KR101972130B1 - Appartus and method for determine air mass flow rate of supersonic intake - Google Patents

Abstract

An embodiment of the present invention provides an apparatus for measuring air mass flow rate at a supersonic intake including an electronic device determining mass flow rate of air sucked into an aircraft based on stored atmosphere data, wherein the atmosphere data contains constant pressure and constant temperature information of the atmosphere according to the altitude, and the electronic device includes a GPS sensing the altitude of the aircraft and determines the constant pressure and the constant temperature of air sucked into the aircraft based on the altitude of the aircraft sensed by the GPS. The apparatus for measuring the air mass flow rate at the supersonic intake can measure the mass flow rate of the air sucked through the air intake without other separately added equipment.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to an apparatus and method for measuring an air mass flow rate of a supersonic suction port,

The following description relates to an apparatus and a method for measuring an air mass flow rate of a supersonic suction port.

In order to control the supersonic engine, the flow rate of the air flowing into the engine must be accurately measured. It is possible to control the air fuel ratio based on the flow rate of the air flowing into the engine or to limit the limit of the fuel amount to efficiently burn the fuel. Therefore, the air mass flow rate at the intake port is a very important measurement variable in controlling the engine, and the air mass flow measurement accuracy has a great influence on the combustion efficiency. If the same amount of fuel is used through the increase of the combustion efficiency, the flight time of the flight vehicle can be improved.

Airborne information, such as static pressure and static temperature and flight speed information, is required to measure the correct air flow during flight. However, it is very difficult to acquire the waiting information directly in flight. Referring to FIG. 1, a conventional apparatus for measuring flow information, which is built in a flight body 900 to calculate an air flow rate, includes a pressure sensor 930 or a sensor mounted on the surface of a flight body 900, (hereinafter referred to as a suction port) between the tip portion 910 and the body 920 based on the pressure and the total temperature of the engine 940 to calculate the air mass flow rate to be transmitted to the engine 940. These separate additional components not only increase the hardware cost, but also adversely affect the flight performance directly or indirectly due to the increase in air resistance.

It is an object of the present invention to provide an air mass flow rate measuring device for a supersonic suction port capable of measuring an air mass flow rate introduced through an air intake port without any additional attachment.

According to one embodiment, the air mass flow rate measuring apparatus may include an electronic device for calculating a mass flow rate of air sucked into the airplane based on previously stored waiting information data.

The waiting information data may include atmospheric pressure and temperature information according to altitude.

The electronic device may include a GPS for sensing an altitude of the air vehicle. The electronic device can determine a static pressure and a static temperature of air sucked into the airplane based on the altitude of the airplane detected from the GPS.

The electronic device includes a navigation device for measuring the speed of the air vehicle; And an air flow rate calculation unit for determining a mass flow rate of the air sucked into the air based on the speed of the air flow and the static pressure and the constant temperature information of the air sucked into the air flow.

The electronic device comprising: a pressure sensor capable of measuring a voltage force; And an air flow rate calculation unit for determining a mass flow rate of the air sucked into the air based on the voltage and the constant pressure and the constant temperature information of the air.

The pressure sensor may be disposed in a hole formed in a tip portion of the flying object.

The electronic device may receive the wait information data from the ground system before the airplane takes-off.

The electronic device can receive the waiting information data from the terrestrial system in real time while the air vehicle is flying.

According to an embodiment of the present invention, there is provided a method of measuring air mass flow rate, the method comprising: receiving atmospheric information data including atmospheric static pressure and constant temperature information according to altitude from a ground system; Sensing an altitude of the air vehicle through GPS; Determining the static pressure and the constant temperature information at the altitude of the air vehicle; And determining the air flow rate based on the determined constant pressure and the constant temperature information.

The air mass flow rate measuring method may further include measuring a speed of the air vehicle through a navigation device.

The air mass flow rate measuring method may further include measuring a voltage at a position of the air vehicle through a pressure sensor.

The air mass flow rate measurement method may further include updating atmospheric information data according to the altitude in real time while the air vehicle is flying.

According to an embodiment, the air mass flow rate measuring device of the supersonic suction port can measure the air mass flow rate introduced through the air intake port without additional attachment.

In addition, it is possible to accurately measure the air mass flow rate by receiving the static pressure and the constant temperature data according to the altitude from the ground system in real time.

Further, it is possible to measure the voltage force of the air flowing into the intake port through the pressure sensor disposed in the hole provided in the tip of the flying object, and to improve the accuracy of the air mass flow measurement through the measured voltage force.

1 is a perspective view showing a conventional air vehicle.
FIG. 2 is a block diagram schematically showing a ground system and an air vehicle according to an embodiment.
3 is a block diagram schematically showing a ground system and an electronic device according to an embodiment transmit and receive information.
4 is a flowchart of steps in which an electronic device according to an embodiment determines an air mass flow rate.
5 is a block diagram schematically illustrating a ground system and a flight according to an embodiment.
6 is a cross-sectional view of a front portion of the air vehicle according to an embodiment.
7 is a block diagram schematically showing a ground system and an electronic device according to an embodiment transmit and receive information.
8 is a flowchart of steps in which an electronic device according to an embodiment determines an air mass flow rate.

Hereinafter, embodiments will be described in detail with reference to exemplary drawings. It should be noted that, in adding reference numerals to the constituent elements of the drawings, the same constituent elements are denoted by the same reference symbols as possible even if they are shown in different drawings. In the following description of the embodiments, detailed description of known functions and configurations incorporated herein will be omitted when it may make the best of an understanding clear.

In describing the components of the embodiment, terms such as first, second, A, B, (a), and (b) may be used. These terms are intended to distinguish the constituent elements from other constituent elements, and the terms do not limit the nature, order or order of the constituent elements. When a component is described as being "connected", "coupled", or "connected" to another component, the component may be directly connected or connected to the other component, Quot; may be " connected, " " coupled, " or " connected. &Quot;

The components included in any one embodiment and the components including common functions will be described using the same names in other embodiments. Unless otherwise stated, the description of any one embodiment may be applied to other embodiments, and a detailed description thereof will be omitted in the overlapping scope.

FIG. 2 is a block diagram schematically showing a ground system and a vehicle according to an embodiment. FIG. 3 is a block diagram schematically showing a ground system and an electronic device according to an embodiment transmit and receive information.

2 to 3, the air vehicle 100 may include an electronic device 110 and an engine 120 according to an embodiment of the present invention.

은 예를 들어 비행 마하수(M), 대기 전압력(

), 대기 전온도(

) 및 제 1 유량 계수(

)와 관련된 <수학식 1>을 통해 결정될 수 있다.The electronic device 110 can be sucked into the air bag 100 to determine the air mass flow rate flowing into the engine. Air mass flow rate (

For example, flight Mach number (M), atmospheric pressure (

), Preheating temperature (

) And the first flow coefficient (

(1) &quot;

&Quot; (1) &quot;

) 및 비행 속도(v)에 관한 <수학식 2>로 정리될 수 있다. Equation (1) represents the atmospheric static pressure (P), the atmospheric temperature (T), the second flow coefficient

And (2) with respect to the flying speed v.

&Quot; (2) &quot;

)을 결정할 수 있다.The electronic device 110 calculates the air mass flow rate (V) based on the information about the atmospheric static pressure P and the atmospheric air temperature T, and the information about the flight speed v in accordance with Equation (2)

Can be determined.

The electronic device 110 may receive and store standby information data from a ground system (GS). The waiting information data may include the atmospheric pressure P and the constant temperature T information according to the altitude H. For example, the waiting information data may be a data table storing a constant pressure P and a constant temperature T at intervals of 10 m in a direction perpendicular to the paper. It is noted that the interval of 10 m is only an example of the altitude (H), and the altitude (H) interval of the waiting information data is not limited thereto.

The electronic device 110 can determine the mass flow rate of the air sucked into the air vehicle 100 based on the stored waiting information data. The electronic device 110 includes an air flow rate calculation unit 111, a GPS 112 capable of sensing the altitude of the air vehicle 100, and a navigation device 113 capable of measuring the airspeed of the air vehicle 100 can do.

) 결정할 수 있다. The electronic device 110 can determine the static pressure P and the constant temperature T of air sucked into the air vehicle 100 based on the altitude of the air vehicle 100 sensed by the GPS 112. [ For example, the electronic device 110 can extract the static pressure P and the constant temperature T corresponding to the altitude of the air vehicle 100 sensed by the GPS 112 from the atmospheric information data. The extracted static pressure P and the constant temperature T information may be transmitted to the air flow rate calculator 111. The air flow rate computation unit 111 computes the air mass flow rate (T) based on the constant pressure P and the constant temperature T information and the flight speed of the air vehicle 100 measured from the navigation device 113

).

)에 기초하여 엔진(120)을 제어할 수 있다. 예를 들어, 전자장치(110)는 공기 질량 유량(

)에 기초하여, 엔진(120) 내부의 공연비를 제어하거나, 엔진(120)의 연소부로 배출되는 연료의 양을 조절할 수 있다.The electronic device 110 determines the determined air mass flow rate (

The engine 120 can be controlled based on the engine speed. For example, electronic device 110 may be configured to measure air mass flow rate

, It is possible to control the air-fuel ratio inside the engine 120 or adjust the amount of fuel discharged to the combustion portion of the engine 120. [

4 is a flow diagram of a method for an electronic device according to an embodiment to determine an air mass flow rate. It should be noted that the following reference numerals are used for the reference numerals used in Figs. 2 and 3.

)을 결정하는 단계(750)를 포함할 수 있다.The method by which the electronic device 110 determines the air mass flow rate comprises the steps of receiving (710) atmospheric static pressure and constant temperature data according to altitude from the terrestrial system (GS) A step 730 of determining the static pressure P and the constant temperature T based on the altitude of the air vehicle 100 and the step 730 of detecting the altitude of the air vehicle 100 through the navigation device 113 (V) of the air mass 100 based on the constant pressure P, the constant temperature T and the velocity v of the air vehicle 100,

(Step 750). &Lt; / RTI &gt;

At step 710, the electronic device 110 may receive standby information data from the ground system GS before the air vehicle 100 takes off. The air vehicle 100 can improve the accuracy of the air mass flow measurement by updating the waiting information data before each take-off.

In addition, the electronic device 110 can receive standby information data in real time from the ground system GS while the air vehicle 100 is flying. The electronic device 110 can update the standby information data by reflecting the standby state that changes instantaneously in real time.

In step 720, the GPS 112 may sense the altitude of the air vehicle 100. [

In step 730, the electronic device 110 may extract the static pressure P and the constant temperature T information according to the altitude sensed from the GPS 112 on the atmospheric information data.

In step 740, the navigation device 113 can measure the flying speed of the air vehicle 100. [

)을 결정할 수 있다. 또한, 전자장치(110)는 결정된 공기 질량 유량(

)에 기초하여 엔진(120, 도 2 참조)을 제어할 수 있다.At step 750 the electronic device 110 determines the air mass flow rate (V) based on the constant pressure P and the constant temperature T information and the velocity v

Can be determined. In addition, the electronic device 110 may determine the determined air mass flow rate (

The engine 120 (see FIG. 2).

FIG. 5 is a block diagram schematically illustrating a ground system and a vehicle in accordance with an embodiment, FIG. 6 is a sectional view of a front portion of a vehicle according to an embodiment, and FIG. 7 is a cross- Fig. 2 is a block diagram schematically showing how information is transmitted and received. Fig.

5 to 7, the air vehicle 200 according to an embodiment may include an electronic device 210 and an engine 220. [

)은 예를 들어 대기 전압력(

), 정압력(P), 대기 정온도(T) 및 제 3 유량 계수(

)와 관련된 <수학식 3>을 통해 결정될 수 있다.The electronic device 210 can be sucked into the air vehicle 100 to determine the air mass flow rate into the engine. Air mass flow rate (

For example, atmospheric power (

), The constant pressure (P), the atmospheric temperature (T), and the third flow coefficient

(3) < / RTI > associated with the &lt; RTI ID = 0.0 &gt;

&Quot; (3) &quot;

)이 얻어질 수 있다. 구체적으로, 전자장치(210)는 비행체(200)의 속도(v)와 바람의 속도로 흡입구로 유입되는 공기의 특성을 모두 포함한 전압력(

)을 이용할 수 있으므로, 높은 정밀도로 공기 질량 유량(

)을 측정할 수 있다. According to Equation (3), it is possible to correct the error due to the wind velocity in the atmosphere, and more accurate air mass flow rate

) Can be obtained. Specifically, the electronic device 210 generates a voltage (V) including both the speed v of the air vehicle 200 and the characteristics of the air flowing into the air inlet at the wind speed

) Can be used, so that the air mass flow rate (

) Can be measured.

)을 측정 가능한 압력 센서(203)를 포함할 수 있다. 압력 센서(203)는 비행체(200)의 첨두부(201)에 형성된 홀에 구비될 수 있다. 따라서, 압력 센서(203)가 구비되더라도 비행체(200)에 인가되는 항력은 증가하지 않을 수 있다.The air vehicle 200 has an air pressure

(Not shown). The pressure sensor 203 may be provided in a hole formed in the tip portion 201 of the air body 200. Therefore, even if the pressure sensor 203 is provided, the drag force applied to the air vehicle 200 may not increase.

The flight body 200 may include a tip portion 201 disposed at the foremost position and including a conical end portion and a body 202 surrounding the tip portion 201. [

The space between the tip portion 201 and the body 202 can be understood as an inlet of the air vehicle 200. When the flying object 200 is flying at supersonic speed, a conical shock wave (SW) may be formed around the tip portion 201 of the flying object 200. It can be understood that the area A of the suction flow to the air vehicle 200 is equal to the area of the air intake of the air vehicle 200. [

)을 측정 가능한 압력 센서(203)를 포함할 수 있다.The electronic device 210 can determine the mass flow rate of the air sucked into the air vehicle 200 based on the stored waiting information data. The electronic device 210 includes an air flow rate calculation unit 211, a GPS 212 capable of sensing the altitude of the air vehicle 200,

(Not shown).

)에 기초하여 공기 질량 유량(

) 결정할 수 있다. The electronic device 210 can determine the static pressure P and the constant temperature T of the air sucked into the air vehicle 200 based on the altitude of the air vehicle 200 sensed by the GPS 212. [ The determined static pressure P and the constant temperature T information may be transmitted to the air flow rate calculation unit 211. The air flow rate computation unit 211 computes the constant pressure P and the constant temperature T information from the pressure sensor 203,

) Based on the air mass flow rate (

).

8 is a flowchart of steps in which an electronic device according to an embodiment determines an air mass flow rate. It should be noted that the following reference numerals are used for reference numerals used in Figs. 5 to 7.

)을 측정하는 단계(840)와, 정압력(P), 정온도(T) 및 전압력(

)에 기초하여 공기 질량 유량(

)을 결정하는 단계(850)를 포함할 수 있다.The method for the electronic device 210 to determine the air mass flow rate comprises the steps of receiving (810) atmospheric static pressure and constant temperature data according to altitude from the terrestrial system (GS) A step 830 of determining a static pressure P and a constant temperature T based on the altitude of the air vehicle 200 and a step 830 of detecting a voltage force

(P), a constant temperature T (T), and a voltage (V)

) Based on the air mass flow rate (

(Step 850). &Lt; / RTI &gt;

In step 810, the electronic device 210 may receive standby information data from the ground system GS before the air vehicle 200 takes off. The air vehicle 200 can improve the accuracy of air mass flow measurement by updating the waiting information data before each take-off.

Also, the electronic device 210 can receive standby information data in real time from the ground system GS while the air vehicle 200 is flying. The electronic device 210 can update the standby information data reflecting the standby state which changes instantaneously in real time.

In step 820, the GPS 212 may sense the elevation of the air vehicle 200. [

At step 830, the electronic device 210 may extract the static pressure P and the constant temperature T information according to the altitude sensed from the GPS 212 on the atmospheric information data.

)을 측정할 수 있다.In step 840, the pressure sensor 203 detects the pressure

) Can be measured.

)에 기초하여 공기 질량 유량(

)을 결정할 수 있다. 또한, 전자장치(210)은 결정된 공기 질량 유량(

)에 기초하여 엔진(220, 도 5 참조)을 제어할 수 있다.At step 750, the electronic device 210 receives the positive pressure P and the constant temperature T information and the measured voltage force &lt; RTI ID = 0.0 &gt;

) Based on the air mass flow rate (

Can be determined. In addition, the electronic device 210 may determine the determined air mass flow rate (

(Refer to FIG. 5).

Although the preferred embodiments of the present invention have been disclosed for illustrative purposes, those skilled in the art will appreciate that various modifications, additions and substitutions are possible, without departing from the scope and spirit of the invention as disclosed in the accompanying claims. For example, it is contemplated that the techniques described may be performed in a different order than the described methods, and / or that components of the described structures, devices, and the like may be combined or combined in other ways than the described methods, Appropriate results can be achieved even if they are replaced or replaced. Therefore, other implementations, equivalents to other embodiments and the claims are also within the scope of the following claims.

Claims (12)

And an electronic device for calculating a mass flow rate of air sucked into the airplane based on previously stored waiting information data,
The waiting information data includes atmospheric pressure and temperature information according to altitude,
The electronic device includes a GPS for sensing an altitude of the air vehicle,
Wherein the electronic device determines a static pressure and a static temperature of air sucked into the airplane based on an altitude of the airplane detected from the GPS.
delete delete The method according to claim 1,
The electronic device includes:
A navigation device for measuring the speed of the air vehicle; And
Further comprising an air flow rate calculation unit for determining a mass flow rate of air sucked into the airplane based on the speed of the airplane, the constant pressure of the air sucked into the airplane, and the constant temperature information, Device.
The method according to claim 1,
The electronic device includes:
A pressure sensor capable of measuring a voltage; And
Further comprising an air flow rate calculation unit for determining a mass flow rate of the air sucked into the airplane based on the voltage force and the positive pressure and the constant temperature information of the air.
6. The method of claim 5,
Wherein the pressure sensor is disposed in a hole formed in a tip portion of the flying object.
The method according to claim 1,
Wherein the electronic device receives the atmospheric information data from the ground system before the airplane takes-off.
8. The method of claim 7,
Wherein the electronic device is capable of receiving the atmospheric information data from the ground system in real time during flight of the air vehicle.
Receiving atmospheric information data including atmospheric static pressure and temperature information according to an altitude from a ground system;
Sensing an altitude of the air vehicle through GPS;
Determining the static pressure and the constant temperature information at the altitude of the air vehicle; And
And determining the air flow rate based on the determined positive pressure and the constant temperature information.
10. The method of claim 9,
Further comprising the step of measuring the speed of the air vehicle through a navigation device.
10. The method of claim 9,
And measuring a voltage at a position of the air vehicle through a pressure sensor.
10. The method of claim 9,
And updating the atmospheric information data according to the altitude in real time during flight of the air vehicle.

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