel pumps, fuel lines 25, fuel level sensor 26 and pressure sensor in the fuel lines 27, lubrication system 28 comprising an oil cooler 29, oil tank 30 and oil supply lines 31, water system cooling part 32 in the water radiator 33, an expansion tank 34, the overflow tank 35 and the coolant lines 36, the air cooling system 37 consisting of one to 38 m electrofans ₁ ÷ 38 _m, fire extinguishing apparatus 39, the control system dd a bolt 40 comprising a throttle actuator 41, a throttle actuator control unit 42, a starter relay 43, a starter 44, a first 45 and a second 46 air pressure sensors, a first 47 and a second 48 air temperature sensors, a first 49 and a second 50 crankshaft position sensors, from one to

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, under-gear space temperature sensor 58, temperature sensor at the inlet of the cooling radiator 59, sensor temperature at the outlet of the cooling radiator 60, the pressure sensor in the drain fuel line 61, the rotor speed sensor 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 fuse block 69, emergency power supply devices 70 and an airfield power supply connector 71, an exhaust system 72 comprising a silencer 73 and exhaust pipes 74, a vibration measuring device 75, filters 76, the exhaust gas discharge device 77 consisting of a flexible conduit 78 and the exhaust fan with electric and a frequency controller 79, a system of ventilation 80, lighting elements 81, one to cameras 82 k _{1 k} ÷ 82, pool control 83, equipped with the first 84 and second 85 computing complexes (electronic computers), the first 86 and second 87 keyboards, the first 88 and second 89 manipulators of the “mouse” type, the first 90 and second 91 documentation devices, the first 92 and second 93 monitors , a set of controls and indicators 94, a video surveillance and registration device 95, a display and registration device 96, a device for matching discrete signals 97, emergency shutdown means 98, the first 99 and second 100 channels of information exchange and with stand equipment, from one to k channels of information exchange with video cameras 101 ₁ ÷ 101 _k , a power supply device 102, consisting of an uninterruptible power supply device 103, a switch 104, a secondary power supply device 105, an interface conversion device 106 and an emergency shutdown device 107, programming device 108, fire extinguishing means 109.

,

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, 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; генератор 67₁, блок цифрового регулятора 68, блок предохранителей 69, устройства аварийного питания 70 и разъем аэродромного питания 71 из состава системы электроснабжения 66, причем генератор 67₁ механически связан с муфтой 14 и подключен через блок предохранителей 69 к устройству аварийного питания 70 и потребителям электроэнергии, размещенными на каркасе фюзеляжа 5, 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 подредукторного пространства 58, датчиком температуры на входе радиатора охлаждения 59, датчиком температуры на выходе радиатора охлаждения 60, датчиком давления в сливной топливной магистрали 61, датчиком оборотов несущего винта 62, катушками зажигания

инжекторами

из состава системы управления двигателя 40, а через четвертую группу входов-выходов - с блоком предохранителей 69, устройства аварийного питания 70 подключены через блок предохранителей 69 к потребителям электроэнергии, размещенным на каркасе фюзеляжа 5, генераторам 67₁÷67_n и разъему аэродромного питания 71, разъем аэродромного питания 71 через блок предохранителей 69 связан с потребителями электроэнергии, размещенными на каркасе фюзеляжа 5, и устройствами аварийного питания 70, генераторы 67₂÷67_n, размещенные на двигателе внутреннего сгорания 8, через блок предохранителей 69 связаны с 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

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

устройство измерения вибрации 75, по периметру фундамента стенда 1 расположены защитные экраны 76, к выхлопным трубам 74 из состава системы выхлопной 72 подведен гибкий трубопровод 78, соединенный с вытяжным вентилятором с электроприводом и частотным регулятором 79 из состава устройства отвода отработавших газов 77, помещение в котором располагается фундамент стенда 1, оборудовано системой приточно-вытяжной вентиляции 80, элементами освещения 81 и видеокамерами 82₁÷82_k, в другом изолированном помещении размещаются пульт управления 83 и устройство электропитания 102, причем к первому вычислительному комплексу 84 из состава пульта управления 83 подключены первая клавиатура 86, первый манипулятор типа «мышь» 88, первое устройство документирования 90, первый монитор 92 и через первый канал информационного обмена с оборудованием стенда 99 устройство индикации и регистрации 96, устройство пилотирования с приводами управления автоматом перекоса 18 и второй вход-выход блока цифрового регулятора 68 из состава системы электроснабжения 66, ко второму вычислительному комплексу 85 из состава пульта управления 83 подключены вторая клавиатура 87, второй манипулятор типа «мышь» 89, второе устройство документирования 91, второй монитор 93 и через второй канал информационного обмена с оборудованием стенда 100 устройство индикации и регистрации 96, устройство пилотирования с приводами управления автоматом перекоса 18 и третий вход-выход блока цифрового регулятора 68 из состава системы электроснабжения 66, к комплекту органов управления и индикации 94 из состава пульта управления 83 через устройство согласования дискретных сигналов 97 и устройство преобразования интерфейсов 106 подключен коммутатор 104 из состава устройства электропитания 102, к устройству видеонаблюдения и регистрации 95 из состава пульта управления 83 через каналы информационного обмена с видеокамерами 101₁÷101_k подключены видеокамеры 82₁÷82_k, к входам устройства бесперебойного питания 103 из состава устройства электропитания 102 подключены внешние источники электроэнергии, а к выходам - устройство вторичных источников питания 105, которое в свою очередь соединено через коммутатор 104 с потребителями электроэнергии из состава устройства-стенда, к входу устройства аварийного отключения 107 из состава устройства электропитания 102 подключены средства аварийного отключения 98 из состава пульта управления 83, а к выходу - коммутатор 104, устройство программирования 108 может подключаться к первому 84 и/или второму 85 вычислительным комплексам из состава пульта управления 83, и/или устройству преобразования интерфейсов 106 из состава устройства электропитания 102, 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 96 из состава пульта управления 83, вместо генератора 67₁ и редуктора 10 с помощью механической передачи через муфту 14 к выходному валу двигателя внутреннего сгорания 8 может подключаться нагрузочное устройство 17, изолированные помещения, в которых располагаются фундамент стенда 1 и пульт управления 83, оборудованы средствами пожаротушения 109.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 73 using the exhaust pipes 74; sub-gear frame 9 with a structure mounted thereon from a reducer 10, output coaxial shafts 11, swashplate 12, coaxial screws 13 and swashplate control drives from a piloting device with swashplate control drives 18, and the output shaft of the internal combustion engine 8 through the clutch 14, the gearbox 10 and the output coaxial shafts 11 are connected to the coaxial screws 13, and the drivers of the piloting device with the drives of the automatic swashplate 18 through the levers 15, the automatic swashplate 12 and the rocker 16 are connected to the coaxial screws 13, the control gears of the swashplate and other components of the piloting device with the control gears of the swashplate 18 are interconnected electrical and information communications; 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 ensure optimal cooling of the internal combustion engine 8, oil cooler 29 from the lubrication system 28 and water radiator 33 from the composition water cooling systems 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; a generator 67 ₁ , a digital controller block 68, a fuse box 69, emergency power supply devices 70 and an airfield power supply connector 71 from the power supply system 66, the generator 67 _{1 being} mechanically connected to the clutch 14 and connected through the fuse block 69 to the emergency power supply device 70 and consumers of electric power placed on the fuselage frame 5, the digital controller block 68 is connected to the starter relay 43, the first 45 and second 46 air pressure sensors, the first 47 and second 48 temperature sensors using the first group of inputs and outputs ry air, the first 49 and second 50 crankshaft position sensors, the 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, gearbox temperature sensor 58, temperature sensor at the inlet of the cooling radiator 59, sensor temperature 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 engine control system 40, and through the fourth group of inputs and outputs - with the fuse box 69, emergency power supply devices 70 are connected through the fuse box 69 to the electricity consumers located on the fuselage frame 5, the generators 67 ₁ ÷ 67 _n and the terminal of the airfield power 71 , the terminal of the airfield power supply 71 through the fuse block 69 is connected to power consumers located on the fuselage frame 5, and emergency power supply devices 70, generators 67 ₂ ÷ 67 _n , placed on the internal combustion engine 8, through a fuse block 69 are connected to consumers of electricity placed on the frame of the fuselage 5 and emergency power supply devices 70, the starter 44 placed on the internal combustion engine 8 is connected to the relay of the starter 43, the spark plug

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

vibration measuring device 75, protective shields 76 are located along the perimeter of the foundation of stand 1, a flexible pipe 78 is connected to the exhaust pipes 74 from the exhaust system 72 and connected to an electric exhaust fan and a frequency regulator 79 from the exhaust gas device 77, the room in which the foundation of stand 1 is located, it is equipped with a supply and exhaust ventilation system 80, lighting elements 81 and video cameras 82 ₁ ÷ 82 _k , in another isolated room there are a control panel 83 and devices about power supply 102, and the first keyboard 86, the first mouse-type manipulator 88, the first documenting device 90, the first monitor 92 and through the first channel of information exchange with the equipment of the stand 99 are connected to the first computer complex 84 from the control panel 83 96, a piloting device with control drives of the swashplate 18 and a second input-output of the digital controller block 68 from the power supply system 66, to the second computer complex 85 from the remote control 83, a second keyboard 87, a second mouse-type manipulator 89, a second documenting device 91, a second monitor 93, and an indication and recording device 96, a piloting device with swashplate control drives 18, and a third input are connected through a second information exchange channel with the equipment of the stand 100 - the output of the digital controller unit 68 from the power supply system 66, to the set of control and display elements 94 from the control panel 83 through the discrete signal matching device 97 and the device eobrazovaniya interfaces 106 connected to the switch 104 from the power supply device 102, the device surveillance and registration 95 from the 83 control unit via the traffic channels with cameras 101 ₁ ÷ 101 _k connected video cameras 82 ₁ ÷ 82 _k, to the inputs of an uninterruptible power supply 103 from the device power supply devices 102 are connected to external power sources, and to the outputs is a secondary power supply device 105, which, in turn, is connected through a switch 104 to consumers of electricity from Ava device stand, to the input of the emergency shutdown device 107 from the power supply device 102 are connected emergency shutdown means 98 from the control panel 83, and to the output is the switch 104, the programming device 108 can be connected to the first 84 and / or second 85 computing complexes from the composition of the control panel 83, and / or the interface conversion device 106 from the power supply device 102, and / or the piloting device with the control drives of the swashplate 18, and / or the digital controller unit 68 from the power supply system 66, and / or an indication and registration device 96 from the control panel 83, instead of the generator 67 ₁ and the gearbox 10, by means of a mechanical transmission through the clutch 14, a load device 17 can be connected to the output shaft of the internal combustion engine 8, isolated rooms , which are the foundation of the stand 1 and the control panel 83, equipped with fire extinguishing means 109.

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 103 through the secondary power supply device 105 and the switch 104 from the power supply device 102, the operating voltage is supplied to the electricity consumers from the control panel 83. The secondary power supply device 105 provides the conversion of primary electricity (AC voltage current) coming from external sources of electric power into the voltage of direct and alternating current with characteristic and necessary to ensure the health of consumers of electricity from the stand composition. The switch 104 performs switching - closing / opening of the electric power transmission circuits from the secondary power supply device 105 to the electric consumers from the stand by commands from the interface conversion device 106 and emergency shutdown device 107. Moreover, the commands from the interface conversion device 106 are used to control the chains that are in the initial position are open, and from the emergency power device - closed.

When power is supplied through the closed circuits of the switch 104 to the first 84 and second 85 computing systems, the first 90 and second 91 documentation devices, the first 92 and second 93 monitors, a video surveillance and registration device 95, an indication and registration device 96 from the control panel 83, initialization preinstalled software on them. At the same time carried out:

a) automatic testing and preparation for operation of hardware and software of the control panel 83:

- the first 84 and second 85 computing complexes, the first 86 and second 87 keyboards, the first 88 and second 89 manipulators of the “mouse” type, the first 90 and second 91 documentation devices, the first 92 and second 93 monitors;

- video surveillance and registration devices 95;

- indicating and recording devices 96;

b) under the control of functional or system software of the first 84 and second 85 computing complexes, automatic testing of the first 99 and second 100 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 84 and second 85 computing complexes on the first 92 and second 93 monitors, respectively;

- on the display elements of the information from the video surveillance and registration device 95 and the display and registration device 96;

d) automatic or at the command of the operators (in the “operator-computer complex” dialogue mode using the first 86 and second 87 keyboards or the first 88 and second 89 manipulators of the “mouse” type) paper-based documentation of the results of initialization of functional software using the first 90 and a second 91 documentation devices.

When power is supplied through the closed circuits of the switch 104 to the cameras 82 ₁ ÷ 82 _k through the channels of information exchange with the cameras 101 ₁ ÷ 101 _k to the video surveillance and registration device 95, video information about the state of the elements of the stand located in an isolated room where the foundation of the stand 1 is located The video surveillance and registration device 95 after initialization of the preinstalled software provides reception, storage and display of the received information with reference to the astrono scale matic time constant in all subsequent stages of the device.

The indicator and registration device 96 after initializing the pre-installed software and testing the first 99 and second 100 channels of information exchange with the equipment of the stand provides reception, storage and display of information received through the first 99 and second 100 channels of information exchange with the equipment of the stand, with reference to the astronomical scale time continuously at all subsequent stages of the device.

When power is supplied through the closed circuits of the switch 104 to the set of control and indication bodies 94 and emergency shutdown means 98, preparations are made for the operation of command transmission chains in the “operator-switch” dialogue mode:

- from a set of controls and indications 94 through a device for matching discrete signals 97 and a device for converting interfaces 106 to a switch 104;

- from the emergency shutdown means 98 through the emergency shutdown device 107 to the switch 104.

Information about the state of the electrical circuits of the switch 104 through the interface conversion device 106 and the discrete signal matching device 97 is transmitted to the set of control and indication bodies 94, 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 105 through closed circuits of the switch 104 and the terminal of the airfield power supply 71 to the fuse block 69 of the power supply system 66.

Main stage

The preparatory phase of the device is completed.

In accordance with the methods and algorithms of operation of the device, sequentially or in parallel for the first 84 and second 85 computing complexes from the control panel 83, automatically, under the control of functional software, or manually by operators, in the dialog “operator-computer complex” using the first 86 and the second 87 keyboards, the first 88 and second 89 manipulators of the “mouse” type, a set of controls and indicators 94, are sequentially implemented:

- inclusion of lighting elements 81;

- inclusion of a system of supply and exhaust ventilation 80;

- inclusion of an exhaust gas device 77;

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

- starting and operation of the internal combustion engine 8;

- promotion of coaxial screws 13;

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

- stop the internal combustion engine 8;

- bringing the elements of the device to its original state.

At the same time, the operation of the device is:

- signal transceiver between the first computing complex 84 and the digital controller 68 and / or the second computing complex 85 and the digital controller 68, respectively, through the first 99 and second 100 communication channels with the equipment of the stand;

- operators that act on the buttons and switches from the set of controls and indications 94. In this case, the circuit / disconnection of the electrical circuits that transmit the input DC voltage supplied through the closed circuit of the switch 104 to the set of controls and indications 94, then on discrete signal matching device 97. Discrete signal matching device 97, in turn, converts the signals coming from the set of controls and indications 94 into a follower the code that is transmitted to the interface conversion device 106, where the signals are converted back from the serial code to discrete signals — DC voltage and then transferred to the switch 104. The switch 104, using the signals from the device, the interface conversion 106 closes / opens the electric power transmission circuits from the device of secondary power sources 105 to consumers of electricity from the stand, thereby forming the necessary control actions on the elements of the device oystva.

The inclusion of lighting elements 81 is performed according to a command formed manually by operators. When a control action is received from the output of the switch 104 to the lighting elements 81 in isolated rooms where the foundation of stand 1 and the operator panel 83 are located, the light comes on. In the future, the light is constantly on at all subsequent stages of the operation of the device and turns off during the bringing of the elements of the device to its original state.

The inclusion of the supply and exhaust ventilation system 80 is performed according to a command formed manually by operators. Upon receipt of the control action from the output of the switch 104 to the supply and exhaust ventilation system 80 in an isolated room where the stand of the bench 1 is located, the forced supply and exhaust ventilation system 80 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 air supply and forced air removal are provided continuously at all subsequent stages of the operation of the device and cease during ementov device to its original state.

The activation of the exhaust gas removal device 77 is performed by a command manually generated by the operators. Upon receipt of the control action from the output of the switch 104 to an exhaust fan with an electric drive and a frequency regulator 79 through a flexible conduit 78, a forced exhaust gas is provided from the exhaust pipes 74 from the exhaust system 72 when the internal combustion engine is running 8. In the future, forced exhaust gas is always provided for all subsequent stages of operation of the device and stops during the bringing of the elements of the device to its original state.

Pre-start control of the device elements is performed according to the commands generated by the first 84 and / or second 85 computing complexes, 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 fuse block 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 подредукторного пространства 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущего винта 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, under-gear space temperature sensor 58, temperature sensor at the inlet of the cooling radiator 59, sensor the temperature 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 подредукторного пространства 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущего винта 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, under-gear space temperature sensor 58, temperature sensor at the inlet of the cooling radiator 59, sensor temperature 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 a recognition is generated in the block of the digital controller 68 successful completion of the test the engine control system 40, otherwise formed sign of the presence of failure of the engine control system 40;

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

- a self-test of the pilot device with the swashplate control drives is performed 18. If the self-test is successful, a message about the readiness of the device for operation is transmitted to the digital controller 68 from the pilot device with the swashplate control drives 18, otherwise a sign of a failure in the piloting device with the drives control swashplate 18;

- 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 block of the digital controller 68, the analog signals from the fuse block 69 and generated by the emergency power supply devices 70 are measured to the fourth group of inputs and outputs by the digital controller 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 is considered completed successfully if in the block of the digital controller 68 there are no signs of failures in the tested systems and devices, which allows you to start starting the internal combustion engine 8.

Starting the internal combustion engine 8 is carried out by a command that is generated by means of the first 84 or second 85 computing complexes and transmitted respectively through the first channel of information exchange with equipment of stand 99 to the second input-output of the block of digital controller 68 or through the second channel of information exchange with equipment of stand 100 to the third input-output of the block of the digital controller 68. The block of the digital controller 68, after receiving a start command, performs cyclograms of starting and operating the internal combustion engine 8, which 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 подредукторного пространства 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущего винта 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, under-gear space temperature sensor 58, temperature sensor at the inlet of the cooling radiator 59, sensor the temperature 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 the signals of the fuse block 69.

Wherein:

- 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 oil radiator 29 and a water radiator 33;

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

- exhaust gases through a muffler 73, exhaust pipes 74, a flexible pipe 78 and an exhaust fan with an electric drive and a frequency controller 79 are removed from the room where the foundation of stand 1 is located;

- atmospheric air through the supply and exhaust ventilation system 80 is supplied to the room where the foundation of stand 1 is located;

- information about the operation of the piloting device with the control drives of the swashplate 18, 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 72 through the first 99 and second 100 channels information exchange with the equipment of the stand is transmitted to the indicating and recording device 96, where it is displayed, is recorded in a long-term memory and stored;

- information about the operation of the piloting device with the control drives of the swashplate 18, 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 72 through the first 99 and second 100 channels information exchange with the equipment of the stand is transferred respectively to the first 84 and second 85 computing complexes, where it is recorded in long-term memory, stored, processed, transmitted to the display, respectively on the first 92 and second 93 monitors, transferring to documentation on the first 90 and second 91 documentation devices.

When the engine output shaft speed exceeds a certain value, it is connected using the coupling 14 of the internal combustion engine 8 to the gearbox 10. The gearbox 10 transfers the rotation from the output shaft of the internal combustion engine 8 through the output coaxial shafts 11 to the coaxial screws 13. The coaxial screws 13 begin to rotate . From the clutch 14 through a mechanical connection provides the rotation of the generator 67 ₁ . Electricity from the output of the generator 67 ₁ is supplied to the fuse block 69 and then to electricity consumers placed on the fuselage frame 5.

If instead of a generator 67 ₁ and a gearbox 10 a load device 17 is installed, then when the engine output shaft speed exceeds a certain value, a connection is made via the clutch 14 of the internal combustion engine 8 to the load device 17. Transmission of rotation is provided via a mechanical transmission (for example, belt) from the output shaft of the internal combustion engine 8 to the load device 17. The load device 17 performs a power take-off from the internal combustion engine 8, thereby simulating the load on the engine created by coaxial screws 13 and / or generator 67 ₁ .

Ground-stand autonomous or complex tests of the elements of an unmanned helicopter with coaxial propellers are carried out according to the commands that are generated by the first 84 and / or second 85 computing systems and transmitted respectively through the first channel of information exchange with the equipment of stand 99 to the second input-output of the digital controller unit 68 and a piloting device with control drives of the swashplate 18 and / or through the second channel of information exchange with the equipment of the stand 100 to the third input-output unit Frova controller 68 and the piloting unit with automatic control actuators 18 skew.

The digital controller block 68, after receiving the commands, by means of the pre-installed functional software implements the simulation of various operating modes of an unmanned helicopter 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 подредукторного пространства 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущего винта 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, under-gear space temperature sensor 58, temperature sensor at the inlet of the cooling radiator 59, sensor the temperature 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 the signals of the fuse block 69.

If a gearbox 10 is connected via a clutch 14 to the output shaft of the internal combustion engine 8, then the pilot device with the swashplate control drives 18 using the pre-installed functional software imitates various operating conditions of the unmanned helicopter carrier system with coaxial screws by controlling the position of the coaxial screws 13 by changing the position swashplate 12, levers 15, rocker 16.

If a load device 17 is connected through a clutch 14 to the output shaft of the internal combustion engine 8, then the load device 17 provides a simulation of various operating conditions of the carrier system of an unmanned helicopter with coaxial screws using an adjustable power take-off from the internal combustion engine 8.

Wherein:

- internal combustion engine 8, fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 72, exhaust gas removal device 77, supply and exhaust ventilation system 80 continue function in the same way as when starting up and ensuring the operation of the internal combustion engine 8;

- information about the operation of the piloting device with the control drives of the swashplate 18, 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 72 through the first 99 and second 100 channels information exchange with the equipment of the stand is transmitted to the indicating and recording device 96, where it is displayed, is recorded in a long-term memory and stored;

- information about the operation of the piloting device with the control drives of the swashplate 18, 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 72 through the first 99 and second 100 channels information exchange with the equipment of the stand is transferred respectively to the first 84 and second 85 computing complexes, where it is recorded in long-term memory, stored, processed, transmitted to the display, respectively on the first 92 and second 93 monitors, transferring to documentation on the first 90 and second 91 documentation devices.

The stop of the internal combustion engine 8 is carried out by a command that is generated by means of the first 84 or second 85 computer systems and is transmitted respectively through the first channel of information exchange with equipment of stand 99 to the second input-output of the block of digital controller 68 or through the second channel of information exchange with equipment of stand 100 to the third input-output of the digital controller 68. The digital controller 68 after receiving a command by means of pre-installed functional software function provides a realization cyclogram stop 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 подредукторного пространства 58, датчика температуры на входе радиатора охлаждения 59, датчика температуры на выходе радиатора охлаждения 60, датчика давления в сливной топливной магистрали 61, датчика оборотов несущего винта 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, under-gear space temperature sensor 58, temperature sensor at the inlet of the cooling radiator 59, sensor the temperature 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 the signals of the fuse block 69.

Wherein:

- internal combustion engine 8, fuel system 19, lubrication system 28, water cooling system 32, air cooling system 37, engine control system 40, power supply system 66, exhaust system 72, exhaust gas removal device 77, supply and exhaust ventilation system 80 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 72 through the first 99 and second 100 channels of information exchange with the equipment of the stand is transmitted to the display device and registration 96, where it is displayed, is recorded in 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 72 through the first 99 and second 100 channels of information exchange with the equipment of the stand is transmitted respectively to the first 84 and second 85 computing complexes, where it is recorded in long-term memory, are stored, processed, transferred to the display for the first 92 and second 93 monitors, respectively, and transferred for documentation to the first 90 and second 91 documentation 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 77 is turned off. Forced exhaust gases from the exhaust pipes 74 from the exhaust system 72 are stopped;

- by a command formed manually by operators, the supply and exhaust ventilation system 80 is turned off. Forced air supply and forced air removal in the isolated room where the foundation of stand 1 is located are stopped;

- by a command formed manually by the operators, the lighting elements 81 are turned off. The light in the isolated rooms where the foundation of stand 1 and the operator panel 83 are located is turned off.

During the main phase of the device:

- indication of the content and results of the functional software of the first 84 and second 85 computing complexes is carried out respectively on the first 92 and second 93 monitors from the control panel 83;

- documenting on paper the contents and results of the functional software of the first 84 and second 85 computing complexes is carried out respectively using the first 90 and second 91 documenting devices from the control panel 83;

- vibration measurement of the constituent elements of the device located on the frame of the fuselage 5, is carried out using a vibration measuring device 75.

Emergency phase

At the preparatory and main stages when detecting signs of abnormal work that adversely affect the safety of operation of the device:

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

b) the functional software of the first 84 and / or second 85 computing systems from the control panel 83 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 dialogue “operator - computer complex” using the first 86 and second 87 keyboards, the first 88 and second 89 manipulators of the mouse type, set of controls and indicators 94, actions are taken to stop the internal combustion engine 8 and bring elements of the device to its original state in the amount provided for at the main stage of the device;

d) the operators by means of an emergency shutdown 98 give a command for an emergency power off of the device through the emergency shutdown device 107 to the switch 104, which opens the electrical circuits for supplying power to consumers of electricity from the device;

e) the operators or the stand’s personnel extinguish the fire using fire extinguishing means 109;

e) the uninterruptible power supply device 103 is supplied with electric energy to the stand in the absence of power from external sources of electricity;

g) fuse block 69 disables faulty sources of electric power: generators 67 ₁ ÷ 67 _n , emergency power supply devices 70, airfield power supply connectors 71 from electric power consumers located on the fuselage frame;

h) the fuse block 69 disconnects the faulty consumers of electric power placed on the fuselage frame from electric power sources: generators 67 ₁ ÷ 67 _n , emergency power supply devices 70, airfield power supply connector 71.

At all stages of the operation of the device, the protection of the operators or stand personnel from accidental or emergency expansion of the device elements located on the fuselage frame 5 is provided by protective screens 76.

To perform fault diagnostics, update functional software and copy information to the first 84 and / or second 85 computer systems from the control panel 83, and / or the interface conversion device 106 from the power supply device 102, and / or the pilot device with automatic control drives skew 18, and / or the block of the digital controller 68 from the power supply system 66, and / or the display and registration device 96 from the control panel 83 can connect devices about programming 108.

This device compared with the prototype allows you to:

- to carry out autonomous and comprehensive tests of the elements of the power plant (fuel system, lubrication system, water cooling system, air cooling system, engine control system), power supply system and the pilot complex of an unmanned helicopter with coaxial screws, which extends the functionality of the device;

- 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, which increases the safety of the device.

The use of the invention in aviation test equipment allows to reduce the time and cost of ground-bench tests of an unmanned helicopter with coaxial screws, due to the lack of the need to create and operate separate device-stands to ensure autonomous testing of each component of the helicopter. 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)

Test bench for elements of an unmanned helicopter with coaxial screws, containing the stand base, power frame, clamping devices, mounting frame, fuselage frame, shock absorbers, engine mount, internal combustion engine, under gear frame, gearbox, output coaxial shafts, skew automatic machine, coaxial screws, clutch , levers, rocker arms and load device, characterized in that it additionally introduces a piloting device with drives for controlling the swash plate, a fuel system in the fuel tank, a filter coarse filters, fine filters, two 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, air cooling system as part of electric fans, fire extinguishing device, engine control system as part of a throttle actuator, throttle actuator control unit, starter relay, starter, two air pressure sensors, two air temperature sensors, two crankshaft position sensors, at least one exhaust temperature sensor, coolant temperature sensor, oil temperature sensor, oil pressure sensor, pressure sensor and air temperature at the engine inlet, damper position sensor, knock sensor, sub gearbox temperature sensor, cooling radiator inlet temperature sensor, dates temperature range at the outlet of the cooling radiator, pressure sensor in the drain fuel line, rotor speed sensor, at least one ignition coil, injectors and spark plugs in an amount two times the number of ignition coils, power supply system comprising at least one generator , digital regulator unit, fuse box, emergency power supply devices and airfield power supply connector, exhaust system consisting of a muffler and exhaust pipes, vibration measuring device, for shield screens, an exhaust gas device as part of a flexible pipe and an exhaust fan with an electric drive and a frequency controller, a supply and exhaust ventilation system, lighting elements, at least one video camera, a control panel equipped with two computer systems, two keyboards, two manipulators of the type mouse ", two documentation devices, two monitors, a set of controls and indicators, a video surveillance and registration device, a display and registration device , a device for matching discrete signals, emergency shutdown means, two channels of information exchange with the equipment of the stand, channels of information exchange with cameras, in the amount corresponding to the number of cameras, a power supply device consisting of an uninterruptible power supply device, a switch, a secondary power supply device, an interface conversion device and emergency shutdown devices, programming device, fire extinguishing means, while the stand foundation is presented It consists of a monolithic reinforced concrete slab with a metal power frame, on which the mounting frame is fixed with clamping devices, and the fuselage frame is rigidly attached to it with bolts, which, in turn, are mounted on it: on the shock absorbers of the engine mount with the internal combustion engine installed on it, moreover, the internal combustion engine is connected to the muffler using exhaust pipes; sub-gear frame with a structure mounted on it from a gearbox, output coaxial shafts, swashplate, coaxial screws and swashplate control drives from a piloting device with swashplate control drives, and the output shaft of the internal combustion engine through a coupling, gearbox and output coaxial shafts connected to coaxial screws, and the pilot device drives with control gears of the swash plate through levers, the swash plate and rocker arms are connected to the coaxial screws, the control drives are Omata skew and other constituent elements of the piloting device swashplate control actuators are electrically interconnected and informational communications; on the shock absorbers, the fuel tank and other elements of the fuel system: coarse filter, fine filters, fuel pumps from the fuel system, and the fuel tank with the fuel level sensor installed in it, using the fuel lines, with the pressure sensor in the fuel lines connected coarse filter, fine filters, fuel pumps connected to injectors from the engine control system, 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, an overflow tank from the composition of the water cooling system using the coolant supply lines are connected to the internal combustion engine; electric fans from the air cooling system, and the electric fans are placed on the fuselage frame so as to provide optimal cooling of the internal combustion engine, the oil radiator from the lubrication system and the 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; one generator, a digital regulator block, a fuse block, emergency power supply devices and an aerodrome power connector from the power supply system, the generator being mechanically connected to the clutch and connected through the fuse block to the emergency power device and electric consumers placed on the fuselage frame, the digital controller block with using the first group of inputs and outputs connected to the starter relay, air pressure sensors, air temperature sensors, crankshaft position sensors, sensors exhaust gas temperature, 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, radiator outlet temperature sensor cooling, pressure sensor in the drain fuel line, rotor speed sensor, ignition coils, injectors from the control system for a needle, and through the fourth group of inputs and outputs - with a fuse box, emergency power devices are connected through a fuse box to power consumers located on the fuselage frame, generators and an aerodrome power connector, the terminal of the airfield power supply is connected to power consumers located on the frame through a fuse box fuselage and emergency power devices, generators placed on an internal combustion engine, through a fuse box connected to consumers of electric power WGIG placed on the frame of the fuselage, and the emergency power supply device, starter, arranged on the internal combustion engine, the starter relay is connected to the spark plugs, arranged in pairs on an internal combustion engine connected to the respective ignition coils; vibration measuring device, protective screens are located around the perimeter of the stand foundation, 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 and exhaust system - exhaust ventilation, lighting system and video cameras, in another isolated room are the control panel and power supply, and to Each computer complex from the control panel includes a keyboard, a mouse-type manipulator, a documenting device, a monitor, and through an information exchange channel with the equipment of the stand, an indication and registration device, a piloting device with swashplate control drives and a digital controller unit from the power supply system, to a set of controls and displays from the control panel through a device for matching discrete signals and a device for converting inter A switch is connected from the power supply device, a video surveillance device and a registration device from the control panel are connected via video exchange channels with video cameras, external power sources are connected to the inputs of the uninterruptible power supply from the power supply device, and a secondary power supply device is connected to the outputs, which , in turn, is connected through a switch with consumers of electricity from the device - stand, to the input of the emergency about disconnection from the power supply device, emergency shutdown means from the control panel are connected, and a switch is connected to the output, the programming device can be connected to computer complexes from the control panel, and / or interface conversion device from the power supply device, and / or the pilot device with drives for controlling the swashplate, and / or the digital controller unit from the power supply system, and / or the display and registration device from the console control, instead of a generator and a reducer, by means of a mechanical transmission, a load device can be connected to the output shaft of the internal combustion engine, the isolated rooms in which the stand base and control panel are located are equipped with fire extinguishing means.

Images