RU2353788C1 - Electronic system of automatic control of ramjet - Google Patents

Abstract

FIELD: engines and pumps.

SUBSTANCE: invention is related to the field of fuel supply control in ramjets. System comprises ramjet, hopper, the first and second electronic control channels, selector, measurer of air temperature downstream normal shock (T*), measurer of full pressure downstream normal shock (Po), measurer of static pressure downstream the first oblique shock (Psh), measurer of hopping needle position, multiplier-divider devices (MDD), comparison unit, unit of dynamic correction, pulse-length modulator (PLM), comparators, unit of time delay, control unit and data exchange bus.

EFFECT: increased accuracy of control, operation reliability and expansion of functional and performance properties.

1 dwg

Description

The invention relates to the field of regulation of the fuel supply in ramjet engines (ramjet).

Known electronic-hydraulic control system for supplying fuel to the ramjet combustion chamber (UK patent No. 2007305, MKI F02K 7/10), consisting of hydromechanical and electronic control units.

The hydromechanical unit contains fuel flow metering devices in the primary and main collectors, a constant differential valve on the primary collector metering device, a constant differential regulator on the main collector metering device, containing a sensing element characterizing fuel consumption through the main collector.

The electronic unit provides the correction of fuel consumption through the main collector in proportion to the electrical control signal of the electrohydraulic converter.

The disadvantages of this system are the increased start-up time of the engine and the limited limits of the correction of fuel consumption by the signal of the electrohydraulic converter.

A known system for automatic control of an air-jet engine (IPC 7 F02C 9/26, RF patent No. 2209990, publ. 08/10/2003).

The system contains dispensers connected through levers with feedback springs with elastic elements characterizing the air flow through the engine. One elastic element is made in the form of a vacuum bellows located in the air cavity, where the pressure is supplied behind the direct shock wave in the diffuser of the air intake, and the other elastic element is in the form of a spring connecting the dispenser with the dispenser lever through the carriage. The fuel consumption corrector is connected to the dispenser and is made in the form of a static servomotor, the control cavity of which is connected to a low-current electro-hydraulic converter, which is connected to the aircraft calculator.

The disadvantages of this system are the lack of consideration of the effect of air temperature behind the direct shock wave and the lack of pressure control behind the first oblique shock wave.

The closest prototype is an electronic hydromechanical system for regulating the supply of fuel to a gas turbine engine (IPC F02C 9/00 1090083, bull. No. 3, publ. 01.27.96).

This system contains a metering device for supplying fuel to a gas turbine engine, a hydromechanical regulator, at least two electronic control channels, an electronic channel monitoring device, an electronic selector, an electro-hydraulic switch, AND logic circuits, electronic keys and a hydraulic selector.

The disadvantages of this system are insufficient regulation accuracy and reliability, limited functional and operational capabilities.

The task of the invention is to increase the accuracy of regulation, reliability and the expansion of functional and operational capabilities.

The problem is solved in that in the electronic automatic control system of a ramjet engine containing a dispenser, a first and second electronic control channels and a selector, a temperature meter behind a direct jump (T *), a total pressure meter behind a direct jump (Po) are introduced , a static pressure meter behind the first oblique jump (Rsk), a metering needle position meter, the first, second, third, fourth and fifth multiplier-dividing devices, a comparison unit, a dynamic unit correction, pulse-width modulator, first, second and third comparators, time delay unit, control unit, data exchange bus with on-board control equipment, while the outputs of the electronic channels are connected respectively to the first inputs of the first and second multiplier divider devices, the outputs of the meter the air temperature behind the direct jump and the static pressure meter behind the first oblique jump are connected to the first inputs of the third and fourth multiplier dividing devices, and the output of the full phenomena after a direct jump - with the first input of the fifth multiplier divider and the second input of the fourth multiplier divider, the output of which is connected to the second input of the third multiplier divider, the output of which is connected to the second inputs of the first and second multiplier divider connected to the inputs of the selector, the output of the selector is connected to the first input of the comparison unit and the first input of the first comparator, the second input of which is connected to the output of the fifth multiplier the device and the second input of the comparison unit, the output of which through the dynamic correction unit and pulse-width modulator is connected to the first input of the dispenser, the second input of which is connected to the output of the first comparator, the first output of the dispenser is connected to the motor, and the second to the meter of the position of the metering needle, the output of which is connected to the second input of the fifth multiplier divider, to the first input of the second comparator and to the input of the third comparator, the output of which is connected to the third input of the dispenser and through time delay lock - with the second input of the second comparator, the output of which is connected to the second additional input of the second electronic control channel, in addition, the inputs of the control unit are connected to the outputs of the first multiplier-divider device, selector, second multiplier-divider device, air temperature meter behind a direct jump , fifth multiplier dividing device, third comparator, metering position of the metering needle, the first comparator and pulse-width modulator, the first output the control unit is connected to the additional first inputs of the electronic control channels and the air temperature meter behind a direct jump, as well as to the additional input of the metering position of the metering needle, the second output is connected to the second additional input of the first electronic control channel, the second additional input of the air temperature meter behind the direct jump and an additional input of the fifth multiplier dividing device, while the additional output of the control unit is connected to the data exchange bus with on-board monitoring equipment.

The drawing shows a functional diagram of the inventive electronic system for automatic control of a ramjet engine. The device contains a ramjet 6, a dispenser 8, the first and second electronic control channels 1, 2, a selector 14, a temperature meter behind a direct jump 3 (T *), a total pressure meter behind a direct jump 5 (Po), a static meter pressure behind the first oblique jump 4 (Rsk), metering position of the metering needle 7, multiplier divider 9, 10, 11, 12 and 13 (MDU), comparison unit 15, dynamic correction unit 16, pulse-width modulator 17 (PWM) , comparators 18, 19, 20, time delay block 21, con Rola 22 and bus 23, data exchange.

The outputs of the electronic channels 1, 2 are connected to the first inputs of the MDU 9, 10, respectively, the outputs of the air temperature meter behind the direct jump 3 and the static pressure meter behind the first oblique jump 4 are connected to the first inputs of the MDU 11, 12, and the output of the total pressure meter is direct jump 5 - with the first input of the MDA 13 and the second input of the MDA 12, the output of which is connected to the second input of the MDA 11, the output of which is connected to the second inputs of the MDA 9, 10, the outputs of which are connected to the inputs of the selector 14, the output of which is connected to the first input of the comparison unit 15 and the first input of the comparator 18, the second input of which is connected to the output of the MDU 13 and the second input of the comparison unit 15, the output of which through the dynamic correction unit 16 and the PWM 17 is connected to the first input of the dispenser 8, the second input of which is connected to the output of the comparator 18, the first output of the dispenser 8 connected to the engine 6, and the second to the meter of the position of the metering needle 7, the output of which is connected to the second input of the MDU 13, with the first input of the comparator 19 and with the input of the comparator 20, the output of which is connected to the third input of the dispenser 8 and through the time delay unit 21 - with the second input of the comparator 19, the output of which is connected to an additional input of the electronic control channel 2, in addition, the inputs of the control unit 22 are connected to the outputs of the MDU 9, selector 14, MDU 10, air temperature meter behind the direct jump 3, MDU 13, comparator 20 , the position meter of the metering needle 7, the comparator 18 and the PWM 17, the first output of the control unit 22 is connected to the first additional inputs of the electronic control channels 1, 2, the air temperature meter behind the direct jump 3 and with an additional input of the position meter dosing needle 7, the second output - with the second additional input of the first electronic control channel 1, the second additional input of the air temperature meter behind the direct jump 3 and the additional input of the MDU 13, and the information output is connected to the data exchange bus 23 with the on-board control equipment.

The system operates as follows.

The control signals n _α (n _α is the coefficient of control of fuel consumption by excess air) and n _π (n _π is the coefficient of control of fuel consumption by surplus) are received from the aircraft to electronic control channels 1 and 2, respectively, at the outputs of which signals K ₁ · N _α and K ₂ · n _π (hereinafter, K ₁ ... K ₁₃ are constant proportionality coefficients), and they are limited in the given ranges, the air temperature signals for respectively enter the inputs of meters 3, 4, 5 from the air intake of engine 6 direct jump m (T *), the static pressure of the first oblique shock RNC and the total pressure of the direct shock P _o and on meter 7 - position signal of the metering needle of the metering device 8, which is proportional to the actual fuel consumption Gtf, and outputs meters 3, 4, 5 , 7 signals are formed accordingly:

K ₃ · T *, K ₄ · P _SK , K ₅ · P ₀ and K ₇ · G _TF .

Multiplier dividing devices (MDUs) 9, 10, 11, 12, 13 process the input signals, resulting in the formation of output signals:

;- at the output of the MDU 13 -

;

;- at the output of the MDU 12 -

;

;- at the output of the MDU 11 -

;

;- at the output of the MDU 10 -

;

;- at the output of the MDU 9 -

;

или

, пропорциональный заданному значению расхода топлива G_Тзад.where G _Tfakt and G _Tzad ^{- the} actual and target values of fuel consumption. Depending on the operating modes of the aircraft and the engine, one of the signals arrives at the output of the selector 14 and at one of the inputs of the comparison unit 15

or

proportional to the set value of fuel consumption G _Tzad .

с выхода МДУ 13 - пропорциональный фактическому расходу топлива, а на его выходе формируется сигнал рассогласования, который, проходя через блок динамической коррекции 16 и ШИМ 17, поступает на первый вход дозирующего устройства 8, которое перемещением дозирующей иглы устанавливает G_ТФ=G_Тзад, в результате чего сигнал рассогласования на выходе блока сравнения 15 становится равным нулю при новом расходе топлива.The second input of the comparison unit 15 receives a signal

from the output of the MDA 13 is proportional to the actual fuel consumption, and at its output a mismatch signal is generated, which, passing through the dynamic correction unit 16 and the PWM 17, is fed to the first input of the metering device 8, which sets G _TF = G _{Tzad by} moving the metering needle, as a result, the error signal at the output of the comparison unit 15 becomes equal to zero at a new fuel consumption.

With large discrepancies in the output signals of the selector 14 and the MDU 9, the comparator 18 is activated and the actuator for accelerating the movement of the metering needle is turned on through the second input of the dispenser 8.

At the first set value of fuel consumption, determined by the output voltage of the meter 7, the comparator 19 is activated and changes the signal at the output of the electronic channel 2, which leads to a change in the engine operating mode, and when the comparator 20 is activated after a time determined by the delay link 21, the signal from the output of the comparator 19 is removed.

When triggering and releasing the comparator 20 in the dispenser, an additional manifold for supplying fuel to the engine is turned on or off.

The control unit 22 performs pre-flight control of this electronic system for regulating the fuel supply to the ramjet engine and provides this information through communication via the data exchange bus 23 with the on-board control equipment.

The proposed control system makes it possible to take into account the influence on the engine operation of the air temperature behind the direct jump (T *), the total pressure behind the direct jump (Po) and the static pressure behind the first oblique jump (Rsk), shorten the start-up time and expand the limits of the ramjet fuel consumption correction. In addition, the control unit allows you to obtain information about the operation of the electronic control system in pre-flight mode.

All this increases the accuracy of regulation and reliability, expands the functional and operational capabilities.

The economic effect of using the invention is achieved due to the fact that the production of the device does not require the creation of special equipment and can be performed on the basis of commercially available items.

Claims (1)

An electronic control system for a ramjet engine containing a dispenser, first and second electronic control channels, a selector, characterized in that a temperature meter for a direct jump, a full pressure meter for a direct jump, a static pressure meter for a first oblique jump are introduced into it , metering position of the metering needle, first, second, third, fourth and fifth multiplier dividing devices, comparison unit, dynamic correction unit, latitude-imp pulse modulator, first, second and third comparators, time delay unit, control unit and data bus with on-board control equipment, while the outputs of the electronic channels are connected respectively to the first inputs of the first and second multiplier dividing devices, the outputs of the air temperature meter are behind a direct jump and the static pressure meter behind the first oblique jump are connected respectively to the first inputs of the third and fourth multiplier-dividing devices, and the output of the total pressure meter is and with a direct jump, with the first input of the fifth multiplier and divider and the second input of the fourth multiplier and divider, the output of which is connected to the second input of the third multiplier and divider, the output of which is connected with the second inputs of the first and second multiplier, the outputs of which are connected with selector inputs, the selector output is connected to the first input of the comparison unit and the first input of the first comparator, the second input of which is connected to the output of the fifth multiplier-divisor device and the second input of the comparison unit, the output of which through the dynamic correction unit and pulse-width modulator is connected to the first input of the dispenser, the second input of which is connected to the output of the first comparator, the first output of the dispenser is connected to the motor, and the second to the meter of the position of the metering needle, the output which is connected to the second input of the fifth multiplier divider, to the first input of the second comparator and to the input of the third comparator, the output of which is connected to the third input of the dispenser and through a block of times oh delay - with the second input of the second comparator, the output of which is connected to an additional second input of the second electronic control channel, in addition, the inputs of the control unit are connected to the outputs of the first multiplier-dividing device, selector, second multiplier-dividing device, air temperature meter behind a direct jump, fifth multiplier divider, third comparator, metering position of the metering needle, the first comparator and pulse-width modulator, the first output of the counter For is connected to the additional first inputs of the electronic control channels and the air temperature meter behind a direct jump, as well as to the additional input of the metering needle position, the second output is connected to the second additional input of the first electronic control channel, the second additional input of the air temperature meter behind the direct jump and additional the input of the fifth multiplier dividing device, while the additional output of the control unit is connected to the data bus with the onboard control equipment.