RU155826U1 - METHOD SENSOR FOR AERODYNAMIC ANGLE AND TRUE AIR SPEED - Google Patents

Abstract

Label sensor for the aerodynamic angle and true airspeed of the aircraft, containing an ionic tag generator, an ionic tag registration channel in the form of a system of receiving electrodes located in a circle centered at the ionic tag generation point, and a pre-amplifier unit, a measuring circuit in the form of a working sector determination channel being a coarse reference channel, a channel for accurate measurement of the angle in the working sector, and a true airspeed channel connected to the input of the computing device, the passages of which are digital outputs along the aerodynamic angle and true airspeed, characterized in that the ion mark generator is made in the form of a sawtooth voltage generator supplied to the spark gap, the discharge circuit of which includes a circuit for detecting the moment of spark breakdown of the interelectrode gap of the spark gap, the output of which is connected to the control input of the voltage measurement circuit at the output of the sawtooth voltage generator at the time of breakdown of the interelectrode gap of the spark discharge at the same time, the output of the voltage measuring circuit at the output of the sawtooth voltage generator at the time of breakdown of the interelectrode gap of the spark gap is connected to the input of the computing device, which is made in the form of a computer that implements both algorithms for determining the aerodynamic angle and true air speed, and algorithms for determining other altitude speed parameters that determine the movement of the aircraft relative to the surrounding air - barometric altitude, outdoor temperature

Description

The utility model relates to the field of measuring parameters of a moving object, in particular, to devices for measuring the magnitude (module), direction angle (aerodynamic angle) of the velocity vector and other parameters of the movement of a moving object relative to the surrounding air environment and can be used as a sensor of aerodynamic angle (angle attack or glide), true airspeed and other altitude and speed parameters of an aircraft, in particular an airplane.

Known devices for measuring the magnitude and angle of direction of the velocity vector of a gas (air) flow, implementing the aerodynamic method (method) of measurement (Petuni AN Methods and techniques for measuring gas flow parameters (pressure and velocity head receivers). M .: Mechanical Engineering, 1972 . - 332 p. - [1]; Gorlin SM, Slezinger II Aeromechanical measurements. Methods and instruments. M: Nauka, 1964. - 636 p. - [2]).

In such devices, a pressure receiver is introduced into a controlled incoming air flow, for example, in the form of a spherical body with a cylindrical base, which senses the full and static pressure of the incoming air flow, which determines the magnitude (module) of the velocity vector of the incoming air flow. The same receiver perceives pressures that carry information about the angular position of the air velocity vector relative to the axes of the receiver, which determine the angles of direction of the air velocity vector.

The use of such devices for measuring the magnitude (module) and aerodynamic angle (angle of attack and slip) of the true airspeed vector of an aircraft, in particular an aircraft, is associated with the need to move pressure receivers beyond the boundary layer of the aircraft, which inevitably leads to a violation of the aerodynamics of the aircraft complicating the design of the aerodynamic angle sensor and airspeed. In this case, a change in the state of the surrounding air environment (density, temperature, atmospheric pressure, humidity, pollution, etc.) leads to the appearance of additional measurement errors, reduce the reliability of the sensor.

Known devices for measuring the magnitude and angle of direction of the vector of true airspeed of a moving object that implement a kinematic measurement method in which a mark is introduced into the incoming air stream and the speed and direction (trajectory) of the mark along with the stream are controlled by registrars (US Patent No. 2872609, CL 73-180. - 1959 - [3]; Application of Japan No. 49-622, G01C 17/26. - 1972. - [4]).

A device is known for measuring the parameters of a moving object (Author's certificate No. 735065, USSR, G01C 21/12, 1980 - [5]), which contains a radiation source (tag), in the form of an ion generator, an ion tag receiver system, made in the form of a code mask placed on the casing of the moving object, the registration scheme of the trajectory of the ionic mark and the measuring circuit for generating the output signal from the measured angle of the air velocity vector (angle of attack or slip) of the moving object.

The ion tag generator, made in the form of a source of pulsed high-voltage voltage, generates a pulse that is supplied to the spark gap. Due to the spark discharge of the spark gap, an ionized region is formed - an ionic mark with a pronounced electrostatic charge of a certain polarity. A charged ionic tag moves together with the incoming air flow and acquires its motion parameters - speed and direction relative to the receiving electrode system. When moving an ionic tag along with the air flow in the direction of its movement, the path of the ionic tag crosses the receiving electrodes of the code mask, which lie in the path of its movement, inducing (inducing) electrostatic charges on them, the combination of which forms a certain code corresponding to the angle of the direction of the mark path, t .e. the corner of the direction of the airspeed vector of the moving object. Induced electrostatic charges are recorded by recorders associated with the receiving electrodes. The output signals of the registrars go to the measuring circuit for generating the output signals, which after decryption (decryption) of the combination of signals from the registrars of ionic tags produces an output signal proportional to the angle of the direction of the true airspeed vector of the moving object, which is sent to the indicator by other consumers.

The prototype is a label sensor of the aerodynamic angle and airspeed, which simultaneously measures the aerodynamic angle and true airspeed, which are determined using a system of receiving electrodes located at the same distance around the center of the center at the point of generation of the ionic mark. In this case, the measuring circuit for generating the output signals is made in the form of a channel for measuring true airspeed, a channel for determining the working sector of the measured angle, which is a rough reference channel, and a channel for accurately measuring the angle in the working sector, connected to the input of the computing device, the outputs of which are digital codes for the measured aerodynamic angle and true air speed (RF Patent for the invention No. 2445634, IPC G01P 5/14. Mark sensor aerodynamic angle and air speed / Ganeev .A., Soldatkin V.M., Urazbakhtin I.R., Makarov N.N., Kozhevnikov V.I. Declaration of 05.05.2010, No. 20108253 / 28. Publish. March 20, 2012. Bull. No. 8 - [ 6]).

In FIG. 1 shows a functional diagram of a device prototype. In FIG. 2 shows a structural diagram of a system of receiving electrodes; FIG. Figure 3 shows the principle of the formation of sinusoidal and cosine informative signals using a system of discrete receiving electrodes located around the circumference.

Functional diagram of the device of the prototype (Fig. 1) contains a board 1 with receiving electrodes 3 in the form of round metal plates located at the same distance along a circle of radius R centered at point 0 of the generation of the ion mark using a spark gap 2. The receiving electrodes 3 are connected to the inputs pre-amplifiers 4 (PU) of the registration channel ions of tags located in the block of pre-amplifiers 5 (BPU). The receiving electrodes are made together with pre-amplifiers in the form of autonomous modules located in the control room, and form a channel for recording ionic marks. The conclusions of the block of preliminary amplifiers are connected to the input of the channel for accurate measurement of the angle 6 (channel for accurate measurement of the aerodynamic angle), to the input of the channel for measuring airspeed 7 and to the input of the channel for determining the working sector 8 of the measured aerodynamic angle (coarse channel). The outputs of all these channels are connected to the input of the computing device 9, the outputs of which are digital codes for the aerodynamic angle N _α and air speed N _ν .

The output signal F of the _GM is also generated at the output of the computing device 9, which is the control input of the mark generator 10 and sets the frequency of the generation of ion marks and the start of the measurement cycle of the aerodynamic angle and air speed.

The board 1 with the receiving electrodes 3 is made on the basis of a metal mask (Fig. 2), which is a thin metal plate 11 on which there are holes 12 located at the same distance l along a circle of radius R. Under the mask 11 is a dielectric board 14 with the receiving electrodes 3. Electrodes 3 are located directly under the holes 12 of the metal mask 11.

This design of the receiving electrode system is quite simple to implement and allows for high accuracy of the formation of sinusoidal and cosine angular characteristics of the informative signals of the receiving electrodes (Fig. 3). The shape of the angular characteristic of a multi-element electrode system is determined by the shape of the characteristic of a separate discrete receiving electrode, the relative position of the electrodes and their connection to the preamplifiers of the channel for recording ionic marks.

Mark sensor aerodynamic angle and airspeed works as follows.

воздушной скорости. Цикл измерения начинается с подачи с выхода вычислительного устройства 9 сигнала F_ГM. В соответствии с сигналом F_ГM генератор метки 10 выдает импульс высоковольтного напряжения на разрядник 2, установленный в точке 0 генерации ионной метки. За счет искрового разряда разрядника в точке 0 образуется ионизированная область - ионная метка с явно выраженным электростатическим зарядом q_м. Заряженная ионная метка перемещается совместно с набегающим воздушным потоком и приобретает его параметры движения - скорость V и направление α относительно оси симметрии платы 1 с приемными электродами 3. При перемещении ионной метки совместно с набегающим воздушным потоком заряженная ионная метка пролетает вблизи приемных электродов и наводит (индуцирует) на них электрические заряды, величина которых зависит от расстояния ионной метки от приемного электрода и углового положения а траектории движения ионной метки.A label sensor of aerodynamic angles and airspeed is installed on the aircraft in such a way that the system 1 with the receiving electrodes 3 (Fig. 1) is in the plane of change of the aerodynamic angle α of the vector

airspeed. The measurement cycle begins with the supply from the output of the computing device 9 of the signal F _GM . In accordance with the signal F _ГМ, the tag generator 10 generates a high-voltage voltage pulse to the spark gap 2 installed at point 0 of the generation of the ion tag. Due to the spark discharge of the spark gap at point 0, an ionized region is formed - an ionic mark with a pronounced electrostatic charge q _m . A charged ionic tag moves together with the incoming air flow and acquires its motion parameters — velocity V and direction α relative to the axis of symmetry of the board 1 with the receiving electrodes 3. When the ionic tag moves together with the incoming air flow, the charged ionic tag flies near the receiving electrodes and induces (induces ) electric charges on them, the magnitude of which depends on the distance of the ionic mark from the receiving electrode and the angular position and trajectory of the ionic mark.

By choosing the design parameters of the receiving electrode system (Fig. 2), positive and negative half-waves of the sinusoidal angular characteristics of the informative signals U (α) (Fig. 3) at the output of even preamplifiers are formed using the receiving electrodes.

Using odd receiving electrodes, positive and negative half-waves of the cosine angular characteristics of the informative signals U (α) are generated at the output of the odd pre-amplifiers.

The output signals of the preamplifiers 4 of the block of preamplifiers 5 (Fig. 1) are fed to the inputs of the channel for determining the working sector 8 (coarse channel) of the measured aerodynamic angle, the channel for accurate measurement of the angle 6 in the working sector and the channel for measuring airspeed 8. The output signals of these channels fed to the inputs of the computing device 9, which according to the results of processing the input information provides digital codes N _α , N _ν for the measured aerodynamic angle α and air speed V _B.

Taking into account the trajectory of the ionic mark in the i-th rough channel, the current value of the measured aerodynamic angle is determined as

).where α _o is the angle covering the working sector of the coarse reference channel (at i _max = 4, α _o = 90 °); i is the number of the working sector (

)

Signals proportional to the sine of Asinα _i and the cosine of Acosα _i , of the measured angle in the working sector of the rough channel are processed in a computing device, the output of which is a digital code N _αm associated with the value α _{p of the} measured aerodynamic angle of the exact channel by the ratio

where α _i is the current value of the aerodynamic angle within the i-th working sector.

During the operation of the true airspeed measuring channel, a time interval τ _{ν of the} flight of the ion mark of the distance R ₀ from the point of generation of the ion mark to the circle with the receiving electrodes is formed. In accordance with the time interval τ _ν , a digital code N _{ν is} generated in the computing device, which is proportional to the true airspeed

(3)

(3)

Digital codes N _α , N _ν are served on the means of displaying information to other consumers.

Thus, the marking sensor of the aerodynamic angle and true airspeed does not have aerodynamic receivers protruding into the incoming air flow, violating the aerodynamics of the aircraft.

The kinematic method of measuring the magnitude (module) and the direction angle of the true airspeed vector is implemented in the marking sensor of the aerodynamic angle and airspeed, at which the accuracy of measuring the aerodynamic angles and true airspeed does not depend on the state of the environment (temperature, atmospheric pressure, density, humidity, and etc.).

The implementation of the system of receiving electrodes in the form of metal plates arranged around the circumference, mounted under the holes of the mask, makes it possible to generate ratiometric informative signals with sinusoidal and cosine angular characteristics and to provide measurement of the aerodynamic angle in the entire range of its variation, i.e. from 0 to 360 ° or ± 180 ° without increasing the overall dimensions of the receiving electrode system. At the same time, the constructive implementation of the receiving electrodes together with the preliminary amplifiers of the recording channel in the form of autonomous modules allows one to significantly increase the noise immunity of the channel for recording ionic marks and increase the resolution in aerodynamic angle and true air speed with small dimensions of the receiving electrode system.

The implementation of the measuring circuit for generating the output signals in the form of a channel for determining the working sector of the measured angle, which is a coarse reference channel, and a channel for accurately measuring the angle in each of the working sectors connected to the computing device, can significantly increase the resolution of the measured aerodynamic angle in the entire range of its change without increasing the number of receiving electrodes and overall dimensions of the receiving electrode system.

The proposed implementation of the channels for determining the working sector of the measured angle and the channel for accurate measurement of the aerodynamic angle inside each working sector provides a reliable definition of the working sector and accurate measurement of the current value of the angle inside each working sector, which also improves the measurement accuracy in a wide range of changes in the aerodynamic angle while changing the value true airspeed.

The proposed implementation of the true airspeed measurement channel allows high accuracy to form the time interval of the flight of the ionic mark from the point of generation to the circle with the receiving electrodes while changing the aerodynamic angle, which increases the accuracy of measuring airspeed.

However, the prototype device has several disadvantages associated with limited functionality to determine other altitude-speed parameters that determine the movement of the aircraft relative to the surrounding air. This limits the use of the tag sensor on airplanes and other aircraft, including unmanned and remotely piloted ones.

The technical result to which the claimed utility model is directed is to increase the efficiency of the use of a tag sensor:

1) in expanding the functionality due to the simultaneous measurement of all altitude-speed parameters that determine the movement of the aircraft relative to the surrounding air environment;

2) in the measurement of altitude-speed parameters of the aircraft motion using one multifunctional sensor;

3) in expanding the functionality of one multifunctional tagging sensor practically without complicating its design scheme.

The technical result is achieved as follows.

In the aerodynamic angle and true airspeed marking sensor containing the ionic mark generator, a system of receiving electrodes in the form of round metal plates located at the same distance along the circumference with the center at the point of generation of the ionic mark and installed directly under the holes of the metal plate - mask mounted on the dielectric board , a channel for recording ionic marks and a measuring circuit for generating output signals in the form of a channel for determining the working sector of the measured angle, With a coarse reference channel, an accurate angle measuring channel, and a true airspeed channel connected to the input of a computing device whose outputs are digital outputs at the aerodynamic angle and true airspeed, the novel feature is that the ion mark generator is designed as a sawtooth voltage generator to a spark gap, in the discharge circuit of which is included a registration circuit for the moment of spark breakdown of the interelectrode gap of the spark gap, the output of which is connected the control input of the voltage measurement circuit at the output of the sawtooth voltage generator at the time of breakdown of the electrode gap of the spark gap, while the output of the voltage measurement circuit at the output of the sawtooth voltage generator at the time of breakdown of the electrode gap of the spark gap is connected to the input of the computing device, which is designed as a computer that implements as algorithms for determining the aerodynamic angle and true airspeed, and algorithms for determining other altitude-s orostnyh parameters that define the motion of the aircraft relative to ambient air - pressure altitude, outside air temperature, air density at a given altitude, airspeed and the Mach number, according to the equations:

;

;

;

;

;

;

;

;

;

;

;

; (4)

;

; (four)

,

, где

,

where

, α_o=90°); Asinα_i и Acosα_i - значения синусоидального и косинусоидального информативных сигналов, регистрируемых каналом точного отсчета в i-ом рабочем секторе; R₀ - расстояние от точки генерации ионной метки до окружности с приемными электродами; τ_ν - интервал времени пролета ионной метки расстояния от точки генерации ионной метки до окружности с приемными электродами; d - расстояние между электродами искрового разрядника; U_ПР - напряжение пробоя межэлектродного промежутка искрового разрядника; Р_Н - абсолютное статическое давление на абсолютной высоте полета Н; α и V_B, Н, Т_Н и ρ_Н, V_пр и М - определяемые высотно-скоростные параметры: аэродинамический угол и истинная воздушная скорость, абсолютная (барометрическая) высота полета, абсолютная температура и плотность воздуха на высоте Н, приборная скорость и число Маха; Р₀=101325 Па=101325 Н/м²=760 мм.рт.ст. и Т₀=288,15 К - среднее абсолютное давление и средняя абсолютная температура стандартной атмосферы при Н=0; τ=0,0065 К/м - температурный градиент, определяющий изменение абсолютной температуры воздуха Т_Н при изменении высоты Н; R=29,27125 м/К - газовая постоянная; k=1,4 - показатель адиабаты воздуха; ρ₀=0,125 кгс²/м⁴=0,125 Н с²/м⁴ - массовая плотность воздуха на высоте Н=0.i is the number of the working sector of the rough channel in which the ionic mark is located; α _o is the angle covering the working sector of the rough channel of reference of the aerodynamic angle (when

, α _o = 90 °); Asinα _i and Acosα _i are the values of the sinusoidal and cosine-informative signals recorded by the exact reference channel in the i-th working sector; R ₀ is the distance from the point of generation of the ionic mark to the circle with the receiving electrodes; τ _ν is the time interval of the flight of the ionic mark of the distance from the point of generation of the ionic mark to the circle with the receiving electrodes; d is the distance between the electrodes of the spark gap; U _PR - breakdown voltage of the interelectrode gap of the spark gap; P _N - absolute static pressure at the absolute height of flight N; α and V _B , N, T _N and ρ _N , V _pr and M are the determined altitude and speed parameters: aerodynamic angle and true air speed, absolute (barometric) flight altitude, absolute temperature and air density at a height of H, instrument speed and Mach number; P ₀ = 101325 Pa = 101325 N / m ² = 760 mm Hg and T ₀ = 288.15 K is the average absolute pressure and the average absolute temperature of the standard atmosphere at H = 0; τ = 0,0065 K / m - the temperature gradient that determines the change in the absolute air temperature T _N with a change in height H; R = 29.27125 m / K - gas constant; k = 1.4 is the adiabatic index of air; ρ ₀ = 0.125 kgf ² / m ⁴ = 0.125 N with ² / m ⁴ - mass density of air at a height of H = 0.

The essence of the utility model is illustrated in FIG. four.

In FIG. Figure 4 shows a functional diagram of a tagged aerodynamic angle and true airspeed sensor with advanced functionality.

Here: 1 - a board with receiving electrodes 3 (PE); 2 - spark gap; 15 is a registration diagram of the moment of spark breakdown of the interelectrode gap of the spark gap; 10 - label generator, made in the form of a sawtooth voltage generator; 16 is a diagram of measuring voltage at the output of a sawtooth voltage generator at the time of breakdown of the interelectrode gap of the spark gap; 5 - block pre-amplifiers channel registration ion tags; 17 is a measuring circuit (IC), including a channel for determining the working sector 8 (coarse channel), a channel for accurate measurement of angle 6 and a channel for measuring airspeed 7; 9 - computing device (WU).

Functional diagram of the tagged sensor of the aerodynamic angle and true airspeed with advanced functionality (Fig. 4) contains a board 1 with receiving electrodes 3 (PE) in the form of round metal plates located at the same distance along a circle of radius R ₀ centered at point 0 of generation ion tag, in which the spark gap 2 is installed, connected to the output of the tag generator 10 (GM). The receiving electrodes are connected to the inputs of the pre-amplifiers 4 located in the block of pre-amplifiers 5 (BPU) of the channel for recording ionic marks 15. The outputs of the BPU are connected to the inputs of the channels of the measuring circuit 16 (IC) - the channel for determining the working sector 8 (coarse reference channel), measuring the angle 6 in the working sector and the airspeed measuring channel 7. The outputs of the channels of the measuring circuit of the IC are connected to the input of the computing device 9 (WU).

To expand the functionality of the marking sensor of the aerodynamic angle and true airspeed and to measure other altitude and speed parameters that determine the movement of the aircraft relative to the determining air environment (barometric altitude H, temperature T _H outdoor air at flight altitude H, air density ρ _N at altitude H, airspeed V, _etc., of the Mach number M and the other associated parameters) ion generator GM labels formed as a sawtooth generator by applying emogo on the spark gap 2. In the circuit of the spark gap circuit 16 is enabled registration points spark electrode gap of the spark gap, the output of which is connected to the control input of the voltage measuring circuit 17 U _OL on the sawtooth generator output when the breakdown spark gap of the interelectrode gap scheme 2. Yield 17 is connected to the input of the WU computing device, which, by the _GM signal F, sets the start-up cycle of the sawtooth voltage generator and the frequency of generation of ionic marks.

The WU computing device is designed as a calculator that implements both algorithms for determining the aerodynamic angle and true airspeed, and algorithms for determining other altitude and speed parameters of the aircraft’s motion relative to the surrounding air, including:

1. According to the measured voltage U _PR at the output of the sawtooth voltage generator at the time of breakdown of the interelectrode gap of the spark gap, using the empirical formula given in the literature: Yu. P. Raiser Gas Discharge Physics: A Training Manual. - M .: The main edition of the physical and mathematical literature. - 1987. - 592 p. - [7],

where U _PR is the breakdown voltage of the interelectrode gap of the spark gap; d is the distance between the electrodes of the spark gap; P _N - the absolute pressure of the ambient air, depending on the height H, with a known value of the distance d, the absolute pressure P _{H is} calculated at a given flight height H, for example, implicitly from the relation

2. According to the calculated absolute static pressure R _{N of the} incoming air flow in accordance with the standard dependencies corresponding to GOST 4401-81 (GOST 4401-81. The atmosphere is standard. Parameters. - M .: Publishing House of Standards. - 1981. - 179 p. - [8]), the absolute flight altitude in the range [-2000m <N <11000m] is determined by the formula

3. Using GOST 5212-74 (GOST 5212-74. Aerodynamic table. Dynamic pressure and air braking temperature for a flight speed of 10 to 4000 km / h. Parameters. - M: Publishing House of Standards. - 1974. -239 p. - [9]), the true airspeed V _B measured by the notch sensor can be represented as

- динамическое давление (скоростной напор) набегающего воздушного потока.where g = 9.80665 m / s ² is the acceleration of gravity; P _P = P _N + P _din - full pressure of the oncoming air flow;

- dynamic pressure (velocity head) of the incoming air flow.

4. Substituting in the expression (8) the values of the parameters V _B and P _N measured by the vortex sensor, we obtain a relation of the form

which establishes an implicit but unambiguous relationship of the true air speed V _B measured by the vortex sensor with the absolute temperature T _N at a height of N.

5. Determining the absolute temperature T _N from relation (9), one can determine the density of air ρ _N at a height of N.

The air density ρ _N at a height of H can be represented (L. Zalmanzon Flowing elements of pneumatic control and control devices. - M.: Publishing House of the USSR Academy of Sciences. - 1961. - 249 p. - [10]) as

where ρ ₀ = 0.125 kgf ² / m ⁴ = 0.125 N with ² / m ⁴ is the mass density of air at a height of H = 0.

6. Then, in accordance with GOST 5212-74 [9], it is possible to determine (calculate) the instrumental flight speed, i.e. true air speed V _B , reduced to normal conditions at the level of H = 0, according to the formula

на высоте Н, например для дозвуковых скоростей полета будет определяться уравнением8. Mach number M, characterizing the ratio of the true air speed V _B to the speed of sound

at a height H, for example, for subsonic flight speeds will be determined by the equation

Thus, by measuring the breakdown voltage U _{PR of the} interelectrode gap of the spark gap, the absolute static pressure P _{N of the} surrounding air at the absolute flight altitude N is determined by dependence (6) and then by dependences (7) - (12) in the calculator of the aerodynamic angle sensor and true airspeed, all altitude-speed parameters of the aircraft’s motion relative to the environment are determined, significantly expanding the functionality of the aerodynamic angle mark sensor and muddy airspeed.

A marking sensor of the aerodynamic angle and true airspeed is installed on the aircraft in such a way that the base axis of the receiving electrode system, corresponding to the zero aerodynamic angle, coincides with the direction of the longitudinal axis of the aircraft, and the plane of the receiving electrodes is in the plane of change of the measured aerodynamic angle.

During the operation of the aerodynamic angle and true airspeed mark sensor, a change in the aerodynamic angle α causes a deviation of the trajectory of motion generated by the spark gap 2 at point O of the ion mark with an electrostatic charge q _m . A charged ionic tag moves together with the incoming air stream, flies near the receiving electrodes 3 and induces (induces) electric charges on them, the magnitude of which depends on the distance of the ionic tag to the receiving electrode and the angular position α of the ionic path. Using the receiving electrodes 3, positive and negative half waves of sinusoidal and cosine angular characteristics of the informative signals U (α) are formed at the outputs of the corresponding pre-amplifiers of the control panel (see Fig. 3). The output signals U (α) of the preamplifier unit 5 (Fig. 3) are fed to the inputs of the measuring circuit 15 in the channels of which signals are generated that determine the working sector i of the coarse reference channel and the exact value α _{p of the} measured angle in the working sector, and the time interval τ _ν the spacing of the ion tag R ₀ from the point 0 of the generation of the ion tag to the circle with the receiving electrodes 3. The output signals of the channels of the measuring circuit are fed to the inputs of the computing device 9.

In each cycle of the generation of the ionic mark using the circuit 16, the moment of spark breakdown of the interelectrode gap of the spark gap is recorded. At the output of circuit 16, a pulse signal is generated, which is fed to the control input of circuit 17, which measures the voltage U _PR at the output of the sawtooth voltage generator at the time of breakdown of the interelectrode gap of the spark gap. The measured breakdown voltage U _PR is supplied to the input of the computing device 9.

The computing device 9, made in the form of a calculator, implements algorithms for determining the aerodynamic angle and true air speed, according to equations (1), (2) and (3) and generates output code signals from the aerodynamic angle α and the true air speed V _{B of the} aircraft. According to equations (6), (7), (8), (9), (10), (11), (12), the calculator determines and generates code signals according to the barometric height H, the absolute outdoor temperature T _N at the flight altitude N , air density ρ _N at an altitude of H, instrument speed V _pr , Mach number M, significantly expanding the functionality and scope of such an integrated multifunctional marking sensor for altitude-speed parameters (air signals) of the aircraft.

Thus, in comparison with the known aerodynamic angle and true airspeed sensors, the marking aerodynamic angle and true airspeed sensors with advanced functionality have a number of significant advantages:

1. Provides simultaneous measurement of all altitude-speed parameters that determine the movement of the aircraft relative to the surrounding air environment, ie It is a multifunctional air signal sensor.

2. The measurement of all altitude-speed parameters of the aircraft’s motion relative to the surrounding air is carried out using one fixed non-protruding flow receiver, which does not distort the aerodynamics of the aircraft and does not affect its aerodynamic characteristics.

3. Measurement of all altitude-speed parameters, ie the expansion of the functionality of the tag sensor is provided without significant complication of its design scheme, and therefore increase the cost of its production.

4. Obtaining the output signals of the notch sensor for all altitude and speed parameters of the aircraft in directly digital form, simplifies their use in modern digital information display systems, control systems and other technical systems.

It should be noted that the range of operating speeds of the multifunctional marking sensor of the aerodynamic angle and true air speed is unlimited by subsonic flight speeds.

The use of a multifunctional marking sensor of the aerodynamic angle and true airspeed on various classes of aircraft, in particular on airplanes and other aircraft, including unmanned and remotely piloted aircraft, as well as on ekranoplanes and other vehicles, makes it possible to expand the boundary of operating speeds , improve the accuracy of measuring altitude and speed parameters, improve the quality of piloting and the effectiveness of solving the tactical and technical problems of flight.

Claims (1)

Label sensor for the aerodynamic angle and true airspeed of the aircraft, containing an ionic tag generator, an ionic tag registration channel in the form of a system of receiving electrodes located in a circle centered at the ionic tag generation point, and a pre-amplifier unit, a measuring circuit in the form of a working sector determination channel being a coarse reference channel, a channel for accurate measurement of the angle in the working sector, and a true airspeed channel connected to the input of the computing device, the passages of which are digital outputs along the aerodynamic angle and true airspeed, characterized in that the ion mark generator is made in the form of a sawtooth voltage generator supplied to the spark gap, the discharge circuit of which includes a circuit for detecting the moment of spark breakdown of the interelectrode gap of the spark gap, the output of which is connected to the control input of the voltage measurement circuit at the output of the sawtooth voltage generator at the time of breakdown of the interelectrode gap of the spark discharge at the same time, the output of the voltage measuring circuit at the output of the sawtooth voltage generator at the time of breakdown of the interelectrode gap of the spark gap is connected to the input of the computing device, which is made in the form of a computer that implements both algorithms for determining the aerodynamic angle and true air speed, and algorithms for determining other altitude speed parameters that determine the movement of the aircraft relative to the surrounding air - barometric altitude, outdoor temperature air, air density at a given flight altitude, instrument speed and Mach number, according to the equations:

;

;

;

where i is the number of the working sector of the rough channel in which the ionic mark is located; α ₀ is the angle that covers the working sector of the rough reference channel of the aerodynamic angle (at

α ₀ = 90 °); Asinα _i and Acosα _i are the values of the sinusoidal and cosine-informative signals recorded by the exact reference channel in the i-th working sector; R ₀ is the distance from the point of generation of the ionic mark to the circle with the receiving electrodes; τ _ν is the time interval of the flight of the ionic mark of the distance from the point of generation of the ionic mark to the circle with the receiving electrodes; d is the distance between the electrodes of the spark gap; P _Y is the absolute static pressure at the absolute flight altitude H; α and V _B , H, T _H and ρ _H , V _pp and M are the determined altitude and speed parameters: aerodynamic angle and true airspeed, absolute (barometric) altitude, absolute temperature and air density at a height of H, instrument speed and Mach number; P ₀ = 101325 Pa = 101325 N / m ² = 760 mm Hg and T ₀ = 288.15 K — average absolute pressure and average absolute temperature of a standard atmosphere at H = 0; τ = 0.0065K / m - a temperature gradient that determines the change in the absolute air temperature T _H with a change in height H; R = 29.27125m / K - gas constant; k = 1.4 is the adiabatic index of air; ρ ₀ = 0.125 kgf ² / m ⁴ = 0.125 N with ² / m ⁴ is the mass density of air at a height of H = 0.

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